WorldWideScience

Sample records for satellite gosat launched

  1. Sensor system for Greenhouse Gas Observing Satellite (GOSAT)

    Science.gov (United States)

    Hamazaki, Takashi; Kuze, Akihiko; Kondo, Kayoko

    2004-11-01

    Global warming has become a very serious issue for human beings. In 1997, the Kyoto Protocol was adopted at the Third Session of the Conference of the Parties to the United Nations Framework Convention on Climate Change (COP3), making it mandatory for developed nations to reduce carbon dioxide emissions by six (6) to eight (8) per cent of their total emissions in 1990, and to meet this goal sometime between 2008 and 2012. The Greenhouse gases Observing SATellite (GOSAT) is design to monitor the global distribution of carbon dioxide (CO2) from orbit. GOSAT is a joint project of Japan Aerospace Exploration Agency (JAXA), the Ministry of Environment (MOE), and the National Institute for Environmental Studies (NIES). JAXA is responsible for the satellite and instrument development, MOE is involved in the instrument development, and NIES is responsible for the satellite data retrieval. The satellite is scheduled to be launched in 2008. In order to detect the CO2 variation of boundary layers, both the technique to measure the column density and the retrieval algorithm to remove cloud and aerosol contamination are investigated. Main mission sensor of the GOSAT is a Fourier Transform Spectrometer with high optical throughput, spectral resolution and wide spectral coverage, and a cloud-aerosol detecting imager attached to the satellite. The paper presents the mission sensor system of the GOSAT together with the results of performance demonstration with proto-type instrument aboard an aircraft.

  2. The Statuses of GOSAT and GOSAT-2 Projects at National Institute for Environmental Studies (NIES)

    Science.gov (United States)

    Matsunaga, Tsuneo; Yokota, Tatsuya; Maksyutov, Shamil; Morino, Isamu; Yoshida, Yukio; Saito, Makoto; Ajiro, Masataka; Uchino, Osamu

    2015-04-01

    Greenhouse Gases Observing Satellite (GOSAT) and its successor, GOSAT-2, are Japanese earth observing satellites for greenhouse gases measurements from space. Both satellite projects are joint efforts among Ministry of the Environment (MOE), Japan Aerospace Exploration Agency (JAXA), and National Institute for Environmental Studies (NIES). GOSAT was launched in January 2009, already finished its design lifetime (five years), and is currently in its extended operation period. GOSAT-2 will be launched in FY2017. Both satellites have Fourier transform spectrometers for the measurements of columnar abundances of greenhouse and other gases and UV-VIS-NIR-SWIR imagers for cloud and aerosol detection. GOSAT-2 instruments (FTS-2 and CAI-2) will be modified or improved based on the experiences of GOSAT instruments (FTS and CAI). FTS-2 improvements will include the extended spectral coverage for carbon monoxide measurement and the intelligent pointing capability to avoid cloud contamination. NIES is responsible for generation, validation, and distribution of higher level products of GOSAT and GOSAT-2. The ground data system for GOSAT, GOSAT Data Handling Facility (GOSAT DHF), has been developed and operated for more than six years. GOSAT DHF will be operated until the termination of the operation of GOSAT spacecraft. GOSAT-2 Data Processing System (G2DPS), an independent ground data system for GOSAT-2, is currently being designed. GOSAT Level 2 products such as column concentration of CO2 and CH4 and Level 4 products such as CO2 and CH4 monthly fluxes for global 64 regions are freely available from GOSAT DHF as described in GOSAT Data Policy. GOSAT-2 products will be similar to GOSAT products but based on more sophisticated data processing algorithm. MOE, JAXA, and NIES are currently discussing GOSAT-2 Data Policy. The validation of GOSAT gas column amount products mainly uses ground-based Total Carbon Column Observation Network (TCCON) data. The validation of GOSAT-2 gas

  3. Taiyuan Satellite Launch Center

    Institute of Scientific and Technical Information of China (English)

    LiuJie

    2004-01-01

    There are three major space launch bases in China, the Jiuquan Satellite Launch Center,the Taiyuan Satellite Launch Center and the Xichang Satellite Launch Center. All the three launch centers are located in sparsely populated areas where the terrain is even and the field of vision is broad. Security, transport conditions and the influence of the axial rotation

  4. Xichang Satellite Launch Center

    Institute of Scientific and Technical Information of China (English)

    LiuJie

    2004-01-01

    Xichang Satellite Launch Center(XSLC) is mainly for geosynchronous orbit launches. The main purpose of XSLC is to launch spacecraft, such as broadcasting,communications and meteorological satellites, into geo-stationary orbit.Most of the commercial satellite launches of Long March vehicles have been from Xichang Satellite Launch Center. With 20 years' development,XSLC can launch 5 kinds of launch vehicles and send satellites into geostationary orbit and polar orbit. In the future, moon exploration satellites will also be launched from XSLC.

  5. Satellite observations of large power plants and megacities from GOSAT

    Science.gov (United States)

    Oda, Tom; Maksyutov, Shamil; Boesch, Hartmut; Butz, Andre; Ganshin, Alexander; Guerlet, Sandrine; Parker, Robert; O'Dell, Chris; Oshchepkov, Sergey; Yoshida, Yukio; Zhuravlev, Ruslan; Yokota, Tatsuya

    2013-04-01

    Fossil fuel CO2 emissions are a major source of CO2 to the global carbon cycle over decadal time scales and international efforts to curb those missions are required for mitigating climate change. Although emissions from nations are estimated and reported to help monitor their compliance of emission reductions, we still lack an objective method to monitor emissions directly. Future carbon-observing space missions are thus expected to provide an independent tool for directly measuring emissions. We proposed and have implemented satellite observations specifically over intense large point sources (LPS), including large fossil-fueled power plants and megacities, worldwide (N > 300) using the Japanese Greenhouse Gases Observing SATelllite (GOSAT). Our target LPS sites have been occasionally included in the observation schedule of GOSAT and the measurements are made using the target observation mode. This proposal was officially accepted by the GOSAT project office and we have attempted to use these data to detect signatures of man-made greenhouse gas emissions. We have submitted our locations of interest on a monthly basis two month prior to observation. We calculated the X_CO2 concentration enhancement due to the LPS emissions. We analyzed GOSAT X_CO2 retrievals from four research groups (five products total): the National Institute for Environmental Studies (NIES) (both the NIES standard Level 2 and NIES-PPDF products), the NASA Atmospheric CO2 from Space (ACOS) team (ACOS Level 2 product), the Netherlands Institute for Space Research (SRON)/Karlsruhe Institute of Technology, Germany (RemoTeC), and the University of Leicester, UK (Full-Physics CO2 retrieval dataset). Although we obtained fewer retrieved soundings relative to what we requested (probably due to geophysical difficulties in the retrievals), we did obtain statistically significant enhancements at some LPS sites where weather condition were ideal for viewing. We also implemented simulations of enhanced X

  6. Satellite observation of atmospheric methane: intercomparison between AIRS and GOSAT TANSO-FTS retrievals

    Science.gov (United States)

    Zou, Mingmin; Xiong, Xiaozhen; Saitoh, Naoko; Warner, Juying; Zhang, Ying; Chen, Liangfu; Weng, Fuzhong; Fan, Meng

    2016-08-01

    Space-borne observations of atmospheric methane (CH4) have been made using the Atmospheric Infrared Sounder (AIRS) on the EOS/Aqua satellite since August 2002 and the Thermal and Near-infrared Sensor for Carbon Observation Fourier Transform Spectrometer (TANSO-FTS) on the Greenhouse Gases Observing Satellite (GOSAT) since April 2009. This study compared the GOSAT TANSO-FTS thermal infrared (TIR) version 1.0 CH4 product with the collocated AIRS version 6 CH4 product using data from 1 August 2010 to 30 June 2012, including the CH4 mixing ratios and the total column amounts. The results show that at 300-600 hPa, where both AIRS and GOSAT-TIR CH4 have peak sensitivities, they agree very well, but GOSAT-TIR retrievals tend to be higher than AIRS in layer 200-300 hPa. At 300 hPa the CH4 mixing ratio from GOSAT-TIR is, on average, 10.3 ± 31.8 ppbv higher than that from AIRS, and at 600 hPa GOSAT-TIR retrieved CH4 is -16.2 ± 25.7 ppbv lower than AIRS CH4. Comparison of the total column amount of CH4 shows that GOSAT-TIR agrees with AIRS to within 1 % in the mid-latitude regions of the Southern Hemisphere and in the tropics. In the mid to high latitudes in the Northern Hemisphere, comparison shows that GOSAT-TIR is ˜ 1-2 % lower than AIRS, and in the high-latitude regions of the Southern Hemisphere the difference of GOSAT from AIRS varies from -3 % in October to +2 % in July. The difference between AIRS and GOSAT TANSO-FTS retrievals is mainly due to the difference in retrieval algorithms and instruments themselves, and the larger difference in the high-latitude regions is associated with the low information content and small degrees of freedom of the retrieval. The degrees of freedom of GOSAT-TIR retrievals are lower than that of AIRS, which also indicates that the constraint in GOSAT-TIR retrievals may be too strong. From the good correlation between AIRS and GOSAT-TIR retrievals and the seasonal variation they observed, we are confident that the thermal infrared

  7. CHINA LAUNCHES NEW SCIENTIFIC SATELLITE

    Institute of Scientific and Technical Information of China (English)

    2004-01-01

    China on Sept. 27, 2004 launched a scientific satellite atop a Long March 2D carrier rocket from Jiuquan Satellite Launch Center in Gansu province. 10 minutes after the launch, the satellite entered a preset orbit and is running sound at the orbit. It is the 20th recoverable satellite for scientific and technological

  8. Experimental Satellite 2 Successfully Launched

    Institute of Scientific and Technical Information of China (English)

    LiuJie

    2004-01-01

    Small satellite Experimental Satellite 2 (SY-2) was launched by LM-2C launch vehicle from Xichang Satellite Launch Center on Nov. 18, 2004. Later the satellite entered the preset sun-synchronous orbit, which is 700 kilometers above the earth. The launch was the eighthmission this year by China Aerospace Science and Technology Corporation(CASC), which aims to test the technology of the satellite, conduct survey and monitoring of the land and resources and geographical environment on a trial basis.

  9. Global CO2 Distributions over Land from the Greenhouse Gases Observing Satellite (GOSAT)

    Science.gov (United States)

    Hammerling, Dorit M.; Michalak, Anna M.; O'Dell, Christopher; Kawa, Randolph S.

    2012-01-01

    January 2009 saw the successful launch of the first space-based mission specifically designed for measuring greenhouse gases, the Japanese Greenhouse gases Observing SATellite (GOSAT). We present global land maps (Level 3 data) of column-averaged CO2 concentrations (X(sub CO2)) derived using observations from the GOSAT ACOS retrieval algorithm, for July through December 2009. The applied geostatistical mapping approach makes it possible to generate maps at high spatial and temporal resolutions that include uncertainty measures and that are derived directly from the Level 2 observations, without invoking an atmospheric transport model or estimates of CO2 uptake and emissions. As such, they are particularly well suited for comparison studies. Results show that the Level 3 maps for July to December 2009 on a lO x 1.250 grid, at six-day resolution capture much of the synoptic scale and regional variability of X(sub CO2), in addition to its overall seasonality. The uncertainty estimates, which reflect local data coverage, X(sub CO2) variability, and retrieval errors, indicate that the Southern latitudes are relatively well-constrained, while the Sahara Desert and the high Northern latitudes are weakly-constrained. A probabilistic comparison to the PCTM/GEOS-5/CASA-GFED model reveals that the most statistically significant discrepancies occur in South America in July and August, and central Asia in September to December. While still preliminary, these results illustrate the usefulness of a high spatiotemporal resolution, data-driven Level 3 data product for direct interpretation and comparison of satellite observations of highly dynamic parameters such as atmospheric CO2.

  10. GOSAT-2 : Science Plan, Products, Validation, and Application

    Science.gov (United States)

    Matsunaga, T.; Morino, I.; Yoshida, Y.; Saito, M.; Hiraki, K.; Yokota, Y.; Kamei, A.; Oishi, Y.; Dupuy, E.; Murakami, K.; Ninomiya, K.; Pang, J. S.; Yokota, T.; Maksyutov, S. S.; Machida, T.; Saigusa, N.; Mukai, H.; Nakajima, M.; Imasu, R.; Nakajima, T.

    2013-12-01

    Based on the success of Greenhouse Gases Observing Satellite (GOSAT) launched in 2009, Ministry of the Environment (MOE), Japan Space Exploration Agency (JAXA), and National Institute for Environmental Studies (NIES) started the preparations for the follow-on satellite, GOSAT-2 in FY2011. The current target launch year of GOSAT-2 is FY2017. The objectives of GOSAT-2 include : 1) Continue and enhance spaceborne greenhouse gases observation started by GOSAT, 2) Improve our understanding of global and regional carbon cycles, and 3) Contribute to the climate change related policies as one of MRV(Measurement, Reporting, and Verification) tools for carbon emission reduction. As a scientific background/rationale of GOSAT-2, GOSAT-2 Science Plan is being edited by GOSAT-2 Science Team Preparation Committee. Not only carbon dioxide and methane but also carbon monoxide, tropospheric ozone, and aerosols are discussed in the plan. GOSAT-2 Level 2 (gas concentrations) and Level 4 (gas fluxes) products will be operationally generated at and distributed from GOSAT-2 Data Handling Facility located in NIES. In addition, a new supercomputer dedicated to GOSAT-2 research and development will be also installed in NIES. GOSAT-2 validation plan is also being discussed. Its baseline is similar to the current GOSAT . But various efforts will be made to extend the coverage of validation data for GOSAT-2. The efforts include the increased commercial passenger aircraft volunteering atmospheric measurements and additional ground-based Fourier transform spectrometers to be newly installed in Asian countries. In addition, a compact accelerator mass spectrometer is being introduced to NIES to investigate the contributions of anthropogenic emissions which is important for GOSAT-2. Climate change related policies include JCM (Joint Crediting Mechanism) in which MRV plays a critical role. MRV tools used in the existing JCM projects are mostly ground-based and site-specific. Satellite atmospheric

  11. GOSAT Air Pollution Watch - Rapid Response System for Local Air Pollution

    Science.gov (United States)

    Matsunaga, T.; Sawada, Y.; Kamei, A.; Uchiyama, A.

    2015-12-01

    GOSAT (Greenhouse Gases Observing Satellite) launched in 2009 and its successor, GOSAT-2, to be launched in FY 2017, have push-broom imaging systems with more than one UV band with higher spatial resolution than OMI, MODIS, and VIIRS. Such imaging systems are useful for mapping the spatial extent of the optically thick air mass with particulate matters. GOSAT Air Pollution Watch, a rapid response system mainly using GOSAT CAI (Cloud and Aerosol Imager) data for local air pollution issues is being developed in NIES (National Institute for Environmental Studies) GOSAT-2 Project. The current design of GOSAT Air Pollution Watch has three data processing steps as follows: Step 1) Making a cloud mask Step 2) Estimating AOT (Aerosol Optical Thickness) in the UV region (380 nm for CAI) Step 3) Converting AOT to atmospheric pollution parameters such as PM2.5 concentration Data processing algorithms in GOSAT Air Pollution Watch are based on GOSAT/GOSAT-2 algorithms for aerosol product generation with some modification for faster and timely data processing. Data from GOSAT Air Pollution Watch will be used to inform the general public the current distribution of the polluted air. In addition, they will contribute to short term prediction of the spatial extent of the polluted air using atmospheric transport models. In this presentation, the background, the current status, and the future prospect of GOSAT Air Pollution Watch will be reported together with the development status of GOSAT-2.

  12. CHINA LAUNCHES 2 SCIENTIFIC EXPERIMENT SATELLITES

    Institute of Scientific and Technical Information of China (English)

    2004-01-01

    China placed 2 scientific experiment satellites into preset orbits atop a LM-4B launch vehicle on Sept. 9, 2004. A LM-4B blasted off at 7:14 am from Taiyuan Satellite Launch Center in Shanxi Province. Sources from the Xi'an Satellite Monitor and Control Center said that one satellite,

  13. Opportunities for Coordinated Observations of CO2 with the Orbiting Carbon Observatory (OCO) and Greenhouse Gases Observing Satellite (GOSAT)

    Science.gov (United States)

    Crisp, David

    2008-01-01

    The Orbiting Carbon Observatory (OCO) and the Greenhouse Gases Observing Satellite (GOSAT) are the first two satellites designed to make global measurements of atmospheric carbon dioxide (CO2) with the precision and sampling needed identify and monitor surface sources and sinks of this important greenhouse gas. Because the operational phases of the OCO and GOSAT missions overlap in time, there are numerous opportunities for comparing and combining the data from these two satellites to improve our understanding of the natural processes and human activities that control the atmospheric CO2 and it variability over time. Opportunities for cross-calibration, cross-validation, and coordinated observations that are currently under consideration are summarized here.

  14. China Launches Two Natural Disaster Monitoring Satellites

    Institute of Scientific and Technical Information of China (English)

    2008-01-01

    @@ China launched two satellites, HJ-1A and HJ-1B, to monitor the environment and natural disasters at 11:25am on September 6 (Beijing time) from the Taiyuan Satellite Launch Center in Shanxi Province. The two satellites are expected to improve the country's ability in the rapid monitoring of environmental changes and reducing calamities.

  15. First China-Europe Satellite Successfully Launched

    Institute of Scientific and Technical Information of China (English)

    HeYing

    2004-01-01

    On December 30, 2003 China successfully launched TC-1,the first of two scientific satellites known as Double Star, The mission,the first time that European instruments were integrated with Chinese satellites,was carried out by a Long March 2C/SM rocket at 3:06 am from the Xichang Satellite Launch Center in Sichuan province.

  16. Enabling Technology for Small Satellite Launch Project

    Data.gov (United States)

    National Aeronautics and Space Administration — Access to space for Small Satellites is enabled by the use of excess launch capacity on existing launch vehicles. A range of sizes, form factors and masses of small...

  17. Enabling Technology for Small Satellite Launch Project

    Data.gov (United States)

    National Aeronautics and Space Administration — Access to space for Small Satellites is enabled by the use of excess launch capacity on existing launch vehicles. A range of sizes, form factors and masses need to...

  18. China Launches First Ever Nano-satellite

    Institute of Scientific and Technical Information of China (English)

    LiuJie

    2004-01-01

    China successfully launched two scientific satellites, including a nano-satellite for the first time, heralding a breakthrough in space technology. A LM-2C rocket carrying Nano-Satellite I (NS-1), which weighs just 25kg and an Experiment Satellite I, weighing 204kg blasted off at 11:59 p.m. on April 18,

  19. Spatially resolving methane emissions in California: constraints from the CalNex aircraft campaign and from present (GOSAT, TES and future (TROPOMI, geostationary satellite observations

    Directory of Open Access Journals (Sweden)

    K. J. Wecht

    2014-02-01

    Full Text Available We apply a continental-scale inverse modeling system for North America based on the GEOS-Chem model to optimize California methane emissions at 1/2° × 2/3° horizontal resolution using atmospheric observations from the CalNex aircraft campaign (May–June 2010 and from satellites. Inversion of the CalNex data yields a best estimate for total California methane emissions of 2.86 ± 0.21 Tg yr−1, compared with 1.92 Tg yr−1 in the EDGAR v4.2 emission inventory used as a priori and 1.51 Tg yr−1 in the California Air Resources Board (CARB inventory used for state regulations of greenhouse gas emissions. These results are consistent with a previous Lagrangian inversion of the CalNex data. Our inversion provides 12 independent pieces of information to constrain the geographical distribution of emissions within California. Attribution to individual source types indicates dominant contributions to emissions from landfills/wastewater (1.1 Tg yr−1, livestock (0.87 Tg yr−1, and gas/oil (0.64 Tg yr−1. EDGAR v4.2 underestimates emissions from livestock while CARB underestimates emissions from landfills/wastewater and gas/oil. Current satellite observations from GOSAT can constrain methane emissions in the Los Angeles Basin but are too sparse to constrain emissions quantitatively elsewhere in California (they can still be qualitatively useful to diagnose inventory biases. Los Angeles Basin emissions derived from CalNex and GOSAT inversions are 0.42 ± 0.08 and 0.31 ± 0.08, respectively. An observation system simulation experiment (OSSE shows that the future TROPOMI satellite instrument (2015 launch will be able to constrain California methane emissions at a detail comparable to the CalNex aircraft campaign. Geostationary satellite observations offer even greater potential for constraining methane emissions in the future.

  20. Design and qualification of the interferometer for the GOSAT-2 spectrometer

    Science.gov (United States)

    Montembault, Yan; Moreau, Louis; Roux, Michel; Buijs, Henry; Soucy, Marc-André

    2016-10-01

    GOSAT-2 is the successor of the Greenhouse gases Observing SATellite (GOSAT, "IBUKI") launched in 2009 by Japan Aerospace Exploration Agency (JAXA). GOSAT-2 will continue and enhance space borne measurements of greenhouse gases started by GOSAT and monitor the impacts of climate change and human activities on the carbon cycle. It will also contribute to climate science and climate change related policies. The GOSAT-2 spacecraft will carry two earth observation instruments: FTS-2, the second generation of the TANSO-FTS and CAI-2, a Cloud and Aerosol Imager. Mitsubishi Electric Corporation is the prime contractor of GOSAT-2. Harris is the subcontractor of the spectrometer. ABB, who successfully designed, manufactured, and delivered the interferometer for the TANSO-FTS instrument for GOSAT, is currently delivering the modulator for the FTS-2 instrument to Mitsubishi Electric Corporation. Built on the TANSO-FTS heritage, FTS-2 is a thermal and near infrared sensor for carbon observation based on a Fourier transform spectrometer featuring larger optical throughput than TANSO-FTS. This paper presents an overview of the design of the FTS-2 interferometer as well as key qualification and performance verification activities conducted on the interferometer flight model.

  1. Lidar observations at prioritized sites for GOSAT validation

    Science.gov (United States)

    Uchino, O.; Morino, I.; Sakai, T.; Izumi, T.; Nagai, T.; Shibata, T.; Hiroshi, O.; Arai, K.; Liley, B.; Bagtasa, G.

    2016-12-01

    The Thermal And Near infrared Sensor for carbon Observation-Fourier Transform Spectrometer (TANSO-FTS) onboard the Greenhouse gases Observing SATellite (GOSAT) measures the Short Wavelength InfraRed (SWIR) spectra of sunlight reflected by the earth surface and atmosphere. The column-averaged dry air mole fractions of carbon dioxide and methane (XCO2 and XCH4, hereafter GOSAT data) retrieved from the TANSO-FTS SWIR spectra could be influenced by aerosol and cirrus could particles. To investigate their influences on the GOSAT data, we deployed two-wavelength (532 and 1064 nm) polarization lidar systems at the Total Carbon Column Observing Network (TCCON) sites of Lauder in New Zealand, Tsukuba, Saga and Rikubetsu in Japan as prioritized validation sites. Vertical profiles of particle backscattering coefficients, backscatter wavelength exponent and total depolarization ratio were obtained by these lidar systems. Based on these physical parameters, we found that the particles had influence on GOSAT XCO2 at Tsukuba and Saga. These lidars detected increases in stratospheric aerosols by the volcanic eruptions of Sarychev Peak, Puyehue-Cordon Caulle, Nabro and Calbuco during 2009 through 2015, which might impact on GOSAT XCO2. Furthermore, we developed an improved version of lidar for validation of GOSAT-2 which will be launched in 2018. The improved lidar can measure the particle extinction-to-backscatter ratio and water vapor mixing ratio profiles up to 5 km in nighttime using N2 and H2O Raman scattering besides above-mentioned physical parameters. This lidar will be installed at Burgos in Philippines with a TCCON FTS in early 2017. We present the observational results of particles and their influences on the GOSAT data.

  2. A General Introduction to Greenhouse Gases Observing Satellite (GOSAT) and Its Products%温室气体观测卫星GOSAT及产品

    Institute of Scientific and Technical Information of China (English)

    侯姗姗; 雷莉萍; 关贤华

    2013-01-01

    为了深入了解国际上新一代温室气体观测卫星及其产品,详细介绍了GOSAT卫星发射背景、卫星平台、传感器设置、地面系统及数据产品特点.GOSAT卫星采用干涉分光技术,结合多种观测方式,可以获得高精度、高时空分辨率的温室气体浓度及廓线资料,其卫星设计及数据应用思路,为我国发展温室气体探测卫星提供了重要参考价值.%Remote sensing plays an important role in monitoring greenhouse gases emissions and the source and sink of greenhouse gases at regional and global scales. GOSAT (Greenhouse gases Observing SATellite) is the first satellite for space borne measurement of the main greenhouse gases CO2 and CH4. An Introduction is made about the emission background, satellite platform, instrument characteristics, and the ground systems of GOSAT,in order to thoroughly understand the advances of satellite greenhouse gases observation in the world. This paper also presents an overview of GOS-AT data products,calibration and validation strategies. Thermal And Near infrared Sensor for carbon Observation Fourier-Transform Spectrometer (TANSO-FTS) is based on the Michelson interferometer, and combine with several observation modes which provides atmospheric greenhouse gases concentration and profile data with high precision. While TANSO-CAI (Cloud and Aerosol Imager) is a radiometer with Ultra Violet (UV), visible, and short wave infrared (SWIR) bands to reduce the interference of cloud and aerosol on greenhouse gases measurements. The satellite design and data applications of GOSAT provide important references for developing greenhouse gas monitor satellites in China.

  3. NASA to launch second business communications satellite

    Science.gov (United States)

    1981-01-01

    The two stage Delta 3910 launch vehicle was chosen to place the second small business satellite (SBS-B) into a transfer orbit with an apogee of 36,619 kilometers and a perigee of 167 km, at an inclination of 27.7 degrees to Earth's equator. The firing and separation sequence and the inertial guidance system are described as well as the payload assist module. Facilities and services for tracking and control by NASA, COMSAT, Intelsat, and SBS are outlined and prelaunch operations are summarized.

  4. A method for colocating satellite XCO2 data to ground-based data and its application to ACOS-GOSAT and TCCON

    Directory of Open Access Journals (Sweden)

    H. Nguyen

    2014-02-01

    Full Text Available Satellite measurements are often compared with higher-precision ground-based measurements as part of validation efforts. The satellite soundings are rarely perfectly coincident in space and time with the ground-based measurements, so a colocation methodology is needed to aggregate "nearby" soundings into what the instrument would have seen at the location and time of interest. We are particularly interested in validation efforts for satellite-retrieved total column carbon dioxide (XCO2, where XCO2 data from Greenhouse Gas Observing Satellite (GOSAT retrievals (ACOS, NIES, RemoteC, PPDF, etc. or SCanning Imaging Absorption SpectroMeter for Atmospheric CHartographY (SCHIACHY are often colocated and compared to ground-based column XCO2 measurement from Total Carbon Column Observing Network (TCCON. Current colocation methodologies for comparing satellite measurements of total column dry-air mole fractions of CO2 (XCO2 with ground-based measurements typically involve locating and averaging the satellite measurements within some latitudinal, longitudinal, and temporal window. We examine a geostatistical colocation methodology that takes a weighted average of satellite observations depending on the "distance" of each observation from a ground-based location of interest. The "distance" function that we use is a modified Euclidian distance with respect to latitude, longitude, time, and mid-tropospheric temperature at 700 hPa. We apply this methodology to XCO2 retrieved from Greenhouse Gas Observing Satellite (GOSAT spectra by the ACOS team, cross-validate the results to TCCON XCO2 ground-based data, and present some comparison between our methodology and standard existing colocation methods showing that in general geostatistical colocation produces smaller mean-squared error.

  5. China Plans to Launch FY-3 Meteorological Satellite in 2006

    Institute of Scientific and Technical Information of China (English)

    2004-01-01

    China's new generation polar orbit weather satellite FY-3 will be launched by LM-4B launch vehicle in 2006. The FY-3 would be equipped with new global, all-weather, multi-spectral, threedimensional sensors. The new satellite, an improved version of the FY-1, has the resolution of 250m and

  6. A method for colocating satellite XCO2 data to ground-based data and its application to ACOS-GOSAT and TCCON

    Science.gov (United States)

    Nguyen, H.; Osterman, G.; Wunch, D.; O'Dell, C.; Mandrake, L.; Wennberg, P.; Fisher, B.; Castano, R.

    2014-08-01

    Satellite measurements are often compared with higher-precision ground-based measurements as part of validation efforts. The satellite soundings are rarely perfectly coincident in space and time with the ground-based measurements, so a colocation methodology is needed to aggregate "nearby" soundings into what the instrument would have seen at the location and time of interest. We are particularly interested in validation efforts for satellite-retrieved total column carbon dioxide (XCO2), where XCO2 data from Greenhouse Gas Observing Satellite (GOSAT) retrievals (ACOS, NIES, RemoteC, PPDF, etc.) or SCanning Imaging Absorption SpectroMeter for Atmospheric CHartographY (SCIAMACHY) are often colocated and compared to ground-based column XCO2 measurement from Total Carbon Column Observing Network (TCCON). Current colocation methodologies for comparing satellite measurements of total column dry-air mole fractions of CO2 (XCO2) with ground-based measurements typically involve locating and averaging the satellite measurements within a latitudinal, longitudinal, and temporal window. We examine a geostatistical colocation methodology that takes a weighted average of satellite observations depending on the "distance" of each observation from a ground-based location of interest. The "distance" function that we use is a modified Euclidian distance with respect to latitude, longitude, time, and midtropospheric temperature at 700 hPa. We apply this methodology to XCO2 retrieved from GOSAT spectra by the ACOS team, cross-validate the results to TCCON XCO2 ground-based data, and present some comparisons between our methodology and standard existing colocation methods showing that, in general, geostatistical colocation produces smaller mean-squared error.

  7. Small Satellite Transceiver for Launch Vehicles Project

    Data.gov (United States)

    National Aeronautics and Space Administration — NAL Research Corporation proposes to develop a small, light-weight, low-cost transceivers capable of establishing satellite communications links for telemetry and...

  8. Small Satellite Transceiver for Launch Vehicles Project

    Data.gov (United States)

    National Aeronautics and Space Administration — NAL Research Corporation proposes to develop a small, light-weight, low-cost transceivers capable of establishing satellite communications links for telemetry and...

  9. Micro, nano and pico satellites launched from the Romanian territory

    Science.gov (United States)

    Savu, G.

    2006-10-01

    In the frame of National Program "Aerospatial" The National Institute of Turbomachinery—COMOTI, Bucharest, Romania proposes a project of launching with minimum cost of microsatellites using the national territory. The geographical position of Romania is optimum for satellites launching due to the presence of the Black Sea in the eastern part of the country and due to its elongated shape, West-East, offering a launching surface of 1500 km (W-E) ×250km (N-S). Two modes of launching were analyzed: vertical, from the soil and horizontal, from a carrier aircraft. The second mode of launching doubtless has some advantages, particularly from the point of view of costs. It was analyzed the launching of a LEO satellite as a payload of a single stage rocket with solid propellant, launched from a fighter aircraft. The aerodynamic coefficients of the rocket, the equation of movement on the trajectory and the rocket engine thrust were calculated using a FORTRAN program—LSCS (language for the simulation the continuous systems). The shape of the trajectory was imposed (not optimized), finally resulting the performances, the main geometrical dimensions of the rocket and the mass of the satellite.

  10. LARES succesfully launched in orbit: satellite and mission description

    CERN Document Server

    Paolozzi, Antonio

    2013-01-01

    On February 13th 2012, the LARES satellite of the Italian Space Agency (ASI) was launched into orbit with the qualification flight of the new VEGA launcher of the European Space Agency (ESA). The payload was released very accurately in the nominal orbit. The name LARES means LAser RElativity Satellite and summarises the objective of the mission and some characteristics of the satellite. It is, in fact, a mission designed to test Einstein's General Relativity Theory (specifically 'frame dragging' and Lense-Thirring effect). The satellite is passive and covered with optical retroreflectors that send back laser pulses to the emitting ground station. This allows accurate positioning of the satellite, which is important for measuring the very small deviations from Galilei-Newton's laws. In 2008, ASI selected the prime industrial contractor for the LARES system with a heavy involvement of the universities in all phases of the programme, from the design to the construction and testing of the satellite and separation...

  11. Technique applied in electrical power distribution for Satellite Launch Vehicle

    Directory of Open Access Journals (Sweden)

    João Maurício Rosário

    2010-09-01

    Full Text Available The Satellite Launch Vehicle electrical network, which is currently being developed in Brazil, is sub-divided for analysis in the following parts: Service Electrical Network, Controlling Electrical Network, Safety Electrical Network and Telemetry Electrical Network. During the pre-launching and launching phases, these electrical networks are associated electrically and mechanically to the structure of the vehicle. In order to succeed in the integration of these electrical networks it is necessary to employ techniques of electrical power distribution, which are proper to Launch Vehicle systems. This work presents the most important techniques to be considered in the characterization of the electrical power supply applied to Launch Vehicle systems. Such techniques are primarily designed to allow the electrical networks, when submitted to the single-phase fault to ground, to be able of keeping the power supply to the loads.

  12. The results of the critical design of the mission instruments of GOSAT-2

    Science.gov (United States)

    Yajima, Yukie; Suto, Hiroshi; Yotsumoto, Kazuhiko; Miyakawa, Takehiro; Hashimoto, Makiko; Shiomi, Kei; Nakajima, Masakatsu; Hirabayashi, Takeshi

    2016-04-01

    The GOSAT-2 is the successor satellite to the GOSAT which is the satellite dedicated to the measurements of the greenhouse gases such as carbon dioxide and methane. GOSAT was launched in January of 2009 and has been operated for about seven years. The development of the GOSAT-2 has been continued for two years, and through the preliminary and critical design phase the detail of the design of the mission instruments were fixed as well as the bus system design. The mission instruments of the GOSAT-2 are TANSO-FTS-2 and TANSO-CAI-2. TANSO-FTS-2 is the Fourier Transform Spectrometer observing greenhouse gases such as Carbon Dioxide and Methane and TANSO-CAI-2 is the imager observing the aerosols and clouds to compensate the TANSO-FTS-2 data and to grasp the movements of the aerosols such as PM2.5. The mission instruments will adopt the same kinds of instruments as GOSAT. But some improvements will be carried. Based on the results of the preliminary design, the design had been refined in the critical design phase and the results of the design meets all of the requirements on the mission instruments derived from the mission requirements to understand CO2 and CH4 sources and sinks and carbon cycle precisely. To improve the measurement accuracy, the signal to noise ratio will be increased by the extension of the aperture size from 64mm to 73mm and cooling the after optics as well as the thermal detectors. And to increase the number of the useful data, GOSAT-2 will equip the function to avoid the clouds during the observation using the images obtained by the monitor camera in FTS. To observe the carbon monoxide, the 2.3μm observation channel will be added. This function will be realized by the extension of the 2.0μm observation band to 2.3μm. The pointing angle in the along track direction will be extend from 20 degrees of GOSAT to 40 degrees to expand the observation area over the ocean where the sun glint is observed. This will make it possible to increase the number

  13. Analyzing six-year-long GOSAT Observational Data

    Science.gov (United States)

    Yokota, T.; Yoshida, Y.; Noda, H.; Morino, I.; Uchino, O.; Takagi, H.; Kim, H. S.; Saito, M.; Maksyutov, S. S.; Fujita, T.; Kawazoe, F.; Ajiro, M.

    2015-12-01

    The Greenhouse gases Observing SATellite (GOSAT) has been operating for more than six-and-a-half years since January 2009. In 2014, GOSAT went through some technical difficulties in the functioning of its solar paddle and sensor pointing mechanism. These problems were overcome later, and the GOSAT observation is still continued without major flaws. GOSAT TANSO-FTS SWIR Level 2 data products, the column-averaged concentrations of carbon dioxide (XCO2) and methane (XCH4) calculated over the past measurement period, have been validated and disseminated to registered researchers and the general public by the NIES GOSAT Project. Also, monthly regional fluxes of CO2 and CH4 (Level 4A data products) over a few year period have been estimated from the FTS SWIR Level 2 data and ground-based GHG monitoring data. Although the above-mentioned technical problems caused a data discontinuity, we accumulated FTS SWIR Level 2 data for more than six years. It is expected that more data will be collected for a few more years while the satellite remains operational. Anomalies in the time series of regional-mean column-averaged concentrations and fluxes are being investigated. In this presentation, we will show the results of the investigation, particularly the ones for some tropical and sub-tropical regions where only few retrievals were obtained due to the influence of frequent cloudiness. Also, we will touch changes in the number of retrievals found over these regions after modifying the satellite's observational pattern. The GOSAT Research Announcement (RA) activities by selected researchers are still continued. In analyzing long-term GOSAT data, events of concentration anomalies (e.g. in 2010 in Europe and in the US, and similar ones in 2013) were found by some of the RA studies. We will summarize the characteristics of GOSAT data products generated over the past several years, and some of the important research outcomes brought by the GOSAT RA researchers.

  14. Chuangxin-1-02 And Shiyan Satellite 3 Launched Atop A LM-2D

    Institute of Scientific and Technical Information of China (English)

    2008-01-01

    @@ A LM-2D launch vehicle blasted off from Jiuquan Satellite Launch Center (JSLC) at 08:15 (Beijing time) on November 5, sending Chuangxin-l-02 and Shiyan Satellite 3 into space. According to the data released by the Xi'an Satellite Control Center (XSCC), Chuangxin-1-02 separated from the launch vehicle 856 seconds after the takeoff, and Shiyan Satellite 3 separated from the rocket 63 seconds thereafter.

  15. LM-3B/E Launched Eutelsat's W3C Satellite

    Institute of Scientific and Technical Information of China (English)

    Bian Ji

    2011-01-01

    At 16:21 Beijing time on October 7,2011,China successfully launched the W3C commercial telecommunications satellite manufactured by Thales Alenia Space for Eutelsat Communications into geostationary transfer orbit by using an enhanced LM-3B (LM-3B/E) launch vehicle from Xichang Satellite Launch Center.

  16. Analysis of satellite-observed CO2 and CH4 of GOSAT for estimation of GHG emissions from power plants and large cities from space

    Science.gov (United States)

    Oda, Tomohiro; Maksyutov, Shamil; Saito, Makoto; Valsala, Vinu; Ganshin, Alexander; Andres, Robert; Koyama, Yuji; Ito, Akihiko; Yoshida, Yukio; Yokota, Tatsuya

    2010-05-01

    National GHG inventories, which are reported on annual basis by country, are a tool to monitor the compliance of GHG emission reduction. National emissions are calculated according to the local activity statistics by sector and thus total emissions and emission changes from the past are obtained. National inventories are presently the only tool available to give a measure of national emissions, although these might not accurately reflect the true quantity of national emissions due to data quality, calculation methods, and time lag. We present an attempt to directly monitor GHG emissions, especially from intense sources such as large power plants and populated cities using GOSAT observations. Our preliminary analysis suggested that emissions from such intense sources cause changes in XCO2, which are detectable by GOSAT, in low wind condition. Since August 2009 we have requested GOSAT targeted mode measurements over large power plants and cities. The large power plants were selected from CARMA (Carbon Monitoring and Action) database by emission intensity, and cities were selected by population ranking. Until to December 2009, 137 XCO2 measurements over 98 observation points were successfully obtained. We evaluated difference between the data at requested points and background concentration, which we defined as monthly mean concentration over 800 km vicinity. An analysis using observational data suggested that XCO2 over requested points might be higher than zonal mean and background concentrations on average, and the range of the difference (1.07 ppm for 3 months) appears to be close to prior estimates. The level of uncertainty at this point (71 % of the mean value) is still at the level of the value itself, however a simple estimate suggests that it can be reduced to about 10% assuming a larger number of measurements, improvements on the retrieval and 5-year operation of GOSAT.

  17. Sentinel-1A - Launching the first satellite and launching the operational Copernicus programme

    Science.gov (United States)

    Aschbacher, Josef; Milagro Perez, Maria Pilar

    2014-05-01

    The first Copernicus satellite, Sentinel-1A, is prepared for launch in April 2014. It will provide continuous, systematic and highly reliable radar images of the Earth. Sentinel-1B will follow around 18 months later to increase observation frequency and establish an operational system. Sentinel-1 is designed to work in a pre-programmed conflict-free operation mode ensuring the reliability required by operational services and creating a consistent long-term data archive for applications based on long time series. This mission will ensure the continuation and improvement of SAR operational services and applications addressing primarily medium- to high-resolution applications through a main mode of operation that features both a wide swath (250 km) and high geometric (5 × 20 m) and radiometric resolution, allowing imaging of global landmasses, coastal zones, sea ice, polar areas, and shipping routes at high resolution. The Sentinel-1 main operational mode (Interferometric Wide Swath) will allow to have a complete coverage of the Earth in 6 days in the operational configuration when the two Sentinel-1 spacecraft will be in orbit simultaneously. High priority areas like Europe, Canada and some shipping routes will be covered almost daily. This high global observation frequency is unprecedented and cannot be reached with any other current radar mission. Envisat, for example, which was the 'workhorse' in this domain up to April 2012, reached global coverage every 35 days. Sentinel-1 data products will be made available systematically and free of charge to all users including institutional users, the general public, scientific and commercial users. The transition of the Copernicus programme from the development to operational phase will take place at about the same time when the first Sentinel-1 satellite will be launched. During the operational phase, funding of the programme will come from the European Union Multiannual Financial Framework (MFF) for the years 2014

  18. GOSAT TIR radiometric validation toward simultaneous GHG column and profile observation

    Science.gov (United States)

    Kataoka, F.; Knuteson, R. O.; Kuze, A.; Shiomi, K.; Suto, H.; Saitoh, N.

    2015-12-01

    The Greenhouse gases Observing SATellite (GOSAT) was launched on January 2009 and continues its operation for more than six years. The thermal and near infrared sensor for carbon observation Fourier-Transform Spectrometer (TANSO-FTS) onboard GOSAT measures greenhouse gases (GHG), such as CO2 and CH4, with wide and high resolution spectra from shortwave infrared (SWIR) to thermal infrared (TIR). This instrument has the advantage of being able to measure simultaneously the same field of view in different spectral ranges. The combination of column-GHG form SWIR band and vertical profile-GHG from TIR band provide better understanding and distribution of GHG, especially in troposphere. This work describes the radiometric validation and sensitivity analysis of TANSO-FTS TIR spectra, especially CO2, atmospheric window and CH4 channels with forward calculation. In this evaluation, we used accurate in-situ dataset of the HIPPO (HIAPER Pole-to-Pole Observation) airplane observation data and GOSAT vicarious calibration and validation campaign data in Railroad Valley, NV. The HIPPO aircraft campaign had taken accurate atmospheric vertical profile dataset (T, RH, O3, CO2, CH4, N2O, CO) approximately pole-to-pole from the surface to the tropopause over the ocean. We implemented these dataset for forward calculation and made the spectral correction model with respect to wavenumber and internal calibration blackbody temperature The GOSAT vicarious calibration campaign have conducted every year since 2009 near summer solstice in Railroad Valley, where high-temperature desert site. In this campaign, we have measured temperature and humidity by a radiosonde and CO2, CH4 and O3 profile by the AJAX airplane at the time of the GOSAT overpass. Sometimes, the GHG profiles over the Railroad Valley show the air mass advection in mid-troposphere depending on upper wind. These advections bring the different concentration of GHG in lower and upper troposphere. Using these cases, we made

  19. New Opportunitie s for Small Satellite Programs Provided by the Falcon Family of Launch Vehicles

    Science.gov (United States)

    Dinardi, A.; Bjelde, B.; Insprucker, J.

    2008-08-01

    The Falcon family of launch vehicles, developed by Space Exploration Technologies Corporation (SpaceX), are designed to provide the world's lowest cost access to orbit. Highly reliable, low cost launch services offer considerable opportunities for risk reduction throughout the life cycle of satellite programs. The significantly lower costs of Falcon 1 and Falcon 9 as compared with other similar-class launch vehicles results in a number of new business case opportunities; which in turn presents the possibility for a paradigm shift in how the satellite industry thinks about launch services.

  20. Progress of Validation of GOSAT Standard Products

    Science.gov (United States)

    Uchino, Osamu

    2010-05-01

    Isamu Morino, Tomoaki Tanaka, Yuki Miyamoto, Yukio Yoshida, Tatsuya Yokota, Toshinobu Machida National Institute for Environmental Studies, Tsukuba, Ibaraki, Japan Debra Wunch, Paul Wennberg Division of Geological and Planetary Sciences, California Institute of Technology, Pasadena, California, USA Geoffrey Toon Jet Propulsion Laboratory, California Institute of Technology, Pasadena, California, USA Thorsten Warneke, Justus Notholt Institute of Environmental Physics, University of Bremen, Bremen, Germany David Griffith, Nicholas Deutscher Department of Chemistry, University of Wollongong, Wollongong New South Wales, Australia Vanessa Sherlock National Institute of Water and Atmospheric Research, Lauder, Central Otago, New Zealand Hidekazu Matsueda, Yousuke Sawa Meteorological Research Institute, 1-1 Nagamine, Tsukuba, Ibaraki 305-0052, Japan Colm Sweeney, Pieter Tans Earth System Research Laboratory, NOAA, Boulder, USA The Greenhouse gases Observing SATellite (GOSAT), launched on 23 January 2009, is the world's first satellite dedicated to measuring the concentrations of the two major greenhouse gases, carbon dioxide (CO2) and methane (CH4), from space. The data measured with the Thermal And Near-infrared Sensor for carbon Observation Fourier Transform Spectrometer (TANSO-FTS) and the Cloud and Aerosol Imager (TANSO-CAI) are processed into several types of data products. Column abundances of CO2 and CH4 (TANSO-FTS SWIR L2 data product) are retrieved from the FTS L1B spectral data. Validation of the FTS Level 2 data product is critical since the data is used for generating the FTS Level 3 (global distributions of column-averaged mixing ratio data of XCO2 and XCH4) and the FTS Level 4 (regional CO2 fluxes and three dimensional distribution of CO2 calculated from the estimated fluxes) products. The reference data to be used for validating abundances are required to have uncertainties of less than 1.0 % (0.3 % or 1 ppm is desirable) for CO2 and 2.0 % for CH4. Ground

  1. PEGASUS - A Flexible Launch Solution for Small Satellites with Unique Requirements

    Science.gov (United States)

    Richards, B. R.; Ferguson, M.; Fenn, P. D.

    The financial advantages inherent in building small satellites are negligible if an equally low cost launch service is not available to deliver them to the orbit they require. The weight range of small satellites puts them within the capability of virtually all launch vehicles. Initially, this would appear to help drive down costs through competition since, by one estimate, there are roughly 75 active space launch vehicles around the world that either have an established flight record or are planning to make an inaugural launch within the year. When reliability, budget constraints, and other issues such as inclination access are factored in, this list of available launch vehicles is often times reduced to a very limited few, if any at all. This is especially true for small satellites with unusual or low inclination launch requirements where the cost of launching on the heavy-lift launchers that have the capacity to execute the necessary plane changes or meet the mission requirements can be prohibitive. For any small satellite, reducing launch costs by flying as a secondary or even tertiary payload is only advantageous in the event that a primary payload can be found that either requires or is passing through the same final orbit and has a launch date that is compatible. If the satellite is able to find a ride on a larger vehicle that is only passing through the correct orbit, the budget and technical capability must exist to incorporate a propulsive system on the satellite to modify the orbit to that required for the mission. For these customers a launch vehicle such as Pegasus provides a viable alternative due to its proven flight record, relatively low cost, self- contained launch infrastructure, and mobility. Pegasus supplements the existing world-wide launch capability by providing additional services to a targeted niche of payloads that benefit greatly from Pegasus' mobility and flexibility. Pegasus can provide standard services to satellites that do not

  2. Regeneratively-Cooled, Pump-Fed Propulsion Technology for Nano / Micro Satellite Launch Vehicles Project

    Data.gov (United States)

    National Aeronautics and Space Administration — Ventions proposes the development of a pump-fed, 2-stage nano launch vehicle for low-cost on demand placement of cube and nano-satellites into LEO. The proposed...

  3. Flexible Low Cost Avionics for NanoSatellite Launch Vehicle Control and GPS Metric Tracking Project

    Data.gov (United States)

    National Aeronautics and Space Administration — In this proposal, Tyvak Nano-Satellite Systems LLC (Tyvak) will develop nano-launch vehicle avionics solutions based on the latest commercial electronics products...

  4. The seasonal variation of the CO2 flux over Tropical Asia estimated from GOSAT, CONTRAIL, and IASI

    NARCIS (Netherlands)

    Basu, S.; Krol, M.; Butz, A.; Clerbaux, C.; Sawa, Y.; Machida, T.; Matsueda, H.; Frankenberg, C.; Hasekamp, O. P.; Aben, I.

    2014-01-01

    We estimate the CO2 flux over Tropical Asia in 2009, 2010, and 2011 using Greenhouse Gases Observing Satellite (GOSAT) total column CO2(XCO2) and in situ measurements of CO2. Compared to flux estimates from assimilating surface measurements of CO2, GOSAT XCO2 estimates a more dynamic seasonal cycle

  5. Three Satellites to Be Launched on One Rocket in 2011

    Institute of Scientific and Technical Information of China (English)

    2005-01-01

    Aspace storm observation project has recently been put into implementation. The project consists of three exploration satellites. One will operate in an orbit of proximity 700km altitude for scientific research in ionosphere and thermosphere, one in an orbit of 50,O00km for near earth magnetic sphere research and the last one in 150,O00km orbit for the research on solar winds outside the earth magnetic sphere.

  6. Launch mission summary and terminal countdown, Delta 153 Satellite Business Systems satellite (SBS-A)

    Science.gov (United States)

    1980-01-01

    A brief summary of the launch vehicle, spacecraft, and mission is contained. Information relative to launch windows, vehicle telemetry coverage, realtime data flow, telemetry coverage by station, selected trajectory information, and a brief sequence of flight events is also included.

  7. Space debris proximity analysis in powered and orbital phases during satellite launch

    Science.gov (United States)

    Bandyopadhyay, Priyankar; Sharma, R. K.; Adimurthy, V.

    2004-01-01

    This paper describes the methodology of the space debris proximity analysis in powered and orbital phase at the time of a satellite launch. The details of the SPADEPRO analysis package, developed for this purpose, are presented. It consists of modules which provide the functions related to ephemeris generation and reconstruction of primary object (launch vehicle or its payload upon insertion), determination of close approaches with resident space objects, computation of the state vector variance of the primary and the secondary objects to represent the knowledge uncertainty, and computation of the collision risk given the variance. This has been successfully applied during the recent launches of the Indian Space Research Organization.

  8. 20 Years Experience with using Low Cost Launch Opportunities for 20 Small Satellite Missions

    Science.gov (United States)

    Meerman, Maarten; Sweeting, Martin, , Sir

    To realise the full potential of modern low cost mini-micro-nano-satellite missions, regular and affordable launch opportunities are required. It is simply not economic to launch individual satellites of 5-300kg on single dedicated launchers costing typically 15-20M per launch. Whilst there have been periodic 'piggy-back' launches of small satellites on US launchers since the 1960's, these have been infrequent and often experienced significant delays due the vagaries of the main (paying!) payload. In 1989, Arianespace provided a critical catalyst to the microsatellite community when it imaginatively developed the ASAP platform on Ariane-4 providing, for the first time, a standard interface and affordable launch contracts for small payloads up to 50kg. During the 1990's, some 20 small satellites have been successfully launched on the Ariane-4 ASAP ring for international customers carrying out a range of operational, technology demonstration and training missions. However, most of these microsatellite missions seek low Earth orbit and especially sun-synchronous orbits, but the number of primary missions into these orbit has declined since 1996 and with it the availability of useful low cost launch opportunities for microsatellites. Whilst Ariane-5 has an enhanced capacity ASAP, it has yet to be widely used due both to the infrequent launches, higher costs, and the GTO orbit required by the majority of customers. China, Japan and India have also provided occasional secondary launches for small payloads, but not yet on a regular basis. Fortunately, the growing interest and demand for microsatellite missions coincided with the emergence of regular, low cost launch opportunities from the former Soviet Union (FSU) - both as secondary 'piggy-back' missions or as multiple microsatellite payloads on converted military ICBMs. Indeed, the FSU now supplies the only affordable means of launching minisatellites (200-500kg) into LEO as dedicated missions on converted missiles as

  9. The Impact of New Trends in Satellite Launches on Orbital Debris Environment

    Science.gov (United States)

    Karacalioglu, Arif Goktug; Stupl, Jan

    2016-01-01

    The main goal of this study is to examine the impact of new trends in satellite launch activities on the orbital debris environment and collision risk. Starting from the launch of the first artificial satellite in 1957, space borne technology has become an indispensable part of our lives. More than 6,000 satellites have been launched into Earth orbit. Though the annual number of satellites launched stayed flat for many decades, the trend has recently changed. The satellite market has been undergoing a major evolution with new space companies replacing the traditional approach of deploying a few large, complex and costly satellites with an approach to use a multitude of smaller, less complex and cheaper satellites. This new approach creates a sharp increase in the number of satellites and so the historic trends are no longer representative. As a foundation for this study, a scenario for satellite deployments based on the publicly announced future satellite missions has been developed. These constellation-deploying companies include, but are not limited to, Blacksky, CICERO, EROS, Landmapper, Leosat, Northstar, O3b, OmniEarth, OneWeb, Orbcomm, OuterNet, PlanetIQ, Planet Labs, Radarsat, RapidEye Next Generation, Sentinel, Skybox, SpaceX, and Spire. Information such as the annual number of launches, the number of orbital planes to be used by the constellation, as well as apogee, perigee, inclination, spacecraft mass and area were included or approximated. Besides the production of satellites, a widespread ongoing effort to enhance orbital injection capabilities will allow delivery of more spacecraft more accurately into Earth orbits. A long list of companies such as Microcosm, Rocket Lab, Firefly Space Systems, Sierra Nevada Corporation and Arca Space Corporation are developing new launch vehicles dedicated for small satellites. There are other projects which intend to develop interstages with propulsive capabilities which will allow the deployment of satellites into

  10. Satellite Splat: An Inelastic Collision with a Surface-launched Projectile

    Science.gov (United States)

    2015-04-23

    Satellite splat: an inelastic collision with a surface-launched projectile Philip R Blanco1 and Carl E Mungan2 1Department of Physics and Astronomy ...orbital motion, inelastic collision, momentum conservation, energy conservation 1. Introduction Introductory physics courses cover momentum conservation

  11. Global CO2 fluxes estimated from GOSAT retrievals of total column CO2

    Directory of Open Access Journals (Sweden)

    S. Basu

    2013-09-01

    Full Text Available We present one of the first estimates of the global distribution of CO2 surface fluxes using total column CO2 measurements retrieved by the SRON-KIT RemoTeC algorithm from the Greenhouse gases Observing SATellite (GOSAT. We derive optimized fluxes from June 2009 to December 2010. We estimate fluxes from surface CO2 measurements to use as baselines for comparing GOSAT data-derived fluxes. Assimilating only GOSAT data, we can reproduce the observed CO2 time series at surface and TCCON sites in the tropics and the northern extra-tropics. In contrast, in the southern extra-tropics GOSAT XCO2 leads to enhanced seasonal cycle amplitudes compared to independent measurements, and we identify it as the result of a land–sea bias in our GOSAT XCO2 retrievals. A bias correction in the form of a global offset between GOSAT land and sea pixels in a joint inversion of satellite and surface measurements of CO2 yields plausible global flux estimates which are more tightly constrained than in an inversion using surface CO2 data alone. We show that assimilating the bias-corrected GOSAT data on top of surface CO2 data (a reduces the estimated global land sink of CO2, and (b shifts the terrestrial net uptake of carbon from the tropics to the extra-tropics. It is concluded that while GOSAT total column CO2 provide useful constraints for source–sink inversions, small spatiotemporal biases – beyond what can be detected using current validation techniques – have serious consequences for optimized fluxes, even aggregated over continental scales.

  12. Global CO2 fluxes estimated from GOSAT retrievals of total column CO2

    Directory of Open Access Journals (Sweden)

    M. Torn

    2013-02-01

    Full Text Available We present one of the first estimates of the global distribution of CO2 surface fluxes using total column CO2 measurements retrieved from the Greenhouse gases Observing SATellite (GOSAT. We derive optimized fluxes from June 2009 to December 2010. We estimate fluxes from surface CO2 measurements to use as baselines for comparing GOSAT data-derived fluxes. Assimilating only GOSAT data, we can reproduce the observed CO2 time series at surface and TCCON sites in the tropics and the northern extra-tropics. In contrast, in the southern extra-tropics GOSAT XCO2 leads to enhanced seasonal cycle amplitudes compared to independent measurements, and we identify it as the result of a land-sea bias in our GOSAT XCO2 retrievals. A bias correction in the form of a global offset between GOSAT land and sea pixels in a joint inversion of satellite and surface measurements of CO2 yields plausible global flux estimates which are more tightly constrained than in an inversion using surface CO2 data alone. We show that assimilating the bias-corrected GOSAT data on top of surface CO2 data (a reduces the estimated global land sink of CO2, and (b shifts the terrestrial net uptake of carbon from the tropics to the extra-tropics. It is concluded that while GOSAT total column CO2 provide useful constraints for source-sink inversions, small spatiotemporal biases – beyond what can be detected using current validation techniques – have serious consequences for optimized fluxes, even aggregated over continental scales.

  13. The Impact of New Trends in Satellite Launches on the Orbital Debris Environment

    Science.gov (United States)

    Karacalioglu, Arif Goektug; Stupl, Jan

    2016-01-01

    The main goal of this study is to examine the impact of new trends in satellite launch activities on the orbital debris environment and collision risk. As a foundation for the study, we developed a deployment scenario for satellites and associated rocket bodies based on publicly announced future missions. The upcoming orbital injection technologies, such as the new launch vehicles dedicated for small spacecraft and propulsive interstages, are also considered in this scenario. We then used a simulation tool developed in-house to propagate the objects within this scenario using variable-sized time-steps as small as one second to detect conjunctions between objects. The simulation makes it possible to follow the short- and long-term effects of a particular satellite or constellation in the space environment. Likewise, the effects of changes in the debris environment on a particular satellite or constellation can be evaluated. It is our hope that the results of this paper and further utilization of the developed simulation tool will assist in the investigation of more accurate deorbiting metrics to replace the generic 25-year disposal guidelines, as well as to guide future launches toward more sustainable and safe orbits.

  14. Hyper Heuristic Approach for Design and Optimization of Satellite Launch Vehicle

    Institute of Scientific and Technical Information of China (English)

    Amer Farhan RAFIQUE; HE Linshu; Ali KAMRAN; Qasim ZEESHAN

    2011-01-01

    Satellite launch vehicle lies at the cross-road of multiple challenging technologies and its design and optimization present a typical example of multidisciplinary design and optimization (MDO) process. The complexity of problem demands highly efficient and effective algorithm that can optimize the design. Hyper heuristic approach (HHA) based on meta-heuristics is applied to the optimization of air launched satellite launch vehicle (ASLV). A non-learning random function (NLRF) is proposed to control low-level meta-heuristics (LLMHs) that increases certainty of global solution, an essential ingredient required in product conceptual design phase of aerospace systems. Comprehensive empirical study is performed to evaluate the performance advantages of proposed approach over popular non-gradient based optimization methods. Design of ASLV encompasses aerodynamics,propulsion, structure, stages layout, mass distribution, and trajectory modules connected by multidisciplinary feasible design approach. This approach formulates explicit system-level goals and then forwards the design optimization process entirely over to optimizer. This distinctive approach for launch vehicle system design relieves engineers from tedious, iterative task and enables them to improve their component level models. Mass is an impetus on vehicle performance and cost, and so it is considered as the core of vehicle design process. Therefore, gross launch mass is to be minimized in HHA.

  15. Post launch calibration and testing of the Advanced Baseline Imager on the GOES-R satellite

    Science.gov (United States)

    Lebair, William; Rollins, C.; Kline, John; Todirita, M.; Kronenwetter, J.

    2016-05-01

    The Geostationary Operational Environmental Satellite R (GOES-R) series is the planned next generation of operational weather satellites for the United State's National Oceanic and Atmospheric Administration. The first launch of the GOES-R series is planned for October 2016. The GOES-R series satellites and instruments are being developed by the National Aeronautics and Space Administration (NASA). One of the key instruments on the GOES-R series is the Advance Baseline Imager (ABI). The ABI is a multi-channel, visible through infrared, passive imaging radiometer. The ABI will provide moderate spatial and spectral resolution at high temporal and radiometric resolution to accurately monitor rapidly changing weather. Initial on-orbit calibration and performance characterization is crucial to establishing baseline used to maintain performance throughout mission life. A series of tests has been planned to establish the post launch performance and establish the parameters needed to process the data in the Ground Processing Algorithm. The large number of detectors for each channel required to provide the needed temporal coverage presents unique challenges for accurately calibrating ABI and minimizing striping. This paper discusses the planned tests to be performed on ABI over the six-month Post Launch Test period and the expected performance as it relates to ground tests.

  16. Bias corrections of GOSAT SWIR XCO2 and XCH4 with TCCON data and their evaluation using aircraft measurement data

    Science.gov (United States)

    Inoue, Makoto; Morino, Isamu; Uchino, Osamu; Nakatsuru, Takahiro; Yoshida, Yukio; Yokota, Tatsuya; Wunch, Debra; Wennberg, Paul O.; Roehl, Coleen M.; Griffith, David W. T.; Velazco, Voltaire A.; Deutscher, Nicholas M.; Warneke, Thorsten; Notholt, Justus; Robinson, John; Sherlock, Vanessa; Hase, Frank; Blumenstock, Thomas; Rettinger, Markus; Sussmann, Ralf; Kyrö, Esko; Kivi, Rigel; Shiomi, Kei; Kawakami, Shuji; De Mazière, Martine; Arnold, Sabrina G.; Feist, Dietrich G.; Barrow, Erica A.; Barney, James; Dubey, Manvendra; Schneider, Matthias; Iraci, Laura T.; Podolske, James R.; Hillyard, Patrick W.; Machida, Toshinobu; Sawa, Yousuke; Tsuboi, Kazuhiro; Matsueda, Hidekazu; Sweeney, Colm; Tans, Pieter P.; Andrews, Arlyn E.; Biraud, Sebastien C.; Fukuyama, Yukio; Pittman, Jasna V.; Kort, Eric A.; Tanaka, Tomoaki

    2016-08-01

    We describe a method for removing systematic biases of column-averaged dry air mole fractions of CO2 (XCO2) and CH4 (XCH4) derived from short-wavelength infrared (SWIR) spectra of the Greenhouse gases Observing SATellite (GOSAT). We conduct correlation analyses between the GOSAT biases and simultaneously retrieved auxiliary parameters. We use these correlations to bias correct the GOSAT data, removing these spurious correlations. Data from the Total Carbon Column Observing Network (TCCON) were used as reference values for this regression analysis. To evaluate the effectiveness of this correction method, the uncorrected/corrected GOSAT data were compared to independent XCO2 and XCH4 data derived from aircraft measurements taken for the Comprehensive Observation Network for TRace gases by AIrLiner (CONTRAIL) project, the National Oceanic and Atmospheric Administration (NOAA), the US Department of Energy (DOE), the National Institute for Environmental Studies (NIES), the Japan Meteorological Agency (JMA), the HIAPER Pole-to-Pole observations (HIPPO) program, and the GOSAT validation aircraft observation campaign over Japan. These comparisons demonstrate that the empirically derived bias correction improves the agreement between GOSAT XCO2/XCH4 and the aircraft data. Finally, we present spatial distributions and temporal variations of the derived GOSAT biases.

  17. The Potential for Methane Isotopologue Channels in GOSAT-2

    Science.gov (United States)

    Malina, Edward; Yoshida, Yukio; Matsunaga, Tsuneo; Muller, Jan-Peter

    2017-04-01

    Of the major Greenhouse Gases (GHGs) currently considered as having a major impact on atmospheric chemistry, Methane is amongst the most important (IPCC, 2014). Methane concentration in the atmosphere has been documented to be rising steadily over the past century, aside from an unexplained short period in the middle of the last decade (Heimann., 2011), leading to renewed efforts to understand global atmospheric Methane. Atmospheric Methane is primarily composed of two key isotopologues, 12CH4 and 13CH4, which have a natural abundance of about 98% and 1.1% respectively. It is a well-established fact that different sources of Methane (i.e. biogenic sources such as methanogens, or non-biogenic such as industrial hydrocarbon burning) vary in the abundance of these isotopologues (Etiope, 2009). The global identification of the ratios of these isotopologues could vastly increase knowledge of global Methane sources, and shed some light on global Methane growth. GOSAT-2 due to be launched in 2018 is a follow on from the original GOSAT mission launched in 2009. GOSAT-2 aims to continue the legacy of GOSAT by providing global measurements of Methane and Carbon Dioxide on a global basis in order to monitor GHG emissions. GOSAT-2 in the context of this study has a significant advantage over GOSAT, which is the extension of the sensitivity of band 3 to 2330nm from 2080nm where significant numbers of Methane spectral lines are located. In this study we apply the well-established Information Content (IC) analysis techniques originally proposed by Rodgers (2000) to determine the potential benefit of retrieving total column Methane isotopologue concentrations assuming bands 2 and 3 of the GOSAT-2/TANSO-FTS-2 instrument. The value of such studies has been proven on multiple occasions and can provide guidance on appropriate potential retrieval setups. Due to the fact that there has been limited research in this area, no 'a priori' state vectors or Variance Covariance Matrices (VCMs

  18. Comparison between IASI and GOSAT retrievals in the thermal infrared

    Science.gov (United States)

    Payan, S.; Camy-peyret, C.; Bureau, J.; Shiomi, K.

    2012-04-01

    GOSAT (Greenhouse Gases Observing SATellite) is a satellite dedicated to the study of greenhouses gases. It carries an infrared Fourier transform spectrometer (The Thermal and Near Infrared Sensor for Carbon Observation Fourier-Transform Spectrometer or TANSO-FTS), which acquires spectra in 4 bands, located in the Near-Infrared (NIR), ShortWave Infrared (SWIR) and Thermal Infrared (TIR). An imager (CAI: Cloud and Aerosols imager) enables to gain information on clouds and aerosols, and this information is used to improve the quality of CO2 and CH4 retrievals. IASI (Infrared Atmospheric Sounding Interferometer) designed by CNES for Eumetsat is carried by the MetOp-A satellite. It is used for operational meteorology and is also interesting for greenhouse gases as well as for atmospheric chemistry and climate. We looked for close spatial and temporal coincidences between IASI and TANSO-FTS nadir spectra. Due to the respective orbits of MetOp-A and GOSAT, this is only achieved at high latitudes. We compared the surface temperature, CO2, CH4, N2O and O3 mixing ratios retrieved from TANSO-FTS and from IASI spectra. We used the [940;980] cm-1 window for CO2 (laser band), [1240;1320] cm-1 for CH4, [1140;1200] cm-1 for N2O, and [980;1100] cm-1 for O3. Since IASI is considered as a reference for radiometric calibrations, we compared the surface temperatures retrieved by GOSAT and IASI in these different windows to assess the GOSAT radiometric calibration. The GOSAT/IASI comparison is done on surface temperature rather than on raw radiances because the different instrumental noise and spectral resolution of these instruments make a direct comparison of the radiances more difficult. The use of different spectral windows enabled us to explore the spectral dependence of the TANSO-FTS radiometric calibration. Cloud-free and spatially homogenous fields of view (IFOVs) were selected using CAI images. Finally, we will show the potential to further improve the results using the

  19. A Mathematical Modeling Approach of the Failure Analysis for the Real-Time Mexican Satellite Space Launch Center

    OpenAIRE

    Omar Ariosto Niño Prieto; Luis Enrique Colmenares Guillén

    2015-01-01

    In this paper, a simulation of the Mathematical Model for Real-Time Satellite Launch Platform approach in Mexico is presented. Mexico holds the fourth best place in the world for building a platform to launch space satellites, since its geographic location is optimal for its construction. It is essential to have the Probabilistic Failure Analysis in Space Systems Engineering from its design, in order to minimize risks and avoid any possible catastrophe. The mathematical approach o...

  20. Post launch calibration and testing of the Geostationary Lightning Mapper on GOES-R satellite

    Science.gov (United States)

    Rafal, Marc; Clarke, Jared T.; Cholvibul, Ruth W.

    2016-05-01

    The Geostationary Operational Environmental Satellite R (GOES-R) series is the planned next generation of operational weather satellites for the United States National Oceanic and Atmospheric Administration (NOAA). The National Aeronautics and Space Administration (NASA) is procuring the GOES-R spacecraft and instruments with the first launch of the GOES-R series planned for October 2016. Included in the GOES-R Instrument suite is the Geostationary Lightning Mapper (GLM). GLM is a single-channel, near-infrared optical detector that can sense extremely brief (800 μs) transient changes in the atmosphere, indicating the presence of lightning. GLM will measure total lightning activity continuously over the Americas and adjacent ocean regions with near-uniform spatial resolution of approximately 10 km. Due to its large CCD (1372x1300 pixels), high frame rate, sensitivity and onboard event filtering, GLM will require extensive post launch characterization and calibration. Daytime and nighttime images will be used to characterize both image quality criteria inherent to GLM as a space-based optic system (focus, stray light, crosstalk, solar glint) and programmable image processing criteria (dark offsets, gain, noise, linearity, dynamic range). In addition ground data filtering will be adjusted based on lightning-specific phenomenology (coherence) to isolate real from false transients with their own characteristics. These parameters will be updated, as needed, on orbit in an iterative process guided by pre-launch testing. This paper discusses the planned tests to be performed on GLM over the six-month Post Launch Test period to optimize and demonstrate GLM performance.

  1. Parametric fault estimation based on H∞ optimization in a satellite launch vehicle

    DEFF Research Database (Denmark)

    Soltani, Mohsen; Izadi-Zamanabadi, Roozbeh; Stoustrup, Jakob

    2008-01-01

    Correct diagnosis under harsh environmental conditions is crucial for space vehiclespsila health management systems to avoid possible hazardous situations. Consequently, the diagnosis methods are required to be robust toward these conditions. Design of a parametric fault detector, where the fault...... estimation is formulated in the so-called standard set-up for Hinfin control design problem, is addressed in this paper. In particular, we investigate the tunability of the design through the dedicated choice of the fault model. The method is applied to the model of turbopump as a subsystem of the jet engine...... for the satellite launch vehicle and the results are discussed....

  2. Post-Launch Calibration and Testing of Space Weather Instruments on GOES-R Satellite

    Science.gov (United States)

    Tadikonda, Sivakumara S. K.; Merrow, Cynthia S.; Kronenwetter, Jeffrey A.; Comeyne, Gustave J.; Flanagan, Daniel G.; Todirita, Monica

    2016-01-01

    The Geostationary Operational Environmental Satellite - R (GOES-R) is the first of a series of satellites to be launched, with the first launch scheduled for October 2016. The three instruments - Solar Ultra Violet Imager (SUVI), Extreme ultraviolet and X-ray Irradiance Sensor (EXIS), and Space Environment In-Situ Suite (SEISS) provide the data needed as inputs for the product updates National Oceanic and Atmospheric Administration (NOAA) provides to the public. SUVI is a full-disk extreme ultraviolet imager enabling Active Region characterization, filament eruption, and flare detection. EXIS provides inputs to solar backgrounds/events impacting climate models. SEISS provides particle measurements over a wide energy-and-flux range that varies by several orders of magnitude and these data enable updates to spacecraft charge models for electrostatic discharge. EXIS and SEISS have been tested and calibrated end-to-end in ground test facilities around the United States. Due to the complexity of the SUVI design, data from component tests were used in a model to predict on-orbit performance. The ground tests and model updates provided inputs for designing the on-orbit calibration tests. A series of such tests have been planned for the Post-Launch Testing (PLT) of each of these instruments, and specific parameters have been identified that will be updated in the Ground Processing Algorithms, on-orbit parameter tables, or both. Some of SUVI and EXIS calibrations require slewing them off the Sun, while no such maneuvers are needed for SEISS. After a six-month PLT period the GOES-R is expected to be operational. The calibration details are presented in this paper.

  3. Post-Launch Calibration and Testing of Space Weather Instruments on GOES-R Satellite

    Science.gov (United States)

    Tadikonda, S. K.; Merrow, Cynthia S.; Kronenwetter, Jeffrey A.; Comeyne, Gustave J.; Flanagan, Daniel G.; Todrita, Monica

    2016-01-01

    The Geostationary Operational Environmental Satellite - R (GOES-R) is the first of a series of satellites to be launched, with the first launch scheduled for October 2016. The three instruments Solar UltraViolet Imager (SUVI), Extreme ultraviolet and X-ray Irradiance Sensor (EXIS), and Space Environment In-Situ Suite (SEISS) provide the data needed as inputs for the product updates National Oceanic and Atmospheric Administration (NOAA) provides to the public. SUVI is a full-disk extreme ultraviolet imager enabling Active Region characterization, filament eruption, and flare detection. EXIS provides inputs to solar back-ground-sevents impacting climate models. SEISS provides particle measurements over a wide energy-and-flux range that varies by several orders of magnitude and these data enable updates to spacecraft charge models for electrostatic discharge. EXIS and SEISS have been tested and calibrated end-to-end in ground test facilities around the United States. Due to the complexity of the SUVI design, data from component tests were used in a model to predict on-orbit performance. The ground tests and model updates provided inputs for designing the on-orbit calibration tests. A series of such tests have been planned for the Post-Launch Testing (PLT) of each of these instruments, and specific parameters have been identified that will be updated in the Ground Processing Algorithms, on-orbit parameter tables, or both. Some of SUVI and EXIS calibrations require slewing them off the Sun, while no such maneuvers are needed for SEISS. After a six-month PLT period the GOES-R is expected to be operational. The calibration details are presented in this paper.

  4. Post-launch calibration and testing of space weather instruments on GOES-R satellite

    Science.gov (United States)

    Tadikonda, Sivakumara S. K.; Merrow, Cynthia S.; Kronenwetter, Jeffrey A.; Comeyne, Gustave J.; Flanagan, Daniel G.; Todirita, Monica

    2016-05-01

    The Geostationary Operational Environmental Satellite - R (GOES-R) is the first of a series of satellites to be launched, with the first launch scheduled for October 2016. The three instruments -- Solar UltraViolet Imager (SUVI), Extreme ultraviolet and X-ray Irradiance Sensor (EXIS), and Space Environment In-Situ Suite (SEISS) provide the data needed as inputs for the product updates National Oceanic and Atmospheric Administration (NOAA) provides to the public. SUVI is a full-disk extreme ultraviolet imager enabling Active Region characterization, filament eruption, and flare detection. EXIS provides inputs to solar backgrounds/events impacting climate models. SEISS provides particle measurements over a wide energy-and-flux range that varies by several orders of magnitude and these data enable updates to spacecraft charge models for electrostatic discharge. EXIS and SEISS have been tested and calibrated end-to-end in ground test facilities around the United States. Due to the complexity of the SUVI design, data from component tests were used in a model to predict on-orbit performance. The ground tests and model updates provided inputs for designing the on-orbit calibration tests. A series of such tests have been planned for the Post-Launch Testing (PLT) of each of these instruments, and specific parameters have been identified that will be updated in the Ground Processing Algorithms, on-orbit parameter tables, or both. Some of SUVI and EXIS calibrations require slewing them off the Sun, while no such maneuvers are needed for SEISS. After a six-month PLT period the GOES-R is expected to be operational. The calibration details are presented in this paper.

  5. Influence of aerosols and thin cirrus clouds on the GOSAT-observed CO2: a case study over Tsukuba

    Directory of Open Access Journals (Sweden)

    A. Bril

    2011-11-01

    Full Text Available Lidar observations of vertical profiles of aerosols and thin cirrus clouds were made at Tsukuba (36.1° N, 140.1° E, Japan, to investigate the influence of aerosols and thin cirrus clouds on the column-averaged dry-air mole fraction of carbon dioxide (XCO2 retrieved from observation data of the Thermal And Near-infrared Sensor for carbon Observation Fourier Transform Spectrometer, measured in the Short-Wavelength InfraRed band (TANSO-FTS SWIR, onboard the Greenhouse gases Observing SATellite (GOSAT. The lidar system measured the backscattering ratio, depolarization ratio, and/or the wavelength exponent of atmospheric particles. The lidar observations and ground-based high-resolution FTS measurements at the Tsukuba Total Carbon Column Observing Network (Tsukuba TCCON site were recorded simultaneously during passages of GOSAT over Tsukuba. GOSAT SWIR XCO2 data (version 01.xx released in August 2010 were compared with the lidar and Tsukuba TCCON data. High-altitude aerosols and thin cirrus clouds had a large impact on the GOSAT SWIR XCO2 results. By taking into account the observed aerosol/cirrus vertical profiles and using a more adequate solar irradiance database in the GOSAT SWIR retrieval, the difference between the GOSAT SWIR XCO2 data and the Tsukuba TCCON data was greatly reduced.

  6. Suborbital Reusable Launch Vehicles as an Opportunity to Consolidate and Calibrate Ground Based and Satellite Instruments

    Science.gov (United States)

    Papadopoulos, K.

    2014-12-01

    XCOR Aerospace, a commercial space company, is planning to provide frequent, low cost access to near-Earth space on the Lynx suborbital Reusable Launch Vehicle (sRLV). Measurements in the external vacuum environment can be made and can launch from most runways on a limited lead time. Lynx can operate as a platform to perform suborbital in situ measurements and remote sensing to supplement models and simulations with new data points. These measurements can serve as a quantitative link to existing instruments and be used as a basis to calibrate detectors on spacecraft. Easier access to suborbital data can improve the longevity and cohesiveness of spacecraft and ground-based resources. A study of how these measurements can be made on Lynx sRLV will be presented. At the boundary between terrestrial and space weather, measurements from instruments on Lynx can help develop algorithms to optimize the consolidation of ground and satellite based data as well as assimilate global models with new data points. For example, current tides and the equatorial electrojet, essential to understanding the Thermosphere-Ionosphere system, can be measured in situ frequently and on short notice. Furthermore, a negative-ion spectrometer and a Faraday cup, can take measurements of the D-region ion composition. A differential GPS receiver can infer the spatial gradient of ionospheric electron density. Instruments and optics on spacecraft degrade over time, leading to calibration drift. Lynx can be a cost effective platform for deploying a reference instrument to calibrate satellites with a frequent and fast turnaround and a successful return of the instrument. A calibrated reference instrument on Lynx can make collocated observations as another instrument and corrections are made for the latter, thus ensuring data consistency and mission longevity. Aboard a sRLV, atmospheric conditions that distort remotely sensed data (ground and spacecraft based) can be measured in situ. Moreover, an

  7. Launch Vehicles Based on Advanced Hybrid Rocket Motors: An Enabling Technology for the Commercial Small and Micro Satellite Planetary Science

    Science.gov (United States)

    Karabeyoglu, Arif; Tuncer, Onur; Inalhan, Gokhan

    2016-07-01

    Mankind is relient on chemical propulsion systems for space access. Nevertheless, this has been a stagnant area in terms of technological development and the technology base has not changed much almost for the past forty years. This poses a vicious circle for launch applications such that high launch costs constrain the demand and low launch freqencies drive costs higher. This also has been a key limiting factor for small and micro satellites that are geared towards planetary science. Rather this be because of the launch frequencies or the costs, the access of small and micro satellites to orbit has been limited. With today's technology it is not possible to escape this circle. However the emergence of cost effective and high performance propulsion systems such as advanced hybrid rockets can decrease launch costs by almost an order or magnitude. This paper briefly introduces the timeline and research challenges that were overcome during the development of advanced hybrid LOX/paraffin based rockets. Experimental studies demonstrated effectiveness of these advanced hybrid rockets which incorporate fast burning parafin based fuels, advanced yet simple internal balistic design and carbon composite winding/fuel casting technology that enables the rocket motor to be built from inside out. A feasibility scenario is studied using these rocket motors as building blocks for a modular launch vehicle capable of delivering micro satellites into low earth orbit. In addition, the building block rocket motor can be used further solar system missions providing the ability to do standalone small and micro satellite missions to planets within the solar system. This enabling technology therefore offers a viable alternative in order to escape the viscous that has plagued the space launch industry and that has limited the small and micro satellite delivery for planetary science.

  8. Radiometric trend of lunar calibration compared with vicarious calibration for GOSAT

    Science.gov (United States)

    Shiomi, K.; Kawakami, S.; Kuze, A.; Suto, H.; Hashiguchi, T.; Kataoka, F.; Higuchi, R.; Bruegge, C. J.; Schwandner, F. M.; Chapsky, L.

    2014-12-01

    GOSAT observes a nearly full moon for the on-orbit radiometric calibration of the FTS SWIR bands and the CAI. Lunar calibrations are operated in April/May for investigation of continuous annual radiometric trends and in June/July, corresponding to the annual Railroad Valley Cal/Val campaign. JAXA's Greenhouse Gases Observing Satellite (GOSAT) is since 2009 in polar orbit to monitor greenhouse gases such as CO2 and CH4 from space. GOSAT consists of a Fourier Transform Spectrometer (TANSO-FTS) and a Cloud and Aerosol Imager (TANSO-CAI). The FTS has 3 polarized SWIR narrow bands and a TIR wide band. The FTS observes globally with gridded points of 10 km FOV using discrete pointing. The CAI carries 4 radiometers in the UV to SWIR with high spatial resolution of 0.5-1.5 km and a wide swath of 1000 km. Since the 3rd year, lunar calibration has been planned to observe at a phase angle around 7 degrees from normal incidence. This choice avoids the reflectance opposition surge in order to target the nearly-unchanged and brightest reflectance as a function of phase angle. The Railroad Valley vicarious calibration campaign is conducted by measuring the surface reflectance and atmospheric parameters coincident with a dedicated GOSAT target observation, to derive top-of-the-atmosphere radiance. The nadir surface reflectance is collected in 500x500 m areas corresponding to the CAI resolution. The off-nadir reflectance is measured simultaneously with BRDF values, for correction. We will summarize the radiometric study of the GOSAT lunar calibration compared with the vicarious calibration. In-flight coincident calibration activities will continue with GOSAT and OCO-2.

  9. CMAQ simulation of atmospheric CO2 concentration in East Asia: Comparison with GOSAT observations and ground measurements

    Science.gov (United States)

    Li, Rong; Zhang, Meigen; Chen, Liangfu; Kou, Xingxia; Skorokhod, Andrei

    2017-07-01

    Satellite observations are widely used in global CO2 assimilations, but their quality for use in regional assimilation systems has not yet been thoroughly determined. Validation of satellite observations and model simulations of CO2 is crucial for carbon flux inversions. In this study, we focus on evaluating the uncertainties of model simulations and satellite observations. The atmospheric CO2 distribution in East Asia during 2012 was simulated using a regional chemical transport model (RAMS-CMAQ) and compared with both CO2 column density (XCO2) from the Gases Observing SATellite (GOSAT) and CO2 concentrations from the World Data Centre for Greenhouse Gases (WDCGG). The results indicate that simulated XCO2 is generally lower than GOSAT XCO2 by 1.19 ppm on average, and their monthly differences vary from 0.05 to 2.84 ppm, with the corresponding correlation coefficients ranging between 0.1 and 0.67. CMAQ simulations are good to capture the CO2 variation as ground-based observations, and their correlation coefficients are from 0.62 to 0.93, but the average value of CMAQ simulation is 2.4 ppm higher than ground-based observation. Thus, we inferred that the GOSAT retrievals may overestimate XCO2, which is consistent with the validation of GOSAT XCO2 using Total Carbon Column Observing Network measurements. The near-surface CO2 concentration was obviously overestimated in GOSAT XCO2. Compared with the relatively small difference between CMAQ and GOSAT XCO2, the large difference in CO2 near surface or their vertical profiles indicates more improvements are needed to reduce the uncertainties in both satellite observations and model simulations.

  10. Launch in orbit of the NINA-2 apparatus aboard the satellite MITA

    Science.gov (United States)

    Casolino, M.; NINA-2 Collaboration

    2001-08-01

    The satellite MITA was launched on July the 15th , 2000 from the cosmodrome of Plesetsk (Russia) with a Cosmos-3M rocket. MITA carries the payload NINA-2 for the study of solar and galactic cosmic rays. The detector used in this mission is identical to the one already flying on the Russian satellite Resurs-O1 n.4 in a 840 km sunsynchronous orbit, but makes use of the extensive computer and telemetry capabilities of MITA bus to improve the active data acquisition time. The scientific objectives of NINA are the study of cosmic nuclei from hydrogen to iron in the energy range between 10 MeV/n and 1 GeV/n during solar maximum period. The device is capable of charge identification up to iron with isotope sensitivity up to oxigen. The 87.3 degrees, 460 km altitude polar orbit allows investigations of cosmic rays of solar and galactic origin as well as the trapped component. In this work we present preliminary results concerning particle identification capabilities and nuclear differential spectra for helium, carbon and oxygen in the energy range between 10 and 50 MeV/n.

  11. Optimization of the GOSAT global observation from space with region-by-region target-mode operations

    Science.gov (United States)

    kuze, A.; Suto, H.; Shiomi, K.; Kawakami, S.; Nakajima, M.

    2013-12-01

    Since its launch in 2009, the Thermal And Near infrared Sensor for carbon Observation Fourier-Transform Spectrometer (TANSO-FTS) onboard the Greenhouse gases Observing SATellite (GOSAT) has continued its grid observation and acquired about 20,000 samples per day. Now that more than 10 programs are planned or proposed to monitor greenhouse gases from space. TANSO-FTS is the only instrument that uses a Fourier transfer spectrometer. It is not an imaging spectrometer but has a symmetrical instrument line shape function (ILSF) that can be expressed to high precision for all wavelengths with a simple analytical function and can reduce fitting errors for atmosphere remote sensing. Therefore, other future instruments can cross-calibrate their data with accurate and precise GOSAT spectra. Since August 2010, TANSO-FTS has selected 3-point cross-track scan mode, which has the current best pointing stability and observes a single point three times in 14 sec. Column-averaged dry air mole fractions of CO2 (XCO2) and CH4 (XCH4) have been well validated at the TCCON sites, where surface albedo is not high and aerosol optical thickness is small. Long term GOSAT data show seasonal and latitudinal variation and annual increase accurately and precisely. JAXA has been processing and providing all the Level 1B spectra data that were acquired on-orbit. Thus the distribution of the Level 1B is spatially equal. The Level 2 users are retrieving XCO2 and XCH4 from the Level 1 by filtering cloud contaminated, aerosol thick, and low signal-to-noise ratio scenes. As a result, the yield rate at cloudy area such as Amazon, south-east Asia, and Central America, low surface albedo area such as snow and ice, bay and channels is very low. Aerosol thick area such as Sahara also has larger errors. Now that GOSAT demonstrated accurate XCO2 and XCH4 remote sensing, demand for emission source measurements of mega cities, power plants, gas fields, and volcanos has increased. In addition to grid

  12. Discussion of vicarious calibration of GOSAT/TANSO-CAI UV-band (380nm) and aerosol retrieval in wildfire region in the OCO-2 and GOSAT observation campaign at Railroad Valley in 2016

    Science.gov (United States)

    Hashimoto, M.; Kuze, A.; Bruegge, C. J.; Shiomi, K.; Kataoka, F.; Kikuchi, N.; Arai, T.; Kasai, K.; Nakajima, T.

    2016-12-01

    The GOSAT (Greenhouse Gases Observing Satellite) / TANSO-CAI (Cloud and Aerosol Imager, CAI) is an imaging sensor to measure cloud and aerosol properties and observes reflected sunlight from the atmosphere and surface of the ground. The sensor has four bands from near ultraviolet (near-UV) to shortwave infrared, 380, 674, 870 and 1600nm. The field of view size is 0.5 km for band-1 through band-3, and 1.5km for band-4. Band-1 (380nm) is one of unique function of the CAI. The near-UV observation offers several advantages for the remote sensing of aerosols over land: Low reflectance of most surfaces; Sensitivity to absorbing aerosols; Absorption of trace gases is weak (Höller et al., 2004). CAI UV-band is useful to distinguish absorbing aerosol (smoke) from cloud. GOSAT-2/TANSO-CAI-2 that will be launched in the future also has UV-bands, 340 and 380nm. We carried out an experiment to calibrate CAI UV-band radiance using data taken in a field campaign of OCO-2 and GOSAT at Railroad Valley in 2016. The campaign period is June 27 to July 3 in 2016. We measured surface reflectance by using USB4000 Spectrometer with 74-UV collimating lens (Ocean Optics) and Spectralon (Labsphere). USB4000 is a UV spectrometer, and its measurement range from 300 to 520nm. We simulated CAI UV-band radiance using a vector type of radiation transfer code, i.e. including polarization calculation, pstar3 (Ota et al., 2010) using measured surface reflectance and atmospheric data, pressure and relative humidity by radiosonde in the same campaign, and aerosol optical depth by AERONET, etc. Then, we evaluated measured UV radiances with the simulated data. We show the result of vicarious calibration of CAI UV-band in the campaign, and discuss about this method for future sensor, CAI-2. Around the campaign period, there was wildfire around Los Angeles, and aerosol optical thickness (AOT) observed by AERONET at Rail Road valley and Caltech sites is also high. We tried to detect and retrieve aerosol

  13. Who launched what, when and why; trends in global land-cover observation capacity from civilian earth observation satellites

    Science.gov (United States)

    Belward, Alan S.; Skøien, Jon O.

    2015-05-01

    This paper presents a compendium of satellites under civilian and/or commercial control with the potential to gather global land-cover observations. From this we show that a growing number of sovereign states are acquiring capacity for space based land-cover observations and show how geopolitical patterns of ownership are changing. We discuss how the number of satellites flying at any time has progressed as a function of increased launch rates and mission longevity, and how the spatial resolutions of the data they collect has evolved. The first such satellite was launched by the USA in 1972. Since then government and/or private entities in 33 other sovereign states and geopolitical groups have chosen to finance such missions and 197 individual satellites with a global land-cover observing capacity have been successfully launched. Of these 98 were still operating at the end of 2013. Since the 1970s the number of such missions failing within 3 years of launch has dropped from around 60% to less than 20%, the average operational life of a mission has almost tripled, increasing from 3.3 years in the 1970s to 8.6 years (and still lengthening), the average number of satellites launched per-year/per-decade has increased from 2 to 12 and spatial resolution increased from around 80 m to less than 1 m multispectral and less than half a meter for panchromatic; synthetic aperture radar resolution has also fallen, from 25 m in the 1970s to 1 m post 2007. More people in more countries have access to data from global land-cover observing spaceborne missions at a greater range of spatial resolutions than ever before. We provide a compendium of such missions, analyze the changes and shows how innovation, the need for secure data-supply, national pride, falling costs and technological advances may underpin the trends we document.

  14. Update on GOSAT TANSO-FTS performance, operations, and data products after more than 6 years in space

    Science.gov (United States)

    Kuze, Akihiko; Suto, Hiroshi; Shiomi, Kei; Kawakami, Shuji; Tanaka, Makoto; Ueda, Yoko; Deguchi, Akira; Yoshida, Jun; Yamamoto, Yoshifumi; Kataoka, Fumie; Taylor, Thomas E.; Buijs, Henry L.

    2016-06-01

    A data set containing more than 6 years (February 2009 to present) of radiance spectra for carbon dioxide (CO2) and methane (CH4) observations has been acquired by the Greenhouse gases Observing SATellite (GOSAT, available at http://data.gosat.nies.go.jp/GosatUserInterfaceGateway/guig/GuigPage/open.do), nicknamed "Ibuki", Thermal And Near infrared Sensor for carbon Observation Fourier Transform Spectrometer (TANSO-FTS). This paper provides updates on the performance of the satellite and TANSO-FTS sensor and describes important changes to the data product, which has recently been made available to users. With these changes the typical accuracy of retrieved column-averaged dry air mole fractions of CO2 and CH4 (XCO2 and XCH4, respectively) are 2 ppm or 0.5 % and 13 ppb or 0.7 %, respectively. Three major anomalies of the satellite system affecting TANSO-FTS are reported: a failure of one of the two solar paddles in May 2014, a switch to the secondary pointing system in January 2015, and most recently a cryocooler shutdown and restart in August 2015. The Level 1A (L1A) (raw interferogram) and the Level 1B (L1B) (radiance spectra) of version V201 described here have long-term uniform quality and provide consistent retrieval accuracy even after the satellite system anomalies. In addition, we discuss the unique observation abilities of GOSAT made possible by an agile pointing mechanism, which allows for optimization of global sampling patterns.

  15. Forest productivity and water stress in Amazonia: observations from GOSAT chlorophyll fluorescence.

    Science.gov (United States)

    Lee, Jung-Eun; Frankenberg, Christian; van der Tol, Christiaan; Berry, Joseph A; Guanter, Luis; Boyce, C Kevin; Fisher, Joshua B; Morrow, Eric; Worden, John R; Asefi, Salvi; Badgley, Grayson; Saatchi, Sassan

    2013-06-22

    It is unclear to what extent seasonal water stress impacts on plant productivity over Amazonia. Using new Greenhouse gases Observing SATellite (GOSAT) satellite measurements of sun-induced chlorophyll fluorescence, we show that midday fluorescence varies with water availability, both of which decrease in the dry season over Amazonian regions with substantial dry season length, suggesting a parallel decrease in gross primary production (GPP). Using additional SeaWinds Scatterometer onboard QuikSCAT satellite measurements of canopy water content, we found a concomitant decrease in daily storage of canopy water content within branches and leaves during the dry season, supporting our conclusion. A large part (r(2) = 0.75) of the variance in observed monthly midday fluorescence from GOSAT is explained by water stress over moderately stressed evergreen forests over Amazonia, which is reproduced by model simulations that include a full physiological representation of photosynthesis and fluorescence. The strong relationship between GOSAT and model fluorescence (r(2) = 0.79) was obtained using a fixed leaf area index, indicating that GPP changes are more related to environmental conditions than chlorophyll contents. When the dry season extended to drought in 2010 over Amazonia, midday basin-wide GPP was reduced by 15 per cent compared with 2009.

  16. On-orbit lunar calibration compared with vicarious calibration for GOSAT

    Science.gov (United States)

    Shiomi, K.; Kawakami, S.; kuze, A.; Suto, H.; Hashiguchi, T.; Kataoka, F.; Higuchi, R.; Bruegge, C.; Schwandner, F. M.

    2013-12-01

    JAXA's Greenhouse Gases Observing Satellite (GOSAT) is since 2009 in polar orbit to monitor greenhouse gases such as CO2 and CH4 from space. GOSAT consists of a Fourier Transform Spectrometer (TANSO-FTS) and a Cloud and Aerosol Imager (TANSO-CAI). The FTS has 3 polarized SWIR narrow bands and a TIR wide band. The FTS observes globally with gridded points of 10 km FOV using discrete pointing. The CAI carries 4 radiometers in the UV to SWIR with high spatial resolution of 0.5-1.5 km and a wide swath of 1000 km. In this study, we compare the lunar calibration results with the results of our annual vicarious calibration campaigns. For lunar calibrations, GOSAT observes a nearly full moon for the on-orbit radiometric calibration of the FTS SWIR bands and the CAI. Lunar calibrations are operated in April for investigation of continuous annual sensitivity trends and in July, corresponding to the annual Railroad Valley Cal/Val campaign. Since the 3rd year, lunar calibration has been planned to observe in a phase angle around 7 degrees to avoid the reflectance opposition surge in order to target the nearly-unchanged and brightest reflectance as a function of phase angle. The Railroad Valley vicarious calibration campaign is conducted by measuring the surface reflectance and atmospheric parameters coincident with a dedicated GOSAT target observation, to derive top-of-the-atmosphere radiance. The nadir surface reflectance is collected in 500x500 m areas corresponding to the CAI resolution. The off-nadir reflectance is obtained simultaneously with BRDF values, for correction. We will discuss the sensitivity study by comparison between the GOSAT lunar observation and the vicarious calibration.

  17. Can satellite-based monitoring techniques be used to quantify volcanic CO2 emissions?

    Science.gov (United States)

    Schwandner, Florian M.; Carn, Simon A.; Kuze, Akihiko; Kataoka, Fumie; Shiomi, Kei; Goto, Naoki; Popp, Christoph; Ajiro, Masataka; Suto, Hiroshi; Takeda, Toru; Kanekon, Sayaka; Sealing, Christine; Flower, Verity

    2014-05-01

    we have conducted repeated target mode observations of now almost 40 persistently active global volcanoes and other point sources, including Etna (Italy), Mayon (Philippines), Hawaii (USA), Popocatepetl (Mexico), and Ambrym (Vanuatu), using GOSAT FTS SWIR data. In this presentation we will summarize results from over three years of measurements and progress toward understanding detectability with this method. In emerging collaboration with the Deep Carbon Observatory's DECADE program, the World Organization of Volcano Observatories (WOVO) global database of volcanic unrest (WOVOdat), and country specific observatories and agencies we see a growing potential for ground based validation synergies. Complementing the ongoing GOSAT mission, NASA is on schedule to launch its OCO-2 satellite in July 2014, which will provide higher spatial but lower temporal resolution. Further orbiting and geostationary satellite sensors are in planning at JAXA, NASA, and ESA.

  18. ESA technology flies on Italian mini-satellite launched from Russia

    Science.gov (United States)

    2000-07-01

    Owned by the Italian space agency (ASI) and developed by Carlo Gavazzi with contributions from many other Italian companies, MITA has two tasks to perform: in a circular orbit at 450 km altitude, the mini satellite will carry a cosmic particle detector, while its platform will be tested for the first time as a vehicle for future scientific missions. MITA also carries the MTS-AOMS payload (MicroTechSensor for Attitude and Orbit Measurement System), developed by Astrium in the framework of ESA's Technology Flight Opportunity trial programme. With the Technology Flight Opportunity scheme, funded by its General Studies Programme, ESA intends to provide access to space for European industry's technology products needing in-orbit demonstration to enhance their competitiveness on the space market. This new form of support to the European space industry ties in with ESA's strategy for fostering the competitiveness of European-made technology for eventual commercialisation. In-orbit demonstration is essential if new technologies are to compete on level terms on non-European markets. It thus consolidates strategic investments made by the space industry. The MTS-AOMS is a highly integrated sensor for autonomous attitude and orbit control systems. It combines three functions in one unit: Earth sensing, star sensing and magnetic field sensing. The equipment incorporates an active pixel array sensor and a 2-D fluxgate magnetometer. The aims of the flight are to verify in situ the payload's inherent functions and performance, which cannot be done on the ground, and to assess the behaviour of this type of technology when exposed to the space environment. The Technology Flight Opportunity rule is that ESA funds the launch and integration costs, industry the development and operating costs. According to present planning, two further in-orbit demonstrations funded by this scheme will be carried out between now and January 2001.

  19. Monitoring greenhouse gas emissions in Australian landscapes: Comparing ground based mobile surveying data to GOSAT observations

    Science.gov (United States)

    Bashir, S.; Iverach, C.; Kelly, B. F. J.

    2016-12-01

    Climate change is threatening the health and stability of the natural world and human society. Such concerns were emphasized at COP21 conference in Paris 2015 which highlighted the global need to improve our knowledge of sources of greenhouse gas and to develop methods to mitigate the effects of their emissions. Ongoing spatial and temporal measurements of greenhouse gases at both point and regional scales is important for clarification of climate change mechanisms and accounting. The Greenhouse gas Observing SATellite (GOSAT) is designed to monitor the global distribution of carbon dioxide (CO2) and methane (CH4) from orbit. As existing ground monitoring stations are limited and still unevenly distributed, satellite observations provide important frequent, spatially extensive, but low resolution observations. Recent developments in portable laser based greenhouse gas measurement systems have enabled the rapid measurement of greenhouse gases in ppb at the ground surface. This study was conducted to map major sources of CO2 and CH4 in the eastern states of Australia at the landscape scale and to compare the results to GOSAT observations. During April 2016 we conducted a regional CH4 and CO2 mobile survey, using an LGR greenhouse gas analyzer. Measurements were made along a 4000 KM circuit through major cities, country towns, dry sclerophyll forests, coastal wetlands, coal mining regions, coal seam gas developments, dryland farming and irrigated agricultural landscapes. The ground-based survey data were then compared with the data (L2) from GOSAT. Ground-based mobile surveys showed that there are clear statistical differences in the ground level atmospheric concentration of CH4 and CO2 associated with all major changes in land use. These changes extend for kilometers, and cover one or more GOSAT pixels. In the coal mining districts the ground-level atmospheric concentration of CH4 exceeded 2 ppm for over 40 km, yet this was not discernable in the retrieved data (L2

  20. Intercomparison of Level 3 fields estimated from OCO-2 and GOSAT-ACOSmeasurements of XCO2

    Science.gov (United States)

    Weir, B.; Chatterjee, A.; Ott, L. E.; Pawson, S.

    2016-12-01

    The GEOS-Carb modeling and assimilation system is an extension of the GEOS-5general circulation model and data assimilation system developed at NASA'sGlobal Modeling and Assimilation Office (GMAO). One of its primary functionsis to ingest observations of carbon dioxide (CO2) and produce estimates andpredictions of atmospheric mixing ratios of CO2 over the Earth. In particular,the system processes retrievals of column-average carbon dioxide (XCO2) basedon near-infrared radiance measurements from the Orbiting Carbon Observatory 2(OCO-2) and the Greenhouse Gases Observing Satellite (GOSAT). The resultingLevel 3 (L3) maps are the most complete and highest resolution assimilatedpicture of global CO2 yet. The extent of its coverage makes the L3 product apowerful tool for the evaluation of the satellite data against independentobservations. This evaluation approach does not require using coincidencecriteria and can be applied across heterogeneous observations (e.g., comparingthe assimilation of XCO2 retrievals to flask samples). This presentationdescribes the evaluation of L3 maps computed from OCO-2 and GOSAT AtmosphericCO2 Observations from Space (GOSAT-ACOS) retrievals against ground-basedmeasurements of XCO2 from the Total Column Carbon Observing Network (TCCON) andin situ measurements from flasks, towers, and aircraft taken by NOAA/ESRL. Theevaluation focuses on comparison of the bias and uncertainty of the tworetrievals and how understanding these differences can improve the use of theretrievals in assimilation systems.

  1. Inter-annual variability of summertime CO2 exchange in Northern Eurasia inferred from GOSAT XCO2

    Science.gov (United States)

    Ishizawa, M.; Mabuchi, K.; Shirai, T.; Inoue, M.; Morino, I.; Uchino, O.; Yoshida, Y.; Belikov, D.; Maksyutov, S.

    2016-10-01

    Northern Eurasia is one of the largest terrestrial carbon reservoirs on the Earth’s surface. However, since the coverage of surface CO2 observations is still limited, the response to the climate variability remains uncertain. We estimated monthly CO2 fluxes for three sub-regions in Northern Eurasia (north of ˜60°N), Northeastern Europe, Western Siberia and Eastern Siberia, using CO2 retrievals from the Japanese Greenhouse Gases Observing SATellite (GOSAT). The variations of estimated CO2 fluxes were examined in terms of the regional climate variability, for the three consecutive growing seasons of 2009-2011. The CO2 fluxes estimated using GOSAT data are highly correlated with the surface temperature anomalies in July and August (r > 0.8) while no correlation is found in the CO2 fluxes estimated only using surface observations. The estimated fluxes from GOSAT data exhibit high negative correlations with one-month lagged positive precipitation anomalies in late summer (r > -0.7) through surface temperature and the Normalized Difference Vegetation Index (NDVI). The results indicate that GOSAT data reflects the changes in terrestrial biospheric processes responding to climate anomalies. In 2010, a large part of Eurasia experienced an extremely hot and dry summer, while cold and wet weather conditions were recorded in Western Siberia. The CO2 fluxes estimated from GOSAT data showed a reduction of net CO2 uptake in Northeastern Europe and Eastern Siberia, but the enhancement of net CO2 uptake in Western Siberia. These opposite sub-regional flux anomalies can be explained by the different climate anomalies on a sub-regional scale in Northern Eurasia. Thus, this study demonstrates that space-based observations by GOSAT compensate for the lack of ground-based observational coverage so as to better capture the inter-annually varying atmosphere-terrestrial biosphere CO2 exchange on a regional scale.

  2. Influence of aerosols and thin cirrus clouds on the GOSAT-observed CO2: a case study over Tsukuba

    Directory of Open Access Journals (Sweden)

    A. Bril

    2012-04-01

    Full Text Available Lidar observations of vertical profiles of aerosols and thin cirrus clouds were made at Tsukuba (36.05° N, 140.12° E, Japan, to investigate the influence of aerosols and thin cirrus clouds on the column-averaged dry-air mole fraction of carbon dioxide (XCO2 retrieved from observation data of the Thermal And Near-infrared Sensor for carbon Observation Fourier Transform Spectrometer, measured in the Short-Wavelength InfraRed band (TANSO-FTS SWIR, onboard the Greenhouse gases Observing SATellite (GOSAT. The lidar system measured the backscattering ratio, depolarization ratio, and/or the wavelength exponent of atmospheric particles. The lidar observations and ground-based high-resolution FTS measurements at the Tsukuba Total Carbon Column Observing Network (Tsukuba TCCON site were recorded simultaneously during passages of GOSAT over Tsukuba. GOSAT SWIR XCO2 data (Version 01.xx released in August 2010 were compared with the lidar and Tsukuba TCCON data. High-altitude aerosols and thin cirrus clouds had a large impact on the GOSAT SWIR XCO2 results. By taking into account the observed aerosol/cirrus vertical profiles and using a more adequate solar irradiance database in the GOSAT SWIR retrieval, the difference between the GOSAT SWIR XCO2 data and the Tsukuba TCCON data was reduced. The 3-band retrieval approach where the aerosol and cirrus profiles were retrieved gave us the best results and the retrieved XCO2 data followed the seasonal cycle of ~8 ppm observed at Tsukuba TCCON site.

  3. A Modular Minimum Cost Launch System for Nano-Satellites Project

    Data.gov (United States)

    National Aeronautics and Space Administration — As minimum cost will be required for a dedicated Nano-Sat Launch Vehicle, a parallel staged, highly modular vehicle architecture is proposed for development. The...

  4. Consistent evaluation of GOSAT, SCIAMACHY, CarbonTracker, and MACC through comparisons to TCCON

    Science.gov (United States)

    Kulawik, S. S.; Wunch, D.; O'Dell, C.; Frankenberg, C.; Reuter, M.; Oda, T.; Chevallier, F.; Sherlock, V.; Buchwitz, M.; Osterman, G.; Miller, C.; Wennberg, P.; Griffith, D. W. T.; Morino, I.; Dubey, M.; Deutscher, N. M.; Notholt, J.; Hase, F.; Warneke, T.; Sussmann, R.; Robinson, J.; Strong, K.; Schneider, M.; Wolf, J.

    2015-06-01

    Consistent validation of satellite CO2 estimates is a prerequisite for using multiple satellite CO2 measurements for joint flux inversion, and for establishing an accurate long-term atmospheric CO2 data record. We focus on validating model and satellite observation attributes that impact flux estimates and CO2 assimilation, including accurate error estimates, correlated and random errors, overall biases, biases by season and latitude, the impact of coincidence criteria, validation of seasonal cycle phase and amplitude, yearly growth, and daily variability. We evaluate dry air mole fraction (XCO2) for GOSAT (ACOS b3.5) and SCIAMACHY (BESD v2.00.08) as well as the CarbonTracker (CT2013b) simulated CO2 mole fraction fields and the MACC CO2 inversion system (v13.1) and compare these to TCCON observations (GGG2014). We find standard deviations of 0.9 ppm, 0.9, 1.7, and 2.1 ppm versus TCCON for CT2013b, MACC, GOSAT, and SCIAMACHY, respectively, with the single target errors 1.9 and 0.9 times the predicted errors for GOSAT and SCIAMACHY, respectively. When satellite data are averaged and interpreted according to error2 = a2+ b2 /n (where n are the number of observations averaged, a are the systematic (correlated) errors, and b are the random (uncorrelated) errors), we find that the correlated error term a = 0.6 ppm and the uncorrelated error term b = 1.7 ppm for GOSAT and a = 1.0 ppm, b = 1.4 ppm for SCIAMACHY regional averages. Biases at individual stations have year-to-year variability of ~ 0.3 ppm, with biases larger than the TCCON predicted bias uncertainty of 0.4 ppm at many stations. Using fitting software, we find that GOSAT underpredicts the seasonal cycle amplitude in the Northern Hemisphere (NH) between 46-53° N. In the Southern Hemisphere (SH), CT2013b underestimates the seasonal cycle amplitude. Biases are calculated for 3-month intervals and indicate the months that contribute to the observed amplitude differences. The seasonal cycle phase indicates

  5. Chinasat 9 to Be Launched in 2007

    Institute of Scientific and Technical Information of China (English)

    2005-01-01

    CASC is chosen by China Satellite Communications Corporation (China Satcom) to launch Chinasat 9 direct broadcasting satellite around July 2007, The satellite will be launched into a geostationary orbit by a LM3B from Xichang Satellite Launch Center,

  6. Inferring regional sources and sinks of atmospheric CO2 from GOSAT XCO2 data

    Directory of Open Access Journals (Sweden)

    F. Deng

    2013-10-01

    Full Text Available We have examined the utility of retrieved column-averaged, dry-air mole fractions of CO2 (XCO2 from the Greenhouse Gases Observing Satellite (GOSAT for quantifying monthly, regional flux estimates of CO2, using the GEOS-Chem four-dimensional variational (4D-Var data assimilation system. We focused on assessing the potential impact of biases in the GOSAT CO2 data on the regional flux estimates. Using different screening and bias correction approaches, we selected three different subsets of the GOSAT XCO2 data for the 4D-Var inversion analyses, and found that the inferred global fluxes were consistent across the three XCO2 inversions. However, the GOSAT observational coverage was a challenge for the regional flux estimates. In the northern extratropics, the inversions were more sensitive to North American fluxes than to European and Asian fluxes due to the lack of observations over Eurasia in winter and over eastern and southern Asia in summer. The regional flux estimates were also sensitive to the treatment of the residual bias in the GOSAT XCO2 data. The largest differences obtained were for Temperate North America and Temperate South America, for which the largest spread between the inversions was 1.02 Pg C and 0.96 Pg C, respectively. In the case of Temperate North America, one inversion suggested a strong source, whereas the second and third XCO2 inversions produced a weak and strong sink, respectively. Despite the discrepancies in the regional flux estimates between the three XCO2 inversions, the a posteriori CO2 distributions were in good agreement (with a mean difference between the three inversions of typically less than 0.5 ppm with independent data from the Total Carbon Column Observing Network (TCCON, the surface flask network, and from the HIAPER Pole-to-Pole Observations (HIPPO aircraft campaign. The discrepancy in the regional flux estimates from the different inversions, despite the agreement of the global flux estimates, suggests

  7. Estimating regional methane surface fluxes: the relative importance of surface and GOSAT mole fraction measurements

    Directory of Open Access Journals (Sweden)

    A. Fraser

    2013-06-01

    Full Text Available We use an ensemble Kalman filter (EnKF, together with the GEOS-Chem chemistry transport model, to estimate regional monthly methane (CH4 fluxes for the period June 2009–December 2010 using proxy dry-air column-averaged mole fractions of methane (XCH4 from GOSAT (Greenhouse gases Observing SATellite and/or NOAA ESRL (Earth System Research Laboratory and CSIRO GASLAB (Global Atmospheric Sampling Laboratory CH4 surface mole fraction measurements. Global posterior estimates using GOSAT and/or surface measurements are between 510–516 Tg yr−1, which is less than, though within the uncertainty of, the prior global flux of 529 ± 25 Tg yr−1. We find larger differences between regional prior and posterior fluxes, with the largest changes in monthly emissions (75 Tg yr−1 occurring in Temperate Eurasia. In non-boreal regions the error reductions for inversions using the GOSAT data are at least three times larger (up to 45% than if only surface data are assimilated, a reflection of the greater spatial coverage of GOSAT, with the two exceptions of latitudes >60° associated with a data filter and over Europe where the surface network adequately describes fluxes on our model spatial and temporal grid. We use CarbonTracker and GEOS-Chem XCO2 model output to investigate model error on quantifying proxy GOSAT XCH4 (involving model XCO2 and inferring methane flux estimates from surface mole fraction data and show similar resulting fluxes, with differences reflecting initial differences in the proxy value. Using a series of observing system simulation experiments (OSSEs we characterize the posterior flux error introduced by non-uniform atmospheric sampling by GOSAT. We show that clear-sky measurements can theoretically reproduce fluxes within 10% of true values, with the exception of tropical regions where, due to a large seasonal cycle in the number of measurements because of clouds and aerosols, fluxes are within 15% of true fluxes. We evaluate our

  8. Metallurgical analysis of a failed maraging steel shear screw used in the band separation system of a satellite launch vehicle

    Directory of Open Access Journals (Sweden)

    S.V.S. Narayana Murty

    2016-10-01

    Full Text Available Maraging steels have excellent combination of strength and toughness and are extensively used for a variety of aerospace applications. In one such critical application, this steel was used to fabricate shear screws of a stage separation system in a satellite launch vehicle. During assembly preparations, one of the shear screws which connected the separation band and band end block has failed at the first thread. Microstructural analysis revealed that the crack originated from the root of the thread and propagated in an intergranular mode. The failure is attributed to combined effect of stress and corrosion leading to stress corrosion cracking.

  9. New Projects Planed/launched By Cei Wg On Satellite Navigation Systems

    Science.gov (United States)

    Oszczak, S.; Manzoni, G.

    In the paper a short description of main projects on satellite positioning and naviga- tion in CEI countries is given. Special attention is devoted to the activity of members of Working Group on Satellite Navigation Systems. The projects in which they are involved and results of performed experiments can be specified as follows: - EGNOS positioning - the first results in CEI area, - application of various transmission tech- niques to diffusion of DGPS/RTK data from reference stations (SWIFT/DARC, RDS, radiobeacons, UHF transmission), - development of integrated GPS/INS methods for car navigation and GIS purposes, - development of software for integration of satellite vehicle position with numerical maps for car navigation, monitoring and acquisition of terrestrial data for GIS, - elaboration of method and software development for nav- igation and monitoring of aircraft during approaching and landing phase of flight, - elaboration of methods and software for integration of 3D satellite positions of user with Digital Terrain Model (DTM), - development of digital technology for bathy- metric survey with satellite positioning technique; mapping of shallow waters, lakes, rivers and inland water reservoirs, The recently planned studies and experiments cover land, marine and aircraft satellite navigation with EGNOS system in CEI countries. The project of extension of the EGNOS system to the Central and East European region is under preparation. Other important research is conducted on mapping of roads and rails tracks using integrated DGPS/INS techniques.

  10. Data fusion of CO2 retrieved from GOSAT and AIRS using regression analysis and fixed rank kriging

    Science.gov (United States)

    Zhou, Cong; Shi, Runhe; Gao, Wei

    2015-09-01

    This paper proposes an improved statistical method for fusing carbon dioxide (CO2) data retrieved from two major instruments, the Greenhouse gases Observing SATellite (GOSAT) and the Atmospheric Infrared Sounder (AIRS). These two datasets were fused to obtain CO2 concentrations near the surface, which is a region that is especially important for studies on carbon sources and sinks. Overall, the CO2 monthly average values from GOSAT are all lower than those from AIRS from 2010 to 2012. The datasets show the similar seasonal cycles of carbon dioxide and show an increasing trend with a determination coefficient of 0.45. A strong correlation was determined by adding the climatic factors as independent variables for regression analysis. The correlation coefficients between the CO2 values from AIRS and GOSAT significantly increased in response. The true CO2 data processes were then predicted using the fixed rank kriging method. This showed that the data-fusion CO2 product provides more reasonable information and that the corresponding mean squared prediction errors are smaller than those from the single GOSAT CO2 dataset.

  11. Pre-Launch Radiometric Performance Characterization of the Advanced Technology Microwave Sounder on the Joint Polar Satellite System-1 Satellite

    Science.gov (United States)

    Smith, Craig K.; Kim, Edward; Leslie, R. Vincent; Lyu, Joseph; McCormick, Lisa M.; Anderson, Kent

    2017-01-01

    The Advanced Technology Microwave Sounder (ATMS) is a space-based, cross-track radiometer for operational atmospheric temperature and humidity sounding, utilizing 22 channels over a frequency range from 23 to 183 gigahertz. The ATMS for the Joint Polar Satellite System-1 has undergone two rounds of re-work in 2014-2015 and 2016, following performance issues discovered during and following thermal vacuum chamber (TVAC) testing at the instrument and observatory level. Final shelf-level testing, including measurement of pass band characteristics and spectral response functions, was completed in December 2016. Final instrument-level TVAC testing and calibration occurred during February 2017. Here we will describe the instrument-level TVAC calibration process, and illustrate with results from the final TVAC calibration effort.

  12. Investigation variation of carbon dioxide based on GOSAT data in peninsular Malaysia

    Science.gov (United States)

    Sim, C. K.; Lim, H. S.; MatJafri, M. Z.

    2015-10-01

    Carbon dioxide (CO2) is an inodorous and transparent gas, and naturally originates in our atmosphere. Due to its optical characteristics, CO2 is the most important greenhouse gas and play a key role in climate change due to an effective thermal infrared (IR) radiation absorber. Satellite observations of atmospheric carbon dioxide (CO2) can significantly improve our knowledge about the sources and sinks of CO2. The remote sensing satellite, namely Greenhouse Gases Observing Satellite (GOSAT) was employed to investigate the spatial and variations of CO2 column-averaged dry airmole fractions, denoted XCO2 over Peninsular Malaysia from January 2013 to December 2013. The analysis of CO2 in the study area shows the significant differences between northeast monsoon (NEM) and the southwest monsoon (SWM). During NEM season, cold air outbreaks from Siberia spreads to equatorial region in the form of north-easterly cold surge winds and associated with a low-level anticyclone over Southeast Asia. Inversely, air masses from the southwest contribute to long-range air pollution due to transportation of atmospheric CO2 by wind is associated with biomass burning in Sumatra, Indonesia. The GOSAT data and the Satellite measurements are able to measure the increase of the atmosphere CO2 values over different regions.

  13. LM-2C Series Launch Vehicles

    Institute of Scientific and Technical Information of China (English)

    XueFuxing

    2004-01-01

    On December 30, 2003, a LM-2C/SM launch vehicle was launched from Xichang Satellite Launch Center (XSLC), successfully sending TC-1 satellite into orbit. The satellite is the first one of the two scientific satellites known as Double Star. The operation orbit of the satellite is the highest compared with China's other satellites ever launched.

  14. Interpreting seasonal changes in the carbon balance of southern Amazonia using measurements of XCO2 and chlorophyll fluorescence from GOSAT

    OpenAIRE

    Parazoo, Nicholas C.; Bowman, Kevin; Frankenberg, Christian; Lee, Jung-Eun; Fisher, Joshua B.; Worden, John; Jones, Dylan B. A.; Berry, Joseph; Collatz, G James; Baker, Ian T.; Jung, Martin; Liu, Junjie; Osterman, Gregory; O'Dell, Chris; Sparks, Athena

    2013-01-01

    Amazon forests exert a major influence on the global carbon cycle, but quantifying the impact is complicated by diverse landscapes and sparse data. Here we examine seasonal carbon balance in southern Amazonia using new measurements of column-averaged dry air mole fraction of CO_2 (XCO_2) and solar induced chlorophyll fluorescence (SIF) from the Greenhouse Gases Observing Satellite (GOSAT) from July 2009 to December 2010. SIF, which reflects gross primary production (GPP), is used to disentang...

  15. Extraction and Analysis of Regional Emission and Absorption Events of Greenhouse Gases with GOSAT and OCO-2

    Science.gov (United States)

    Kasai, K.; Shiomi, K.; Konno, A.; Tadono, T.; Hori, M.

    2016-12-01

    Global observation of greenhouse gases such as carbon dioxide (CO2) and methane (CH4) with high spatio-temporal resolution and accurate estimation of sources and sinks are important to understand greenhouse gases dynamics. Greenhouse Gases Observing Satellite (GOSAT) has observed column-averaged dry-air mole fractions of CO2 (XCO2) and CH4 (XCH4) over 7 years since January 2009 with wide swath but sparse pointing. Orbiting Carbon Observatory-2 (OCO-2) has observed XCO2 jointly on orbit since July 2014 with narrow swath but high resolution. We use two retrieved datasets as GOSAT observation data. One is ACOS GOSAT/TANSO-FTS Level 2 Full Product by NASA/JPL, and the other is NIES TANSO-FTS L2 column amount (SWIR). By using these GOSAT datasets and OCO-2 L2 Full Product, the biases among datasets, local sources and sinks, and temporal variability of greenhouse gases are clarified. In addition, CarbonTracker, which is a global model of atmospheric CO2 and CH4 developed by NOAA/ESRL, are also analyzed for comparing between satellite observation data and atmospheric model data. Before analyzing these datasets, outliers are screened by using quality flag, outcome flag, and warn level in land or sea parts. Time series data of XCO2 and XCH4 are obtained globally from satellite observation and atmospheric model datasets, and functions which express typical inter-annual and seasonal variation are fitted to each spatial grid. Consequently, anomalous events of XCO2 and XCH4 are extracted by the difference between each time series dataset and the fitted function. Regional emission and absorption events are analyzed by time series variation of satellite observation data and by comparing with atmospheric model data.

  16. Heading Toward Launch with the Integrated Multi-Satellite Retrievals for GPM (IMERG)

    Science.gov (United States)

    Huffman, George J.; Bolvin, David T.; Nelkin, Eric J.; Adler, Robert F.

    2012-01-01

    The Day-l algorithm for computing combined precipitation estimates in GPM is the Integrated Multi-satellitE Retrievals for GPM (IMERG). We plan for the period of record to encompass both the TRMM and GPM eras, and the coverage to extend to fully global as experience is gained in the difficult high-latitude environment. IMERG is being developed as a unified U.S. algorithm that takes advantage of strengths in the three groups that are contributing expertise: 1) the TRMM Multi-satellite Precipitation Analysis (TMPA), which addresses inter-satellite calibration of precipitation estimates and monthly scale combination of satellite and gauge analyses; 2) the CPC Morphing algorithm with Kalman Filtering (KF-CMORPH), which provides quality-weighted time interpolation of precipitation patterns following cloud motion; and 3) the Precipitation Estimation from Remotely Sensed Information using Artificial Neural Networks using a Cloud Classification System (PERSIANN-CCS), which provides a neural-network-based scheme for generating microwave-calibrated precipitation estimates from geosynchronous infrared brightness temperatures. In this talk we summarize the major building blocks and important design issues driven by user needs and practical data issues. One concept being pioneered by the IMERG team is that the code system should produce estimates for the same time period but at different latencies to support the requirements of different groups of users. Another user requirement is that all these runs must be reprocessed as new IMERG versions are introduced. IMERG's status at meeting time will be summarized, and the processing scenario in the transition from TRMM to GPM will be laid out. Initially, IMERG will be run with TRMM-based calibration, and then a conversion to a GPM-based calibration will be employed after the GPM sensor products are validated. A complete reprocessing will be computed, which will complete the transition from TMPA.

  17. Regional CO2 flux estimates for 2009–2010 based on GOSAT and ground-based CO2 observations

    Directory of Open Access Journals (Sweden)

    S. Maksyutov

    2013-09-01

    Full Text Available We present the application of a global carbon cycle modeling system to the estimation of monthly regional CO2 fluxes from the column-averaged mole fractions of CO2 (XCO2 retrieved from spectral observations made by the Greenhouse gases Observing SATellite (GOSAT. The regional flux estimates are to be publicly disseminated as the GOSAT Level 4 data product. The forward modeling components of the system include an atmospheric tracer transport model, an anthropogenic emissions inventory, a terrestrial biosphere exchange model, and an oceanic flux model. The atmospheric tracer transport was simulated using isentropic coordinates in the stratosphere and was tuned to reproduce the age of air. We used a fossil fuel emission inventory based on large point source data and observations of nighttime lights. The terrestrial biospheric model was optimized by fitting model parameters to observed atmospheric CO2 seasonal cycle, net primary production data, and a biomass distribution map. The oceanic surface pCO2 distribution was estimated with a 4-D variational data assimilation system based on reanalyzed ocean currents. Monthly CO2 fluxes of 64 sub-continental regions, between June 2009 and May 2010, were estimated from GOSAT FTS SWIR Level 2 XCO2 retrievals (ver. 02.00 gridded to 5° × 5° cells and averaged on a monthly basis and monthly-mean GLOBALVIEW-CO2 data. Our result indicated that adding the GOSAT XCO2 retrievals to the GLOBALVIEW data in the flux estimation brings changes to fluxes of tropics and other remote regions where the surface-based data are sparse. The uncertainties of these remote fluxes were reduced by as much as 60% through such addition. Optimized fluxes estimated for many of these regions, were brought closer to the prior fluxes by the addition of the GOSAT retrievals. In most of the regions and seasons considered here, the estimated fluxes fell within the range of natural flux variabilities estimated with the component models.

  18. Commentary to "LARES successfully launched in orbit: Satellite and mission description" by A. Paolozzi and I. Ciufolini

    CERN Document Server

    Iorio, Lorenzo

    2014-01-01

    We comment on some statements in a recent paper by Paolozzi and Ciufolini concerning certain remarks raised by us on the realistic accuracy obtainable in testing the general relativistic Lense-Thirring effect in the gravitational field of the Earth with the newly launched LARES satellite together with the LAGEOS and LAGEOS II spacecraft in orbit for a long time. The orbital configuration of LARES is different from that of the originally proposed LAGEOS-3. Indeed, while the latter one should have been launched to the same altitude of LAGEOS (i.e. about $h_{\\rm L}=5890$ km) in an orbital plane displaced by $180$ deg with respect to that of LAGEOS ($I_{\\rm L}=110$ deg, $I_{\\rm L3}=70$ deg), LARES currently moves at a much smaller altitude (about $h_{\\rm LR}=1440$ km) and at a slightly different inclination ($I_{\\rm LR} = 69.5$ deg). As independently pointed out in the literature by different authors, the overall accuracy of a LARES-LAGEOS-LAGEOS II Lense-Thirring test may be unfavorably \\textcolor{black}{impacte...

  19. On the joint use of IASI and GOSAT retrievals in the thermal infrared

    Science.gov (United States)

    Bureau, J.; Payan, S.; Camy-Peyret, C.; Clerbaux, C.; Coheur, P.; Hurtmans, D.; Hadji-Lazaro, J.; Bauduin, S.; George, M.

    2012-12-01

    GOSAT (Greenhouse Gases Observing SATellite) is a satellite dedicated to the study of greenhouses gases. It carries an infrared Fourier transform spectrometer (Thermal And Near infrared Sensor for carbon Observation-Fourier Transform Spectrometer or TANSO-FTS), which acquires spectra in 4 bands, located in the Near-Infrared (NIR), ShortWave Infrared (SWIR) and Thermal Infrared (TIR). An imager (Cloud and Aerosol Imager or TANSO-CAI) enables to gain information on clouds and aerosols, and this information is used to improve the quality of CO2 and CH4 retrievals. IASI (Infrared Atmospheric Sounding Interferometer) designed by CNES for Eumetsat is carried by the MetOp-A satellite. It is used for operational meteorology and is also interesting for greenhouse gases as well as for atmospheric chemistry and climate. We looked for close spatial and temporal coincidences with six TCCON sites where high resolution FTIR measurements are performed routinely. Cloud-free and spatially homogeneous fields of view (IFOVs) were selected using CAI images. The TCCON retrieved VMR profiles have been used as reference and compared with those we retrieved from coincident measurements of GOSAT and IASI. We used the [1240;1320] cm-1 window for CH4, and the [980;1100] cm-1 window for O3 retrieval. Finally, we will highlight the potential to further improve the results using the synergy between measurements in the TIR and the SWIR spectral domains.

  20. Lessons Learned from GOSAT; Instrument Design, Calibration, Operation, Data Processing, and International Collaboration

    Science.gov (United States)

    Kuze, A.; Suto, H.; Shiomi, K.; Nakajima, M.

    2012-12-01

    Advantage of satellite observation is its ability to monitor long term and global distribution with a single instrument. Ozone observation from space has been successful for long term monitoring purposes. Monitoring gradual increase and distribution of greenhouse gases in the troposphere with sub-percent accuracy has become a challenging subject. Interference of cloud and aerosol in radiative transfer has to be corrected for troposphere measurement. Accurate O2-A band measurement can retrieve surface pressure and aerosol distribution property. We have selected a Fourier Transform spectrometer (FTS) to achieve high throughput and wide spectral coverage with uniform spectral resolution. On the other hand, it is difficult to modulate short wave such as 0.76μm and avoid micro vibration interference. Prelaunch, we took special care to select optical components of excellent surface quality and isolate vibration. Design parameters such as IFOV, spectral resolution, observation interval within limited satellite resources must be carefully optimized. Greenhouse gases Observing SATellite (GOSAT) has been providing global high spectral resolution data for almost 4 years. Instrument performance, radiometric calibration, radiative transfer calculation and laboratory spectroscopy are all important. The first step was to reduce bias of column-averaged dry air mole fractions (the Level 2 product) of CO2 and CH4 (XCO2 and XCH4) and validate using well calibrated data such as TCCON. After 2 years of operation, latitudinal distribution of zonal mean and seasonal variation at these sites can be measured with better than 2ppm accuracy. However, validations are limited to ideal conditions. Next step is to evaluate consistency of measured values from long periods since launch, different surface types, and various input radiance with different instrument gain. For long term radiometric calibration, we have uses vicarious, onboard solar diffuser, and lunar calibration data. Over the ocean

  1. Methane Footprint Measurements with IASI and GOSAT - Identification of Source Regions from Space

    Science.gov (United States)

    Malina, E.; Muller, J. P.; Walton, D.; Potts, D.

    2015-12-01

    To date, satellite instruments such as SCIAMACHY and GOSAT-TANSO-FTS have largely focused on regional scale methane output (Kort, A. E., et al. 2014), in order to gain insight into significant methane source regions (such as the Four Corners). However, such an approach does not tackle the root of the issue; the individual sources of methane that account for the total global methane budget, e.g. oil wells and marshland. In this study we aim to use existing satellite sensors onboard Metop and GOSAT to locate point sources of methane from space. We use nine years of global methane measurements from Metop-IASI A/B in order to exploit the exceptionally high global coverage of the instruments (total coverage of the Earth twice a day), and its relatively small spatial footprint in order to accurately identify these methane source regions. Using these data we show which regions have persistent sources (such as the Four Corners), and which are fugitive (methane bubbles in the Arctic), changing from one month to the next. Following the identification of significant source regions using IASI, we increase the resolution by cross-referencing with the higher spatial resolution (but patchy) GOSAT data, in order to answer the question of whether individual gas sources can be identified from space. This study partially follows the method proposed by Kort, who used SCIAMACHY to identify general areas of high methane release in the USA, focusing on the oilrigs in the Four Corners region. This study takes Kort's work further and attempts to identify individual sources (both natural and anthropogenic) using the GOSAT/IASI combination, backed up with ground-based knowledge of sources, such as the FrackTracker database and known natural sources such as the "Door to Hell" in Turkmenistan. Finally we show validation by comparing the individual footprints against methane measurements from the TCCON (Wunch, D., et al. 2010), thus providing confidence in the use of individual satellites

  2. The Outline of GOSAT-2 mission:requirements and specifications of mission instruments

    Science.gov (United States)

    Nakajima, Masakatsu; Suto, Hiroshi; Yotsumoto, Kazuhiko; Abe, Masashi; Kuze, Akihiko

    2013-04-01

    GOSAT which was launched on 23rd of January, 2009 has been operated over four years and an area for improvements such as the observation specifications and hardware methods as well as the measurement accuracy. Therefore we have studied the mission of the GOSAT follow-on, that is GOSAT-2 to leverage greenhouse gases observation from space for the science as well as the practical use such as the effort against global warming by the improvements of the observation performances. At first, we defined the requirements for the concentration measurement accuracies, the estimation error of the net flux and so on which should be accomplished in the next generation based on the GOSAT observation results. Secondly, the specifications of the mission instruments have been studied to satisfy the mission requirements and were defined. To confirm the possibilities of the defined specifications, we have carried out trial manufacture and considerations and redefined the specifications of the mission instruments. The principal improvement point is the increase of the number of the useful data. A large part of GOSAT data have been contaminated with the clouds and only a few percent of the measured data are used. To increase the useful data, we considered the following some kinds of methods. 1. Reduction of the IFOV size; It is possible to reduce the influence of the clouds if the IFOV size becomes small. But it is hard to compensate the reduction of the SNR, so we will give up the reduction of the IFOV size. 2. Adoption of multi FOV;GOSAT has only one FOV and we have considered to increase the number of the FOV to increase the number of the data by the adoption of the multi photo diodes detector. But the optical cross talk which is generated by the multipath reflection between cover glass and photo diodes is too large and exceeded our requirement. So we gave up the adoption of the multi FOVs. 3. Adoption of an intelligent pointing; We are considering to detect the clouds in the FOV of

  3. EOF-based regression algorithm for the fast retrieval of atmospheric CO2 total column amount from the GOSAT observations

    Science.gov (United States)

    Bril, Andrey; Maksyutov, Shamil; Belikov, Dmitry; Oshchepkov, Sergey; Yoshida, Yukio; Deutscher, Nicholas M.; Griffith, David; Hase, Frank; Kivi, Rigel; Morino, Isamu; Notholt, Justus; Pollard, David F.; Sussmann, Ralf; Velazco, Voltaire A.; Warneke, Thorsten

    2017-03-01

    This paper presents a novel retrieval algorithm for the rapid retrieval of the carbon dioxide total column amounts from high resolution spectra in the short wave infrared (SWIR) range observations by the Greenhouse gases Observing Satellite (GOSAT). The algorithm performs EOF (Empirical Orthogonal Function)-based decomposition of the measured spectral radiance and derives the relationship of limited number of the decomposition coefficients in terms of the principal components with target gas amount and a priori data such as airmass, surface pressure, etc. The regression formulae for retrieving target gas amounts are derived using training sets of collocated GOSAT and ground-based observations. The precision/accuracy characteristics of the algorithm are analyzed by the comparison of the retrievals with those from the Total Carbon Column Observing Network (TCCON) measurements and with the modeled data, and appear similar to those achieved by full-physics retrieval algorithms.

  4. Preliminary validation of column-averaged volume mixing ratios of carbon dioxide and methane retrieved from GOSAT short-wavelength infrared spectra

    Directory of Open Access Journals (Sweden)

    I. Morino

    2010-12-01

    Full Text Available Column-averaged volume mixing ratios of carbon dioxide and methane retrieved from the Greenhouse gases Observing SATellite (GOSAT Short-Wavelength InfraRed observation (GOSAT SWIR XCO2 and XCH4 were compared with the reference data obtained by ground-based high-resolution Fourier Transform Spectrometers (g-b FTSs participating in the Total Carbon Column Observing Network (TCCON.

    Through calibrations of g-b FTSs with airborne in-situ measurements, the uncertainty of XCO2 and XCH4 associated with the g-b FTS was determined to be 0.8 ppm (~0.2% and 4 ppb (~0.2%, respectively. The GOSAT products are validated with these calibrated g-b FTS data. Preliminary results are as follows: The GOSAT SWIR XCO2 and XCH4 (Version 01.xx are biased low by 8.85 ± 4.75 ppm (2.3 ± 1.2% and 20.4 ± 18.9 ppb (1.2 ± 1.1%, respectively. The precision of the GOSAT SWIR XCO2 and XCH4 is considered to be about 1%. The latitudinal distributions of zonal means of the GOSAT SWIR XCO2 and XCH4 show similar features to those of the g-b FTS data.

  5. Characteristics of Four-years of GOSAT/TANSO-FTS TIR V1.0 CO2 and CH4 Products

    Science.gov (United States)

    Saitoh, N.; Kimoto, S.; Sugimura, R.; Imasu, R.; Shiomi, K.; Kuze, A.; Kataoka, F.; Knuteson, R. O.; Machida, T.; Sawa, Y.; Matsuda, H.

    2015-12-01

    Greenhouse Gases Observing Satellite (GOSAT) was launched on 23 January 2009, and has continued to make global observations, including both nadir and off-nadir measurements, for more than six years since its launch. The thermal infrared (TIR) band of Thermal and Near-infrared Sensor for Carbon Observation Fourier Transform Spectrometer (TANSO-FTS) on board the GOSAT has observed CO2 and CH4 profiles. We have analyzed the four-year data from 2010 through 2013 of the latest released version of the TIR Level 2 (L2) CO2 and CH4 products (V1.0). Comparisons of the TIR upper atmospheric CO2 product with CO2 data from Comprehensive Observation Network for Trace Gases by Airliner (CONTRAIL) aircraft measurements show that the growth rate estimated from the TIR CO2 data is slightly lower than that from the CONTRAIL data. Overall, the TIR V1.0 CO2 product has better quality in the upper troposphere and lower stratosphere than the a priori judging from comparisons with the collocated aircraft data. In spring and summer, however, the quality of the TIR L2 CO2 products became slightly worse than in the other seasons, especially in the low and northern-mid latitudes. This is because the corresponding a priori had a larger bias and the TIR Level 1B (L1B) radiance spectra might have a larger bias in the spring-summer seasons. Here, we have tested several types of correction methods to modify the L1B spectral bias, and then compared CO2 and CH4 concentrations retrieved after applying spectral bias correction factors with coincident CONTRAIL and HIAPER Pole-to-Pole Observation (HIPPO) aircraft data. The comparison results suggest that the L1B spectral bias correction factor should be changed depending on wavelength. In addition, it should be expressed as a function of on-board internal calibration blackbody temperatures. This is because they are weak season-dependent parameters; they were clearly lower in spring and summer.

  6. The validation of the Yonsei CArbon Retrieval algorithm with improved aerosol information using GOSAT measurements

    Science.gov (United States)

    Jung, Yeonjin; Kim, Jhoon; Kim, Woogyung; Boesch, Hartmut; Goo, Tae-Young; Cho, Chunho

    2017-04-01

    Although several CO2 retrieval algorithms have been developed to improve our understanding about carbon cycle, limitations in spatial coverage and uncertainties due to aerosols and thin cirrus clouds are still remained as a problem for monitoring CO2 concentration globally. Based on an optimal estimation method, the Yonsei CArbon Retrieval (YCAR) algorithm was developed to retrieve the column-averaged dry-air mole fraction of carbon dioxide (XCO2) using the Greenhouse Gases Observing SATellite (GOSAT) measurements with optimized a priori CO2 profiles and aerosol models over East Asia. In previous studies, the aerosol optical properties (AOP) are the most important factors in CO2 retrievals since AOPs are assumed as fixed parameters during retrieval process, resulting in significant XCO2 retrieval error up to 2.5 ppm. In this study, to reduce these errors caused by inaccurate aerosol optical information, the YCAR algorithm improved with taking into account aerosol optical properties as well as aerosol vertical distribution simultaneously. The CO2 retrievals with two difference aerosol approaches have been analyzed using the GOSAT spectra and have been evaluated throughout the comparison with collocated ground-based observations at several Total Carbon Column Observing Network (TCCON) sites. The improved YCAR algorithm has biases of 0.59±0.48 ppm and 2.16±0.87 ppm at Saga and Tsukuba sites, respectively, with smaller biases and higher correlation coefficients compared to the GOSAT operational algorithm. In addition, the XCO2 retrievals will be validated at other TCCON sites and error analysis will be evaluated. These results reveal that considering better aerosol information can improve the accuracy of CO2 retrieval algorithm and provide more useful XCO2 information with reduced uncertainties. This study would be expected to provide useful information in estimating carbon sources and sinks.

  7. GOSAT/TANSO-FTS Measurement of Volcanic and Geothermal CO2 Emissions

    Science.gov (United States)

    Schwandner, Florian M.; Carn, Simon A.; Newhall, Christopher G.

    2010-05-01

    volcanic CO2 anomalies using GOSAT and correlation with Aura/OMI, AIRS, and ASTER determined SO2 fluxes and ground based monitoring of CO2 and other geophysical and geochemical parameters. This will provide the ground work for future higher spatial resolution satellite missions. This is a joint effort from two GOSAT-IBUKI data application projects: "Satellite-Borne Quantification of Carbon Dioxide Emissions from Volcanoes and Geothermal Areas" (PI Schwandner), and "Application of GOSAT/TANSO-FTS to the Measurement of Volcanic CO2 Emissions" (PI Carn).

  8. Monitoring carbon dioxide from space: Retrieval algorithm and flux inversion based on GOSAT data and using CarbonTracker-China

    Science.gov (United States)

    Yang, Dongxu; Zhang, Huifang; Liu, Yi; Chen, Baozhang; Cai, Zhaonan; Lü, Daren

    2017-08-01

    Monitoring atmospheric carbon dioxide (CO2) from space-borne state-of-the-art hyperspectral instruments can provide a high precision global dataset to improve carbon flux estimation and reduce the uncertainty of climate projection. Here, we introduce a carbon flux inversion system for estimating carbon flux with satellite measurements under the support of "The Strategic Priority Research Program of the Chinese Academy of Sciences—Climate Change: Carbon Budget and Relevant Issues". The carbon flux inversion system is composed of two separate parts: the Institute of Atmospheric Physics Carbon Dioxide Retrieval Algorithm for Satellite Remote Sensing (IAPCAS), and CarbonTracker-China (CT-China), developed at the Chinese Academy of Sciences. The Greenhouse gases Observing SATellite (GOSAT) measurements are used in the carbon flux inversion experiment. To improve the quality of the IAPCAS-GOSAT retrieval, we have developed a post-screening and bias correction method, resulting in 25%-30% of the data remaining after quality control. Based on these data, the seasonal variation of XCO2 (column-averaged CO2 dry-air mole fraction) is studied, and a strong relation with vegetation cover and population is identified. Then, the IAPCAS-GOSAT XCO2 product is used in carbon flux estimation by CT-China. The net ecosystem CO2 exchange is -0.34 Pg C yr-1 (±0.08 Pg C yr-1), with a large error reduction of 84%, which is a significant improvement on the error reduction when compared with in situ-only inversion.

  9. Elevated uptake of CO2 over Europe inferred from GOSAT XCO2 retrievals: a real phenomenon or an artefact of the analysis?

    Directory of Open Access Journals (Sweden)

    L. Feng

    2015-01-01

    Full Text Available Estimates of the natural CO2 flux over Europe inferred from in situ measurements of atmospheric CO2 mole fraction have been used previously to check top-down flux estimates inferred from space-borne dry-air CO2 column (XCO2 retrievals. Recent work has shown that CO2 fluxes inferred from XCO2 data from the Japanese Greenhouse gases Observing SATellite (GOSAT have a larger seasonal amplitude and a more negative annual net CO2 balance than those inferred from the in situ data. The causes of this enhanced European CO2 uptake have since become the focus of recent studies. We show this elevated uptake over Europe could largely be explained by mis-fitting data due to regional biases. We establish a reference in situ inversion that uses an Ensemble Kalman Filter (EnKF to assimilate surface flask data and the XCO2 data from the surface-based Total Carbon Column Observing Network (TCCON. The same EnKF system is also used to assimilate two, independent versions of GOSAT XCO2 data. We find that the GOSAT-inferred European terrestrial biosphere uptake peaks during the summer, similar to the reference inversion, but the net annual flux is 1.18 ± 0.1 GtC a−1 compared to a value of 0.56 ± 0.1 GtC a−1 for our control inversion that uses only in situ data. To reconcile these two estimates, we have performed a series of numerical experiments that assimilate observations with biases or assimilate synthetic observations for which part or all of the GOSAT XCO2 data are replaced with model data. We find that 50–80% of the elevated European uptake in 2010 inferred from GOSAT data is due to retrievals outside the immediate European region, while most of the remainder can be explained by a sub-ppm retrieval bias over Europe. We have used data assimilation techniques to estimate monthly GOSAT XCO2 biases from the joint assimilation of in situ observations and GOSAT XCO2 retrievals. We find a monthly varying bias of up to 0.5 ppm can explain an overestimate of the

  10. Characterization and correction of spectral distortions induced by microvibrations onboard the GOSAT Fourier transform spectrometer.

    Science.gov (United States)

    Suto, Hiroshi; Yoshida, Jun; Desbiens, Raphael; Kawashima, Takahiro; Kuze, Akihiko

    2013-07-10

    Microvibrations onboard greenhouse gases observing satellite (GOSAT) cause scan speed variations in the TANSO Fourier transform spectrometer. The associated periodic sampling errors generate ghost features in O2 A-band spectra, where surface pressure and aerosol properties are retrieved to determine the optical path through the atmosphere. A correction algorithm has been developed to re-compute the interferograms at equally spaced sampling intervals. The key is to determine iteratively the amplitude and phase of sinusoidal perturbations with predetermined frequencies to minimize the magnitude of the out-of-band ghosts artifacts after correction of the sampling grid. This correction algorithm drastically reduces errors in retrieved surface pressure and improves agreement with ground-based observations.

  11. Ten Years of Near-Surface-Sensitive Satellite Observations of Carbon Dioxide and Methane: Selected Results Related to Natural and Anthropogenic Sources and Sinks

    Science.gov (United States)

    Buchwitz, M. A.; Reuter, M.; Schneising, O.; Bovensmann, H.; Burrows, J. P.

    2014-12-01

    Prior to the recently successfully launched OCO-2 mission, global near-surface-sensitive satellite observations of carbon dioxide (CO2) have been made with SCIAMACHY/ENVISAT during 2002-2012 and are still being made since 2009 with TANSO-FTS/GOSAT, which also deliver atmospheric methane (CH4). The SCIAMACHY and GOSAT overlapping time series of atmospheric column-averaged mole fractions, i.e., XCO2 and XCH4, now cover more than 10 years. During the last years significant progress has been made in improving the quality of the XCO2 and XCH4 data products retrieved from SCIAMACHY and GOSAT and in extending the time series so that more and more applications can be addressed. In this presentation we present some recent results related to CO2 and CH4 sources and sinks. The SCIAMACHY products have been generated using retrieval algorithms developed at University of Bremen. For XCO2 we use an ensemble of data products generated using GOSAT retrieval algorithms developed in Japan (at NIES), in the US (at NASA/JPL and collaborating institutes) and at European institutions (University of Leicester, UK, and SRON, Netherlands, in collaboration with KIT, Germany). Focus will be on three applications: (i) An assessment of the strength of the European terrestrial carbon sink during 2003-2010 based on an ensemble of SCIAMACHY (2003-2010) and GOSAT (2010) XCO2 data products, (ii) an assessment of CO2 and NO2 anthropogenic emission and emission ratio trends using co-located SCIAMACHY XCO2 and NO2 observations over Europe, North America and East Asia, and (iii) an analysis of SCIAMACHY XCH4 retrievals during 2006-2011 over North America focusing on fugitive methane emissions from oil and gas production using tight geological formations ("fracking"). It will be shown that (i) the European terrestrial carbon sink appears to be stronger than expected, (ii) that recent Chinese CO2 and NO2 emissions are increasing but with a trend towards reduced NO2-to-CO2 emission ratios pointing to

  12. Comparison of XH2O Retrieved from GOSAT Short-Wavelength Infrared Spectra with Observations from the TCCON Network

    Directory of Open Access Journals (Sweden)

    Eric Dupuy

    2016-05-01

    Full Text Available Understanding the atmospheric distribution of water (H 2 O is crucial for global warming studies and climate change mitigation. In this context, reliable satellite data are extremely valuable for their global and continuous coverage, once their quality has been assessed. Short-wavelength infrared spectra are acquired by the Thermal And Near-infrared Sensor for carbon Observation-Fourier Transform Spectrometer (TANSO-FTS aboard the Greenhouse gases Observing Satellite (GOSAT. From these, column-averaged dry-air mole fractions of carbon dioxide, methane and water vapor (XH 2 O have been retrieved at the National Institute for Environmental Studies (NIES, Japan and are available as a Level 2 research product. We compare the NIES XH 2 O data, Version 02.21, with retrievals from the ground-based Total Carbon Column Observing Network (TCCON, Version GGG2014. The datasets are in good overall agreement, with GOSAT data showing a slight global low bias of −3.1% ± 24.0%, good consistency over different locations (station bias of −1.53% ± 10.35% and reasonable correlation with TCCON (R = 0.89. We identified two potential sources of discrepancy between the NIES and TCCON retrievals over land. While the TCCON XH 2 O amounts can reach 6000–7000 ppm when the atmospheric water content is high, the correlated NIES values do not exceed 5500 ppm. This could be due to a dry bias of TANSO-FTS in situations of high humidity and aerosol content. We also determined that the GOSAT-TCCON differences directly depend on the altitude difference between the TANSO-FTS footprint and the TCCON site. Further analysis will account for these biases, but the NIES V02.21 XH 2 O product, after public release, can already be useful for water cycle studies.

  13. The performance of Yonsei CArbon Retrieval (YCAR) algorithm with improved aerosol information using GOSAT measurements over East Asia

    Science.gov (United States)

    Jung, Y.; Kim, J.; Kim, W.; Boesch, H.; Yoshida, Y.; Cho, C.; Lee, H.; Goo, T. Y.

    2016-12-01

    The Greenhouse Gases Observing SATellite (GOSAT) is the first satellite dedicated to measure atmospheric CO2 concentrations from space that can able to improve our knowledge about carbon cycle. Several studies have performed to develop the CO2 retrieval algorithms using GOSAT measurements, but limitations in spatial coverage and uncertainties due to aerosols and thin cirrus clouds are still remained as a problem for monitoring CO2 concentration globally. In this study, we develop the Yonsei CArbon Retrieval (YCAR) algorithm based on optimal estimation method to retrieve the column-averaged dry-air mole fraction of carbon dioxide (XCO2) with optimized a priori CO2 profiles and aerosol models over East Asia. In previous studies, the aerosol optical properties (AOP) and the aerosol top height used to cause significant errors in retrieved XCO2 up to 2.5 ppm. Since this bias comes from a rough assumption of aerosol information in the forward model used in CO2 retrieval process, the YCAR algorithm improves the process to take into account AOPs as well as aerosol vertical distribution; total AOD and the fine mode fraction (FMF) are obtained from the ground-based measurements closely located, and other parameters are obtained from a priori information. Comparing to ground-based XCO2 measurements, the YCAR XCO2 product has a bias of 0.59±0.48 ppm and 2.16±0.87 ppm at Saga and Tsukuba sites, respectively, showing lower biases and higher correlations rather than the GOSAT standard products. These results reveal that considering better aerosol information can improve the accuracy of CO2 retrieval algorithm and provide more useful XCO2 information with reduced uncertainties.

  14. China's Recoverable Satellites

    Institute of Scientific and Technical Information of China (English)

    Tang Boehang

    2008-01-01

    @@ By the end of 2006, China had launched 24 recoverable satellites (FSW) in total. Among them, 23 were launched successfully, of which all but one were successfully recovered. Recoverable satellites launched by China are listed in Table 1.

  15. Four Dimensional CO2 Data Assimilation of GOSAT Observation Data Using a Local Ensemble Transform Kalman Filter (LETKF)

    Science.gov (United States)

    Maki, T.; Sekiyama, T. T.; Miyoshi, T.; Nakamura, T.; Iwasaki, T.

    2015-12-01

    Impacts of CO2 concentration data obtained from satellite (GOSAT TIR L2 Ver. 1.0) measurements on the estimation of global surface CO2 fluxes have been investigated using an ensemble-based four-dimensional data assimilation system (LETKF). An online atmospheric transport model (MJ98-CDTM) is employed in the data assimilation system to optimize surface CO2 fluxes from real observations at spatial and temporal resolutions of 6 days and about 2.8° (T42), respectively. The features of GOSAT TIR L2 Ver. 1.0 data are their larger data number than that of SWIR L2 (about 10 times) and smaller standard deviation than their former version (TIR L2 Ver. 0.01). These points are the advantageous features to CO2 data assimilation. One of the most important issues in satellite data assimilation is a bias correction technique. Therefore, we have tested 4 types of satellite bias correction experiments (w/o bias correction, monthly mean bias correction, all data bias correction and globally constant bias correction) using independent CO2 concentration analysis (JMA CO2 distribution) in our data assimilation system. Our results showed that estimated CO2 concentration and fluxes are significantly sensitive to bias correction scheme. The reason may come from that model biases are important issue on data assimilation. In conclusion, suitable satellite data bias correction allows obtaining realistic CO2 concentration field and modifying surface CO2 flux almost entire earth surface. In addition, this satellite bias correction scheme makes it possible to use multiple satellite observation data simultaneously in CO2 data assimilation.

  16. Water vapor isotopologues retrievals from high resolution GOSAT short-wave infrared spectra

    Directory of Open Access Journals (Sweden)

    C. Frankenberg

    2012-09-01

    Full Text Available Remote sensing of the isotopic composition of water vapor can provide valuable information on the hydrological cycle. Here, we demonstrate feasibility of retrievals of the relative abundance of HDO (the HDO/H2O ratio from the Japanese GOSAT satellite. For this purpose, we use high spectral resolution nadir radiances around 6400 cm−1 (1.56 μm to retrieve vertical column amounts of H2O and HDO. Retrievals of H2O correlate well with ECMWF (European Centre for Medium-Range Weather Forecasts integrated profiles (r2 = 0.96. Typical precision errors in the retrieved column averaged deuterium depletion (δD are 20–40‰. We validate δD against a TCCON (Total Carbon Column Observing Network ground-based station in Lamont, Oklahoma. Using retrievals in very dry areas over Antarctica, we detect a small systematic offset in retrieved H2O and HDO column amounts and take this into account for a bias-correction of δD. Monthly averages of δD in the June 2009 to September 2011 time-frame are well correlated with TCCON (r2 = 0.79 and exhibit a slope of 0.98 (1.23 if not bias corrected. We also compare seasonal averages on the global scale with results from the SCIAMACHY instrument in the 2003–2005 timeframe. Despite the lack of temporal overlap, seasonal averages in general agree well, with spatial correlations (r2 ranging from 0.62 in September through November to 0.83 in June through August. However, we observe higher variability in GOSAT δD, indicated by fitted slopes between 1.2 and 1.46. The discrepancies are likely related to differences in vertical sensitivities but warrant further validation of both GOSAT and SCIAMACHY and an extension of the validation dataset.

  17. Validation of GOSAT/TANSO-FTS TIR UTLS CO2 data (Version 1.0 using CONTRAIL measurements

    Directory of Open Access Journals (Sweden)

    N. Saitoh

    2015-12-01

    Full Text Available The thermal infrared (TIR band of the Thermal and Near Infrared Sensor for Carbon Observation (TANSO–Fourier Transform Spectrometer (FTS on board the Greenhouse Gases Observing Satellite (GOSAT has been observing carbon dioxide (CO2 concentrations in several atmospheric layers since its launch. This study compared TANSO-FTS TIR V1.0 CO2 data and CO2 data obtained in the Comprehensive Observation Network for TRace gases by AIrLiner (CONTRAIL project in the upper troposphere and lower stratosphere (UTLS, where the TIR band of TANSO-FTS is most sensitive to CO2 concentrations, to validate the quality of the TIR V1.0 UTLS CO2 data from 287 to 162 hPa. From a comparison made during flights between Tokyo and Sydney, the averages of the TIR upper atmospheric CO2 data agreed well with the averages of the data obtained by the CONTRAIL Continuous CO2 Measuring Experiment (CME within 0.1 % for all of the seasons in the Southern Hemisphere. The results of a comparison for all of the eight airline routes showed that the agreement between the TIR and CONTRAIL CO2 data was within 0.5 % on average in the Northern Hemisphere, which was better than the agreement between a priori and CONTRAIL CO2 data. The quality of TIR lower stratospheric CO2 data depends largely on the information content, and therefore has a seasonal dependence. In high latitudes, TIR V1.0 lower stratospheric CO2 data are only valid in the summer. The magnitude of bias in the TIR upper atmospheric CO2 data did not have a clear longitudinal dependence. The comparison results for flights in northern low and middle latitudes showed that the agreement between TIR and CONTRAIL CO2 data in the upper troposphere was worse in the spring and summer than in the fall and winter. This could be attributed to a larger negative bias in the upper atmospheric a priori CO2 data in the spring and summer and a seasonal dependence of spectral bias in TANSO-FTS TIR Level 1B (L1B radiance data. The negative bias

  18. A study of the validation of atmospheric CO2 from satellite hyper spectral remote sensing

    Directory of Open Access Journals (Sweden)

    Miao Zhang

    2014-09-01

    Full Text Available Three total column dry-air mole fractions of CO2 (XCO2 products from satellite retrievals, namely SCIAMACHY, NIES-GOSAT, and ACOS-GOSAT, in the Northern Hemisphere were validated by ground data from the Total Carbon Column Observing Network (TCCON. The results showed that the satellite data have the same seasonal fluctuations as in the TCCON data, with maximum in April or May and minimum in August or September. The three products all underestimate the XCO2. The ACOS-GOSAT and the NIES-GOSAT products are roughly equivalent, and their mean standard deviations are 2.26 × 10−6 and 2.27 × 10−6 respectively. The accuracy of the SCIMACHY product is slightly lower, with a mean standard deviation of 2.91 × 10−6.

  19. VENESAT-1 Successfully Launched

    Institute of Scientific and Technical Information of China (English)

    2008-01-01

    @@ Venezuelan first satellite VENESAT-1 (or Simon Bolivar) was sent to space from the Xichang Satellite Launch Center(XSLC) at 0:53 (Beijing time) on October 30 atop a LM-3B launch vehicle. About 12 minutes later, the satellite entered the preset GTO orbit at the altitude of 36,000km. After four maneuvers, the satellite was normally positioned at 78 degrees west longitude at 15:39 (Beijing time) on November 9,beaming the majority of Latin America and part of the Caribbean region.

  20. Carbon Monitoring System Flux Estimation and Attribution: Impact of ACOS-GOSAT X(CO2) Sampling on the Inference of Terrestrial Biospheric Sources and Sinks

    Science.gov (United States)

    Liu, Junjie; Bowman, Kevin W.; Lee, Memong; Henze, David K.; Bousserez, Nicolas; Brix, Holger; Collatz, G. James; Menemenlis, Dimitris; Ott, Lesley; Pawson, Steven; Jones, Dylan; Nassar, Ray

    2014-01-01

    Using an Observing System Simulation Experiment (OSSE), we investigate the impact of JAXA Greenhouse gases Observing SATellite 'IBUKI' (GOSAT) sampling on the estimation of terrestrial biospheric flux with the NASA Carbon Monitoring System Flux (CMS-Flux) estimation and attribution strategy. The simulated observations in the OSSE use the actual column carbon dioxide (X(CO2)) b2.9 retrieval sensitivity and quality control for the year 2010 processed through the Atmospheric CO2 Observations from Space algorithm. CMS-Flux is a variational inversion system that uses the GEOS-Chem forward and adjoint model forced by a suite of observationally constrained fluxes from ocean, land and anthropogenic models. We investigate the impact of GOSAT sampling on flux estimation in two aspects: 1) random error uncertainty reduction and 2) the global and regional bias in posterior flux resulted from the spatiotemporally biased GOSAT sampling. Based on Monte Carlo calculations, we find that global average flux uncertainty reduction ranges from 25% in September to 60% in July. When aggregated to the 11 land regions designated by the phase 3 of the Atmospheric Tracer Transport Model Intercomparison Project, the annual mean uncertainty reduction ranges from 10% over North American boreal to 38% over South American temperate, which is driven by observational coverage and the magnitude of prior flux uncertainty. The uncertainty reduction over the South American tropical region is 30%, even with sparse observation coverage. We show that this reduction results from the large prior flux uncertainty and the impact of non-local observations. Given the assumed prior error statistics, the degree of freedom for signal is approx.1132 for 1-yr of the 74 055 GOSAT X(CO2) observations, which indicates that GOSAT provides approx.1132 independent pieces of information about surface fluxes. We quantify the impact of GOSAT's spatiotemporally sampling on the posterior flux, and find that a 0.7 gigatons of

  1. Monitoring Ocean CO2 Fluxes from Space: GOSAT and OCO-2

    Science.gov (United States)

    Crisp, David

    2012-01-01

    The ocean is a major component of the global carbon cycle, emitting over 330 billion tons of carbon dioxide (CO2) into the atmosphere each year, or about 10 times that emitted fossil fuel combustion and all other human activities [1, 2]. The ocean reabsorbs a comparable amount of CO2 each year, along with 25% of the CO2 emitted by these human activities. The nature and geographic distribution of the processes controlling these ocean CO2 fluxes are still poorly constrained by observations. A better understanding of these processes is essential to predict how this important CO2 sink may evolve as the climate changes.While in situ measurements of ocean CO2 fluxes can be very precise, the sampling density is far too sparse to quantify ocean CO2 sources and sinks over much of the globe. One way to improve the spatial resolution, coverage, and sampling frequency is to make observations of the column averaged CO2 dry air mole fraction, XCO2, from space [4, 5, 6]. Such measurements could provide global coverage at high resolution (space based sensors designed specifically for this task. GOSAT was successfully launched on January 23, 2009, and has been returning measurements of XCO2 since April 2009. The OCO mission was lost in February 2009, when its launch vehicle malfunctioned and failed to reach orbit. In early 2010, NASA authorized a re-flight of OCO, called OCO-2, which is currently under development.

  2. China's Meteorological Satellite Application System

    Institute of Scientific and Technical Information of China (English)

    Zhang Jiashen

    2008-01-01

    @@ China's meteorological satellite program consists of five systems,namely the satellite system,the launch vehicle system,the launch center system,TT&C and the ground application system.The satellite system consists of FengYun (FY) polar orbiting series and FY geostationary series,which are launched by LM launch vehicles from Taiyan Satellite Launch Center (TSLC) and Xichang Satellite Launch Center (XSLC) respectively.

  3. Global Analysis of Carbon Sources and Sinks with a Comprehensive Model Optimized with GOSAT/Tanso Observations

    Science.gov (United States)

    Denning, A.; Lokupitiya, R. S.; Zupanski, D.; Kawa, S. R.; Baker, D. F.; Doney, S. C.; Gurney, K. R.

    2009-12-01

    We present a system to analyze GOSAT/Tanso data using a combination of existing models of CO2 exchanges due to hourly photosynthesis and respiration, daily air-sea gas exchange, biomass burning, Fossil Fuel Emissions, and atmospheric transport. This comprehensive system allows direct comparison to the observed record of both in-situ and remotely sensed atmospheric CO2 at hourly timescales. We have previously demonstrated that a lower-resolution version of the system has good skill at replicating diurnal, synoptic, and seasonal variations over vegetated land surfaces. The system is driven by meteorological output from the NASA Goddard EOS Data Assimilation System, version 5. Surface weather from the system drives calculations of terrestrial ecosystem metabolism (radiation, precipitation, humidity, temperature) and air-sea gas exchange (wind), with other input data coming from satellite data products (e.g., fPAR and LAI from MODIS, and ocean color from SeaWiFS and MODIS). The analysis system is evaluated using synthetic data on a 2 x 2.5 degree (lat x lon) global grid. Synthetic data are sampled in cloud-free columns along the GOSAT orbital ephemeris and used to estimate multiplicative biases to component fluxes by Ensemble Data Assimilation. The system is quite successful at retrieving mechanistic estimates of spatial patterns of surface carbon fluxes on monthly and annual timescales over land, but is less skillful over the oceans.

  4. Determining the Economic Plausibility of Dual Manifesting Reusable Launch Vehicles and Reusable Orbital Transfer Vehicles for the Replenishment of Military Satellites

    Science.gov (United States)

    2011-07-28

    C4)~ ;1 6c . Lt io )V - CM- C4V r- If C14 0)0 0D0 VcE ) ) O( -0) V-00 0Df-0C -U’ o0C00 C)0 GO M C) Vco’) m r- e C)0[- -Oc 𔃺 C N --- 0 60 6 NNNc6 r- ’j...Satellite Launch Policies: The Dynamic Case," submitted for publication in Management Science, November 1995. Griffin, M.D. and Claybaugh, W.R. "On the...34Policy Recommendations for a Shipment- Consolidation Program," Journal of Business Logistics, 15:87-111 (1994). Hill, P. and Peterson, C. Mechanics and

  5. Comparison of atmospheric CH4 concentration observed by GOSAT and in-situ measurements in Thailand and India

    Science.gov (United States)

    Hayashida, S.; Ono, A.; Ishikawa, S.; Terao, Y.; Takeuchi, W.

    2012-12-01

    The concentration of atmospheric methane (CH4) has more than doubled since pre-industrial levels and the observed long-term changes in the CH4 concentration have been attributed to anthropogenic activity. However, despite the importance of atmospheric CH4 in global warming, the strength of individual sources of CH4 remains highly uncertain [e.g.,Dlugokencky et al., 2011]. To characterize and quantify the emissions of CH4 especially in Monsoon Asia and Siberia, which are the most important regions as CH4 source, we started a new project, "Characterization and Quantification of global methane emissions by utilizing GOSAT and in-situ measurements " by support of the Environment Research and Technology Development Fund (ERTDF) from June 2012 under the umbrella of Ministry of Environment Japan. The projects includes (1) satellite data applications, (2) in-situ measurements in Siberia, over Western Pacific and in Monsoon Asia, (3) development of the inverse model to derive CH4 emissions by top-down approach, and (4) flux measurements in Siberia and Asia to improve the bottom-up inventories. As an initiatory approach in the project, we started air sampling in Thailand and India where there are only a few CH4 data of direct sampling with high precision. We took eight air samples at Kohn Kaen and Pimai in Thailand on June 9 and 10, 2012. The high CH4 concentration near rice paddy field contrasted to the lower CH4 concentration near Cassava field. We are planning to take more samples in India in mid-August. The satellite CH4 data including GOSAT and SCIAMACHY are also compared with the Land Surface Water Coverage (LSWC) and the Normalized Difference Vegetation Index (NDVI). The analysis revealed the seasonal variation in of xCH4 is closely related to the variation of the LSWC, coupled with NDVI. However, the satellite measurements are all column-averaged mixing ratio (xCH4), and therefore do not necessarily reflect high CH4 concentration near the surface over the emission

  6. LM-4B Launch Vehicle

    Institute of Scientific and Technical Information of China (English)

    RenShufang

    2004-01-01

    The history of LM-4B traces back to the end of the 1970s. The feasibility study of LM-4 began in 1982 and the engineering development was initiated in the following year.Initially, the LM-4 served as a back-up launch vehicle for LM-3 to launch China's communications satellites. After the successful launch of China's first communications satellites by LM-3 in 1984, the main mission of the LM-4 was shifted to launch sun-synchronous orbit meteorological satellites.

  7. China Plans To Carry Out 15 Launch Missions In 2008

    Institute of Scientific and Technical Information of China (English)

    2008-01-01

    @@ In 2007,China made 10 launch missions and achieved complete success,including the launch of Chang'e-1 satellite,in-orbit delivery of Nigcomsat-1 and 100th launch of Long March series launch vehicle.

  8. The pre-launch status of TanSat Mission: Instrument, Retrieval algorithm, Flux inversion and Validation

    Science.gov (United States)

    Liu, Yi; Yin, Zengshan; Yang, Zhongdong; Zheng, Yuquan; Yan, Changxiang; Tian, Xiangjun; Yang, Dongxu

    2016-04-01

    After 5 years development, The Chinese carbon dioxide observation satellite (TanSat), the first scientific experimental CO2 satellite of China, step into the pre-launch phase. The characters of pre-launch carbon dioxide spectrometer have been optimized during the laboratory test and calibration. Radiometric calibration shows a SNR of 440 (O2A 0.76um band), 300 (CO2 1.61um band) and 180 (CO2 2.06um band) on average in the typical radiance condition. Instrument line shape was calibrated automatically in using a well design testing system with laser control and record. After a series of test and calibration in laboratory, the instrumental performances meet the design requirements. TanSat will be launched on August 2016. The optimal estimation theory was involved in TanSat XCO2 retrieval algorithm in a full physics way with simulation of the radiance transfer in atmosphere. Gas absorption, aerosol and cirrus scattering and surface reflectance associate with wavelength dispersion have been considered in inversion for better correction the interference errors to XCO2. In order to simulate the radiance transfer precisely and efficiently, we develop a fast vector radiative transfer simulation method. Application of TanSat algorithm on GOSAT observation (ATANGO) is appropriate to evaluate the performance of algorithm. Validated with TCCON measurements, the ATANGO product achieves a 1.5 ppm precision. A Chinese carbon cycle data- assimilation system Tan-Tracker is developed based on the atmospheric chemical transport model GEOS-Chem. Tan-Tracker is a dual-pass data-assimilation system in which both CO2 concentrations and CO2 fluxes are simultaneously assimilated from atmospheric observations. A validation network has been established around China to support a series of CO2 satellite of China, which include 3 IFS-125HR and 4 Optical Spectrum Analyzer etc.

  9. Global high-resolution simulations of CO2 and CH4 using a NIES transport model to produce a priori concentrations for use in satellite data retrievals

    Directory of Open Access Journals (Sweden)

    S. Maksyutov

    2013-01-01

    Full Text Available The Greenhouse gases Observing SATellite (GOSAT measures column-averaged dry air mole fractions of carbon dioxide and methane (XCO2 and XCH4, respectively. Since the launch of GOSAT, model-simulated three-dimensional concentrations from a National Institute for Environmental Studies offline tracer Transport Model (NIES TM have been used as a priori concentration data for operational near real-time retrievals of XCO2 and XCH4 from GOSAT short-wavelength infrared spectra at NIES. Although the choice of a priori profile has only a minor effect on retrieved XCO2 or XCH4, a realistic simulation with minimal deviation from observed data is desirable. In this paper, we describe the newly developed version of NIES TM that has been adapted to provide global and near real-time concentrations of CO2 and CH4 using a high-resolution meteorological dataset, the Grid Point Value (GPV prepared by the Japan Meteorological Agency. The spatial resolution of the NIES TM is set to 0.5° × 0.5° in the horizontal in order to utilise GPV data, which have a resolution of 0.5° × 0.5°, 21 pressure levels and a time interval of 3 h. GPV data are provided to the GOSAT processing system with a delay of several hours, and the near real-time model simulation produces a priori concentrations driven by diurnally varying meteorology. A priori variance–covariance matrices of CO2 and CH4 are also derived from the simulation outputs and observation-based reference data for each month of the year at a resolution of 0.5° × 0.5° and 21 pressure levels. Model performance is assessed by comparing simulation results with the GLOBALVIEW dataset and other observational data. The overall root-mean-square differences between model predictions and GLOBALVIEW analysis are estimated to be 1.45 ppm and 12.52 ppb for CO2 and CH4, respectively, and the seasonal correlation coefficients are 0.87 for CO2 and 0.53 for CH4. The model showed good performance particularly at oceanic and free

  10. Detection of global tropospheric clouds and polar stratospheric clouds over Antarctica using thermal infrared spectral data observed by TANSO-FTS/GOSAT

    Science.gov (United States)

    Someya, Yu; Imasu, Ryoichi; Ota, Yoshifumi; Saitoh, Naoko

    2014-05-01

    Global tropospheric cloud distribution was derived from thermal infrared band data observed by Thermal And Near infrared Sensor for carbon Observation - Fourier Transform Spectrometer (TANSO-FTS) onboard Greenhouse gases Observation SATellite (GOSAT). It is expected that this band has ability to detect optically thin clouds compared with Cloud and Aerosol Imager (CAI) which is the other sensor on GOSAT. In addition, polar stratospheric clouds (PSCs) which can be harder to detect than the tropospheric clouds because of high reflectivity or low temperature of the surface and their low optical thickness were also detected. We have modified CO2 slicing method which was developed as one of the cirrus cloud detection techniques using thermal infrared band data to detect thin clouds more stably. The pseudo spectral channels were defined as sets of several actual spectral channels between 700cm-1 and 750cm-1 which have weighting function peak height in a same height range for each 0.5km. These pseudo channels were optimized with simulation studies using a multi-scattering radiative transfer code, Polarized radiance System for Transfer of Atmospheric Radiation (Pstar) 3 for several temperature profile patterns prepared based on latitudes and temperature at 500hPa. GOSAT data was analyzed with the combination of these pseudo channels determined for each of observation points from these simulations and the results were compared with the observational results from Cloud-Aerosol Lidar with Orthogonal Polarization (CALIOP) / Cloud-Aerosol Lidar and Infrared Pathfinder Satellite Observation (CALIPSO). The comparisons about global cloud are based on the coincident observations in 2010. Monthly occurrences of Antarctic PSCs were compared for each grid area from June to September in 2010. As a result, the correlation coefficients in each month are 0.76, 0.71, 0.75, and 0.61 relatively. Though that is low value in September, it can be explained by decrease of occurrences.

  11. A computer model for evaluation of launch vehicle and target tracking error assignments for direct ascent, deep space ASAT (Anti-satellite) systems

    Science.gov (United States)

    Barclay, R. C.

    1983-12-01

    An unclassified computer model was developed for first order evaluation of deep space Anti-satellite (ASAT) targeting error assignments. Two independent error sources are modeled. With deep space tracking accuracies on the order of kilometers, there is uncertainty in the exact target position. Errors introduced by the launch vehicle guidance system result in uncertainty in the exact position of the ASAT itself. Once the target is acquired by the ASAT sensor subsystem, the maneuver subsystem must then have the capability to make the necessary trajectory corrections to precent a miss. The model assumes a direct ascent vehicle for which the user selects a trajectory by choosing the burnout and intercept position vectors, and a time of flight between them. Monte Carlo simulation is used to generate errors in burnout position and velocity, and intercept position from trivariate normal distributions scaled to user input standard deviations. This is repeated for 500 iterations, from which a mean miss distance and delta V required for trajectory correction can be determined, and used for further analysis.

  12. Flight Record of the Long March Series of Launch Vehicles

    Institute of Scientific and Technical Information of China (English)

    He Ying

    2010-01-01

    @@ (Continued) THE 56TH LAUNCH The FY-1C meteorological satellite and the Shijian 5 (SJ-5) satellite were put into their predetermined orbits by a LM-4B launch vehicle on May 10,1999. Launch Site: Taiyuan Satellite Launch Center Launch Result: Success At 09:33 on May 10, a LM-4B lifted off with two satellites.749 seconds after the lift-off, the FY-1C satellite separated with the rocket, and the SJ-5 satellite separated with LM-4B 814 seconds after it was fired.The two satellites entered sun-synchronous orbit which is 870km above the Earth.

  13. Correction of Spectral Distortion on Oxygen a-Band Due to Non-Linear Phase Delay Onboard Tanso-FTS/Gosat

    Science.gov (United States)

    Suto, H.; Butz, A.; Kuze, A.

    2014-12-01

    To observe the global column concentration of carbon dioxide (CO2) and methane (CH4) from space, the Greenhouse gases Observing SATellite (GOSAT) was launched on January 23, 2009, and has started the operational observation. Thermal and Near Infrared Sensor for Carbon Observation - Fourier Transform Spectrometer (TANSO-FTS) has been continuously measuring CO2 and CH4 distributions globally, and the retrieved column CO2 and CH4 data have been distributed to the public. To make a successful retrieval of XCO2 and XCH4, the spectral quality of Oxygen A-band is the most importance. Over five years in-orbit operation of TANSO-FTS, the spectral distortion related with input radiance on Oxygen A-band have been observed and reduced the retrieval accuracy and precision of XCO2 and XCH4. It suggests that the Oxygen A-band signal chain has non-linear response against input radiance. To characterize the non-linear response of signal chain against input signal levels, the test procedure is newly developed coupled with the modulated laser light, simultaneous signal acquisition system and on-ground TANSO-FTS, which called engineering model. The results present clearly that the analogue signal chain of Oxygen A-band excites the non-linear response both of amplitude and phase delay against input signal levels. Also, the non-linear interferogram drives both of the artificial spectra on the out-band region and the spectral distortion linked with absorption spectral lines. To improve the spectral quality of Oxygen A-band, these artificial and distorted spectra have to correct with properly. The newly correction algorithm for level-1 processing was developed and the corrected spectra were retrieved and validated by applying RemoTeC algorithm. Comparing with the previous version of level-1 products, the agreement between observation and theoretical calculation is well improved and the biases of biases of XCO2 and XCH4 against ground validation site are reduced.

  14. A development of cloud top height retrieval using thermal infrared spectra observed with GOSAT and comparison with CALIPSO data

    Science.gov (United States)

    Someya, Yu; Imasu, Ryoichi; Saitoh, Naoko; Ota, Yoshifumi; Shiomi, Kei

    2016-05-01

    An algorithm based on CO2 slicing, which has been used for cirrus cloud detection using thermal infrared data, was developed for high-resolution radiance spectra from satellites. The channels were reconstructed based on sensitivity height information of the original spectral channels to reduce the effects of measurement errors. Selection of the reconstructed channel pairs was optimized for several atmospheric profile patterns using simultaneous studies assuming a cloudy sky. That algorithm was applied to data by the Greenhouse gases Observing SATellite (GOSAT). Results were compared with those obtained from the space-borne lidar instrument on-board Cloud-Aerosol Lidar and Infrared Pathfinder Satellite Observations (CALIPSO). Monthly mean cloud amounts from the slicing generally agreed with those from CALIPSO observations despite some differences caused by surface temperature biases, optically very thin cirrus, multilayer structures of clouds, extremely low cloud tops, and specific atmospheric conditions. Comparison of coincident data showed good agreement, except for some cases, and revealed that the improved slicing method is more accurate than the traditional slicing method. Results also imply that improved slicing can detect low-level clouds with cloud top heights as low as approximately 1.5 km.

  15. Flight Record Of Long March Series Of Launch Vehicles

    Institute of Scientific and Technical Information of China (English)

    He Ying

    2008-01-01

    @@ (Continued) The 13th Launch On February 1, 1986, a LM-3 launch vehicle sent DFH-2, the 3rd geosynehronous experimental communications satellite of China, into space. The satellite entered the preset orbit.

  16. LM-3B Launch Vehicle

    Institute of Scientific and Technical Information of China (English)

    RenShufang

    2005-01-01

    LM-3B launch vehicle is a heavy three-stage liquid propellant strap-on launch vehicle, which was developed based on the mature technologies of the LM-3A and LM-2E. It not only has the highest payload capacity to send China's satellites to GTO, but is also one of the most advanced launch vehicles in the world with high reliability, reasonable price and perfect technological design.

  17. Viewing the effects of anthropogenic emission control from the change of CO2 concentration observed by GOSAT in China during the 2014 APEC summit

    Science.gov (United States)

    Lei, L.; Zhong, H.; Liu, L.; Yang, S., Sr.

    2016-12-01

    The growth of the global anthropogenic carbon emission stalled in 2014, according to data from International Energy Agency (IEA). This paper presents a practical application of satellite observation for detecting the regional enhancement of CO2 induced by underlying anthropogenic CO2 emissions especially during the 2014 Asia-Pacific Economic Cooperation (APEC) summit. We collected the column averaged dry air mole fraction (XCO2) data from Greenhouse Observation SATellite (GOSAT) from Jan. 2010 to Dec. 2015, which are provided by Japan GOSAT project team. The spatial change of the 5-year averaged XCO2 derived by gap filling [Zeng et al., TGRS, 2014], as shown in Fig.1, demonstrated that high XCO2prefer to correspond to the most intensive power plants. We calculated the regional contrasts between source and almost without emission (Fig.2), which are defined based on emission and potential temperature. The source, which is defined around Beijing, has many big power plants (Fig.1). The regional contrast showed 1-3 ppm with large seasonal variations while it is the lowest in summer due to influence of biospheric fluxes and especially show abnormal fluctuation in autumn 2014 (Fig.3). XCO2 fell from 398.9 ppm in 15-30 Oct. before APEC to 395.7 ppm during 1-11 Nov. 2014 APEC in source area around Beijing, and the contrast decreased from 4.5 ppm to 1.0 ppm (Table 1). This abnormal decline of XCO2 likely indicate the effects of controlling action for strong local source emissions such as closed many small inefficient coal-fired power plants from the beginning of 2014, banned on burning straw, especially in addition to temporally shut down the big coal-power plants and limiting the number of vehicles running during the APEC summit within the large zone covering the six provinces around Beijing. The large reduction was reported in aerosol of 50% above during the APEC summit (Sun et al., Sci. report, 2016). Our results agree to the potential of satellite observations to

  18. An Inversion Analysis of Recent Variability in Natural CO2 Fluxes Using GOSAT and In Situ Observations

    Science.gov (United States)

    Wang, James S.; Kawa, S. Randolph; Collatz, G. James; Baker, David F.; Ott, Lesley

    2015-01-01

    About one-half of the global CO2 emissions from fossil fuel combustion and deforestation accumulates in the atmosphere, where it contributes to global warming. The rest is taken up by vegetation and the ocean. The precise contribution of the two sinks, and their location and year-to-year variability are, however, not well understood. We use two different approaches, batch Bayesian synthesis inversion and variational data assimilation, to deduce the global spatiotemporal distributions of CO2 fluxes during 2009-2010. One of our objectives is to assess different sources of uncertainties in inferred fluxes, including uncertainties in prior flux estimates and observations, and differences in inversion techniques. For prior constraints, we utilize fluxes and uncertainties from the CASA-GFED model of the terrestrial biosphere and biomass burning driven by satellite observations and interannually varying meteorology. We also use measurement-based ocean flux estimates and two sets of fixed fossil CO2 emissions. Here, our inversions incorporate column CO2 measurements from the GOSAT satellite (ACOS retrieval, filtered and bias-corrected) and in situ observations (individual flask and afternoon-average continuous observations) to estimate fluxes in 108 regions over 8-day intervals for the batch inversion and at 3 x 3.75 weekly for the variational system. Relationships between fluxes and atmospheric concentrations are derived consistently for the two inversion systems using the PCTM atmospheric transport model driven by meteorology from the MERRA reanalysis. We compare the posterior fluxes and uncertainties derived using different data sets and the two inversion approaches, and evaluate the posterior atmospheric concentrations against independent data including aircraft measurements. The optimized fluxes generally resemble those from other studies. For example, the results indicate that the terrestrial biosphere is a net CO2 sink, and a GOSAT-only inversion suggests a shift in

  19. 微纳卫星专用发射运载器发展趋势研究%Research on the Trends of Developing Dedicated Launch Vehicle for Micro/Nano Satellite

    Institute of Scientific and Technical Information of China (English)

    战培国

    2013-01-01

    微纳卫星低成本、快速专用发射运载器是近些年来航天运输领域人们研究关注的问题之一。本文在简要介绍国外微纳卫星发展现状及趋势的基础上,分析微纳卫星发射运载器市场及供求关系,研究专用发射运载器研发及概念技术发展趋势,探讨专用发射运载器在民用和军事领域的发展前景。%The low-cost/responsive dedicated launch vehicle for micro/nano satellite is one of the problem in the area of aerospace transportation. This paper introduces development states and trends of micro/nano satelite , analyzes the supply and demand of the dedicated launch vehicle market, researches the development, concept and technology of the dedicated launch vehicle, discusses the trends of the dedicated launch vehicle in civil and military area.

  20. FY-3A Launched Atop A LM-4C Launch Vehicle

    Institute of Scientific and Technical Information of China (English)

    Rain.L

    2008-01-01

    @@ FY-3A,the first satellite of China's new generation of polar-orbiting meteorological satellites,was launched into space atop a modified LM-4C launch vehicle.The satellite separated from the rocket 19 minutes after the takeoff.Flying at an altitude of 807km with an inclination of 98.8 degrees,the satellite circles in polar orbit 14 times everyday,covering the whole globe twice a day.

  1. Development of a new platform for airborne measurements of atmospheric CO2 and CH4 and comparison with GOSAT measurements at Railroad Valley playa, Nevada

    Science.gov (United States)

    Tadic, J.; Loewenstein, M.; Iraci, L. T.; Gore, W.; Schiro, K. A.; Olson, R. A.; Sheffner, E. J.; Yates, E. L.

    2011-12-01

    Measurements of carbon dioxide (CO2) play an important role in understanding the global carbon cycle and its contribution to global warming. In recent years methane (CH4) has received increasing attention as the second most important anthropogenic greenhouse gas because of the high uncertainty of its sources and sinks. Aircraft measurements of greenhouse gases are essential for observations in the free troposphere and lower stratosphere to better understand changes at regional and continental scales. Recently new types of high-accuracy analyzers based on cavity-ring down spectroscopy have become available for use on aircraft. One of them, Picarro 2301-m, was remodeled and adapted for use outside the cabin of an Alpha Jet. In this unique attempt, the instrument was redesigned from a single unit to multiple units that fit inside the Alpha jet wing pod, with special emphasis on internal thermal management. After remodeling, the platform was tested in a laboratory, in a chamber with variable pressure and temperature, and in the field. This newly developed platform exhibits several important characteristics: the modular structure of the platform allows usage of other instruments simultaneously, the platform is capable of measuring both vertical and horizontal profiles of CO2 and CH4, and it is very insensitive to flight maneuvers. The new platform was used on 22-26th of June, 2011, to create spatial and temporal profiles of CO2 and CH4 over a playa in Railroad Valley, Nevada, USA. The playa is a flat, dry lakebed with virtually no vegetation, approximately 15 km x 15 km in size, 1434 m in elevation and 110 km southwest of the nearest city (Ely, Nevada). The time and location of flights were selected to coincide with the overpass of Greenhouse Gases Observing Satellite (GOSAT). Airborne (Alpha Jet) in-situ measurements of CO2 and CH4 were collected to support the vicarious calibration experiment to validate column-averaged dry air mole fractions of CO2 and CH4 (XCO2 and

  2. CubeSat Launch Initiative

    Science.gov (United States)

    Higginbotham, Scott

    2016-01-01

    The National Aeronautics and Space Administration (NASA) recognizes the tremendous potential that CubeSats (very small satellites) have to inexpensively demonstrate advanced technologies, collect scientific data, and enhance student engagement in Science, Technology, Engineering, and Mathematics (STEM). The CubeSat Launch Initiative (CSLI) was created to provide launch opportunities for CubeSats developed by academic institutions, non-profit entities, and NASA centers. This presentation will provide an overview of the CSLI, its benefits, and its results.

  3. China Returning to International Commercial Launch Service Market

    Institute of Scientific and Technical Information of China (English)

    SunQing

    2005-01-01

    China launched its first commercial mission after 6 years since July 1999. APStar 6, the communications satellite manufactured by Alcatel Space, lifted off from Xichang Satellite Launch Center and was put into preset orbit by the LM-3B launch vehicle on the evening of April 12, 2005.

  4. The potential of clear-sky carbon dioxide satellite retrievals

    Directory of Open Access Journals (Sweden)

    R. R. Nelson

    2015-12-01

    Full Text Available Since the launch of the Greenhouse Gases Observing Satellite (GOSAT in 2009, retrieval algorithms designed to infer the column-averaged dry-air mole fraction of carbon dioxide (XCO2 from hyperspectral near-infrared observations of reflected sunlight have been greatly improved. They now generally include the scattering effects of clouds and aerosols, as early work found that absorption-only retrievals, which neglected these effects, often incurred unacceptably large errors, even for scenes with optically thin cloud or aerosol layers. However, these "full-physics" retrievals tend to be computationally expensive and may incur biases from trying to deduce the properties of clouds and aerosols when there are none present. Additionally, algorithms are now available that can quickly and effectively identify and remove most scenes in which cloud or aerosol scattering plays a significant role. In this work, we test the hypothesis that non-scattering, or "clear-sky", retrievals may perform as well as full-physics retrievals for sufficiently clear scenes. Clear-sky retrievals could potentially avoid errors and biases brought about by trying to infer properties of clouds and aerosols when none are present. Clear-sky retrievals are also desirable because they are orders of magnitude faster than full-physics retrievals. Here we use a simplified version of the Atmospheric Carbon Observations from Space (ACOS XCO2 retrieval algorithm that does not include the scattering and absorption effects of clouds or aerosols. It was found that for simulated Orbiting Carbon Observatory-2 (OCO-2 measurements, the clear-sky retrieval had errors comparable to those of the full-physics retrieval. For real GOSAT data, the clear-sky retrieval had nearly indistinguishable error characteristics over land, but roughly 30–60 % larger errors over ocean, depending on filtration level, compared to the full-physics retrieval. In general, the clear-sky retrieval had XCO2 root

  5. Scientific Satellites

    Science.gov (United States)

    1967-01-01

    followed Hale’s into orbit. In 1879, Jules Verne wrote about launching small satellites with a gun possessing a muzzle velocity of 10 000 m/sec (ref. 3...was activated in 1950.11 It was located only a few tens of miles from the spot where Jules Verne had his Baltimore Gun Club fire a manned projectile to...principle, satellites can be launched by a single impulse applied at the Earth’s surface-say, with a large cannon, & la Jules Verne (sec. 8-3). In

  6. Retrieval of sea surface temperature and trace gas column averaged from GOSAT, IASI-A, and IASI-B over the Arctic Ocean in summer 2010 and 2013

    Science.gov (United States)

    Payan, Sébastien; Camy-Peyret, Claude; Bureau, Jérôme

    2016-04-01

    The Arctic Ocean is a very important region of the globe in which the effect of climate change can be detected over short time periods. We have used the possibility provided by the three infrared sounders TANSO-FTS on the GOSAT platform, IASI-A, and IASI-B on the MetOp platforms to retrieve the sea surface temperature (Tsurf) and the column averaged mixing ratio of several trace gases (CO2, CH4, N2O, O3) for pairs of nearly coinciding footprints (IFOVs) at small time separations (typically for IASI 46 min and 54 min depending on which satellite has first observed the corresponding scene). A strict filtering based on the AVHRR cloud fraction and the radiance analysis within the GOSAT and IASI footprints lead to a large number of quasi-coinciding IFOVs for which a 1D-var inversion (Tsurf and XCO2 as the main parameters in the state vector, plus scaling factors for the profiles of H2O and O3) has been performed. As an example, we used during retrieval the atmospheric window between 940 and 980 cm-1 (CO2 laser band) for which the sensitivity to the surface is maximum. The statistics of the comparison between IASI-A and IASI-B retrievals is presented and compared to the corresponding Eumetsat L2 products. The months of July and August for the years 2010 and 2013 have been considered since in these Arctic summer conditions the ice pack coverage is reduced. The differences between these two consecutive years is discussed and a comparison with 2010 (for which only IASI-A was in orbit) is confirming that IASI can indeed be used for climate change studies.

  7. A Cluster of CO2 Change Characteristics with GOSAT Observations for Viewing the Spatial Pattern of CO2 Emission and Absorption

    Directory of Open Access Journals (Sweden)

    Da Liu

    2015-11-01

    Full Text Available Satellite observations can be used to detect the changes of CO2 concentration at global and regional scales. With the column-averaged CO2 dry-air mole fraction (Xco2 data derived from satellite observations, the issue is how to extract and assess these changes, which are related to anthropogenic emissions and biosphere absorptions. We propose a k-means cluster analysis to extract the temporally changing features of Xco2 in the Central-Eastern Asia using the data from 2009 to 2013 obtained by Greenhouse Gases Observing Satellite (GOSAT, and assess the effects of anthropogenic emissions and biosphere absorptions on CO2 changes combining with the data of emission and vegetation net primary production (NPP. As a result, 14 clusters, which are 14 types of Xco2 seasonal changing patterns, are obtained in the study area by using the optimal clustering parameters. These clusters are generally in agreement with the spatial pattern of underlying anthropogenic emissions and vegetation absorptions. According to correlation analysis with emission and NPP, these 14 clusters are divided into three groups: strong emission, strong absorption, and a tendency of balancing between emission and absorption. The proposed clustering approach in this study provides us with a potential way to better understand how the seasonal changes of CO2 concentration depend on underlying anthropogenic emissions and vegetation absorptions.

  8. An advanced retrieval algorithm for greenhouse gases using polarization information measured by GOSAT TANSO-FTS SWIR I: Simulation study

    Science.gov (United States)

    Kikuchi, N.; Yoshida, Y.; Uchino, O.; Morino, I.; Yokota, T.

    2016-11-01

    We present an algorithm for retrieving column-averaged dry air mole fraction of carbon dioxide (XCO2) and methane (XCH4) from reflected spectra in the shortwave infrared (SWIR) measured by the TANSO-FTS (Thermal And Near infrared Sensor for carbon Observation Fourier Transform Spectrometer) sensor on board the Greenhouse gases Observing SATellite (GOSAT). The algorithm uses the two linear polarizations observed by TANSO-FTS to improve corrections to the interference effects of atmospheric aerosols, which degrade the accuracy in the retrieved greenhouse gas concentrations. To account for polarization by the land surface reflection in the forward model, we introduced a bidirectional reflection matrix model that has two parameters to be retrieved simultaneously with other state parameters. The accuracy in XCO2 and XCH4 values retrieved with the algorithm was evaluated by using simulated retrievals over both land and ocean, focusing on the capability of the algorithm to correct imperfect prior knowledge of aerosols. To do this, we first generated simulated TANSO-FTS spectra using a global distribution of aerosols computed by the aerosol transport model SPRINTARS. Then the simulated spectra were submitted to the algorithms as measurements both with and without polarization information, adopting a priori profiles of aerosols that differ from the true profiles. We found that the accuracy of XCO2 and XCH4, as well as profiles of aerosols, retrieved with polarization information was considerably improved over values retrieved without polarization information, for simulated observations over land with aerosol optical thickness greater than 0.1 at 1.6 μm.

  9. ZY-1 02C Flew into Space- A Perfect Ending for the 2011 Space Launches

    Institute of Scientific and Technical Information of China (English)

    2011-01-01

    at 11:26 on December 22,a LM-4B launch vehicle lifted the ZY-1 02C satellite into space from the Taiyuan Satellite Launch Center,marking the complete success of the final launch mission of this year.13 minutes later,the satellite entered into sun-synchronous circular orbit after separating with the rocket.

  10. Small Space Launch: Origins & Challenges

    Science.gov (United States)

    Freeman, T.; Delarosa, J.

    2010-09-01

    The United States Space Situational Awareness capability continues to be a key element in obtaining and maintaining the high ground in space. Space Situational Awareness satellites are critical enablers for integrated air, ground and sea operations, and play an essential role in fighting and winning conflicts. The United States leads the world space community in spacecraft payload systems from the component level into spacecraft, and in the development of constellations of spacecraft. In the area of launch systems that support Space Situational Awareness, despite the recent development of small launch vehicles, the United States launch capability is dominated by an old, unresponsive and relatively expensive set of launchers in the Expandable, Expendable Launch Vehicles (EELV) platforms; Delta IV and Atlas V. The United States directed Air Force Space Command to develop the capability for operationally responsive access to space and use of space to support national security, including the ability to provide critical space capabilities in the event of a failure of launch or on-orbit capabilities. On 1 Aug 06, Air Force Space Command activated the Space Development & Test Wing (SDTW) to perform development, test and evaluation of Air Force space systems and to execute advanced space deployment and demonstration projects to exploit new concepts and technologies, and rapidly migrate capabilities to the warfighter. The SDTW charged the Launch Test Squadron (LTS) with the mission to develop the capability of small space launch, supporting government research and development space launches and missile defense target missions, with operationally responsive spacelift for Low-Earth-Orbit Space Situational Awareness assets as a future mission. This new mission created new challenges for LTS. The LTS mission tenets of developing space launches and missile defense target vehicles were an evolution from the squadrons previous mission of providing sounding rockets under the Rocket

  11. Capture Scheme of the Antenna in Ka-band for Launch Vehicle Based on Tracking and Data Relay Satellite%运载火箭Ka频段天基测控的天线捕获方法

    Institute of Scientific and Technical Information of China (English)

    宫长辉; 曾贵明; 张恒

    2011-01-01

    In order to transmit the space-based signal, the capture and track between the tracking and data relay satellite(TDRS) antenna and the user's aerocraft antenna should be completed firstly. In this paper, the uncertain area of the antenna scan is analyzed, adopting antenna-scan capture scheme for capturing the antenna on TORS by the phased-array antenna on launch vehicle. The values of the antenna array and EIRP are conformed and the capture time is given by computer simulation.%为实现天基信息的传输,首先要完成中继卫星天线与用户飞行器天线之间的捕获与跟踪.针对箭载相控阵天线对中继卫星的捕获,采用Ka频段相控阵天线扫描捕获策略,分析了天线扫描的不确定区域,确定了天线阵元数及EIRP值,给出了捕获时间的仿真结果,为工程应用提供参考.

  12. Flight Record Of The Long March Series Of Launch Vehicles

    Institute of Scientific and Technical Information of China (English)

    He Ying

    2009-01-01

    @@ (Continued) The 27th launch On August 9, 1992, a LM-2D launch vehicle sent the 13th recoverable satellite into space. The satellite operated in orbit for 16 days, fulfilled missions of scientific exploration and technical experiment and returned on August 25.

  13. CGWIC S gned The Contract for Launching APStar 6B

    Institute of Scientific and Technical Information of China (English)

    SunQing

    2005-01-01

    Following the successful launch of APStar 6 on April 12, 2005,China Great Wall Industry Corporation (CGWIC), as the general contractor, will provide APStar 6B satellite and launch service with the LM-3B rocket for APT Satellite Holdings Ltd., Hong Kong (APT)

  14. Flight Record Of Long March Series Of Launch Vehicles

    Institute of Scientific and Technical Information of China (English)

    He Ying

    2008-01-01

    @@ (Continued) The 7th Launch On September 9,1982,a LM-2C launch vehicle sent the 4th recoverable satellite,FSW-4 into space.The satellite returned to Earth on September 14 after it fulfilled its mission for scientific research and tests during 5-day operation in space.

  15. Handbook of satellite applications

    CERN Document Server

    Madry, Scott; Camacho-Lara, Sergio

    2017-01-01

    The first edition of this ground breaking reference work was the most comprehensive reference source available about the key aspects of the satellite applications field. This updated second edition covers the technology, the markets, applications and regulations related to satellite telecommunications, broadcasting and networking—including civilian and military systems; precise satellite navigation and timing networks (i.e. GPS and others); remote sensing and meteorological satellite systems. Created under the auspices of the International Space University based in France, this brand new edition is now expanded to cover new innovative small satellite constellations, new commercial launching systems, innovation in military application satellites and their acquisition, updated appendices, a useful glossary and more.

  16. Fight Record Of Long March Series Of Launch Vehicles

    Institute of Scientific and Technical Information of China (English)

    He Ying

    2008-01-01

    @@ On June 1,2007,China launched SinoSat-3,a communications satellite,onboard a Long March(LM)-3A launch vehicle,marking the 100th flight of the Long March series of launch vehicles and the 58th consecutive success since October 1996 (at the end of 2007,the number of consecutive successes was further increased to 62).

  17. LM-3B/E will launch Apstar 7

    Institute of Scientific and Technical Information of China (English)

    Zong He

    2009-01-01

    @@ China Great Wall Industry Corporation (CGWlC), a subsidiary of China Aerospace Science and Technology Corporation (CASC), signed a launch services contract with Hong Kong APT Satellite Co., Ltd in Beijing on November 8. According to the contract, a Long March 3B enhanced launch vehicle (LM-3B/E) will launch a French Thales Alenia Space made APstar 7 communications satellite into space in the first half year of 2012.

  18. Satellite-derived methane emissions from inundation in Bangladesh

    Science.gov (United States)

    Peters, C. N.; Bennartz, R.; Hornberger, G. M.

    2017-05-01

    The uncertainty in methane (CH4) source strength of rice fields and wetlands is particularly high in South Asia CH4 budgets. We used satellite observations of CH4 column mixing ratios from Atmospheric Infrared Sounder (AIRS), Scanning Imaging Absorption Spectrometer for Atmospheric Chartography (SCIAMACHY), and Greenhouse Gases Observing Satellite (GOSAT) to estimate the contribution of Bangladesh emissions to atmospheric CH4 concentrations. Using satellite-derived inundation area as a proxy for source area, we developed a simple inverse advection model that estimates average annual CH4 surface fluxes to be 4, 9, and 19 mg CH4 m-2 h-1 in AIRS, SCIAMACHY, and GOSAT, respectively. Despite this variability, our flux estimates varied over a significantly narrower range than reported values for CH4 surface fluxes from a survey of 32 studies reporting ground-based observations between 0 and 260 mg CH4 m-2 h-1. Upscaling our satellite-derived surface flux estimates, we estimated total annual CH4 emissions for Bangladesh to be 1.3 ± 3.2, 1.8 ± 2.0, 3.1 ± 1.6 Tg yr-1, depending on the satellite. Our estimates of total emissions are in line with the median of total emission values for Bangladesh reported in earlier studies.

  19. Comparative Study on Cloud Parameter Estimation Among GOSAT/CAI, MODIS, CALIPSO/CALIOP and Landsat-8/OLI with Laser Radar: Lidar as Truth Data

    Directory of Open Access Journals (Sweden)

    Kohei Arai

    2016-10-01

    Full Text Available A comparative study on cloud parameter estimation among GOSAT/CAI, MODIS, CALIPSO/CALIOP and Landsat-8/OLI is carried out using Laser Radar: Lidar as a truth data. Optical depth, size distribution, as well as cirrus type of clouds are cloud parameters. In particular, cirrus cloud detection is tough issue. 1.38 µm channel is required for its detection. Although MODIS and Landsat-8/OLI have such channel, the other mission instruments, CAI and CALIPSO/CALIOP do not have such channel. As a truth data of cloud parameter, ground based Lidar is used in this comparative study. From the Lidar, backscattered echo signal and depolarization coefficient are obtained as a function of altitude. Therefore, cloud type, vertical profile can be derived from the Lidar data. CALIPSO/CALIOP is satellite based Lidar which allows observation of clouds from space. Although the directions of laser light emissions between CALIPSO/CALIOP and the ground based Lidar are different, their principles are same. Therefore, it is expected that CALIPSO/CALIOP data derived cloud parameters are similar to the ground based Lidar data derived cloud parameters. The experimental results show the aforementioned facts and are useful for improvement of cloud parameter estimation accuracy with several sensor data combinations.

  20. A LM-3B Launch Vehicle Sent Chinasat-9 Into Space

    Institute of Scientific and Technical Information of China (English)

    2008-01-01

    @@ The Chinasat-9 direct-broadcast television satellite was launched by a LM-3B launch vehicle from Xichang Satellite Launch Center (XSLC) on June 9.According to Xi'an Satellite Control Center (XSCC),the satellite entered the preset super-geosynchronous transfer orbit 26 minutes after the liftoff with an apogee of 49887km,a perigee of 214km and an inclination of 24.2 degrees.

  1. CHINA RETRIEVES 19th RECOVERABLE SATELLITE

    Institute of Scientific and Technical Information of China (English)

    2004-01-01

    China on Sept.25 recovered its 19th recoverable sci-tech experimental satellite 27 days after the satellite orbited in space. The satellite, which was launched on Aug.29 from the Jiuquan Satellite Launch Center in Gansu Province, northwest China, touched the ground at 7:55 a.m.on Sept.25. The satellite, atop a Long March 2C carrier rocket, is mainly for

  2. Characterization and correction of non-linearity effect on oxygen spectra of TANSO-FTS onboard GOSAT

    Science.gov (United States)

    Suto, H.; Frankenberg, C.; Crisp, D.; kuze, A.

    2011-12-01

    The Thermal and Near Infrared Sensor for carbon Observations Fourier Transform Spectrometer (TANSO-FTS) onboard the Greenhouse gases Observing SATellite (GOSAT) collects high spectral resolution spectra of reflected sunlight in the molecular oxygen (O2) A-band near 760 nm, the carbon dioxide (CO2) bands near 1600 and 2060 nm, and the methane (CH4) band near 1660 nm. The O2 measurements are used to estimate the surface pressure and the dry air column, which are used to define the column-averaged CO2 and CH4 dry air mole fractions, XCO2 and XCH4. O2 measurements are ideal for this application because the O2 dry air mole fraction is almost constant and well known. However, systematic errors in the O2 measurements can introduce biases in the XCO2 and XCH4 retrievals from TANSO-FTS. For example, 1% overestimate of the O2 column retrievals introduced a 10 hPa high bias in surface pressure and a 4 hPa low bias in XCO2 in early retrievals. This near-global bias has been traced to uncertainties in the O2 A-band absorption cross sections. Other spatially-varying O2 errors have been traced to uncertainties in the calibration of the TANSO-FTS A-band channel. For example, non-linearity in the A-band channel response introduces errors in the depths of both O2 lines and solar Fraunhofer lines. There are three possible sources of non-linearity: detector, analogue circuit (amplifier and electric filters), and analogue to digital converter (ADC). Observations acquired with the flight instrument and laboratory experiments with TANSO-FTS engineering model (EM) is being used to discriminate and correct these errors. The EM tests have largely vindicated the silicon photo-diode detector, but show that the non-linearity of the analogue circuit and ADC is almost identical to that seen in data acquired by the on-orbit flight model. We have developed and applied a correction to the measured interferograms from the flight instrument and confirmed it validity by showing that the Fraunhofer

  3. The Canadian Arctic ACE/OSIRIS Validation Project at PEARL: Validating Satellite Observations Over the High Arctic

    Science.gov (United States)

    Walker, Kaley A.; Strong, Kimberly; Fogal, Pierre F.; Drummond, James R.

    2016-04-01

    Ground-based measurements provide critical data for the validation of satellite retrievals of atmospheric trace gases and for the assessment of long-term stability of these measurements. As of February 2016, the Canadian-led Atmospheric Chemistry Experiment (ACE) satellite mission has been making measurements of the Earth's atmosphere for nearly twelve years and Canada's Optical Spectrograph and InfraRed Imager System (OSIRIS) instrument on the Odin satellite has been operating for fourteen years. As ACE and OSIRIS operations have extended beyond their planned two-year missions, there is an ongoing need to validate the trace gas data profiles from the ACE-Fourier Transform Spectrometer (ACE-FTS), the Measurement of Aerosol Extinction in the Stratosphere and Troposphere Retrieved by Occultation (ACE-MAESTRO) and OSIRIS. In particular, validation comparisons are needed during Arctic springtime to understand better the measurements of species involved in stratospheric ozone chemistry. To this end, thirteen Canadian Arctic ACE/OSIRIS Validation Campaigns have been conducted during the spring period (February - April in 2004 - 2016) at the Polar Environment Atmospheric Research Laboratory (PEARL) in Eureka, Nunavut (80N, 86W). For the past decade, these campaigns have been undertaken in collaboration with the Canadian Network for the Detection of Atmospheric Change (CANDAC). The spring period coincides with the most chemically active time of year in the Arctic, as well as a significant number of satellite overpasses. A suite of as many as 12 ground-based instruments, as well as frequent balloon-borne ozonesonde and radiosonde launches, have been used in each campaign. These instruments include: a ground-based version of the ACE-FTS (PARIS - Portable Atmospheric Research Interferometric Spectrometer), a terrestrial version of the ACE-MAESTRO, a SunPhotoSpectrometer, two CANDAC zenith-viewing UV-visible grating spectrometers, a Bomem DA8 Fourier transform spectrometer

  4. Landsat Data Continuity Mission - Launch Fever

    Science.gov (United States)

    Irons, James R.; Loveland, Thomas R.; Markham, Brian L.; Masek, Jeffrey G.; Cook, Bruce; Dwyer, John L.

    2012-01-01

    The year 2013 will be an exciting period for those that study the Earth land surface from space, particularly those that observe and characterize land cover, land use, and the change of cover and use over time. Two new satellite observatories will be launched next year that will enhance capabilities for observing the global land surface. The United States plans to launch the Landsat Data Continuity Mission (LDCM) in January. That event will be followed later in the year by the European Space Agency (ESA) launch of the first Sentinel 2 satellite. Considered together, the two satellites will increase the frequency of opportunities for viewing the land surface at a scale where human impact and influence can be differentiated from natural change. Data from the two satellites will provide images for similar spectral bands and for comparable spatial resolutions with rigorous attention to calibration that will facilitate cross comparisons. This presentation will provide an overview of the LDCM satellite system and report its readiness for the January launch.

  5. Retrieval algorithm for CO2 and CH4 column abundances from short-wavelength infrared spectral observations by the Greenhouse Gases Observing Satellite

    Directory of Open Access Journals (Sweden)

    I. Morino

    2010-11-01

    Full Text Available The Greenhouse gases Observing SATellite (GOSAT was launched on 23 January 2009 to monitor the global distributions of carbon dioxide and methane from space. It has operated continuously since then. Here we describe a retrieval algorithm for column abundances of these gases from the short-wavelength infrared spectra obtained by the Thermal And Near infrared Sensor for carbon Observation-Fourier Transform Spectrometer (TANSO-FTS. The algorithm consists of three steps. First, cloud-free observational scenes are selected by several cloud-detection methods. Then, column abundances of carbon dioxide and methane are retrieved based on the optimal estimation method. Finally, the retrieval quality is examined to exclude low-quality and/or aerosol-contaminated results. Most of the retrieval random errors come from the instrumental noise. The interferences by auxiliary parameters retrieved simultaneously with gas abundances are small. The evaluated precisions of the retrieved column abundances for single observations are less than 1% in most cases. The interhemispherical differences and the temporal variation patterns of the retrieved column abundances agree well with the current state of knowledge.

  6. Retrieval algorithm for CO2 and CH4 column abundances from short-wavelength infrared spectral observations by the Greenhouse gases observing satellite

    Directory of Open Access Journals (Sweden)

    I. Morino

    2011-04-01

    Full Text Available The Greenhouse gases Observing SATellite (GOSAT was launched on 23 January 2009 to monitor the global distributions of carbon dioxide and methane from space. It has operated continuously since then. Here, we describe a retrieval algorithm for column abundances of these gases from the short-wavelength infrared spectra obtained by the Thermal And Near infrared Sensor for carbon Observation-Fourier Transform Spectrometer (TANSO-FTS. The algorithm consists of three steps. First, cloud-free observational scenes are selected by several cloud-detection methods. Then, column abundances of carbon dioxide and methane are retrieved based on the optimal estimation method. Finally, the retrieval quality is examined to exclude low-quality and/or aerosol-contaminated results. Most of the retrieval random errors come from instrumental noise. The interferences due to auxiliary parameters retrieved simultaneously with gas abundances are small. The evaluated precisions of the retrieved column abundances for single observations are less than 1% in most cases. The interhemispherical differences and temporal variation patterns of the retrieved column abundances show features similar to those of an atmospheric transport model.

  7. Consistent regional fluxes of CH4 and CO2 inferred from GOSAT proxy XCH4 : XCO2 retrievals, 2010-2014

    Science.gov (United States)

    Feng, Liang; Palmer, Paul I.; Bösch, Hartmut; Parker, Robert J.; Webb, Alex J.; Correia, Caio S. C.; Deutscher, Nicholas M.; Domingues, Lucas G.; Feist, Dietrich G.; Gatti, Luciana V.; Gloor, Emanuel; Hase, Frank; Kivi, Rigel; Liu, Yi; Miller, John B.; Morino, Isamu; Sussmann, Ralf; Strong, Kimberly; Uchino, Osamu; Wang, Jing; Zahn, Andreas

    2017-04-01

    We use the GEOS-Chem global 3-D model of atmospheric chemistry and transport and an ensemble Kalman filter to simultaneously infer regional fluxes of methane (CH4) and carbon dioxide (CO2) directly from GOSAT retrievals of XCH4 : XCO2, using sparse ground-based CH4 and CO2 mole fraction data to anchor the ratio. This work builds on the previously reported theory that takes into account that (1) these ratios are less prone to systematic error than either the full-physics data products or the proxy CH4 data products; and (2) the resulting CH4 and CO2 fluxes are self-consistent. We show that a posteriori fluxes inferred from the GOSAT data generally outperform the fluxes inferred only from in situ data, as expected. GOSAT CH4 and CO2 fluxes are consistent with global growth rates for CO2 and CH4 reported by NOAA and have a range of independent data including new profile measurements (0-7 km) over the Amazon Basin that were collected specifically to help validate GOSAT over this geographical region. We find that large-scale multi-year annual a posteriori CO2 fluxes inferred from GOSAT data are similar to those inferred from the in situ surface data but with smaller uncertainties, particularly over the tropics. GOSAT data are consistent with smaller peak-to-peak seasonal amplitudes of CO2 than either the a priori or in situ inversion, particularly over the tropics and the southern extratropics. Over the northern extratropics, GOSAT data show larger uptake than the a priori but less than the in situ inversion, resulting in small net emissions over the year. We also find evidence that the carbon balance of tropical South America was perturbed following the droughts of 2010 and 2012 with net annual fluxes not returning to an approximate annual balance until 2013. In contrast, GOSAT data significantly changed the a priori spatial distribution of CH4 emission with a 40 % increase over tropical South America and tropical Asia and a smaller decrease over Eurasia and temperate

  8. Rockot Launch Vehicle Commercial Operations for Grace and Iridium Program

    Science.gov (United States)

    Viertel, Y.; Kinnersley, M.; Schumacher, I.

    2002-01-01

    The GRACE mission and the IRIDIUM mission on ROCKOT launch vehicle are presented. Two identical GRACE satellites to measure in tandem the gravitational field of the earth with previously unattainable accuracy - it's called the Gravity Research and Climate Experiment, or and is a joint project of the U.S. space agency, NASA and the German Centre for Aeronautics and Space Flight, DLR. In order to send the GRACE twins into a 500x500 km , 89deg. orbit, the Rockot launch vehicle was selected. A dual launch of two Iridium satellites was scheduled for June 2002 using the ROCKOT launch vehicle from Plesetsk Cosmodrome in Northern Russia. This launch will inject two replacement satellites into a low earth orbit (LEO) to support the maintenance of the Iridium constellation. In September 2001, Eurockot successfully carried out a "Pathfinder Campaign" to simulate the entire Iridium mission cycle at Plesetsk. The campaign comprised the transport of simulators and related equipment to the Russian port-of-entry and launch site and also included the integration and encapsulation of the simulators with the actual Rockot launch vehicle at Eurockot's dedicated launch facilities at Plesetsk Cosmodrome. The pathfinder campaign lasted four weeks and was carried out by a joint team that also included Khrunichev, Russian Space Forces and Eurockot personnel on the contractors' side. The pathfinder mission confirmed the capability of Eurockot Launch Services to perform the Iridium launch on cost and on schedule at Plesetsk following Eurockot's major investment in international standard preparation, integration and launch facilities including customer facilities and a new hotel. In 2003, Eurockot will also launch the Japanese SERVI'S-1 satellite for USEF. The ROCKOT launch vehicle is a 3 stage liquid fuel rocket whose first 2 stages have been adapted from the Russian SS-19. A third stage, called "Breeze", can be repeatedly ignited and is extraordinarily capable of manoeuvre. Rockot can place

  9. Analysis of Long-Range Transport of Carbon Dioxide Using Satellite and Modeling Data over East Asia

    Science.gov (United States)

    Moon, K. J.; Choi, W. J.; Kim, S. Y.; Kim, D. R.; Chang, L. S.; Lee, S. D.; Lee, J. B.; Kim, S. K.; Hong, J.

    2015-12-01

    This study aims to evaluate the long-range transport of CO2 in East Asian region, using concentration data from a ground-based measurement site, column averaged concentration data of GOSAT observations, and the chemical transport model (GEOS-Chem) results for the period June 2009 to May 2011. We performed a validation of the data from GOSAT and GEOS-Chem with total column observations (TCCON). Satellite data and model simulation results show very similar seasonal variation and spatial distribution with well-known difference with TCCON data. The analysis of the long-range transport and high concentration (HC) events using surface/satellite observations and modeling results was conducted. During the HC events, the concentrations of CO2 and other air pollutants such as SO2 and CO are higher than that of all episodes. It means that CO2 known as a globally well-mixed gas may also play as a finger-print of human activity with unique regional characteristics like other air pollutants. The comprehensive analysis, in particular with GOSAT CO2 observation data, shows that CO2 plume with high concentration can be long-range transported with 1-2 days duration with regional scale. This analysis with satellite data and modeling conducted in this study can help better understanding of the behavior of CO2 and its impact on climate change and the carbon cycle.

  10. Spatial and temporal distribution characteristics of near-surface CO2 concentration over China based on GOSAT data

    Science.gov (United States)

    Zhao, Jing; Cui, Weihong; Sun, Yunhua

    2014-11-01

    To study the spatial and temporal distribution characteristics of near-surface CO2 concentration over China, the data of GOSAT L4B and auxiliary data of Mt Waliguan background observations, population density, total energy consumption (coal) and GDP in 2009 were applied to this study. The ArcGIS Geostatistical Analytical Method was used. The ground-based validation was processed by comparing GOSAT data with Mt Waliguan background observations. The variation characteristics of the near-surface CO2 concentration over China was analysed spatially and temporally. The results show that: GOSAT retrieved near-surface products are consistent with Mt Waliguan ground-based measurement; Near-surface CO2 concentration over China is relatively concentrated, and has significant differences between the East and the West, with a overall characteristic that CO2 concentration in the east of China is high and in the west is low; Near-surface CO2 concentration over China has a significant seasonal variation characteristic, and the monthly average concentration rise to the highest value of 396.512 ppmv in April (spring), which is significantly higher than other seasons, decline to the lowest value of 382.781 ppmv in July (summer); All relationships illustrate a big uncertainty, resulting a conclusion that the reasons causing the spatial distribution of near-surface CO2 concentration may be varied, could not be easily determined as anthropogenic or natural ressons, which need further study.

  11. Gravity Probe B:. Launch and Initialization

    Science.gov (United States)

    Keiser, G. M.; Bencze, W. J.; Brumley, R. W.; Buchman, S.; Clarke, B.; Debra, D.; Everitt, C. W. F.; Green, G.; Heifetz, M. I.; Hipkins, D. N.; Holmes, T.; Li, J.; Mester, J.; Muhlfelder, B.; Murray, D.; Ohshima, Y.; Parkinson, B. W.; Salomon, M.; Santiago, D.; Shestople, P.; Silbergleit, A. S.; Solomonik, V.; Taber, M.; Turneaure, J. P.

    2005-04-01

    The scientific instrument and the major subsystems of the Gravity Probe B satellite are described. Following launch, the initial on-orbit operations were designed to check the operations of each of these major subsystems, provide an initial on-orbit calibration of the scientific instrument, set up the instrument in its operational mode, and spin up and align each of the four gyroscopes.

  12. Iraq Radiosonde Launch Records

    Data.gov (United States)

    National Oceanic and Atmospheric Administration, Department of Commerce — Iraqi upper air records loaned to NCDC from the Air Force 14th Weather Squadron. Scanned notebooks containing upper air radiosonde launch records and data. Launches...

  13. Launching technological innovations

    DEFF Research Database (Denmark)

    Talke, Katrin; Salomo, Søren

    2009-01-01

    have received less attention. This study considers the interdependencies between strategic, internally and externally, directed tactical launch activities and investigates both direct and indirect performance effects. The analysis is based upon data from 113 technological innovations launched...

  14. ESPA Satellite Dispenser for ORBCOMM Generation 2

    OpenAIRE

    2013-01-01

    ORBCOMM’s machine-to-machine (M2M) solutions offer global asset monitoring and messaging services through a powerful Low Earth Orbit (LEO) satellite constellation. The original constellation deployment consisted of thirtyfive satellites launched in the late 1990s. ORBCOMM is launching the new ORBCOMM Generation 2 (OG2) satellites to upgrade and expand the constellation network. The OG2 satellites being manufactured by Sierra Nevada Corporation will have more data capacity with the potential f...

  15. NASA Facts: Nanosatellite Launch Adapter System (NLAS)

    Science.gov (United States)

    Chartres, James; Cappuccio, Gelsomina

    2013-01-01

    The Nanosatellite Launch Adapter System (NLAS) was developed to increase access to space while simplifying the integration process of miniature satellites, called nanosats or cubesats, onto launch vehicles. A standard cubesat measures about 4inches (10 cm) long, 4 inches wide,and 4 inches high, and is called a one-unit (1U) cubesat. A single NLAS provides the capability to deploy 24U of cubesats. The system is designed to accommodate satellites measuring 1U, 1.5U, 2U, 3U and 6U sizes for deployment into orbit. The NLAS may be configured for use on different launch vehicles. The system also enables flight demonstrations of new technologies in the space environment.

  16. GRYPHON: Air launched space booster

    Science.gov (United States)

    1993-06-01

    The project chosen for the winter semester Aero 483 class was the design of a next generation Air Launched Space Booster. Based on Orbital Sciences Corporation's Pegasus concept, the goal of Aero 483 was to design a 500,000 pound air launched space booster capable of delivering 17,000 pounds of payload to Low Earth Orbit and 8,000 pounds of payload to Geosynchronous Earth Orbit. The resulting launch vehicle was named the Gryphon. The class of forty senior aerospace engineering students was broken down into eight interdependent groups. Each group was assigned a subsystem or responsibility which then became their field of specialization. Spacecraft Integration was responsible for ensuring compatibility between subsystems. This group kept up to date on subsystem redesigns and informed those parties affected by the changes, monitored the vehicle's overall weight and dimensions, and calculated the mass properties of the booster. This group also performed the cost/profitability analysis of the Gryphon and obtained cost data for competing launch systems. The Mission Analysis Group was assigned the task of determining proper orbits, calculating the vehicle's flight trajectory for those orbits, and determining the aerodynamic characteristics of the vehicle. The Propulsion Group chose the engines that were best suited to the mission. This group also set the staging configurations for those engines and designed the tanks and fuel feed system. The commercial satellite market, dimensions and weights of typical satellites, and method of deploying satellites was determined by the Payloads Group. In addition, Payloads identified possible resupply packages for Space Station Freedom and identified those packages that were compatible with the Gryphon. The guidance, navigation, and control subsystems were designed by the Mission Control Group. This group identified required tracking hardware, communications hardware telemetry systems, and ground sites for the location of the Gryphon

  17. Assessing 5 years of GOSAT Proxy XCH4 data and associated uncertainties

    Directory of Open Access Journals (Sweden)

    R. J. Parker

    2015-06-01

    Full Text Available We present 5 years of GOSAT XCH4 retrieved using the "proxy" approach. The Proxy XCH4 data are validated against ground-based TCCON observations and are found to be of high-quality with a small bias of 4.8 ppb (~ 0.27% and a single-sounding precision of 13.4 ppb (~ 0.74%. The station-to-station bias (a measure of the relative accuracy is found to be 4.2 ppb. For the first time the XCH4 / XCO2 ratio component of the Proxy retrieval is validated (bias of 0.014 ppb ppm−1 (~ 0.3%, single-sounding precision of 0.033 ppb ppm−1 (~ 0.72%. The uncertainty relating to the model XCO2 component of the Proxy XCH4 is assessed through the use of an ensemble of XCO2 models. While each individual XCO2 model is found to agree well with the TCCON validation data (r=0.94–0.97, it is not possible to select one model as the best from our comparisons. The median XCO2 value of the ensemble has a smaller scatter against TCCON (a standard deviation of 0.92 ppm than any of the individual models whilst maintaining a small bias (0.15 ppm. This model median XCO2 is used to calculate the Proxy XCH4 with the maximum deviation of the ensemble from the median used as an estimate of the uncertainty. We compare this uncertainty to the a posteriori retrieval error and find typically that the model XCO2 uncertainty becomes significant during summer months when the a posteriori error is at its lowest due to the increase in signal related to increased summertime reflected sunlight. We assess the significance of these model and retrieval uncertainties on flux inversion by comparing the GOSAT XCH4 against modelled XCH4 from TM5-4DVAR constrained by NOAA surface observations (MACC reanalysis scenario S1-NOAA. We find that for the majority of regions the differences are much larger than the estimated uncertainties. Our findings show that useful information will be provided to the inversions for the majority of regions in addition to that already provided by the assimilated

  18. Assessing 5 years of GOSAT Proxy XCH4 data and associated uncertainties

    Directory of Open Access Journals (Sweden)

    R. J. Parker

    2015-11-01

    Full Text Available We present 5 years of GOSAT XCH4 retrieved using the "proxy" approach. The Proxy XCH4 data are validated against ground-based TCCON observations and are found to be of high quality with a small bias of 4.8 ppb (∼ 0.27 % and a single-sounding precision of 13.4 ppb (∼ 0.74 %. The station-to-station bias (ameasure of the relative accuracy is found to be 4.2 ppb. For the first time the XCH4 / XCO2 ratio component of the Proxy retrieval is validated (bias of 0.014 ppb ppm−1 (∼ 0.30 %, single-sounding precision of 0.033 ppb ppm−1 (∼ 0.72 %. The uncertainty relating to the model XCO2 component of the Proxy XCH4 is assessed through the use of an ensemble of XCO2 models. While each individual XCO2 model is found to agree well with the TCCON validation data (r = 0.94–0.97, it is not possible to select one model as the best from our comparisons. The median XCO2 value of the ensemble has a smaller scatter against TCCON (a standard deviation of 0.92 ppm than any of the individual models whilst maintaining a small bias (0.15 ppm. This model median XCO2 is used to calculate the Proxy XCH4 with the maximum deviation of the ensemble from the median used as an estimate of the uncertainty. We compare this uncertainty to the a posteriori retrieval error (which is assumed to reduce with sqrt(N and find typically that the model XCO2 uncertainty becomes significant during summer months when the a posteriori error is at its lowest due to the increase in signal related to increased summertime reflected sunlight. We assess the significance of these model and retrieval uncertainties on flux inversion by comparing the GOSAT XCH4 against modelled XCH4 from TM5-4DVAR constrained by NOAA surface observations (MACC reanalysis scenario S1-NOAA. We find that for the majority of regions the differences are much larger than the estimated uncertainties. Our findings show that useful information will be provided to the inversions for the majority of regions in addition

  19. NATO-3C/Delta launch

    Science.gov (United States)

    1978-01-01

    NATO-3C, the third in a series of NATO defense-related communication satellites, is scheduled to be launched on a delta vehicle from the Eastern Test Range no earlier than November 15, 1978. NATO-3A and -3B were successfully launched by Delta vehicles in April 1976 and January 1977, respectively. The NATO-3C spacecraft will be capable of transmitting voice, data, facsimile, and telex messages among military ground stations. The launch vehicle for the NATO-3C mission will be the Delta 2914 configuration. The launch vehicle is to place the spacecraft in a synchronous transfer orbit. The spacecraft Apogee Kick motor is to be fired at fifth transfer orbit apogee to circularize its orbit at geosynchronous altitude of 35,900 km(22,260 miles) above the equator over the Atlantic Ocean somewhere between 45 and 50 degrees W longitude.

  20. Space Acquisitions: GAO Assessment of DOD Responsive Launch Report

    Science.gov (United States)

    2015-10-29

    number of satellites may be needed to provide the same level of capability, and the transition from existing system designs could increase costs...Also, DOD currently lacks requirements for responsive launch, but plans to validate future responsive launch requirements as it gains knowledge about...Programs Congressional Relations Public Affairs Please Print on Recycled Paper.

  1. women Contrlbute to Satellite Technology

    Institute of Scientific and Technical Information of China (English)

    1994-01-01

    IN the early morning of August 14, 1992, at the Xichang satellite launching center, China Central Television Station was about to do a live, worldwide broadcast on the launching of an Australian communications satellite made by the United States. With the order of the commander, "Ignition," people could watch the white rocket rise, pierce the blue sky and race toward the space with a long flaming tail trailing behind it.

  2. On the detection of strong emissions of methane in the Arctic using spectral measurements from IASI and GOSAT

    Science.gov (United States)

    Bourakkadi, Zakia; Payan, Sébastien; Bureau, Jérôme

    2014-05-01

    Boreal ecosystems store significant quantities of organic carbon (C) for thousands of years. Most are presently sequestered in permafrost. In recent years, several studies highlighted that climate warming and thawing of permafrost in the Arctic acts on the mobilization of old stored carbon (c) and contribute to a sustained release of methane (CH4) to the atmosphere [1],[2],[3]. Because methane is an important greenhouse gas, it is necessary to estimate his sources and sinks in the Arctic. The objective of this study is to evaluate and quantify methane strong emission in this region of the globe using spectral measurements from two satellite instruments: IASI-MetOp and TANSO-FTS. The Infrared Atmospheric Sounding Interferometer (IASI) is a Fourier transform spectrometer coupled with an integrated imaging system that observes and measures infrared radiation emitted by the Earth and the atmosphere in the spectral range 645-2760cm-1, which covered the methane ?4 and ?3 absorption band[4]. IASI provides global Earth's coverage twice a day and delivers about 1 300 000 spectra per day[5]. The second instrument which we will use in this study is the Thermal And Near-infrared Sensor for Carbon Observation-Fourier Transform Spectrometer (TANSO-FTS), it has a wide TIR band (5,5-14,3μm)which contain the methane ?4absorption band.TANSO-FTS completes one revolution in about 100 minutes and it comes back to the same location in 3 days period. Over these 3 days, FTS takes 56 000 measurements covering the entire globe[6]. To have a good estimation of methane emission above the Arctic, we must exploit a vast amount of spectral information from IASI and TANSO-FTS. But it is well known that performing line-by-line radiative transfer model is a time-consuming process. So, if we need to exploit large data we have to look fast method. In this work, we will use a simple approach based on the Singular Value Decomposition (SVD) to identify spectra over large source of methane. A more

  3. Three ZY-2 Satellites Forming A Constellation

    Institute of Scientific and Technical Information of China (English)

    SunQing

    2005-01-01

    China successfully put its earth resource satellite, the third of ZY-2, into the orbit aboard a LM-4B launch vehicle that blasted off at 11:10 am on Nov. 6, 2004 from Taiyuan Satellite Launch Center in Shanxi Province.

  4. An Overview Of Operational Satellites Built By China: Communications Satellites (Part1)

    Institute of Scientific and Technical Information of China (English)

    Guang Bo

    2008-01-01

    @@ Communications satellite technology has seen great advances since Decemher 1958 when the Americans launched the first experimental communications satellite.Currently, satellite communications account for over 80 percent of the intercontinental communications traffic and 100 percent of international live TV broadcast, while taking part in domestic and regional services. Moreover, the satellite communication service is showing a favorable continuous growth tendency.

  5. CASC Exported Its First Whole Satellite PAKSAT-1R for An Asian Customer

    Institute of Scientific and Technical Information of China (English)

    Rain Liu

    2011-01-01

    China Great Wall Industry Corporation (CGWIC) performed its first international commercial launch contract in 2011 by launching PAKSAT-1R communications satellite into space in August.It was one of three commercial launches scheduled by CGWIC in 2011.

  6. Australia and the new reusable launch vehicles

    Science.gov (United States)

    Stalker, R. J.

    The new generation of reusable launch vehicles represented by ESA's Hermes and HOTOL, NASA's National Aerospace Plane, and the DFVLR's Saenger, promises to radically alter the economic basis of space flight by allowing such operations as the on-orbit servicing of satellites. Attention is presently drawn to the opportunities that arise for Australia's aerospace industry from the availability in Australia of two wind tunnel facilities capable of furnishing the requisite hypersonic aerothermodynamics testing capabilities for these vehicles' development.

  7. The TAOS/STEP Satellite

    OpenAIRE

    Edwards, David; Hosken, Robert

    1995-01-01

    The Technology for Autonomous Operational Survivability / Space Test Experiments Platform (TAOS/STEP) satellite was launched on a Taurus booster from Vandenberg Air Force Base into a nearly circular, 105 degree inclined orbit on March 13, 1994. The purpose of this satellite is twofold: 1) to test a new concept in multiple procurements of fast-track modular satellites and 2) to test a suite of Air Force Phillips Laboratory payloads in space. The TAOS payloads include the Microcosm Autonomous N...

  8. Arianespace streamlines launch procedures

    Science.gov (United States)

    Lenorovitch, Jeffrey M.

    1992-06-01

    Ariane has entered a new operational phase in which launch procedures have been enhanced to reduce the length of launch campaigns, lower mission costs, and increase operational availability/flexibility of the three-stage vehicle. The V50 mission utilized the first vehicle from a 50-launcher production lot ordered by Arianespace, and was the initial flight with a stretched third stage that enhances Ariane's performance. New operational procedures were introduced gradually over more than a year, starting with the V42 launch in January 1991.

  9. Inverse modelling of CH4 emissions for 2010-2011 using different satellite retrieval products from GOSAT and SCIAMACHY

    NARCIS (Netherlands)

    Alexe, M.; Bergamaschi, P.; Segers, A.; Detmers, R.; Butz, A.; Hasekamp, O.; Guerlet, S.; Parker, R.; Boesch, H.; Frankenberg, C.; Scheepmaker, R.A.; Dlugokencky, E.; Sweeney, C.; Wofsy, S.C.; Kort, E.A.

    2015-01-01

    At the beginning of 2009 new space-borne observations of dry-air column-averaged mole fractions of atmospheric methane (XCH4) became available from the Thermal And Near infrared Sensor for carbon Observations-Fourier Transform Spectrometer (TANSO-FTS) instrument on board the Greenhouse Gases Observi

  10. Launch Services, a Proven Model

    Science.gov (United States)

    Trafton, W. C.; Simpson, J.

    2002-01-01

    From a commercial perspective, the ability to justify "leap frog" technology such as reusable systems has been difficult to justify because the estimated 5B to 10B investment is not supported in the current flat commercial market coupled with an oversupply of launch service suppliers. The market simply does not justify investment of that magnitude. Currently, next generation Expendable Launch Systems, including Boeing's Delta IV, Lockheed Martin's Atlas 5, Ariane V ESCA and RSC's H-IIA are being introduced into operations signifying that only upgrades to proven systems are planned to meet the changes in anticipated satellite demand (larger satellites, more lifetime, larger volumes, etc.) in the foreseeable future. We do not see a new fleet of ELVs emerging beyond that which is currently being introduced, only continuous upgrades of the fleet to meet the demands. To induce a radical change in the provision of launch services, a Multinational Government investment must be made and justified by World requirements. The commercial market alone cannot justify such an investment. And if an investment is made, we cannot afford to repeat previous mistakes by relying on one system such as shuttle for commercial deployment without having any back-up capability. Other issues that need to be considered are national science and security requirements, which to a large extent fuels the Japanese, Chinese, Indian, Former Soviet Union, European and United States space transportation entries. Additionally, this system must support or replace current Space Transportation Economies with across-the-board benefits. For the next 10 to 20 years, Multinational cooperation will be in the form of piecing together launch components and infrastructure to supplement existing launch systems and reducing the amount of non-recurring investment while meeting the future requirements of the End-User. Virtually all of the current systems have some form of multinational participation: Sea Launch

  11. Big Bang launch

    CERN Document Server

    2008-01-01

    Physicists from the University, along with scientists and engineers around the world, watched with fevered anticipation as the world's biggest scientific experiment was launched in September. (1/1 page)

  12. Anchor Trial Launch

    Science.gov (United States)

    NCI has launched a multicenter phase III clinical trial called the ANCHOR Study -- Anal Cancer HSIL (High-grade Squamous Intraepithelial Lesion) Outcomes Research Study -- to determine if treatment of HSIL in HIV-infected individuals can prevent anal canc

  13. Genomic Data Commons launches

    Science.gov (United States)

    The Genomic Data Commons (GDC), a unified data system that promotes sharing of genomic and clinical data between researchers, launched today with a visit from Vice President Joe Biden to the operations center at the University of Chicago.

  14. Water-cooled spacecraft: DART to be launched by Russian Volna (Stingray) rocket

    NARCIS (Netherlands)

    Hartmann, L.

    2002-01-01

    A25 September 2005, Barents Sea, near Murmansk.Ten metres under the surface of the sea, the launch tube of the Mstislav, a Rostropovich class nuclear submarine, grinds open. The countdown for the launch of a Volna R-29R slbm (Submarine-Launched Ballistic Missile) starts: For many years, satellites w

  15. IBF Launched in China

    Institute of Scientific and Technical Information of China (English)

    Guo Yan

    2009-01-01

    @@ The India Business Forum(IBF)organized by the Confederation of Indian Industry(CII)and the Indian Embassy to China was officially launched in Beijing,on April 16,2009.With the theme of"Impact of Global Economic Crisis:Challenges and Opportunities for India and China",IBF(China)was launched to provide a lobby to promote bilateral trade and economic cooperation between the two countries.

  16. New product launch

    OpenAIRE

    Andžič, Vedrana

    2007-01-01

    The aim of this Master's thesis is description of new electric water heater launch process. The theoretical part of the thesis deals with marketing mix and goes deeper in explanation of product lifecycle theory. Theoretical part is the basis for practical part. Practical part describes company Ariston Thermo in brief and deals with technical parameters of new electric water heater VELIS as well as distribution and price policy during the launch process. The key part of the thesis is dedicated...

  17. Evaluation of Product Launch

    OpenAIRE

    MARŠÁLKOVÁ, Nina

    2012-01-01

    This bachelor thesis deals with the evaluation of the launch of product on the market and the proposal of a more appropriate solution. Author has chosen company Aponia software, s.r.o. with a place of business in Brno. It is small company which produces and sells navigations for mobile devices. During writing this thesis author focus on the launch of navigation for operating system Android on the market.

  18. Throttleable GOX/ABS launch assist hybrid rocket motor for small scale air launch platform

    Science.gov (United States)

    Spurrier, Zachary S.

    Aircraft-based space-launch platforms allow operational flexibility and offer the potential for significant propellant savings for small-to-medium orbital payloads. The NASA Armstrong Flight Research Center's Towed Glider Air-Launch System (TGALS) is a small-scale flight research project investigating the feasibility for a remotely-piloted, towed, glider system to act as a versatile air launch platform for nano-scale satellites. Removing the crew from the launch vehicle means that the system does not have to be human rated, and offers a potential for considerable cost savings. Utah State University is developing a small throttled launch-assist system for the TGALS platform. This "stage zero" design allows the TGALS platform to achieve the required flight path angle for the launch point, a condition that the TGALS cannot achieve without external propulsion. Throttling is required in order to achieve and sustain the proper launch attitude without structurally overloading the airframe. The hybrid rocket system employs gaseous-oxygen and acrylonitrile butadiene styrene (ABS) as propellants. This thesis summarizes the development and testing campaign, and presents results from the clean-sheet design through ground-based static fire testing. Development of the closed-loop throttle control system is presented.

  19. Fast Development Of China's Small Satellite Industry

    Institute of Scientific and Technical Information of China (English)

    Sun Hongjin

    2009-01-01

    @@ China Spacesat Co., Ltd of China Academy of Space Technology (CAST) recently said, along with the successful launch of HJ-1A/B for the environment and disaster monitoring and forecasting small satellite constellation and after years of efforts, small satellite development technology has achieved fruitful results, and the development status has been greatly improved.China's small satellite technology has realized a great-leap-forward in development from a single satellite model to series model, from the satellite program to space industry. China has explored a development road for China's small satellite industrialization, and a modern small satellite development base has resulted.

  20. Chartering Launchers for Small Satellites

    Science.gov (United States)

    Hernandez, Daniel

    The question of how to launch small satellites has been solved over the years by the larger launchers offering small satellites the possibility of piggy-backing. Specific fixtures have been developed and commercialized: Arianespace developed the ASAP interface, the USAF studied ESPA, NASA has promoted Shuttle launch possibilities, Russian authorities and companies have been able to find solutions with many different launchers... It is fair to say that most launcher suppliers have worked hard and finally often been able to find solutions to launch most small satellites into orbit. It is also true, however, that most of these small satellites were technology demonstration missions capable of accepting a wide range of orbit and launch characteristics: orbit altitude and inclination, launch date, etc. In some cases the small satellite missions required a well-defined type of orbit and have therefore been obliged to hire a small launcher on which they were the prime passenger. In our paper we would like to propose an additional solution to all these possibilities: launchers could plan well in advance (for example about 3 years), trips to precisely defined orbits to allow potential passengers to organize themselves and be ready on the D-Day. On the scheduled date the chartered launcher goes to the stated orbit while on another date, another chartered launcher goes to another orbit. The idea is to organize departures for space like trains or airplanes leaving on known schedules for known destinations.

  1. Satellite Communications: The Indian Scenario

    Directory of Open Access Journals (Sweden)

    Dr. Ranjit Singh

    2014-05-01

    Full Text Available India has launched as many as 73 Indian satellites as of today since its first attempt in 1975. Besides serving traditional markets of telephony and broadcasting, satellites are on the frontiers of advanced applications as telemedicine, distance learning, environment monitoring, remote sensing, and so on. Satellite systems are optimized for services such as Internet access, virtual private networks and personal access. Costs have been coming down in recent years to the point where satellite broadband is becoming competitive. This article is an attempt to view this important topic from Indian perspective. India’s Project GAGAN, GPS Aided Geo Augmented Navigation is discussed.

  2. Plan of advanced satellite communication experiments using ETS-6

    Science.gov (United States)

    Ikegami, Tetsushi

    1989-01-01

    In 1992, an Engineering Test Satellite 6 is scheduled to be launched by an H-2 rocket. The missions of ETS-6 are to establish basic technologies of inter-satellite communications using S-band, millimeter waves and optical beams and of fixed and mobile satellite communications using multibeam antenna on board the satellite. A plan of the experiments is introduced.

  3. Athermal laser launch telescopes

    NARCIS (Netherlands)

    Kamphues, F.G.; Henselmans, R.; Rijnveld, N.; Lemmen, M.H.J.; Doelman, N.J.; Nijkerk, M.D.

    2011-01-01

    ESO has developed a concept for a compact laser guide star unit for use in future Adaptive Optics (AO) systems. A small powerful laser is combined with a telescope that launches the beam, creating a single modular unit that can be mounted directly on a large telescope. This approach solves several

  4. Athermal laser launch telescopes

    NARCIS (Netherlands)

    Kamphues, F.G.; Henselmans, R.; Rijnveld, N.; Lemmen, M.H.J.; Doelman, N.J.; Nijkerk, M.D.

    2011-01-01

    ESO has developed a concept for a compact laser guide star unit for use in future Adaptive Optics (AO) systems. A small powerful laser is combined with a telescope that launches the beam, creating a single modular unit that can be mounted directly on a large telescope. This approach solves several o

  5. Several thoughts for using new satellite remote sensing and global modeling for aerosol and cloud climate studies

    Science.gov (United States)

    Nakajima, Teruyuki; Hashimoto, Makiko; Takenaka, Hideaki; Goto, Daisuke; Oikawa, Eiji; Suzuki, Kentaroh; Uchida, Junya; Dai, Tie; Shi, Chong

    2017-04-01

    The rapid growth of satellite remote sensing technologies in the last two decades widened the utility of satellite data for understanding climate impacts of aerosols and clouds. The climate modeling community also has received the benefit of the earth observation and nowadays closed-collaboration of the two communities make us possible to challenge various applications for societal problems, such as for global warming and global-scale air pollution and others. I like to give several thoughts of new algorithm developments, model use of satellite data for climate impact studies and societal applications related with aerosols and clouds. Important issues are 1) Better aerosol detection and solar energy application using expanded observation ability of the third generation geostationary satellites, i.e. Himawari-8, GOES-R and future MTG, 2) Various observation functions by directional, polarimetric, and high resolution near-UV band by MISR, POLDER&PARASOL, GOSAT/CAI and future GOSAT2/CAI2, 3) Various applications of general purpose-imagers, MODIS, VIIRS and future GCOM-C/SGLI, and 4) Climate studies of aerosol and cloud stratification and convection with active and passive sensors, especially climate impact of BC aerosols using CLOUDSAT&CALIPSO and future Earth Explorer/EarthCARE.

  6. Small satellites and their regulation

    CERN Document Server

    Jakhu, Ram S

    2014-01-01

    Since the launch of UoSat-1 of the University of Surrey (United Kingdom) in 1981, small satellites proved regularly to be useful, beneficial, and cost-effective tools. Typical tasks cover education and workforce development, technology demonstration, verification and validation, scientific and engineering research as well as commercial applications. Today the launch masses range over almost three orders of magnitude starting at less than a kilogram up to a few hundred kilograms, with budgets of less than US$ 100.00 and up to millions within very short timeframes of sometimes less than two years. Therefore each category of small satellites provides specific challenges in design, development and operations. Small satellites offer great potentials to gain responsive, low-cost access to space within a short timeframe for institutions, companies, regions and countries beyond the traditional big players in the space arena. For these reasons (particularly the low cost of construction, launch and operation), small (m...

  7. Geostationary Space Launch Vehicles and the U.S. Dilemma

    Science.gov (United States)

    1994-06-17

    maintaining capability. The goal for satellite companies has been to push the size and weight limits of space launch vehicles. A new technology has...Week & Space Tecnolog , 10 January 1994, p. 27. 7. "Satellites: No Wires, No Cables," The Providence Sunday Journal, 3 April 1994, p. Fl. 2-17 CHAPTER I1...payload-to-takeoff weight ratios, but seldom performed as originally marketed because the first few flights were usually basic systems that did not push

  8. Satellite Communication.

    Science.gov (United States)

    Technology Teacher, 1985

    1985-01-01

    Presents a discussion of communication satellites: explains the principles of satellite communication, describes examples of how governments and industries are currently applying communication satellites, analyzes issues confronting satellite communication, links mathematics and science to the study of satellite communication, and applies…

  9. Cassini launch contingency effort

    Science.gov (United States)

    Chang, Yale; O'Neil, John M.; McGrath, Brian E.; Heyler, Gene A.; Brenza, Pete T.

    2002-01-01

    On 15 October 1997 at 4:43 AM EDT, the Cassini spacecraft was successfully launched on a Titan IVB/Centaur on a mission to explore the Saturnian system. It carried three Radioisotope Thermoelectric Generators (RTGs) and 117 Light Weight Radioisotope Heater Units (LWRHUs). As part of the joint National Aeronautics and Space Administration (NASA)/U.S. Department of Energy (DoE) safety effort, a contingency plan was prepared to address the unlikely events of an accidental suborbital reentry or out-of-orbital reentry. The objective of the plan was to develop procedures to predict, within hours, the Earth impact footprints (EIFs) for the nuclear heat sources released during the atmospheric reentry. The footprint predictions would be used in subsequent notification and recovery efforts. As part of a multi-agency team, The Johns Hopkins University Applied Physics Laboratory (JHU/APL) had the responsibility to predict the EIFs of the heat sources after a reentry, given the heat sources' release conditions from the main spacecraft. (No ablation burn-through of the heat sources' aeroshells was expected, as a result of earlier testing.) JHU/APL's other role was to predict the time of reentry from a potential orbital decay. The tools used were a three degree-of-freedom trajectory code, a database of aerodynamic coefficients for the heat sources, secure links to obtain tracking data, and a high fidelity special perturbation orbit integrator code to predict time of spacecraft reentry from orbital decay. In the weeks and days prior to launch, all the codes and procedures were exercised. Notional EIFs were derived from hypothetical reentry conditions. EIFs predicted by JHU/APL were compared to those by JPL and US SPACECOM, and were found to be in good agreement. The reentry time from orbital decay for a booster rocket for the Russian Progress M-36 freighter, a cargo ship for the Mir space station, was predicted to within 5 minutes more than two hours before reentry. For the

  10. STS-121 Launch

    Science.gov (United States)

    2006-01-01

    Space Shuttle Discovery and its seven-member crew launched at 2:38 p.m. (EDT) to begin the two-day journey to the International Space Station (ISS) on the historic Return to Flight STS-121 mission. The shuttle made history as it was the first human-occupying spacecraft to launch on Independence Day. During its 12-day mission, this utilization and logistics flight delivered a multipurpose logistics module (MPLM) to the ISS with several thousand pounds of new supplies and experiments. In addition, some new orbital replacement units (ORUs) were delivered and stowed externally on the ISS on a special pallet. These ORUs are spares for critical machinery located on the outside of the ISS. During this mission the crew also carried out testing of Shuttle inspection and repair hardware, as well as evaluated operational techniques and concepts for conducting on-orbit inspection and repair.

  11. The Vega launch vehicle

    Science.gov (United States)

    Geffroy, B.; Fabrizi, R.; Guilleux, Willy; Berna, Claude

    2004-11-01

    ESA, ELV, Arianespace are introducing for the small satellites market a new class of launcher, VEGA, complementing the European launchers portfolio (Ariane 5, Soyuz). ESA is leading the development and qualification programme with Prime Contractor ELV, while Arianespace is insuring the marketing, sales and operations of the Vega launcher from the European Spaceport in Kourou, French Guiana.

  12. Launch of Zoological Letters.

    Science.gov (United States)

    Fukatsu, Takema; Kuratani, Shigeru

    2016-02-01

    A new open-access journal, Zoological Letters, was launched as a sister journal to Zoological Science, in January 2015. The new journal aims at publishing topical papers of high quality from a wide range of basic zoological research fields. This review highlights the notable reviews and research articles that have been published in the first year of Zoological Letters, providing an overview on the current achievements and future directions of the journal.

  13. Launching Another Crisis

    Institute of Scientific and Technical Information of China (English)

    2006-01-01

    North Korea's test-firing of a range of missiles gets a mixed reaction from the international communityWhen the Democratic People's Republic of Korea (DPRK) test-fired a stream of missiles on July 5, it drew sharp concerns from a global communi- ty perpetually concerned over stability and security in the Asia-Pacific region. According to government reports from South Korea, the DPRK launched at least seven missiles from two sites along its east

  14. Launch Control Network Engineer

    Science.gov (United States)

    Medeiros, Samantha

    2017-01-01

    The Spaceport Command and Control System (SCCS) is being built at the Kennedy Space Center in order to successfully launch NASA’s revolutionary vehicle that allows humans to explore further into space than ever before. During my internship, I worked with the Network, Firewall, and Hardware teams that are all contributing to the huge SCCS network project effort. I learned the SCCS network design and the several concepts that are running in the background. I also updated and designed documentation for physical networks that are part of SCCS. This includes being able to assist and build physical installations as well as configurations. I worked with the network design for vehicle telemetry interfaces to the Launch Control System (LCS); this allows the interface to interact with other systems at other NASA locations. This network design includes the Space Launch System (SLS), Interim Cryogenic Propulsion Stage (ICPS), and the Orion Multipurpose Crew Vehicle (MPCV). I worked on the network design and implementation in the Customer Avionics Interface Development and Analysis (CAIDA) lab.

  15. Three-Axis Satellite Attitude Control Based on Magnetic Torquing

    DEFF Research Database (Denmark)

    Wisniewski, Rafal

    1995-01-01

    Recently small satellite missions have gained considerable interest due to low-cost launch opportunities and technilogical improvement of micro-electronics.......Recently small satellite missions have gained considerable interest due to low-cost launch opportunities and technilogical improvement of micro-electronics....

  16. Three-Axis Satellite Attitude Control Based on Magnetic Torquing

    DEFF Research Database (Denmark)

    Wisniewski, Rafal

    1995-01-01

    Recently small satellite missions have gained considerable interest due to low-cost launch opportunities and technilogical improvement of micro-electronics.......Recently small satellite missions have gained considerable interest due to low-cost launch opportunities and technilogical improvement of micro-electronics....

  17. Applying satellite retrievals to identify urban emissions of GHG's over East Asia

    Science.gov (United States)

    Shim, C.; Henze, D. K.

    2016-12-01

    Here we have used satellite retrievals to identify GHG's emissions over East Asia. With multi-year GOSAT CO2/CH4 products (2009 - 2014) and recent OCO-2 retrievals (2014 - 2015), better availability of the data enabled to show the regional/local scale (less than 1° x 1° spatial resolution) urban GHG's emissions. We identified the urban emissions from the enhanced values of xCO2/xCH4 and estimated the correlation of those signals with available GHG's emissions inventory over East Asia. Also, some of those retrievals were compared with ground/aircraft measurements to verify those remotely sensed data. Those efforts are useful to identify regional/local anthropogenic GHG's emissions over East Asia where the GHG's emissions inventories are still uncertain, which can support government policy to mitigate air pollution. In addition, we introduce our efforts to constrain the emissions of CO2 from GOSAT/OCO-2 data using 4-Dvar inverse modeling framework and we show some preliminary results. This study represents the current progress to understand sub-continental scale atmospheric CO2 variabilities and its emissions with recent satellite retrievals and advanced modeling.

  18. Planck pre-launch status: The optical system

    DEFF Research Database (Denmark)

    Tauber, J. A.; Nørgaard-Nielsen, Hans Ulrik; Ade, P. A. R.

    2010-01-01

    Planck is a scientific satellite that represents the next milestone in space-based research related to the cosmic microwave background, and in many other astrophysical fields. Planck was launched on 14 May of 2009 and is now operational. The uncertainty in the optical response of its detectors...

  19. Planck pre-launch status: The Planck mission

    DEFF Research Database (Denmark)

    Tauber, J. A.; Mandoles, N.; Puget, J.-L.

    2010-01-01

    The European Space Agency's Planck satellite, launched on 14 May 2009, is the third-generation space experiment in the field of cosmic microwave background (CMB) research. It will image the anisotropies of the CMB over the whole sky, with unprecedented sensitivity ( ~ 2 × 10-6) and angular...

  20. Launch Services Program EMC Issues

    Science.gov (United States)

    trout, Dawn

    2004-01-01

    Presentation covers these issues: (1) Vehicles of the Launch Services Program, (2) RF Environment, (3) Common EMC Launch Vehicle Payload Integration Issues, (4) RF Sensitive Missions and (5) Lightning Monitoring,

  1. Launch Stabilisation System for Vertical Launch of a Missile

    Directory of Open Access Journals (Sweden)

    K. Sreekumar

    2005-07-01

    Full Text Available The launch platform stabilisation control system is a roll-pitch stabilised platform for the vertical launch of a missile from a naval ship. Stabilisation of the launch platform is achievedwith the help of embedded controllers and electro-hydraulic servo control system. The launch platform is stabilised wrt true horizontal with a 2-axis (roll and pitch stabilisation systemconsisting of a gimbal and a set of three high-pressure servo hydraulic actuators. The control system uses rate gyro and tilt sensor feedbacks for stabilising the platform. This paper outlines the details of the launch platform stabilisation control system, results of digital simulation, and the performance during sea trials.

  2. Expendable launch vehicle studies

    Science.gov (United States)

    Bainum, Peter M.; Reiss, Robert

    1995-01-01

    Analytical support studies of expendable launch vehicles concentrate on the stability of the dynamics during launch especially during or near the region of maximum dynamic pressure. The in-plane dynamic equations of a generic launch vehicle with multiple flexible bending and fuel sloshing modes are developed and linearized. The information from LeRC about the grids, masses, and modes is incorporated into the model. The eigenvalues of the plant are analyzed for several modeling factors: utilizing diagonal mass matrix, uniform beam assumption, inclusion of aerodynamics, and the interaction between the aerodynamics and the flexible bending motion. Preliminary PID, LQR, and LQG control designs with sensor and actuator dynamics for this system and simulations are also conducted. The initial analysis for comparison of PD (proportional-derivative) and full state feedback LQR Linear quadratic regulator) shows that the split weighted LQR controller has better performance than that of the PD. In order to meet both the performance and robustness requirements, the H(sub infinity) robust controller for the expendable launch vehicle is developed. The simulation indicates that both the performance and robustness of the H(sub infinity) controller are better than that for the PID and LQG controllers. The modelling and analysis support studies team has continued development of methodology, using eigensensitivity analysis, to solve three classes of discrete eigenvalue equations. In the first class, the matrix elements are non-linear functions of the eigenvector. All non-linear periodic motion can be cast in this form. Here the eigenvector is comprised of the coefficients of complete basis functions spanning the response space and the eigenvalue is the frequency. The second class of eigenvalue problems studied is the quadratic eigenvalue problem. Solutions for linear viscously damped structures or viscoelastic structures can be reduced to this form. Particular attention is paid to

  3. Launch Vehicle Control Center Architectures

    Science.gov (United States)

    Watson, Michael D.; Epps, Amy; Woodruff, Van; Vachon, Michael Jacob; Monreal, Julio; Levesque, Marl; Williams, Randall; Mclaughlin, Tom

    2014-01-01

    Launch vehicles within the international community vary greatly in their configuration and processing. Each launch site has a unique processing flow based on the specific launch vehicle configuration. Launch and flight operations are managed through a set of control centers associated with each launch site. Each launch site has a control center for launch operations; however flight operations support varies from being co-located with the launch site to being shared with the space vehicle control center. There is also a nuance of some having an engineering support center which may be co-located with either the launch or flight control center, or in a separate geographical location altogether. A survey of control center architectures is presented for various launch vehicles including the NASA Space Launch System (SLS), United Launch Alliance (ULA) Atlas V and Delta IV, and the European Space Agency (ESA) Ariane 5. Each of these control center architectures shares some similarities in basic structure while differences in functional distribution also exist. The driving functions which lead to these factors are considered and a model of control center architectures is proposed which supports these commonalities and variations.

  4. AVS on satellite

    Science.gov (United States)

    Zhao, Haiwu; Wang, Guozhong; Hou, Gang

    2005-07-01

    AVS is a new digital audio-video coding standard established by China. AVS will be used in digital TV broadcasting and next general optical disk. AVS adopted many digital audio-video coding techniques developed by Chinese company and universities in recent years, it has very low complexity compared to H.264, and AVS will charge very low royalty fee through one-step license including all AVS tools. So AVS is a good and competitive candidate for Chinese DTV and next generation optical disk. In addition, Chinese government has published a plan for satellite TV signal directly to home(DTH) and a telecommunication satellite named as SINO 2 will be launched in 2006. AVS will be also one of the best hopeful candidates of audio-video coding standard on satellite signal transmission.

  5. A High-Payload Fraction, Pump-Fed, 2-Stage Nano Launch Vehicle Project

    Data.gov (United States)

    National Aeronautics and Space Administration — Ventions proposes the development of a pump-fed, 2-stage nano launch vehicle for low-cost on-demand placement of cube and nano-satellites into LEO. The proposed...

  6. Standard Electric Interface for Payload and Launch Vehicle Enabling Secondary Rideshare Project

    Data.gov (United States)

    National Aeronautics and Space Administration — Access to space for Small Satellites is enabled by the use of excess launch capacity. An integration process that minimizes risk to the primary, allows parallel...

  7. New Product Launching Ideas

    Science.gov (United States)

    Kiruthika, E.

    2012-09-01

    Launching a new product can be a tense time for a small or large business. There are those moments when you wonder if all of the work done to develop the product will pay off in revenue, but there are many things are can do to help increase the likelihood of a successful product launch. An open-minded consumer-oriented approach is imperative in todayís diverse global marketplace so a firm can identify and serve its target market, minimize dissatisfaction, and stay ahead of competitors. Final consumers purchase for personal, family, or household use. Finally, the kind of information that the marketing team needs to provide customers in different buying situations. In high-involvement decisions, the marketer needs to provide a good deal of information about the positive consequences of buying. The sales force may need to stress the important attributes of the product, the advantages compared with the competition; and maybe even encourage ìtrialî or ìsamplingî of the product in the hope of securing the sale. The final stage is the post-purchase evaluation of the decision. It is common for customers to experience concerns after making a purchase decision. This arises from a concept that is known as ìcognitive dissonance

  8. Magnetic Launch Assist

    Science.gov (United States)

    Jacobs, W. A.

    2000-01-01

    With the ever-increasing cost of getting to space and the need for safe, reliable, and inexpensive ways to access space, NASA is taking a look at technologies that will get us there. One of these technologies is Magnetic Launch Assist (MagLev). This is the concept of using both magnetic levitation and magnetic propulsion to provide an initial velocity by using electrical power from ground sources. The use of ground based power can significantly reduce operational costs over the consumables necessary to attain the same velocity. The technologies to accomplish this are both old and new. The concept of MagLev has been around for a long time and several MagLev Trains have already been made. Where NASA's MagLev diverges from the traditional train is in the immense power required to propel this vehicle to 600 feet per second in less than 10 seconds. New technologies or the upgrade of existing technologies will need to be investigated in areas of energy storage and power switching. Plus the separation of a very large mass (the space vehicle) and the aerodynamics of that vehicle while on the carrier are also of great concern and require considerable study and testing. NASA's plan is to mature these technologies in the next 10 years to achieve our goal of launching a full sized space vehicle off a MagLev rail.

  9. Nanosatellite swarm support for larger satellites

    NARCIS (Netherlands)

    Verhoeven, Chris; Engelen, Steven; Noroozi, Arash; Bentum, Marinus Jan; Sundaramoorthy, Prem; Meijer, Robert

    2011-01-01

    Nano-satellites are small (less than 10 kg) and low cost satellites of which quite a number has been launched the last few years, mostly as university educational or research projects. The development of professional scientific and commercial applications is still in its infancy and there are only

  10. Nanosatellite swarm support for larger satellites

    NARCIS (Netherlands)

    Verhoeven, Chris; Engelen, Steven; Noroozi, Arash; Sundaramoorthy, Prem; Bentum, Mark; Meijer, Robert

    2011-01-01

    Nano-satellites are small (less than 10 kg) and low cost satellites of which quite a number has been launched the last few years, mostly as university educational or research projects. The development of professional scientific and commercial applications is still in its infancy and there are only f

  11. Advanced Communications Technology Satellite (ACTS)

    Science.gov (United States)

    Gedney, Richard T.; Schertler, Ronald J.

    1989-01-01

    The NASA Advanced Communications Technology Satellite (ACTS) was conceived to help maintain U.S. leadership in the world's communications-satellite market. This experimental satellite is expected to be launched by NASA in 1992 and to furnish the technology necessary for establishing very small aperture terminal digital networks which provide on-demand full-mesh connectivity, and 1.544-MBPS services with only a single hop. Utilizing on-board switching and processing, each individual voice or data circuit can be separately routed to any location in the network. This paper provides an overview of the ACTS and discusses the value of the technology for future communications systems.

  12. The french educational satellite arsene

    Science.gov (United States)

    Danvel, M.; Escudier, B.

    ARSENE (Ariane, Radio-amateur, Satellite pour l'ENseignement de l'Espace) is a telecommunications satellite for Amateur Space Service. Its main feature is that more than 100 students from French engineering schools and universities have been working since 1979 for definition phase and satellite development. The highest IAF awards has been obtained by "ARSENE students" in Tokyo (1980) and Rome (1981). The French space agency, CNES and French aerospace industries are supporting the program. The European Space Agency offered to place ARSENE in orbit on the first Ariane mark IV launch late 1985.

  13. Launch Decisions of Pharmaceutical Companies

    Directory of Open Access Journals (Sweden)

    Abdülkadir Civan

    2016-04-01

    Full Text Available This paper models the launch decision of pharmaceutical companies in regard to new drugs and country markets. New drugs are launched with a delay or not launched at all in many countries. Considering that many of these new drugs would have created health benefits to the patients, there seems to be welfare loss. We use market characteristics to explain this phenomenon. We show that most of the estimated launch with a delay and no-launch decision is due to observable market characteristics. The model has an accuracy of 70 percent in explaining the no-launch decision. Intellectual property rights protection is especially important. The policy implication is that stronger property rights increase the likelihood and speed of new drug launch.

  14. 14 CFR 417.111 - Launch plans.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Launch plans. 417.111 Section 417.111... TRANSPORTATION LICENSING LAUNCH SAFETY Launch Safety Responsibilities § 417.111 Launch plans. (a) General. A launch operator must implement written launch plans that define how launch processing and flight of a...

  15. Launch vehicle selection model

    Science.gov (United States)

    Montoya, Alex J.

    1990-01-01

    Over the next 50 years, humans will be heading for the Moon and Mars to build scientific bases to gain further knowledge about the universe and to develop rewarding space activities. These large scale projects will last many years and will require large amounts of mass to be delivered to Low Earth Orbit (LEO). It will take a great deal of planning to complete these missions in an efficient manner. The planning of a future Heavy Lift Launch Vehicle (HLLV) will significantly impact the overall multi-year launching cost for the vehicle fleet depending upon when the HLLV will be ready for use. It is desirable to develop a model in which many trade studies can be performed. In one sample multi-year space program analysis, the total launch vehicle cost of implementing the program reduced from 50 percent to 25 percent. This indicates how critical it is to reduce space logistics costs. A linear programming model has been developed to answer such questions. The model is now in its second phase of development, and this paper will address the capabilities of the model and its intended uses. The main emphasis over the past year was to make the model user friendly and to incorporate additional realistic constraints that are difficult to represent mathematically. We have developed a methodology in which the user has to be knowledgeable about the mission model and the requirements of the payloads. We have found a representation that will cut down the solution space of the problem by inserting some preliminary tests to eliminate some infeasible vehicle solutions. The paper will address the handling of these additional constraints and the methodology for incorporating new costing information utilizing learning curve theory. The paper will review several test cases that will explore the preferred vehicle characteristics and the preferred period of construction, i.e., within the next decade, or in the first decade of the next century. Finally, the paper will explore the interaction

  16. Satellite television analogue and digital reception techniques

    CERN Document Server

    Benoit, Herve

    1999-01-01

    Satellite television is part of the lives of millions of television viewers worldwide and its influence is set to increase significantly with the launch of digital satellite television services.This comprehensive reference book, written by the author of the highly successful 'Digital Television', provides a technical overview of both analogue and digital satellite TV. Written concisely and thoroughly, it covers all aspects of satellite TV necessary to understand its operation and installation. It also covers the evolution of satellite television, and contains a detailed glossary of tec

  17. Educational Benefits From the AAU-cubesat Student Satellite Project

    DEFF Research Database (Denmark)

    Alminde, Lars

    2003-01-01

    In September 2001 Aalborg university started the AAU-cubesat project that reached it climax when the student built satellite was launched into space on the 30th of June 2003 on top of a former Russian ICBM. AAU-cubesat was among the first five satellites to be launched that are built within......-satellite designs will be given. In addition as the project has been carried through by students then the educational value will be addressed as well....

  18. Intercomparison of XH2O Data from the GOSAT TANSO-FTS (TIR and SWIR and Ground-Based FTS Measurements: Impact of the Spatial Variability of XH2O on the Intercomparison

    Directory of Open Access Journals (Sweden)

    Hirofumi Ohyama

    2017-01-01

    Full Text Available Spatial and temporal variability of atmospheric water vapor (H2O is extremely high, and therefore it is difficult to accurately evaluate the measurement precision of H2O data by a simple comparison between the data derived from two different instruments. We determined the measurement precisions of column-averaged dry-air mole fractions of H2O (XH2O retrieved independently from spectral radiances in the thermal infrared (TIR and the short-wavelength infrared (SWIR regions measured using a Thermal And Near-infrared Sensor for carbon Observation-Fourier Transform Spectrometer (TANSO-FTS onboard the Greenhouse gases Observing SATellite (GOSAT, by an intercomparison between the two TANSO-FTS XH2O data products and the ground-based FTS XH2O data. Furthermore, the spatial variability of XH2O was also estimated in the intercomparison process. Mutually coincident XH2O data above land for the period ranging from April 2009 to May 2014 were intercompared with different spatial coincidence criteria. We found that the precisions of the TANSO-FTS TIR and TANSO-FTS SWIR XH2O were 7.3%–7.7% and 3.5%–4.5%, respectively, and that the spatial variability of XH2O was 6.7% within a radius of 50 km and 18.5% within a radius of 200 km. These results demonstrate that, in order to accurately evaluate the measurement precision of XH2O, it is necessary to set more rigorous spatial coincidence criteria or to take into account the spatial variability of XH2O as derived in the present study.

  19. 大气二氧化碳遥感反演精度检验及时空特征分析%Atmospheric Carbon Dioxide Satellite Remote Sensing Retrieval Accuracy Inspection and Spatio-temporal Characteristics Analysis

    Institute of Scientific and Technical Information of China (English)

    何茜; 余涛; 程天海; 顾行发; 谢东海; 吴俣

    2012-01-01

    distribution of CO2. As the technology of satellite remote sensing is growing rapidly, a series of satellites, launched for detecting atmospheric CO2 concentration, including SCIAMACHY, GOSAT and AIRS, have been collecting a large amount of global CO2 concentration distribution data for many years. This paper gives analyses by comparing those satellite data among themselves in some parameter indexes and conducts validation by comparing those remote sensing data to the long-term global ground-based observation records. The results indicate that, among those three CO2 satellite remote sensing products, the SCIAMACHY data is systemically slightly higher than ground-based observations and limited in coverage, the GOSAT data is predominant in stability but inferior in systematic errors which is nearly 9ppmv on average lower than ground-based data, and the AIRS data, which is better than the aforementioned two satellites in both coverage and accuracy, whose monthly global coverage is up to 90%, the average error is less than 2ppmv(0. 5%) from the ground-based observations and the correlation coefficient is greater than 0. 9, can be able to better reflect the global distributions of atmospheric CO2 concentratioa An investigation from satellite and ground-based observations shows that the global spatial distribution of CO2 concentration represent significant latitude distribution and land-sea distribution, and there is a significant seasonal variation in CO2 concentration that illustrates a peak most likely in April and a valley in August.

  20. LHCb launches new website

    CERN Multimedia

    2008-01-01

    A new public website for the LHCb experiment was launched last Friday to coincide with CERN’s Open Day weekend. Designed to provide accessible information on all aspects of the experiment, the website contains images and key facts about the LHCb detector, its design and installation and the international team behind the project. "LHCb is going to be one of the most important b-physics experiments in the world when it starts taking data later this year", explains Roger Forty, the experiment’s deputy spokesperson. "We hope the website will be a valuable resource, enabling people to learn about this fascinating area of research." The new website can be found at: http://cern.ch/lhcb-public

  1. COLD-SAT orbital experiment configured for Altas launch

    Science.gov (United States)

    Schuster, J. R.; Bennett, F. O.; Wachter, J. P.

    1990-01-01

    A study was done of the feasibility of conducting liquid hydrogen orbital storage, acquisition, and transfer experiments aboard a spacecraft launched by a commercial Atlas launch vehicle. Three hydrogen tanks are mated to a spacecraft bus that is similar to that used for three-axis-controlled satellites. The bus provides power, communications, and attitude control along with acceleration levels ranging from 10 exp -6 to 10 exp -4 g. At launch, all the liquid hydrogen is contained in the largest tank, which has an insulation system designed for both space operation and the short-term launch pad and ascent environment. This tank is much lighter and lower in cost than a vacuum-jacketed design, and is made possible by the experiment tanking options available due to the hydrogen-fueled Centaur upper stage of the Atlas I.

  2. Cibola flight experiment satellite

    Science.gov (United States)

    Davies, P.; Liddle, Doug; Paffett, John; Sweeting, Martin; Curiel, A.; Sun, Wei; Eves, Stuart

    2004-11-01

    In order to achieve an "economy of scale" with respect to payload capacity the major trend in telecommunications satellites is for larger and larger platforms. With these large platforms the level of integration between platform and payload is increasing leading to longer delivery schedules. The typical lifecycle for procurement of these large telecommunications satellites is now 3-6 years depending on the level of non-recurring engineering needed. Surrey Satellite Technology Ltd (SSTL) has designed a low-cost platform aimed at telecommunications and navigation applications. SSTL's Geostationary Minisatellite Platform (GMP) is a new entrant addressing the lower end of the market with payloads up to 250kg requiring less than 1.5 kW power. The British National Space Centre through the MOSAIC Small Satellite Initiative supported the development of GMP. The main design goals for GMP are low-cost for the complete mission including launch and operations and a platform allowing flexible payload accommodation. GMP is specifically designed to allow rapid development and deployment with schedules typically between 1 and 2 years from contract signature to flight readiness. GMP achieves these aims by a modular design where the level of integration between the platform and payload is low. The modular design decomposes the satellite into three major components - the propulsion bay, the avionics bay and the payload module. Both the propulsion and avionics bays are reusable, largely unchanged, and independent of the payload configuration. Such a design means that SSTL or a 3rd party manufacturer can manufacture the payload in parallel to the platform with integration taking place quite late in the schedule. In July 2003 SSTL signed a contract for ESA's first Galileo navigation satellite known as GSTBV2/A. The satellite is based on GMP and ESA plan to launch it into a MEO orbit late in 2005. The second flight of GMP is likely to be in 2006 carrying a geostationary payload

  3. Upgraded Radiometer Improves Observation of Meteorological Satellite

    Institute of Scientific and Technical Information of China (English)

    2004-01-01

    @@ A new meteorological satellite, Fengyun-2C,was successfully launched at 9:20 am on Oct. 19 in Xichang Satellite Launch Center in China's southwest province of Sichuan. The Fengyun-2 (or FY-2,meaning "winds and clouds" in Chinese) is a geostationary meteorological satellite series of China.China started its FY-2 development program in 1980 and has sent two experimental models of FY-2 series in 1997 and 2000 respectively. The FY2-C is China's first professional one in the series.

  4. Engineering Test Satellite VI (ETS-VI)

    Science.gov (United States)

    Horii, M.; Funakawa, K.

    1991-01-01

    The Engineering Test Satellite-VI (ETS-VI) is being developed as the third Japanese three-axis stabilized engineering test satellite to establish the 2-ton geostationary operational satellite bus system and to demonstrate the high performance satellite communication technology for future operational satellites. The satellite is expected to be stationed at 154 deg east latitude. It will be launched from the Tanegashima Space Center in Japan by a type H-II launch vehicle. The Deep Space Network (DSN) will support the prelaunch compatibility test, data interface verification testing, and launch rehersals. The DSN primary support period is from launch through the final AEF plus 1 hour. Contingency support is from final AEF plus 1 hour until launch plus 1 month. The coverage will consist of all the 26-m antennas as prime and the 34-m antennas at Madrid and Canberra as backup. Maximum support will consist of two 8-hour tracks per station for a 7-day period, plus the contingency support, if required. Information is given in tabular form for DSN support, telemetry, command, and tracking support responsibility.

  5. Educational Benefits From the AAU-cubesat Student Satellite Project

    DEFF Research Database (Denmark)

    Alminde, Lars

    2003-01-01

    In September 2001 Aalborg university started the AAU-cubesat project that reached it climax when the student built satellite was launched into space on the 30th of June 2003 on top of a former Russian ICBM. AAU-cubesat was among the first five satellites to be launched that are built within...... the cubesat concept that prescribes a satellite with dimensions 10x10x10cm and mass one kilogram. These constraints clearly limits the possibilities for the satellite in terms of possible scientific missions, but on the other hand: by building satellites of this size a technology push is created...... that in the future will help to reduce the size of both scientific and commercial satellites and thus help to drive down the launch cost. This paper will describe the overall architecture of the AAU-cubesat. Results from the operation phase will be stated, and recommendations on further work on pico-satellite...

  6. Methane cross-validation between three Fourier transform spectrometers: SCISAT ACE-FTS, GOSAT TANSO-FTS, and ground-based FTS measurements in the Canadian high Arctic

    Science.gov (United States)

    Holl, Gerrit; Walker, Kaley A.; Conway, Stephanie; Saitoh, Naoko; Boone, Chris D.; Strong, Kimberly; Drummond, James R.

    2016-05-01

    We present cross-validation of remote sensing measurements of methane profiles in the Canadian high Arctic. Accurate and precise measurements of methane are essential to understand quantitatively its role in the climate system and in global change. Here, we show a cross-validation between three data sets: two from spaceborne instruments and one from a ground-based instrument. All are Fourier transform spectrometers (FTSs). We consider the Canadian SCISAT Atmospheric Chemistry Experiment (ACE)-FTS, a solar occultation infrared spectrometer operating since 2004, and the thermal infrared band of the Japanese Greenhouse Gases Observing Satellite (GOSAT) Thermal And Near infrared Sensor for carbon Observation (TANSO)-FTS, a nadir/off-nadir scanning FTS instrument operating at solar and terrestrial infrared wavelengths, since 2009. The ground-based instrument is a Bruker 125HR Fourier transform infrared (FTIR) spectrometer, measuring mid-infrared solar absorption spectra at the Polar Environment Atmospheric Research Laboratory (PEARL) Ridge Laboratory at Eureka, Nunavut (80° N, 86° W) since 2006. For each pair of instruments, measurements are collocated within 500 km and 24 h. An additional collocation criterion based on potential vorticity values was found not to significantly affect differences between measurements. Profiles are regridded to a common vertical grid for each comparison set. To account for differing vertical resolutions, ACE-FTS measurements are smoothed to the resolution of either PEARL-FTS or TANSO-FTS, and PEARL-FTS measurements are smoothed to the TANSO-FTS resolution. Differences for each pair are examined in terms of profile and partial columns. During the period considered, the number of collocations for each pair is large enough to obtain a good sample size (from several hundred to tens of thousands depending on pair and configuration). Considering full profiles, the degrees of freedom for signal (DOFS) are between 0.2 and 0.7 for TANSO-FTS and

  7. Satellite observations of ground water changes in New Mexico

    Science.gov (United States)

    In 2002 NASA launched the Gravity Recovery and Climate Experiment (GRACE) satellite mission. GRACE consists of two satellites with a separation of about 200 km.  By accurately measuring the separation between the twin satellites, the differences in the gravity field can be determined. Monthly observ...

  8. The Advanced Stellar Compass onboard the Oersted satellite

    DEFF Research Database (Denmark)

    Jørgensen, John Leif; Eisenman, Allan R.; Liebe, Carl Christian;

    1997-01-01

    In 1997 the first Danish satellite will be launched. The primarily scientific objective of the satellite is to map the magnetic field of the Earth. The attitude of the satellite is determined by an advanced stellar compass (star tracker). An advanced stellar compass consists of a CCD camera conne...

  9. Cost Considerations of Transition toward a Disaggregated Satellite Architecture

    Science.gov (United States)

    2013-02-14

    announcement, the Air Force awarded contracts to Lockheed Martin, Orbital Sciences, and SpaceX to provide small-satellite launch services.18 SpaceX has...238M per launch.19 SpaceX advertises its Falcon 9 rockets for $54M per launch,20 almost one-tenth the latest EELV cost estimate. For small...positive impact this change would have on disaggregation costs. Switching to SpaceX launches drives down the cost of both the aggregated and disaggregated

  10. Satellite Upper Air Network (SUAN)

    Science.gov (United States)

    Reale, Tony L.; Thorne, Peter

    2004-10-01

    During the past 20 years of NOAA operational polar satellites, it has become evident that a growing problem concerning their utilization in Climate and also Numerical Weather Prediction (NWP) applications are the systematic errors and uncertainties inherent in the satellite measurements. Similar arguments can be made for global radiosonde observations. These uncertainties are often larger than the sensitive signals and processes, that satellite and radiosonde measurements are designed to reveal, particularly in the realm of climate. Possible strategies to quantify and compensate for these problems include the analysis of satellite overlap data and/or available collocations of satellite and ground truth (radiosonde) observations. However, overlap observations are typically not available except in extreme polar regions and current sampling strategies for compiling collocated radiosonde and satellite observations are insufficient, further compounding the inherent uncertainties in the ground-truth radiosonde data. A Satellite Upper Air Network is proposed to provide reference radiosonde launches coincident with operational polar satellite(s) overpass. The SUAN consist of 36 global radiosonde stations sub-sampled from the Global Upper Air Network (GUAN), and is designed to provide a robust, global sample of collocated radiosonde and satellite observations conducive to the monitoring and validation of satellite and radiosonde observations. The routine operation of such a network in conjunction with operational polar satellites would provide a long-term of performance for critical observations of particular importance for climate. The following report presents a candidate network of 36 upper-air sites that could comprise a SUAN. Their selection along with the mutual benefit across the satellite, radiosonde, climate, numerical weather prediction (NWP) and radiative transfer (RT) model areas are discussed.

  11. Peer Review of Launch Environments

    Science.gov (United States)

    Wilson, Timmy R.

    2011-01-01

    Catastrophic failures of launch vehicles during launch and ascent are currently modeled using equivalent trinitrotoluene (TNT) estimates. This approach tends to over-predict the blast effect with subsequent impact to launch vehicle and crew escape requirements. Bangham Engineering, located in Huntsville, Alabama, assembled a less-conservative model based on historical failure and test data coupled with physical models and estimates. This white paper summarizes NESC's peer review of the Bangham analytical work completed to date.

  12. Tactical Satellite 3

    Science.gov (United States)

    Davis, T. M.; Straight, S. D.; Lockwook, R. B.

    2008-08-01

    Tactical Satellite 3 is an Air Force Research Laboratory Science and Technology (S&T) initiative that explores the capability and technological maturity of small, low-cost satellites. It features a low cost "plug and play" modular bus and low cost militarily significant payloads - a Raytheon developed Hyperspectral imager and secondary payload data exfiltration provided by the Office of Naval Research. In addition to providing for ongoing innovation and demonstration in this important technology area, these S&T efforts also help mitigate technology risk and establish a potential concept of operations for future acquisitions. The key objectives are rapid launch and on-orbit checkout, theater commanding, and near-real time theater data integration. It will also feature a rapid development of the space vehicle and integrated payload and spacecraft bus by using components and processes developed by the satellite modular bus initiative. Planned for a late summer 2008 launch, the TacSat-3 spacecraft will collect and process images and then downlink processed data using a Common Data Link. An in-theater tactical ground station will have the capability to uplink tasking to spacecraft and will receive full data image. An international program, the United Kingdom Defence Science and Technology Laboratory (DSTL) and Australian Defence Science and Technology Organisation (DSTO) plan to participate in TacSat-3 experiments.

  13. Urban poor program launched.

    Science.gov (United States)

    1991-01-01

    The government of the Philippines has launched a program to deal with the rapidly growing urban poor population. 60 cities (including Metro Manila) are expected to increase their bloated population by 3.8% over 1990 which would be 27.7 million for 1991. Currently there is an exodus of people from the rural areas and by 2000 half the urban population will be squatters and slum dwellers. Basic services like health and nutrition are not expected to be able to handle this type of volume without a loss in the quality of service. The basic strategy of the new program is to recruit private medical practitioners to fortify the health care delivery and nutrition services. Currently the doctor/urban dweller ration is 1:9000. The program will develop a system to pool the efforts of government and private physicians in servicing the target population. Barangay Escopa has been chosen as the pilot city because it typifies the conditions of a highly populated urban area. The projects has 2 objectives: 1) demonstrate the systematic delivery of health and nutrition services by the private sector through the coordination of the government, 2) reduce mortality and morbidity in the community, especially in the 0-6 age group as well as pregnant women and lactating mothers.

  14. Launch Support Video Site

    Science.gov (United States)

    OFarrell, Zachary L.

    2013-01-01

    The goal of this project is to create a website that displays video, countdown clock, and event times to customers during launches, without needing to be connected to the internal operations network. The requirements of this project are to also minimize the delay in the clock and events to be less than two seconds. The two parts of this are the webpage, which will display the data and videos to the user, and a server to send clock and event data to the webpage. The webpage is written in HTML with CSS and JavaScript. The JavaScript is responsible for connecting to the server, receiving new clock data, and updating the webpage. JavaScript is used for this because it can send custom HTTP requests from the webpage, and provides the ability to update parts of the webpage without having to refresh the entire page. The server application will act as a relay between the operations network, and the open internet. On the operations network side, the application receives multicast packets that contain countdown clock and events data. It will then parse the data into current countdown times and events, and create a packet with that information that can be sent to webpages. The other part will accept HTTP requests from the webpage, and respond to them with current data. The server is written in C# with some C++ files used to define the structure of data packets. The videos for the webpage will be shown in an embedded player from UStream.

  15. AMS ready for launch

    CERN Multimedia

    Katarina Anthony

    2011-01-01

    On 29 April, the Alpha Magnetic Spectrometer (AMS) will complete its long expedition to the International Space Station on board the space shuttle Endeavour. The Endeavour is set to lift off from NASA’s Kennedy Space Station at 15:47 EST (21:47 CET).   Samuel Ting, principal investigator for the AMS project, and Rolf Heuer, CERN Director-General, visit the Kennedy Space Centre before the AMS launch.  Courtesy of NASA and Kennedy Space Center. AMS is a CERN recognised experiment, created by an internal collaboration of 56 institutes. It will be the first large magnetic spectrometer to be used in space, and has been designed to function as an external module on the ISS. AMS will measure cosmic rays without atmospheric interference, allowing researchers on the ground to continue their search for dark matter and antimatter in the Universe. Data collected by AMS will be analysed in CERN’s new AMS Control Centre in Building 946 (due for completion in June 2011). The End...

  16. Miniaurizable, High Performance, Fiber-Optic Gyroscopes for Small Satellites Project

    Data.gov (United States)

    National Aeronautics and Space Administration — Small satellites require much lighter weight, smaller, and long life Attitude control components that can withstand stressing launch conditions and space vibration...

  17. Preliminary Location Accuracy Assessments of 3rd Satellite of TH-1

    OpenAIRE

    2016-01-01

    The TH-1 satellite is the first stereo mapping transmission satellite in China, and the primary mission goal of the satellite is for topographic mapping at 1:50 000 scale and high-accuracy location without Ground Control Points (GCPs). 1st, 2nd satellites of TH-1 were launched on August 24, 2010, May 6, 2012, and 3rd satellite was launched on October 26, 2015. Now, three satellites of TH-1 are well operating on its orbit. After evaluation, the location accuracy of 1st satellite without GCPs i...

  18. LM-3A Launch Vehicle

    Institute of Scientific and Technical Information of China (English)

    RenShufang

    2004-01-01

    The LM-3A launch vehicle is a large three-stage liquidpropellant launch vehicle developed on the basis ot LM-3 ana LM-2C. By incorporating the mature technologies of LM-3 and adding a more powerful improved LOX/LH cryogenic third stage and more capable control system, LM-3A has a

  19. Launch Vehicle Dynamics Demonstrator Model

    Science.gov (United States)

    1963-01-01

    Launch Vehicle Dynamics Demonstrator Model. The effect of vibration on launch vehicle dynamics was studied. Conditions included three modes of instability. The film includes close up views of the simulator fuel tank with and without stability control. [Entire movie available on DVD from CASI as Doc ID 20070030984. Contact help@sti.nasa.gov

  20. The Arctic Regional Communications Small SATellite (ARCSAT)

    Science.gov (United States)

    Casas, Joseph; Kress, Martin; Sims, William; Spehn, Stephen; Jaeger, Talbot; Sanders, Devon

    2013-01-01

    Traditional satellite missions are extremely complex and expensive to design, build, test, launch and operate. Consequently many complementary operational, exploration and research satellite missions are being formulated as a growing part of the future space community capabilities using formations of small, distributed, simple to launch and inexpensive highly capable small scale satellites. The Arctic Regional Communications small SATellite (ARCSAT) initiative would launch a Mini-Satellite "Mothership" into Polar or Sun Sync low-earth-orbit (LEO). Once on orbit, the Mothership would perform orbital insertion of four internally stored independently maneuverable nanosatellites, each containing electronically steerable antennas and reconfigurable software-defined radios. Unlike the traditional geostationary larger complex satellite communication systems, this LEO communications system will be comprised of initially a five small satellite formation that can be later incrementally increased in the total number of satellites for additional data coverage. ARCSAT will provide significant enabling capabilities in the Arctic for autonomous voice and data communications relay, Maritime Domain Awareness (MDA), data-extraction from unattended sensors, and terrestrial Search & Rescue (SAR) beacon detection missions throughout the "data starved desert" of the Arctic Region.

  1. HETE Satellite Power Subsystem

    OpenAIRE

    1993-01-01

    The HETE (High-Energy Transient Experiment) satellite a joint project between MIT's Center for Space Research and AeroAstro. is a high-energy gamma-ray burst/X-Ray/UV observatory platform. HETE will be launched into a 550 km circular orbit with an inclination of 37.7°, and has a design lifetime of 18 months. This paper presents a description of the spacecraft's power subsystem, which collects, regulates, and distributes power to the experiment payload modules and to the various spacecraft sub...

  2. Magnetic Launch Assist Demonstration Test

    Science.gov (United States)

    2001-01-01

    This image shows a 1/9 subscale model vehicle clearing the Magnetic Launch Assist System, formerly referred to as the Magnetic Levitation (MagLev), test track during a demonstration test conducted at the Marshall Space Flight Center (MSFC). Engineers at MSFC have developed and tested Magnetic Launch Assist technologies. To launch spacecraft into orbit, a Magnetic Launch Assist System would use magnetic fields to levitate and accelerate a vehicle along a track at very high speeds. Similar to high-speed trains and roller coasters that use high-strength magnets to lift and propel a vehicle a couple of inches above a guideway, a launch-assist system would electromagnetically drive a space vehicle along the track. A full-scale, operational track would be about 1.5-miles long and capable of accelerating a vehicle to 600 mph in 9.5 seconds. This track is an advanced linear induction motor. Induction motors are common in fans, power drills, and sewing machines. Instead of spinning in a circular motion to turn a shaft or gears, a linear induction motor produces thrust in a straight line. Mounted on concrete pedestals, the track is 100-feet long, about 2-feet wide and about 1.5-feet high. The major advantages of launch assist for NASA launch vehicles is that it reduces the weight of the take-off, the landing gear, the wing size, and less propellant resulting in significant cost savings. The US Navy and the British MOD (Ministry of Defense) are planning to use magnetic launch assist for their next generation aircraft carriers as the aircraft launch system. The US Army is considering using this technology for launching target drones for anti-aircraft training.

  3. Satellite Laser Ranging Photon-Budget Calculations for a Single Satellite Cornercube Retroreflector: Attitude Control Tolerance

    Science.gov (United States)

    2015-11-01

    UNCLASSIFIED Satellite Laser Ranging Photon-Budget Calculations for a Single Satellite Cornercube Retroreflector: Attitude Control Tolerance Philip C...the SLR station, and the direction of the satellite from the SLR station. The required attitude control tolerance is to within 17◦ of the optimal... attitude control strategy determined in the present work. A pre-launch measurement of the re- flectance (diffraction) pattern of each retroreflector is

  4. The DARPA/USAF Falcon Program Small Launch Vehicles

    Science.gov (United States)

    Weeks, David J.; Walker, Steven H.; Thompson, Tim L.; Sackheim, Robert; London, John R., III

    2006-01-01

    Earlier in this decade, the U.S. Air Force Space Command and the Defense Advanced Research Projects Agency (DARPA), in recognizing the need for low-cost responsive small launch vehicles, decided to partner in addressing this national shortcoming. Later, the National Aeronautics and Space Administration (NASA) joined in supporting this effort, dubbed the Falcon Program. The objectives of the Small Launch Vehicle (SLV) element of the DARPA/USAF Falcon Program include the development of a low-cost small launch vehicle(s) that demonstrates responsive launch and has the potential for achieving a per mission cost of less than $5M when based on 20 launches per year for 10 years. This vehicle class can lift 1000 to 2000 lbm payloads to a reference low earth orbit. Responsive operations include launching the rocket within 48 hours of call up. A history of the program and the current status will be discussed with an emphasis on the potential impact on small satellites.

  5. Satellite RNAs and Satellite Viruses.

    Science.gov (United States)

    Palukaitis, Peter

    2016-03-01

    Satellite RNAs and satellite viruses are extraviral components that can affect either the pathogenicity, the accumulation, or both of their associated viruses while themselves being dependent on the associated viruses as helper viruses for their infection. Most of these satellite RNAs are noncoding RNAs, and in many cases, have been shown to alter the interaction of their helper viruses with their hosts. In only a few cases have the functions of these satellite RNAs in such interactions been studied in detail. In particular, work on the satellite RNAs of Cucumber mosaic virus and Turnip crinkle virus have provided novel insights into RNAs functioning as noncoding RNAs. These effects are described and potential roles for satellite RNAs in the processes involved in symptom intensification or attenuation are discussed. In most cases, models describing these roles involve some aspect of RNA silencing or its suppression, either directly or indirectly involving the particular satellite RNA.

  6. Commercial satellite broadcasting for Europe

    Science.gov (United States)

    Forrest, J. R.

    1988-12-01

    A review is presented of the current television broadcasting situation in European countries, which involves a varied mix of terrestrial VHF or UHF systems and cable networks. A small market has emerged in Europe for receivers using the low-power telecommunications satellite transmission between the program providers and cable network companies. This is expected to change with the launch of medium-power pan-European telecommunication satellites (e.g. ASTRA, EUTELSAT II), which are now directly addressing the market of home reception. DBS (direct broadcast satellite) in the UK, using the D-MAC transmission standard, will offer three additional television channels, data broadcasting services, and a planned evolution to compatible forms of wide-screen, high-definition television. Comments are given on receiver and conditional access system standardization. Some views are expressed on satellite broadcasting as part of an overall broadcasting framework for the future.

  7. Mobile satellite service in the United States

    Science.gov (United States)

    Agnew, Carson E.; Bhagat, Jai; Hopper, Edwin A.; Kiesling, John D.; Exner, Michael L.; Melillo, Lawrence; Noreen, Gary K.; Parrott, Billy J.

    1988-05-01

    Mobile satellite service (MSS) has been under development in the United States for more than two decades. The service will soon be provided on a commercial basis by a consortium of eight U.S. companies called the American Mobile Satellite Consortium (AMSC). AMSC will build a three-satellite MSS system that will offer superior performance, reliability and cost effectiveness for organizations requiring mobile communications across the U.S. The development and operation of MSS in North America is being coordinated with Telesat Canada and Mexico. AMSC expects NASA to provide launch services in exchange for capacity on the first AMSC satellite for MSAT-X activities and for government demonstrations.

  8. China's FY-3 Polar Orbit Meteorological Satellite And Its Applications

    Institute of Scientific and Technical Information of China (English)

    Zhang Jiashen; Fang Meng; Sun Anlai

    2009-01-01

    @@ FY-3 is China's second generation of polar orbit meteorological satellite. FY-3A,the first of the FY-3 series,was launched on May 27,2008 from Taiyuan Satellite Launeh Center. After 5 months of in-orbit test,the satellite and its ground application system were put into trial operation on November 18,2008,marking the successful technical upgrading of China's polar-orbit meteorological satellite.

  9. The Falcon I Launch Vehicle

    OpenAIRE

    Koenigsmann, Hans; Musk, Elon; Shotwell, Gwynne; Chinnery, Anne

    2004-01-01

    Falcon I is the first in a family of launch vehicles designed by Space Exploration Technologies to facilitate low cost access to space. Falcon I is a mostly reusable, two stage, liquid oxygen and kerosene powered launch vehicle. The vehicle is designed above all for high reliability, followed by low cost and a benign flight environment. Launched from Vandenberg, a standard Falcon I can carry over 1000 lbs to sun-synchronous orbit and 1500 lbs due east to 100 NM. To minimize failure modes, the...

  10. Centriolar satellites

    DEFF Research Database (Denmark)

    Tollenaere, Maxim A X; Mailand, Niels; Bekker-Jensen, Simon

    2015-01-01

    Centriolar satellites are small, microscopically visible granules that cluster around centrosomes. These structures, which contain numerous proteins directly involved in centrosome maintenance, ciliogenesis, and neurogenesis, have traditionally been viewed as vehicles for protein trafficking...... highlight newly discovered regulatory mechanisms targeting centriolar satellites and their functional status, and we discuss how defects in centriolar satellite components are intimately linked to a wide spectrum of human diseases....

  11. Atlas V Launch Incorporated NASA Glenn Thermal Barrier

    Science.gov (United States)

    Dunlap, Patrick H., Jr.; Steinetz, Bruce M.

    2004-01-01

    In the Spring of 2002, Aerojet experienced a major failure during a qualification test of the solid rocket motor that they were developing for the Atlas V Enhanced Expendable Launch Vehicle. In that test, hot combustion gas reached the O-rings in the nozzle-to-case joint and caused a structural failure that resulted in loss of the nozzle and aft dome sections of the motor. To improve the design of this joint, Aerojet decided to incorporate three braided carbon-fiber thermal barriers developed at the NASA Glenn Research Center. The thermal barriers were used to block the searing-hot 5500 F pressurized gases from reaching the temperature-sensitive O-rings that seal the joint. Glenn originally developed the thermal barriers for the nozzle joints of the space shuttle solid rocket motors, and Aerojet decided to use them on the basis of the results of several successful ground tests of the thermal barriers in the shuttle rockets. Aerojet undertook an aggressive schedule to redesign the rocket nozzle-to-case joint with the thermal barriers and to qualify it in time for a launch planned for the middle of 2003. They performed two successful qualification tests (Oct. and Dec. 2002) in which the Glenn thermal barriers effectively protected the O-rings. These qualification tests saved hundreds of thousands of dollars in development costs and put the Lockheed-Martin/Aerojet team back on schedule. On July 17, 2003, the first flight of an Atlas V boosted with solid rocket motors successfully launched a commercial satellite into orbit from Cape Canaveral Air Force Station. Aero-jet's two 67-ft solid rocket boosters performed flawlessly, with each providing thrust in excess of 250,000 lbf. Both motors incorporated three Glenn-developed thermal barriers in their nozzle-to-case joints. The Cablevision satellite launched on this mission will be used to provide direct-to-home satellite television programming for the U.S. market starting in late 2003. The Atlas V is a product of the

  12. STS-70 Launch - Nikon E-2 Digital Image

    Science.gov (United States)

    1995-01-01

    This test images was taken with a Nikon E-2 Digital Imaging System camera and are provided courtesy of Nikon (GIF 450x450 JPEG 1280x1000): The second Shuttle launch in 16 days hurtles off the pad into a sweltering summer sky. The unstable weather typical to Florida in the summertime didn't have a chance to coalesce and impact this morning's launch window, and the Space Shuttle Discovery began its planned seven-day, 22-hour flight on Mission STS-70 from Launch Pad 39B at 9:41:55.078 a.m. EDT, just seconds off schedule. On board for Discovery's 21st spaceflight are a crew of five: Commander Terence 'Tom' Henricks; Pilot Kevin R. Kregel; and Mission Specialists Nancy Jane Currie, Donald A. Thomas and Mary Ellen Weber. The crew's primary objective during the 70th Shuttle flight is to deploy the Tracking and Data Relay Satellite (TDRS-G), which will join a constellation of other TDRS spacecraft already on orbit. TDRS-G is destined to become an on- orbit, fully operational 'ready reserve' satellite, available along with one other ready reserve TDRS spacecraft to back up the two primary TDRS satellites positions, TDRS East over the Atlantic Ocean and TDRS West over the Pacific. Assured capability of the TDRS communications network is essential for linking Earth-orbiting spacecraft such as the Shuttle and the Hubble Space Telescope with the ground.

  13. Satellite theory

    Science.gov (United States)

    Kozai, Y.

    1981-04-01

    The dynamical characteristics of the natural satellite of Mars, Jupiter, Saturn, Uranus and Neptune are analyzed on the basis of the solar tidal perturbation factor and the oblateness factor of the primary planet for each satellite. For the inner satellites, for which the value of the solar tidal factor is much smaller than the planetary oblateness factor, it is shown that the eccentricity and inclination of satellite orbits are generally very small and almost constant; several pairs of inner satellites are also found to exhibit commensurable mean motions, or secular accelerations in mean longitude. In the case of the outer satellites, for which solar perturbations are dominant, secular perturbations and long-period perturbations may be derived by the solution of equations of motion reduced to one degree of freedom. The existence of a few satellites, termed intermediary satellites, for which the solar tidal perturbation is on the order of the planetary oblateness factor, is also observed, and the pole of the orbital plane of the satellite is noted to execute a complex motion around the pole of the planet or the orbital plane of the planet.

  14. Hewitt launches Research Councils UK

    CERN Multimedia

    2002-01-01

    "Trade and Industry Secretary Patricia Hewitt today launched 'Research Councils UK' - a new strategic partnership that will champion research in science, engineering and technology across the UK" (1 page).

  15. Persistant Launch Range Surveillance Project

    Data.gov (United States)

    National Aeronautics and Space Administration — Launch site infrastructure and space vehicle assets represent multi-billion dollar investments that must be protected. Additionally, personnel and equipment must be...

  16. Communication Satellites 1958 to 1986

    Science.gov (United States)

    1984-10-01

    effort that is still advancing the state of the art . 2-1 3. EXPERIMENTAL SATELLITES Although the performance of communication satellites could be...bandwidths was much beyond the state of the art . The choice of the Delta launch vehicle provided basic design constraints such as size, weight, and... Griego M6/215 A. S. Gilcrest M4/958 T. J. Carr M5/699 C. H. Bredall M5/690 J. B. Bryson M5/669 R. L. Porter M5/692 T. M. Bedbury M5/669 R. D. Smith

  17. The Cosmic Background Explorer Satellite

    Science.gov (United States)

    Mather, J.; Kelsall, T.

    1980-01-01

    The Cosmic Background Explorer (COBE) satellite, planned for launch in 1985, will measure the diffuse infrared and microwave radiation of the universe over the entire wavelength range from a few microns to 1.3 cm. It will include three instruments: a set of microwave isotropy radiometers at 23, 31, 53, and 90 GHz, an interferometer spectrometer from 1 to 100/cm, and a filter photometer from 1 to 300 microns. The COBE satellite is designed to reach the sensitivity limits set by foreground sources such as the interstellar and interplanetary dust, starlight, and galactic synchrotron radiation, so that a diffuse residual radiation may be interpreted unambiguously as extragalactic

  18. Advanced Communications Technology Satellite (ACTS)

    Science.gov (United States)

    Olmstead, Dean A.; Schertler, Ronald J.

    The benefits that will be offered by the NASA-sponsored communication spacecraft ACTS which is scheduled for launch in 1992 are described together with examples of demonstrations on proposed data, video, and voice applications supported by the advanced ACTS technologies. Compared to existing satellite service, the ACTS will provide lower cost, better service, greater convenience, and improved service reliability of telecommunications to customers around the world. In addition, the pioneering ACTS technology will provide many capabilities qualitatively different from those of current satellite systems, such as on-demand assignment, frequency reuse, and the flexible targeting of spot beams directly to the very-small-aperture terminals at customer premises.

  19. Mobile satellite communications for consumers

    Science.gov (United States)

    Noreen, Gary K.

    1991-11-01

    The RadioSat system based on MSAT satellites and scheduled for launch in 1994 is described. The RadioSat system will provide integrated communications and navigation services to consumers, including nationwide digital audio broadcasts, data broadcasts, precision navigation, and two-way voice and data communications. Particular attention is given to the MSAT satellite system capabilities and economics. It is concluded that the RadioSat system will be capable of providing a low-cost, highly flexible two-way communications for consumers that can be adapted to various applications.

  20. Magnetic Launch Assist Experimental Track

    Science.gov (United States)

    1999-01-01

    In this photograph, a futuristic spacecraft model sits atop a carrier on the Magnetic Launch Assist System, formerly known as the Magnetic Levitation (MagLev) System, experimental track at the Marshall Space Flight Center (MSFC). Engineers at MSFC have developed and tested Magnetic Launch Assist technologies that would use magnetic fields to levitate and accelerate a vehicle along a track at very high speeds. Similar to high-speed trains and roller coasters that use high-strength magnets to lift and propel a vehicle a couple of inches above a guideway, a Magnetic Launch Assist system would electromagnetically drive a space vehicle along the track. A full-scale, operational track would be about 1.5-miles long and capable of accelerating a vehicle to 600 mph in 9.5 seconds. This track is an advanced linear induction motor. Induction motors are common in fans, power drills, and sewing machines. Instead of spinning in a circular motion to turn a shaft or gears, a linear induction motor produces thrust in a straight line. Mounted on concrete pedestals, the track is 100-feet long, about 2-feet wide, and about 1.5-feet high. The major advantages of launch assist for NASA launch vehicles is that it reduces the weight of the take-off, the landing gear, the wing size, and less propellant resulting in significant cost savings. The US Navy and the British MOD (Ministry of Defense) are planning to use magnetic launch assist for their next generation aircraft carriers as the aircraft launch system. The US Army is considering using this technology for launching target drones for anti-aircraft training.

  1. STS-53 Launch and Landing

    Science.gov (United States)

    1992-01-01

    Footage of various stages of the STS-53 Discovery launch is shown, including shots of the crew at breakfast, getting suited up, and departing to board the Orbiter. The launch is seen from many vantage points, as is the landing. On-orbit activities show the crew performing several medical experiments, such as taking a picture of the retina and measuring the pressure on the eyeball. One crewmember demonstrates how to use the rowing machine in an antigravity environment.

  2. NASA's Space Launch System: Momentum Builds Towards First Launch

    Science.gov (United States)

    May, Todd; Lyles, Garry

    2014-01-01

    NASA's Space Launch System (SLS) is gaining momentum programmatically and technically toward the first launch of a new exploration-class heavy lift launch vehicle for international exploration and science initiatives. The SLS comprises an architecture that begins with a vehicle capable of launching 70 metric tons (t) into low Earth orbit. Its first mission will be the launch of the Orion Multi-Purpose Crew Vehicle (MPCV) on its first autonomous flight beyond the Moon and back. SLS will also launch the first Orion crewed flight in 2021. SLS can evolve to a 130-t lift capability and serve as a baseline for numerous robotic and human missions ranging from a Mars sample return to delivering the first astronauts to explore another planet. Managed by NASA's Marshall Space Flight Center, the SLS Program formally transitioned from the formulation phase to implementation with the successful completion of the rigorous Key Decision Point C review in 2014. At KDP-C, the Agency Planning Management Council determines the readiness of a program to go to the next life-cycle phase and makes technical, cost, and schedule commitments to its external stakeholders. As a result, the Agency authorized the Program to move forward to Critical Design Review, scheduled for 2015, and a launch readiness date of November 2018. Every SLS element is currently in testing or test preparations. The Program shipped its first flight hardware in 2014 in preparation for Orion's Exploration Flight Test-1 (EFT-1) launch on a Delta IV Heavy rocket in December, a significant first step toward human journeys into deep space. Accomplishments during 2014 included manufacture of Core Stage test articles and preparations for qualification testing the Solid Rocket Boosters and the RS-25 Core Stage engines. SLS was conceived with the goals of safety, affordability, and sustainability, while also providing unprecedented capability for human exploration and scientific discovery beyond Earth orbit. In an environment

  3. An SDR based AIS receiver for satellites

    DEFF Research Database (Denmark)

    Larsen, Jesper Abildgaard; Mortensen, Hans Peter; Nielsen, Jens Frederik Dalsgaard

    2011-01-01

    For a few years now, there has been a high interest in monitoring the global ship traffic from space. A few satellite, capable of listening for ship borne AIS transponders have already been launched, and soon the AAUSAT3, carrying two different types of AIS receivers will also be launched. One...... of the AIS receivers onboard AAUSAT3 is an SDR based AIS receiver. This paper serves to describe the background of the AIS system, and how the SDR based receiver has been integrated into the AAUSAT3 satellite. Amongst some of the benefits of using an SDR based receiver is, that due to its versatility, new...

  4. New global observations of the terrestrial carbon cycle from GOSAT: Patterns of vegetation fluorescence with gross primary productivity

    Science.gov (United States)

    Frankenberg, C.; Fisher, J. B.; Lee, J.; Guanter, L.; Van der Tol, C.; Toon, G. C.; kuze, A.; Yokota, T.; Badgley, G. M.; Butz, A.; Jung, M.; Saatchi, S. S.; Worden, J.

    2011-12-01

    Our ability to close the Earth's carbon budget and predict feedbacks in a warming climate depends critically on knowing where, when and how carbon dioxide is exchanged between the land and atmosphere. Terrestrial gross primary production (GPP) constitutes the largest flux component in the global carbon budget, however significant uncertainties remain in GPP estimates and its seasonality. Solar-induced chlorophyll fluorescence is a powerful proxy for assessing biomass photosynthetic activity since photosynthesis and fluorescence are directly coupled processes. This gives rise to re-emission of light between approximately 670 and 780 nm. Passive methods to quantify the fluorescence signal are mainly based on the filling-in of highly saturated O2 absorption structures. This method, however, was mostly applied in field-based measurements and is not directly applicable to space-borne retrievals. We show that variability of aerosols in the atmosphere load and surface pressure cannot be unequivocally disentangled from fluorescence since all these factor impact the absorption depths of O2 lines. This gives rise to biases in the retrieved scattering properties in typical multi-spectral XCO2 retrievals when using the O2 A band but not when focussing solely of solar Fraunhofer lines. We will a) present our retrieval method based on an iterative, non-linear least-squares fitting of Fraunhofer lines, b) discuss the potential impact on XCO2 retrievals and c) show recent fluorescence results from more than one year of GOSAT data. Empirically, we show that global spaceborne observations of solar induced chlorophyll fluorescence exhibit a strong linear correlation with GPP. We found that the fluorescence emission even without any additional meteorological, vegetation type or model information has the same or better predictive skill in estimating GPP as those derived from traditional remotely-sensed vegetation indices using ancillary data and model assumptions. Our results

  5. Further evaluation of wetland emission estimates from the JULES land surface model using SCIAMACHY and GOSAT atmospheric column methane measurements

    Science.gov (United States)

    Hayman, Garry; Comyn-Platt, Edward; McNorton, Joey; Chipperfield, Martyn; Gedney, Nicola

    2016-04-01

    The atmospheric concentration of methane began rising again in 2007 after a period of near-zero growth [1,2], with the largest increases observed over polar northern latitudes and the Southern Hemisphere in 2007 and in the tropics since then. The observed inter-annual variability in atmospheric methane concentrations and the associated changes in growth rates have variously been attributed to changes in different methane sources and sinks [2,3]. Wetlands are generally accepted as being the largest, but least well quantified, single natural source of CH4, with global emission estimates ranging from 142-284 Tg yr-1 [3]. The modelling of wetlands and their associated emissions of CH4 has become the subject of much current interest [4]. We have previously used the HadGEM2 chemistry-climate model to evaluate the wetland emission estimates derived using the UK community land surface model (JULES, the Joint UK Land Earth Simulator) against atmospheric observations of methane, including SCIAMACHY total methane columns [5] up to 2007. We have undertaken a series of new HadGEM2 runs using new JULES emission estimates extended in time to the end of 2012, thereby allowing comparison with both SCIAMACHY and GOSAT atmospheric column methane measurements. We will describe the results of these runs and the implications for methane wetland emissions. References [1] Rigby, M., et al.: Renewed growth of atmospheric methane. Geophys. Res. Lett., 35, L22805, 2008; [2] Nisbet, E.G., et al.: Methane on the Rise-Again, Science 343, 493, 2014; [3] Kirschke, S., et al.,: Three decades of global methane sources and sinks, Nature Geosciences, 6, 813-823, 2013; [4] Melton, J. R., et al.: Present state of global wetland extent and wetland methane modelling: conclusions from a model inter-comparison project (WETCHIMP), Biogeosciences, 10, 753-788, 2013; [5] Hayman, G.D., et al.: Comparison of the HadGEM2 climate-chemistry model against in situ and SCIAMACHY atmospheric methane data, Atmos. Chem

  6. Spatio-temporal approach to moving window block kriging of satellite data v1.0

    Science.gov (United States)

    Tadić, Jovan M.; Qiu, Xuemei; Miller, Scot; Michalak, Anna M.

    2017-02-01

    Numerous existing satellites observe physical or environmental properties of the Earth system. Many of these satellites provide global-scale observations, but these observations are often sparse and noisy. By contrast, contiguous, global maps are often most useful to the scientific community (i.e., Level 3 products). We develop a spatio-temporal moving window block kriging method to create contiguous maps from sparse and/or noisy satellite observations. This approach exhibits several advantages over existing methods: (1) it allows for flexibility in setting the spatial resolution of the Level 3 map, (2) it is applicable to observations with variable density, (3) it produces a rigorous uncertainty estimate, (4) it exploits both spatial and temporal correlations in the data, and (5) it facilitates estimation in real time. Moreover, this approach only requires the assumption that the observable quantity exhibits spatial and temporal correlations that are inferable from the data. We test this method by creating Level 3 products from satellite observations of CO2 (XCO2) from the Greenhouse Gases Observing Satellite (GOSAT), CH4 (XCH4) from the Infrared Atmospheric Sounding Interferometer (IASI) and solar-induced chlorophyll fluorescence (SIF) from the Global Ozone Monitoring Experiment-2 (GOME-2). We evaluate and analyze the difference in performance of spatio-temporal vs. recently developed spatial kriging methods.

  7. The AAU-cubesat Student Satellite Project: Architectual Overview and Lessons Learnt

    DEFF Research Database (Denmark)

    Østergaard, Kasper Zinck; Alminde, Lars; Bisgaard, Morten

    2004-01-01

    In September 2001 Aalborg university started the AAU-cubesat project that reached its climax when the student built satellite was launched into space on the 30th of June 2003 on top of a former Russian ICBM. AAU-cubesat was among the first five satellites to be launched that are built within the ...

  8. The AAU-cubesat Student Satellite Project: Architectual Overview and Lessons Learnt

    DEFF Research Database (Denmark)

    Østergaard, Kasper Zinck; Alminde, Lars; Bisgaard, Morten

    In September 2001 Aalborg university started the AAU-cubesat project that reached its climax when the student built satellite was launched into space on the 30th of June 2003 on top of a former Russian ICBM. AAU-cubesat was among the first five satellites to be launched that are built within the ...

  9. Chinese Satellites Serve Beijing Olympic Games

    Institute of Scientific and Technical Information of China (English)

    Ren Shufang

    2008-01-01

    @@ METEOROLOGICAL SATELLITES PROVIDING WEATHER SERVICES As the opening and closing ceremonies and many competition events such as athletics, football, cycling and sailing etc., were held in open air stadiums, field or on water, it was of great importance to provide exact weather forecasts and on-time climate information to prepare for disastrous weather so as to ensure the Olympic Games proceeded smoothly. For this purpose, China launched the meteorological satellite service project in 2002 to safeguard the 2008 Beijing Olympic Games.

  10. UNESCOsat: The United Nations’ First Satellite

    OpenAIRE

    Platt, Donald

    2010-01-01

    An international effort is underway to produce the first satellite in the history of the United Nations. The idea of the preparation and launch, with the endorsement of the UNESCO branch of the United Nations, of an international satellite to promote science education, public awareness of science, and international co-operation in the basic sciences, was presented by the National Commission of the Russian Federation for UNESCO to the UNESCO basic sciences committee. The General Conference of ...

  11. Satellite Communications

    CERN Document Server

    Pelton, Joseph N

    2012-01-01

    The field of satellite communications represents the world's largest space industry. Those who are interested in space need to understand the fundamentals of satellite communications, its technology, operation, business, economic, and regulatory aspects. This book explains all this along with key insights into the field's future growth trends and current strategic challenges. Fundamentals of Satellite Communications is a concise book that gives all of the key facts and figures as well as a strategic view of where this dynamic industry is going. Author Joseph N. Pelton, PhD, former Dean of the International Space University and former Director of Strategic Policy at Intelstat, presents a r

  12. Space Launch System Spacecraft and Payload Elements: Making Progress Toward First Launch

    Science.gov (United States)

    Schorr, Andrew A.; Creech, Stephen D.

    2016-01-01

    tool is producing tanks for the SLS core stage. This paper will particularly focus on work taking place at Marshall Space Flight Center (MSFC) and United Launch Alliance in Alabama, where upper stage and adapter elements of the vehicle are being constructed and tested. Providing the Orion crew capsule/launch vehicle interface and in-space propulsion via a cryogenic upper stage, the Spacecraft/Payload Integration and Evolution (SPIE) Element serves a key role in achieving SLS goals and objectives. The SPIE element marked a major milestone in 2014 with the first flight of original SLS hardware, the Orion Stage Adapter (OSA) which was used on Exploration Flight Test-1 with a design that will be used again on EM-1. Construction is already underway on the EM-1 Interim Cryogenic Propulsion Stage (ICPS), an in-space stage derived from the Delta Cryogenic Second Stage. Manufacture of the Orion Stage Adapter and the Launch Vehicle Stage Adapter is set to begin at the Friction Stir Facility located at MSFC while structural test articles are either completed (OSA) or nearing completion (Launch Vehicle Stage Adapter). An overview is provided of the launch vehicle capabilities, with a specific focus on SPIE Element qualification/testing progress, as well as efforts to provide access to deep space regions currently not available to the science community through a secondary payload capability utilizing CubeSat-class satellites.

  13. Canadian Space Launch: Exploiting Northern Latitudes For Efficient Space Launch

    Science.gov (United States)

    2015-04-01

    facility and therefore has some basic infrastructure in place. It housed 4,500 personnel and launched over 3,500 sub-orbital flights.49 While the... Melbourne , FL. http://www.spaceops2012.org/ proceedings/documents/id1295313- Paper-002.pdf (accessed 10 Mar 2015). Winters, Nathan J. “Enabling the

  14. Multi-mission Satellite Management

    Science.gov (United States)

    Jamilkowski, M. L.; Teter, M. A.; Grant, K. D.; Dougherty, B.; Cochran, S.

    2015-12-01

    NOAA's next-generation environmental satellite, the Joint Polar Satellite System (JPSS) replaces the current Polar-orbiting Operational Environmental Satellites (POES). JPSS satellites carry sensors which collect meteorological, oceanographic, climatological, and solar-geophysical observations of the earth, atmosphere, and space. The first JPSS satellite was launched in 2011 and is currently NOAA's primary operational polar satellite. The JPSS ground system is the Common Ground System (CGS), and provides command, control, and communications (C3) and data processing (DP). A multi-mission system, CGS provides combinations of C3/DP for numerous NASA, NOAA, DoD, and international missions. In preparation for the next JPSS satellite, CGS improved its multi-mission capabilities to enhance mission operations for larger constellations of earth observing satellites with the added benefit of streamlining mission operations for other NOAA missions. CGS's multi-mission capabilities allows management all of assets as a single enterprise, more efficiently using ground resources and personnel and consolidating multiple ground systems into one. Sophisticated scheduling algorithms compare mission priorities and constraints across all ground stations, creating an enterprise schedule optimized to mission needs, which CGS executes to acquire the satellite link, uplink commands, downlink and route data to the operations and data processing facilities, and generate the final products for delivery to downstream users. This paper will illustrate the CGS's ability to manage multiple, enterprise-wide polar orbiting missions by demonstrating resource modeling and tasking, production of enterprise contact schedules for NOAA's Fairbanks ground station (using both standing and ad hoc requests), deconflicting resources due to ground outages, and updating resource allocations through dynamic priority definitions.

  15. Satellite Geomagnetism

    DEFF Research Database (Denmark)

    Olsen, Nils; Stolle, Claudia

    2012-01-01

    Observations of Earth’s magnetic field from space began more than 50 years ago. A continuous monitoring of the field using low Earth orbit (LEO) satellites, however, started only in 1999, and three satellites have taken highprecision measurements of the geomagnetic field during the past decade...... ability to characterize and understand the many sources that contribute to Earth’s magnetic field. In this review, we summarize investigations of Earth’s interior and environment that have been possible through the analysis of high-precision magnetic field observations taken by LEO satellites........ The unprecedented time-space coverage of their data opened revolutionary new possibilities for monitoring, understanding, and exploring Earth’s magnetic field. In the near future, the three-satellite constellation Swarm will ensure continuity of such measurement and provide enhanced possibilities to improve our...

  16. HJ-1A And HJ-1B Small Satellite Constellation For Environment And Disaster Monitoring

    Institute of Scientific and Technical Information of China (English)

    Bai Zhaoguang

    2009-01-01

    @@ HJ-1A and HJ-1B small satellites were launched atop a LM-2C/SMA on September 6, 2008 from Taiyuan Satellite Launch Center. The satellites began to transmit back images from September 8 and the constellation formed on October 13. After 5 months of orbit testing and operationevaluation, China's first optical satelliteconstellation passed its performancereview and was delivered to the Ministryof Civil Affairs and the Ministry ofEnvironmental Protection by ChinaAerospace Science and Technology Corporation and China Satellite Launch6 Tracking Control General.

  17. Satellite (Natural)

    Science.gov (United States)

    Murdin, P.

    2000-11-01

    In its most general sense, any celestial object in orbit around a similar larger object. Thus, for example, the Magellanic Clouds are satellite galaxies of our own Milky Way galaxy. Without qualification, the term is used to mean a body in orbit around a planet; an alternative term is moon. The term natural satellite distinguishes these bodies from artificial satellites—spacecraft placed in orbi...

  18. ERTS-A satellite imagery

    Science.gov (United States)

    Colvocoresses, Alden P.

    1970-01-01

    The first satellite designed to survey the Earth's resources is scheduled to be launched in 1972. This satellite, known as ERTS-A, will telemeter frames of imagery each covering 100-nautical-mile squares of the Earth. Except for the internal anomalies in the sensor system, the imagery, after being properly scaled, rectified, and controlled, may be considered an orthographic view of the Earth and used as a planimetric photomap. The accuracy of this photomap will be limited, principally by the geometric fidelity of the sensor system rather than by external effects, such as relief displacement, which restrict the direct cartographic use of the conventional aerial photograph. ERST-A is not designed as a topographic mapping satellite but does have real potential' for thematic mapping particularly in areas now covered by topographic maps.

  19. Landsat—Earth observation satellites

    Science.gov (United States)

    ,

    2015-11-25

    Since 1972, Landsat satellites have continuously acquired space-based images of the Earth’s land surface, providing data that serve as valuable resources for land use/land change research. The data are useful to a number of applications including forestry, agriculture, geology, regional planning, and education. Landsat is a joint effort of the U.S. Geological Survey (USGS) and the National Aeronautics and Space Administration (NASA). NASA develops remote sensing instruments and the spacecraft, then launches and validates the performance of the instruments and satellites. The USGS then assumes ownership and operation of the satellites, in addition to managing all ground reception, data archiving, product generation, and data distribution. The result of this program is an unprecedented continuing record of natural and human-induced changes on the global landscape.

  20. A preliminary study on dead geostationary satellite removal

    Institute of Scientific and Technical Information of China (English)

    2010-01-01

    The collision between satellites IRIDIUM 33 and COSMOS 2251 indicated that the clash of two on-orbit satellites was becoming an inevitable reality. Our calculation with the two-line orbit element by NORAD showed that some two geostationary satellites had approached very close in July 2009. Therefore, more attention should be given to avoid such collisions. This paper analyzes the orbital long-term variation of a dead satellite drifting in the geostationary orbit. Also, the negative effects posed by dead satellites upon the on-orbit operational geostationary satellites are studied. Then the paper proposes a novel idea to launch a satellite sweeper whose purpose is to collect the on-orbit dead satellites and help them de-orbit to a "graveyard". The satellite sweeper consists of a parent satellite and a child satellite. The child satellite collects a dead satellite and transfers it to a higher orbit. The parent satellite stationed in the geostationary orbit is in charge of refueling the child satellite. The strategy of maneuver and rendezvous is presented and a series of formulas are derived. The analysis results show that our method to clean the geostationary orbital zone is practical and fuel-saving. With the help of just a few satellite sweepers, we can gain a clean environment of geostationary orbit environment again.

  1. Healthy Border 2020 Embassy Launch

    Science.gov (United States)

    The U.S.-Mexico Border Health Commission launched the Healthy Border 2020 at the Mexican Embassy in the United States on June 24, 2015. This new initiative aims to strengthening what was accomplished on the previous plan of action entitled Healthy Border 2010.

  2. Evolved Expendable Launch Vehicle (EELV)

    Science.gov (United States)

    2015-12-15

    2015. When the draft RFP was posted a Space and Missile Systems Center (SMC) internal Comment Resolution Matrix ( CRM ) was inadvertently exposed for...competitiveness; and benefit the U.S. economy. The overall goal of the EELV December 2015 SAR March 14, 2016 16:05:14 UNCLASSIFIED 8 launch system investment is

  3. Prospects For China's Expendable Launch Vehicle

    Institute of Scientific and Technical Information of China (English)

    Long Lehao; Wang Xiaojun; Rong Yi

    2009-01-01

    @@ The expendable launch vehicle ( ELV) is the major means for human beings to enter space. Up until April 2009, China's Long March (LM) series launch vehicle has conducted 117 launches, and realized 75 consecutive successful launches since October 1996, which marks China's ELV development has entered a new historical era. Based on the analysis of China's LM series launch vehicle development status, combining with the new generation launch vehicle development, this raises a development prospect for China's ELV to meet the demands for future launch vehicle technology development.

  4. NASA's Space Launch System: Momentum Builds Toward First Launch

    Science.gov (United States)

    May, Todd A.; Lyles, Garry M.

    2014-01-01

    NASA's Space Launch System (SLS) is gaining momentum toward the first launch of a new exploration-class heavy lift launch vehicle for international exploration and science initiatives. The SLS comprises an architecture that begins with a vehicle capable of launching 70 metric tons (t) into low Earth orbit. It will launch the Orion Multi-Purpose Crew Vehicle (MPCV) on its first autonomous flight beyond the Moon and back in December 2017. Its first crewed flight follows in 2021. SLS can evolve to a130-t lift capability and serve as a baseline for numerous robotic and human missions ranging from a Mars sample return to delivering the first astronauts to explore another planet. The SLS Program formally transitioned from the formulation phase to implementation with the successful completion of the rigorous Key Decision Point C review in 2014. As a result, the Agency authorized the Program to move forward to Critical Design Review, scheduled for 2015. In the NASA project life cycle process, SLS has completed 50 percent of its major milestones toward first flight. Every SLS element manufactured development hardware for testing over the past year. Accomplishments during 2013/2014 included manufacture of core stage test articles, preparations for qualification testing the solid rocket boosters and the RS-25 main engines, and shipment of the first flight hardware in preparation for the Exploration Flight Test-1 (EFT-1) in 2014. SLS was conceived with the goals of safety, affordability, and sustainability, while also providing unprecedented capability for human exploration and scientific discovery beyond Earth orbit. In an environment of economic challenges, the SLS team continues to meet ambitious budget and schedule targets through the studied use of hardware, infrastructure, and workforce investments the United States made in the last half century, while selectively using new technologies for design, manufacturing, and testing, as well as streamlined management approaches

  5. Educational Benefits from the AAU-Cubesat Student Satellite Project

    DEFF Research Database (Denmark)

    Alminde, Lars

    2003-01-01

    In September 2001 Aalborg university started the AAU-cubesat project that reached it climax when the student built satellite was launched into space on the 30th of June 2003 on top of a former Russian ICBM. AAU-cubesat was among the first five satellites to be launched that are built within the c...... on pico-satellite designs will be given. In addition as the project has been carried through by students then the educational value will be addressed as well.......In September 2001 Aalborg university started the AAU-cubesat project that reached it climax when the student built satellite was launched into space on the 30th of June 2003 on top of a former Russian ICBM. AAU-cubesat was among the first five satellites to be launched that are built within...... the cubesat concept that prescribes a satellite with dimensions 10x10x10cm and mass one kilogram. These constraints clearly limits the possibilities for the satellite in terms of possible scientific missions, but on the other hand: by building satellites of this size a technology push is created...

  6. A decade of ERS satellite orbits and altimetry

    NARCIS (Netherlands)

    Scharroo, R.

    2002-01-01

    The First European Remote Sensing Satellite, ERS-1, was launched in July 1991, fol- lowed by ERS-2 in April 1995. Both satellites carry a radar altimeter to serve oper- ational applications and scientific research in the fields of geodesy, oceanography, glaciology and meteorology. Together, the sate

  7. Mapping of satellite Earth observations using moving window block kriging

    Science.gov (United States)

    Tadić, J. M.; Qiu, X.; Yadav, V.; Michalak, A. M.

    2015-10-01

    Global gridded maps (a.k.a. Level 3 products) of Earth system properties observed by satellites are central to understanding the spatiotemporal variability of these properties. They also typically serve either as inputs into biogeochemical models or as independent data for evaluating such models. Spatial binning is a common method for generating contiguous maps, but this approach results in a loss of information, especially when the measurement noise is low relative to the degree of spatiotemporal variability. Such "binned" fields typically also lack a quantitative measure of uncertainty. Geostatistical mapping has previously been shown to make higher spatiotemporal resolution maps possible, and also provides a measure uncertainty associated with the gridded products. This study proposes a flexible moving window block kriging method that can be used as a tool for creating high spatiotemporal resolution maps from satellite data. It relies only on the assumption that the observed physical quantity exhibits spatial correlation that can be inferred from the observations. The method has several innovations relative to previously applied methods: (1) it provides flexibility in the spatial resolution of the contiguous maps, (2) it is applicable for physical quantities with varying spatiotemporal coverage (i.e., density of measurements) by utilizing a more general and versatile data sampling approach, and (3) it provides rigorous assessments of the uncertainty associated with the gridded products. The method is demonstrated by creating Level 3 products from observations of column-integrated carbon dioxide (XCO2) from the GOSAT (Greenhouse Gases Observing Satellite) satellite, and solar induced fluorescence (SIF) from the GOME-2 (Global Ozone Monitoring Experiment-2) instrument.

  8. Space debris proximity analysis in powered and orbital phases during satelitte launch

    Science.gov (United States)

    Bandyopadhyay, P.; Sharma, R.; Adimurthy, V.

    The need to protect a launch vehicle in its ascent phase as well as the payload upon injection in particular and to prevent generation of debris in general through collision has led to many recent developments in the methodologies of SPAce DEbris PROximity (SPADEPRO) analysis, which is required for COLlision Avoidance or COLA studies. SPADEPRO refers to assessment of collision risk between catalogued resident space objects and launch vehicle or satellite of interest. The detection of close approaches to satellites/launch vehicles during the launch and early post-deployment phase of their lifetimes is an important subset of the overall problem. Potential collisions during this period can usually be avoided by adjusting the time of launch within a specified launch window. In Ref- 1 a series of filters through which candidate objects have to pass before determining its close approach distances from either analytical propagators like SGP4/SDP4 or any numerical prediction package, has been described. Unfortunately, this detection technique cannot strictly be applied since assumption of orbital motion is violated when powered launch trajectories are considered. Ref- 2 has proposed an algorithm for determining launch window blackout intervals based on the avoidance of close approaches for trajectories, which are fixed relative to an Earth Centered Earth Fixed (ECEF) reference frame. In this paper, authors approximate the powered launch trajectory into a series of orbital trajectories so that those trajectories envelope the powered launch trajectory in position-velocity phase space. Following this, filters described in Ref- 1 have been utilized to find out potential candidates from resident space objects. In Ref- 2, 3 &4 the blackout period has been observed when the closest approach distance is below a certain threshold. Instead, in this paper authors use collision probability, considering dispersions in respective trajectories of resident space objects and launch vehicle

  9. Satellite mobile data service for Canada

    Science.gov (United States)

    Egan, Glenn R.; Sward, David J.

    A commercial mobile satellite system which is to be constructed and operated in Canada is examined. This is done in two phases. First, mobile data services was introduced. Hub equipment and 3000 mobile data terminals were supplied. Over the satellite tests were performed. The mobile data service provides full two way digital messaging automatic vehicle location and fleet management services. The second phase is to construct, launch and make operational the MSAT satellite and associated network control facilities. The implementation is examined of the mobile data service in Canada, including the technical description. Marketing and applications are also examined.

  10. The introduction to GNOS instrument for FY-3 satellite

    Science.gov (United States)

    Du, Qifei

    2016-07-01

    Global Navigation Satellite System (GNSS) Radio occultation (RO) has become a major atmospheric and ionospheric remote sensing technique and been widely used for numerical weather prediction and global climate monitoring applications. The first GNSS Occultation Sounder (GNOS) developed and manufactured by National Space Science Center (NSSC), Chinese Academy of Science is a RO payload, which has been onboard Fengyun-3 C (FY-3C) satellite and been launched on September 23, 2013. FY-3 series satellites are the Chinese second generation polar-orbiting meteorological satellites with sun-synchronous orbits. During RO events, the GNOS instruments measure the phase delay caused by the Earth's atmospheric and ionospheric refraction between the GNSS satellites and FY-3 satellites, as the relative position between the GNSS satellites and the FY-3 satellites varying, vertical profiles of RO observations (i.e. phase and amplitude) will be obtained, which can be used to derived the atmospheric and ionospheric physical properties such as press, temperature, humidity and ionospheric electron density. In my presentation, we present the characteristics of GNOS instruments for FY-3 series satellites and the result by the instrument in orbit. Firstly, we present the characteristics of GNOS instrument for FY-3C satellite and its precision of atmosphere occultation data. Additionally, we introduce the characteristics of GNOS instrument for FY-3D satellite which will be launched in 2016. Finally, we show the next generation GNOS instrument and its characteristics for the following FY-3 satellites.

  11. Economic benefits of the Space Station to commercial communication satellite operators

    Science.gov (United States)

    Price, Kent M.; Dixson, John E.; Weyandt, Charles J.

    1987-01-01

    The economic and financial aspects of newly defined space-based activities, procedures, and operations (APOs) and associated satellite system designs are presented that have the potential to improve economic performance of future geostationary communications satellites. Launch insurance, launch costs, and the economics of APOs are examined. Retrieval missions and various Space Station scenarios are addressed. The potential benefits of the new APOs to the commercial communications satellite system operator are quantified.

  12. General Purpose Satellites: a concept for affordable low earth orbit vehicles

    OpenAIRE

    Boyd, Austin W.; Fuhs, Allen E.

    1997-01-01

    A general purpose satellite has been designed which will be launched from the Space Shuttle using a NASA Get-Away-Special (GAS) canister. The design is based upon the use of a new extended GAS canister and a low profile launch mechanism. The satellite is cylindrical. measuring 19 inches in diameter and 35 inches long. The maximum vehicle weight is 250 pounds, of which 50 pounds is dedicated to user payloads. The remaining 200 pounds encompasses the satellite structure and support ...

  13. Europe over the moon with new satellite

    CERN Multimedia

    2002-01-01

    ESA has taken delivery of a 3kg device that it plans to use to complete the first high-resolution map of the moon. The D-CIXS (Demonstration of a Compact Imaging X-Ray Spectrometer) will be aboard the SMART-1 satellite to be launched from French Guyana in South America next February (1/2 page).

  14. Performance evaluation of multi-sensor data-fusion systems in launch vehicles

    Indian Academy of Sciences (India)

    B N Suresh; K Sivan

    2004-04-01

    In this paper, the utilization of multi-sensors of different types, their characteristics, and their data-fusion in launch vehicles to achieve the goal of injecting the satellite into a precise orbit is explained. Performance requirements of sensors and their redundancy management in a typical launch vehicle are also included. The role of an integrated system level-test bed for evaluating multi-sensors and mission performance in a typical launch vehicle mission is described. Some of the typical simulation results to evaluate the effect of the sensors on the overall system are highlighted.

  15. JPSS-1 VIIRS pre-launch radiometric performance

    Science.gov (United States)

    Oudrari, Hassan; McIntire, Jeff; Xiong, Xiaoxiong; Butler, James; Efremova, Boryana; Ji, Qiang; Lee, Shihyan; Schwarting, Tom

    2015-09-01

    The Visible Infrared Imaging Radiometer Suite (VIIRS) on-board the first Joint Polar Satellite System (JPSS) completed its sensor level testing on December 2014. The JPSS-1 (J1) mission is scheduled to launch in December 2016, and will be very similar to the Suomi-National Polar-orbiting Partnership (SNPP) mission. VIIRS instrument was designed to provide measurements of the globe twice daily. It is a wide-swath (3,040 km) cross-track scanning radiometer with spatial resolutions of 370 and 740 m at nadir for imaging and moderate bands, respectively. It covers the wavelength spectrum from reflective to long-wave infrared through 22 spectral bands [0.412 μm to 12.01 μm]. VIIRS observations are used to generate 22 environmental data products (EDRs). This paper will briefly describe J1 VIIRS characterization and calibration performance and methodologies executed during the pre-launch testing phases by the independent government team, to generate the at-launch baseline radiometric performance, and the metrics needed to populate the sensor data record (SDR) Look-Up-Tables (LUTs). This paper will also provide an assessment of the sensor pre-launch radiometric performance, such as the sensor signal to noise ratios (SNRs), dynamic range, reflective and emissive bands calibration performance, polarization sensitivity, bands spectral performance, response-vs-scan (RVS), near field and stray light responses. A set of performance metrics generated during the pre-launch testing program will be compared to the SNPP VIIRS pre-launch performance.

  16. ENGINEERING CONTRACT ON FY-2 BATCH 2 SATELLITES SIGNED

    Institute of Scientific and Technical Information of China (English)

    SunQing

    2004-01-01

    The signing ceremony of the Engineering Contract on FY-2 Batch 2 (FY-2 02) Satellites was held in Beijing by Commission of Science, Technology and Industry for National Defense (COSTIND) on August 31, 2004. The contract on the development and manufacture of FY-2 batch 2 satellites and the contract on the launch, test and control of FY-2 Batch 2 satellites were signed by China Meteorological Administration (CMA),

  17. NASA's Space Launch System: Moving Toward the Launch Pad

    Science.gov (United States)

    Creech, Stephen D.; May, Todd A.

    2013-01-01

    The National Aeronautics and Space Administration's (NASA's) Space Launch System (SLS) Program, managed at the Marshall Space Flight Center (MSFC), is making progress toward delivering a new capability for human space flight and scientific missions beyond Earth orbit. Designed with the goals of safety, affordability, and sustainability in mind, the SLS rocket will launch the Orion Multi-Purpose Crew Vehicle (MPCV), equipment, supplies, and major science missions for exploration and discovery. Supporting Orion's first autonomous flight to lunar orbit and back in 2017 and its first crewed flight in 2021, the SLS will evolve into the most powerful launch vehicle ever flown via an upgrade approach that will provide building blocks for future space exploration. NASA is working to deliver this new capability in an austere economic climate, a fact that has inspired the SLS team to find innovative solutions to the challenges of designing, developing, fielding, and operating the largest rocket in history. This paper will summarize the planned capabilities of the vehicle, the progress the SLS Program has made in the 2 years since the Agency formally announced its architecture in September 2011, the path it is following to reach the launch pad in 2017 and then to evolve the 70 metric ton (t) initial lift capability to 130-t lift capability after 2021. The paper will explain how, to meet the challenge of a flat funding curve, an architecture was chosen that combines the use and enhancement of legacy systems and technology with strategic new developments that will evolve the launch vehicle's capabilities. This approach reduces the time and cost of delivering the initial 70 t Block 1 vehicle, and reduces the number of parallel development investments required to deliver the evolved 130 t Block 2 vehicle. The paper will outline the milestones the program has already reached, from developmental milestones such as the manufacture of the first flight hardware, to life

  18. Passive and active launch vibration studies in the LVIS program

    Science.gov (United States)

    Edberg, Donald L.; Bartos, Bruce; Goodding, James C.; Wilke, Paul S.; Davis, Torey

    1998-06-01

    A U.S. Air Force-sponsored team consisting of Boeing (formerly McDonnell Douglas), Honeywell Satellite Systems, and CSA Engineering has developed technology to reduce the vibration felt by an isolated payload during launch. Spacecraft designers indicate that a launch vibration isolation system (LVIS) could provide significant cost benefits in payload design, testing, launch, and lifetime. This paper contains developments occurring since those reported previously. Simulations, which included models of a 6,500 pound spacecraft, an isolating payload attach fitting (PAF) to replace an existing PAF, and the Boeing Delta II launch vehicle, were used to generate PAF performance requirements for the desired levels of attenuation. Hardware was designed to meet the requirements. The isolating PAF concept replaces portions of a conventional metallic fitting with hydraulic- pneumatic struts featuring a unique hydraulic cross-link feature that stiffens under rotation to meet rocking restrictions. The pneumatics provide low-stiffness longitudinal support. Two demonstration isolating PAF struts were designed, fabricated and tested to determine their stiffness and damping characteristics and to verify the performance of the hydraulic crosslink concept. Measurements matched analytical predictions closely. An active closed-loop control system was simulated to assess its potential isolation performance. A factor of 100 performance increase over the passive case was achieved with minor weight addition and minimal power consumption.

  19. National Security Space Launch Report

    Science.gov (United States)

    2006-01-01

    widely used, with applications in wireless ground communications, authentication of electronic transactions, and management of large computerized networks ...flight of the Ariane 5G in 1996),23 cost is a major factor in the program’s success. The launch costs for an Ariane 5 are in the $130 million to $150...Knauf, Deputy Director, Directorate of Space Acquisition (SAF/USA). VADM James D. McArthur, Jr., Commander, Naval Network Warfare Command—“Naval Space

  20. Educational Applications of Communications Satellites in Canada. New Technologies in Canadian Education Series. Paper 12.

    Science.gov (United States)

    Richmond, J. Murray

    Canada has explored the use of satellites as a means to provide information and communications services to geographically isolated populations since 1962. Between 1972 and 1984, five series of satellites known as Anik A, B, C, and D and Hermes were launched. Each satellite provided expanded communications services, and each led to research and…

  1. Odyssey, an optimized personal communications satellite system

    Science.gov (United States)

    Rusch, Roger J.

    Personal communications places severe demands on service providers and transmission facilities. Customers are not satisfied with the current levels of service and want improvements. Among the characteristics that users seek are: lower service rates, hand held convenience, acceptable time delays, ubiquitous service, high availability, reliability, and high quality. The space industry is developing commercial space systems for providing mobile communications to personal telephones. Provision of land mobile satellite service is fundamentally different from the fixed satellite service provided by geostationary satellites. In fixed service, the earth based antennas can depend on a clear path from user to satellite. Mobile users in a terrestrial environment commonly encounter blockage due to vegetation, terrain or buildings. Consequently, high elevation angles are of premium value. TRW studied the issues and concluded that a Medium Earth Orbit constellation is the best solution for Personal Communications Satellite Service. TRW has developed Odyssey, which uses twelve satellites in medium altitude orbit to provide personal communications satellite service. The Odyssey communications system projects a multibeam antenna pattern to the Earth. The attitude control system orients the satellites to ensure constant coverage of land mass and coastal areas. Pointing can be reprogrammed by ground control to ensure optimized coverage of the desired service areas. The payload architecture features non-processing, "bent pipe" transponders and matrix amplifiers to ensure dynamic power delivery to high demand areas. Circuit capacity is 3000 circuits per satellite. Each satellite weighs 1917 kg (4226 pounds) at launch and the solar arrays provide 3126 Watts of power. Satellites are launched in pairs on Ariane, Atlas, or other vehicles. Each satellite is placed in a circular orbit at an altitude of 10,354 km. There are three orbit planes inclined at 55° to the equatorial plane

  2. Autonomous rendezvous and proximate motion of satellites - A covariance analysis

    Science.gov (United States)

    Mackison, Donald L.; Morenthaler, George W.

    1992-08-01

    The construction of large (10 exp 6 kg) spacecraft in orbit will, in order to meet the requirements of interplanetary launch windows and restrictions of launch facilities require the launch of several 100,000-kg payloads using the Heavy Lift Launch Vehicle (HLLV), and their subsequent in-orbit assembly into a completed spacecraft. This assembly will require that the components rendezvous and dock within a reasonable time, taking into consideration launch window restrictions and the operating time limits on the component spacecraft. This will require that the rendezvous and docking operations be accomplished autonomously, without ground control. The trajectory and attitude control of a chase satellite to rendezvous with a target satellite are modeled using the Euler-Hill equations of relative orbital motion, and a linearized set of relative attitude parameters. The effect of uncertainties in the orbit dynamics and sensors, and the attitude dynamics and sensors are modeled using a linearized covariance analysis.

  3. Low Earth orbit communications satellite

    Science.gov (United States)

    Moroney, D.; Lashbrook, D.; Mckibben, B.; Gardener, N.; Rivers, T.; Nottingham, G.; Golden, B.; Barfield, B.; Bruening, J.; Wood, D.

    1992-01-01

    A current thrust in satellite communication systems considers a low-Earth orbiting constellations of satellites for continuous global coverage. Conceptual design studies have been done at the time of this design project by LORAL Aerospace Corporation under the program name GLOBALSTAR and by Motorola under their IRIDIUM program. This design project concentrates on the spacecraft design of the GLOBALSTAR low-Earth orbiting communication system. Overview information on the program was gained through the Federal Communications Commission licensing request. The GLOBALSTAR system consists of 48 operational satellites positioned in a Walker Delta pattern providing global coverage and redundancy. The operational orbit is 1389 km (750 nmi) altitude with eight planes of six satellites each. The orbital planes are spaced 45 deg., and the spacecraft are separated by 60 deg. within the plane. A Delta 2 launch vehicle is used to carry six spacecraft for orbit establishment. Once in orbit, the spacecraft will utilize code-division multiple access (spread spectrum modulation) for digital relay, voice, and radio determination satellite services (RDSS) yielding position determination with accuracy up to 200 meters.

  4. Europe's first Moon probe prepares for launch

    Science.gov (United States)

    2003-08-01

    The European Space Agency’s SMART-1 spacecraft was delivered to Kourou, French Guiana, on July 15 and is currently being prepared for launch atop an Ariane 5 during the night from August 28 to 29. The launch window will open at 20:04 local time (01:04 on August 29 morning CEST) and will remain open for26 minutes. The 367 kg spacecraft will share Ariane’s V162 launch with two commercial payloads: the Indian Space Research Organisation’s Insat 3E and Eutelsat’s e-Bird communication satellites. The smallest spacecraft in the trio, SMART-1, will travel in the lower position, inside a cylindrical adapter, and will be the last to be released. A generic Ariane 5 will be in charge of placing these three payloads in a standard geostationary transfer orbit from which each will begin its own journey towards its final operational orbit. SMART-1, powered by its ion engine, will reach its destination in about 16 months, having followed a long spiralling trajectory. SMART-1’s ion engine will be used to accelerate the probe and raise its orbit until it reaches the vicinity of the Moon, some 350,000 to 400,000 km from Earth. Then, following gravity assists from a series of lunar swingbys in late September, late October and late November 2004, SMART-1 will be “captured” by the Moon’s gravity in December 2004 and will begin using its engine to slow down and reduce the altitude of its lunar orbit. Testing breakthrough technologies and studying the Moon SMART-1 is not a standard outer space probe. As ESA’s first Small Mission for Advanced Research in Technology, it is primarily designed to demonstrate innovative and key technologies for future deep space science missions. However, once it has arrived at its destination, it will also perform an unprecedented scientific study of the Moon. SMART-1 is a very small spacecraft (measuring just one cubic metre). Its solar arrays, spanning 14 metres, will deliver 1.9 kW of power, about 75% of which will be used for the probe

  5. A method for analyzing strategic product launch

    OpenAIRE

    XIAO Junji

    2007-01-01

    This paper proposes a method to analyze how the manufacturers make product launch decisions in a multi-product oligopoly market, and how the heterogeneity in their products affects the manufacturers' decisions on model launch and withdrawal.

  6. AstroSat: From Inception to Realization and Launch

    Indian Academy of Sciences (India)

    P. C. Agrawal

    2017-06-01

    The origin of the idea of AstroSat multi wavelength satellite mission and how it evolved over the next 15 years from a concept to the successful development of instruments for giving concrete shape to this mission, is recounted in this article. AstroSat is the outcome of intense deliberations in the Indian astronomy community leading to a consensus for a multi wavelength Observatory having broad spectral coverage over five decades in energy covering near-UV, far-UV, soft X-ray and hard X-ray bands. The multi wavelength observation capability of AstroSat with a suite of 4 co-aligned instruments and an X-ray sky monitor on a single satellite platform, imparts a unique character to this mission. AstroSat owes its realization to the collaborative efforts of the various ISRO centres, several Indian institutions, and a few institutions abroad which developed the 5 instruments and various sub systems of the satellite. AstroSat was launched on September 28, 2015 from India in a near equatorial 650 km circular orbit. The instruments are by and large working as planned and in the past 14 months more than 200 X-ray and UV sources have been studied with it. The important characteristics of AstroSat satellite and scientific instruments will be highlighted.

  7. Mapping of satellite Earth observations using moving window block kriging

    Directory of Open Access Journals (Sweden)

    J. M. Tadić

    2014-08-01

    Full Text Available Global gridded maps (a.k.a. Level 3 products of Earth system properties observed by satellites are central to understanding the spatiotemporal variability of these properties. They also typically serve either as inputs into biogeochemical models, or as independent data for evaluating such models. Spatial binning is a common method for generating contiguous maps, but this approach results in a loss of information, especially when the measurement noise is low relative to the degree of spatiotemporal variability. Such "binned" fields typically also lack a quantitative measure of uncertainty. Geostatistical mapping has previously been shown to make higher spatiotemporal resolution maps possible, and also provides a measure of the uncertainty associated with the gridded products. This study proposes a flexible moving window block kriging method that can be used as a tool for creating high spatiotemporal resolution maps from satellite data. It relies only on the assumption that the observed physical quantity exhibits spatial correlation that can be inferred from the observations. The method has several innovations relative to previously applied methods: (1 it provides flexibility in the spatial resolution of the contiguous maps (2 it is applicable for physical quantities with varying spatiotemporal coverage (i.e., density of measurements by utilizing a more general and versatile data sampling approach, and (3 it provides rigorous assessments of the uncertainty associated with the gridded products. The method is demonstrated by creating Level 3 products from observations of column-integrated carbon dioxide (XCO2 from the GOSAT satellite, and solar induced fluorescence (SIF from the GOME-2 instrument.

  8. New product development and product launch strategies

    OpenAIRE

    Filiz Bozkurt Bekoğlu; Ahu Ergen

    2016-01-01

    In today’s highly competitive environment, a balanced product portfolio, success in new product development and product launch are important factors for the sustainability of organizations. The aim of the study is to reveal the right product launch steps for the companies through theory and case study. In the study, new product development and product launch strategies are first investigated theoretically. Afterwards, a successful product series launch case from cosmetics sector is analyzed. ...

  9. THE HARBOUR DEFENCE MOTOR LAUNCHES

    Directory of Open Access Journals (Sweden)

    W.H. Rice

    2012-02-01

    Full Text Available One of the handiest small craft to emerge from the Second World War was the 72 fet Harbour Defence Motor Launch. It's purpose was to patrol harbours and their approaches and to guard against attack by swimmers or underwater vehicles such as 'chariots' or even submarines. For this task the craft was fitted with a small ASDIC outfit and carried eight depth charges. Surface armament comprised a three-pounder gun on the foredeck, twin Lewis guns on the bridge and a 20 mm Oerlikon aft.

  10. Launch vehicle systems design analysis

    Science.gov (United States)

    Ryan, Robert; Verderaime, V.

    1993-01-01

    Current launch vehicle design emphasis is on low life-cycle cost. This paper applies total quality management (TQM) principles to a conventional systems design analysis process to provide low-cost, high-reliability designs. Suggested TQM techniques include Steward's systems information flow matrix method, quality leverage principle, quality through robustness and function deployment, Pareto's principle, Pugh's selection and enhancement criteria, and other design process procedures. TQM quality performance at least-cost can be realized through competent concurrent engineering teams and brilliance of their technical leadership.

  11. Closed End Launch Tube (CELT)

    Science.gov (United States)

    Lueck, Dale E.; Immer, Christopher D.

    2004-02-01

    A small-scale test apparatus has been built and tested for the CELT pneumatic launch assist concept presented at STAIF 2001. The 7.5 cm (3-inch) diameter × 305 M (1000 feet) long system accelerates and pneumatically brakes a 6.35 cm diameter projectile with variable weight (1.5 - 5 Kg). The acceleration and braking tube has been instrumented with optical sensors and pressure transducers at 14 stations to take data throughout the runs. Velocity and pressure profiles for runs with various accelerator pressures and projectile weights are given. This test apparatus can serve as an important experimental tool for verifying this concept.

  12. Macroeconomic Benefits of Low-Cost Reusable Launch Vehicles

    Science.gov (United States)

    Shaw, Eric J.; Greenberg, Joel

    1998-01-01

    The National Aeronautics and Space Administration (NASA) initiated its Reusable Launch Vehicle (RLV) Technology Program to provide information on the technical and commercial feasibility of single-stage to orbit (SSTO), fully-reusable launchers. Because RLVs would not depend on expendable hardware to achieve orbit, they could take better advantage of economies of scale than expendable launch vehicles (ELVs) that discard costly hardware on ascent. The X-33 experimental vehicle, a sub-orbital, 60%-scale prototype of Lockheed Martin's VentureStar SSTO RLV concept, is being built by Skunk Works for a 1999 first flight. If RLVs achieve prices to low-earth orbit of less than $1000 US per pound, they could hold promise for eliciting an elastic response from the launch services market. As opposed to the capture of existing market, this elastic market would represent new space-based industry businesses. These new opportunities would be created from the next tier of business concepts, such as space manufacturing and satellite servicing, that cannot earn a profit at today's launch prices but could when enabled by lower launch costs. New business creation contributes benefits to the US Government (USG) and the US economy through increases in tax revenues and employment. Assumptions about the costs and revenues of these new ventures, based on existing space-based and aeronautics sector businesses, can be used to estimate the macroeconomic benefits provided by new businesses. This paper examines these benefits and the flight prices and rates that may be required to enable these new space industries.

  13. Drift wave launching in a linear quadrupole

    Energy Technology Data Exchange (ETDEWEB)

    Tessema, G.Y.; Elliott, J.A.; Rusbridge, M.G. (Manchester Univ. (UK). Inst. of Science and Technology)

    1989-12-01

    Drift waves have been successfully launched from flag probes in a steady-state magnetized plasma, and the launching mechanism has been identified. Non-linear interactions are observed between launched and intrinsic waves. A wide range of further experimental studies is thus made possible, of fundamental relevance to plasma confinement. (author).

  14. A figure of merit for competing communications satellite designs

    Science.gov (United States)

    Lovell, R. R.; Fordyce, S. W.

    1983-01-01

    Trends in launch schedules, weights, power, and space segment costs per transponder year for Intelsats and North American domsats (domestic communications satellites) are discussed. The Intelsat system currently services 25,000 point to point telephone links at any one moment, and a $3 billion order has been placed for Intelsat VIs, which feature 36,000 telephone circuits each. The Intelsat VI spacecraft will weigh 1670 kg in orbit, a continuance of the trend to heavier satellites, while the domsats will stay at 650 kg due to launch vehicle limitations. Direct television broadcast satellites are being designed for receive only (R/O) earth stations, with each satellite capable of servicing 50,000 individual ground stations. Competition is growing for C and Ku band satellite transponders for DBS, with costs $350,000 each. No standardized design has yet emerged.

  15. Vibration and acoustic testing of TOPEX/Poseidon satellite

    Science.gov (United States)

    Boatman, Dave; Scharton, Terry; Hershfeld, Donald; Larkin, Paul

    1992-01-01

    The satellite was subjected to a 1.5G swept sine vibration test and a 146 dB overall level acoustic test, in accordance with Ariane launch vehicle requirements, at the NASA Goddard Space Flight Center. Extensive pretest analysis of the sine test was conducted to plan the input notching and to justify vibration testing the satellite only in the longitudinal axis. A unique measurement system was utilized to determine the six components of interface force between the shaker and the satellite in the sine vibration test. The satellite was heavily instrumented in both the sine vibration and acoustic test in order to insure that the launch loads were enveloped with appropriate margin and that satellite responses did not exceed the compatibilities of the structure and equipment. The test specification, objectives, instrumentation, and test results are described herein.

  16. The Next Landsat Satellite: The Landsat Data Continuity Mission

    Science.gov (United States)

    Rons, James R.; Dwyer, John L.; Barsi, Julia A.

    2012-01-01

    The Landsat program is one of the longest running satellite programs for Earth observations from space. The program was initiated by the launch of Landsat 1 in 1972. Since then a series of six more Landsat satellites were launched and at least one of those satellites has been in operations at all times to continuously collect images of the global land surface. The Department of Interior (DOI) U.S. Geological Survey (USGS) preserves data collected by all of the Landsat satellites at their Earth Resources Observation and Science (EROS) Center in Sioux Falls, South Dakota. This 40-year data archive provides an unmatched record of the Earth's land surface that has undergone dramatic changes in recent decades due to the increasing pressure of a growing population and advancing technologies. EROS provides the ability for anyone to search the archive and order digital Landsat images over the internet for free. The Landsat data are a public resource for observing, characterizing, monitoring, trending, and predicting land use change over time providing an invaluable tool for those addressing the profound consequences of those changes to society. The most recent launch of a Landsat satellite occurred in 1999 when Landsat 7 was placed in orbit. While Landsat 7 remains in operation, the National Aeronautics and Space Administration (NASA) and the DOI/ USGS are building its successor satellite system currently called the Landsat Data Continuity Mission (LDCM). NASA has the lead for building and launching the satellite that will carry two Earth-viewing instruments, the Operational Land Imager (OLI) and the Thermal Infrared Sensor (TIRS). The OLI will take images that measure the amount of sunlight reflected by the land surface at nine wavelengths of light with three of those wavelengths beyond the range of human vision. T1RS will collect coincident images that measure light emitted by the land surface as a function of surface temperature at two longer wavelengths well beyond the

  17. How supernovae launch galactic winds?

    Science.gov (United States)

    Fielding, Drummond; Quataert, Eliot; Martizzi, Davide; Faucher-Giguère, Claude-André

    2017-09-01

    We use idealized three-dimensional hydrodynamic simulations of global galactic discs to study the launching of galactic winds by supernovae (SNe). The simulations resolve the cooling radii of the majority of supernova remnants (SNRs) and thus self-consistently capture how SNe drive galactic winds. We find that SNe launch highly supersonic winds with properties that agree reasonably well with expectations from analytic models. The energy loading (η _E= \\dot{E}_wind/ \\dot{E}_SN) of the winds in our simulations are well converged with spatial resolution while the wind mass loading (η _M= \\dot{M}_wind/\\dot{M}_\\star) decreases with resolution at the resolutions we achieve. We present a simple analytic model based on the concept that SNRs with cooling radii greater than the local scaleheight break out of the disc and power the wind. This model successfully explains the dependence (or lack thereof) of ηE (and by extension ηM) on the gas surface density, star formation efficiency, disc radius and the clustering of SNe. The winds our simulations are weaker than expected in reality, likely due to the fact that we seed SNe preferentially at density peaks. Clustering SNe in time and space substantially increases the wind power.

  18. Enabling Science and Deep Space Exploration through Space Launch System (LSL) Secondary Payload Opportunities

    Science.gov (United States)

    Singer, Jody; Pelfrey, Joseph; Norris, George

    2016-01-01

    For the first time in almost 40 years, a NASA human-rated launch vehicle has completed its Critical Design Review (CDR). By reaching this milestone, NASA's Space Launch System (SLS) and Orion spacecraft are on the path to launch a new era of deep space exploration. NASA is making investments to expand science and exploration capability of the SLS by developing the capability to deploy small satellites during the trans-lunar phase of the mission trajectory. Exploration Mission 1 (EM-1), currently planned for launch no earlier than July 2018, will be the first mission to carry such payloads on the SLS. The EM-1 launch will include thirteen 6U Cubesat small satellites that will be deployed beyond low earth orbit. By providing an earth-escape trajectory, opportunities are created for advancement of small satellite subsystems, including deep space communications and in-space propulsion. This SLS capability also creates low-cost options for addressing existing Agency strategic knowledge gaps and affordable science missions. A new approach to payload integration and mission assurance is needed to ensure safety of the vehicle, while also maintaining reasonable costs for the small payload developer teams. SLS EM-1 will provide the framework and serve as a test flight, not only for vehicle systems, but also payload accommodations, ground processing, and on-orbit operations. Through developing the requirements and integration processes for EM-1, NASA is outlining the framework for the evolved configuration of secondary payloads on SLS Block upgrades. The lessons learned from the EM-1 mission will be applied to processes and products developed for future block upgrades. In the heavy-lift configuration of SLS, payload accommodations will increase for secondary opportunities including small satellites larger than the traditional Cubesat class payload. The payload mission concept of operations, proposed payload capacity of SLS, and the payload requirements for launch and

  19. Comparison of CO2 retrievals from IASI-A, IASI-B and GOSAT in the thermal infrared for nearly coincident measurements over the Arctic ocean in summer

    Science.gov (United States)

    Camy-Peyret, Claude; Bureau, Jerome; Payan, Sebastien

    2015-04-01

    The capabilities to retrieve reliable information on the concentration of greenhouse gases in the lower atmosphere from thermal infrared (TIR) spectra collected by nadir sounders is still to be assessed. We have selected the two months period of July-August in the high latitude polar region where it is possible to observe almost coincident or superimposed footprints (IFOV) of the three infrared sounders considered in this study, namely IASI-A, IASI-B (on the MetOp platforms) and TANSO-FTS (on GOSAT). Retrievals of the column averaged mixing ratio of carbon dioxide XCO2 (and of the surface temperature) have been performed for three years i.e. 2010, 2013 and 2014 over Arctic waters. The summer period was chosen because ice free IFOVs (in the latitude band 68N to 82N) can be selected for which retrievals are less sensitive to surface inhomogeneity (as compared to IFOVs located over land). The emissivity of sea water is also better constrained. The inversion configuration (using the atmospheric window covering the so-called CO2 laser band in the interval 940-980 cm-1) will be described. The sensitivity of the retrieved XCO2 to the different layers of the lower atmosphere as a function of thermal contrast, temperature and humidity profiles will be presented. The precision/accuracy of the retrieved XCO2 will be discussed and compared between sounders. The CO2 trends is clearly captured over the years analysed in this work. The retrieved values will be compared to similar XCO2 products available from other sources (Leicester Univ., NIES, SRON/KIT). Some remaining spectroscopic issues in the vicinity of 948 cm-1 have been identified and circumvented. The retrieved sea surface temperature Tsurf used as a control variable is also providing an additional check of the performances of the retrievals and is compared to the Eumetsat IASI Tsurf product. These results are interesting starting points for preparing future missions like IASI-NG on MetOp-SG as well as GOSAT-2.

  20. 14 CFR 1214.117 - Launch and orbit parameters for a standard launch.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 5 2010-01-01 2010-01-01 false Launch and orbit parameters for a standard..., Reimbursable Customers § 1214.117 Launch and orbit parameters for a standard launch. To qualify for the...) Launch from Kennedy Space Center (KSC) into the customer's choice of two standard mission orbits: 160...

  1. Magnetic Launch Assist Vehicle-Artist's Concept

    Science.gov (United States)

    1999-01-01

    This artist's concept depicts a Magnetic Launch Assist vehicle clearing the track and shifting to rocket engines for launch into orbit. The system, formerly referred as the Magnetic Levitation (MagLev) system, is a launch system developed and tested by Engineers at the Marshall Space Flight Center (MSFC) that could levitate and accelerate a launch vehicle along a track at high speeds before it leaves the ground. Using an off-board electric energy source and magnetic fields, a Magnetic Launch Assist system would drive a spacecraft along a horizontal track until it reaches desired speeds. The system is similar to high-speed trains and roller coasters that use high-strength magnets to lift and propel a vehicle a couple of inches above a guideway. A full-scale, operational track would be about 1.5-miles long, capable of accelerating a vehicle to 600 mph in 9.5 seconds, and the vehicle would then shift to rocket engines for launch into orbit. The major advantages of launch assist for NASA launch vehicles is that it reduces the weight of the take-off, the landing gear, the wing size, and less propellant resulting in significant cost savings. The US Navy and the British MOD (Ministry of Defense) are planning to use magnetic launch assist for their next generation aircraft carriers as the aircraft launch system. The US Army is considering using this technology for launching target drones for anti-aircraft training.

  2. A Pre-launch Analysis of NASA's SMAP Mission Data

    Science.gov (United States)

    Escobar, V. M.; Brown, M. E.

    2012-12-01

    Product applications have become an integral part of converting the data collected into actionable knowledge that can be used to inform policy. Successfully bridging scientific research with operational decision making in different application areas requires looking into thematic user requirements and data requirements. NASA's Soil Moisture Active/Passive mission (SMAP) has an applications program that actively seeks to integrate the data prior to launch into a broad range of environmental monitoring and decision making systems from drought and flood guidance to disease risk assessment and national security SMAP is a a combined active/passive microwave instrument, which will be launched into a near-polar orbit in late 2014. It aims to produce a series of soil moisture products and soil freeze/thaw products with an accuracy of +/- 10%, a nominal resolution of between 3 and 40km, and latency between 12 hours and 7 days. These measurements will be used to enhance the understanding of processes that link the water, energy and carbon cycles, and to extend the capabilities of weather and climate prediction models. The driving success of the SMAP applications program is joining mission scientists to thematic end users and leveraging the knowledge base of soil moisture data applications, increase the speed SMAP data product ingestion into critical processes and research, improving societal benefits to science. Because SMAP has not yet launched, the mission is using test algorithms to determine how the data will interact with existing processes. The objective of this profession review is to solicit data requirements, accuracy needs and current understanding of the SMAP mission from the user community and then feed that back into mission product development. Thus, understanding how users will apply SMAP data, prior to the satellite's launch, is an important component of SMAP Applied Sciences and one of NASA's measures for mission success. This paper presents an analysis of

  3. Female condom launched in UK.

    Science.gov (United States)

    1992-01-01

    The lone-awaited female condom, Femidom, is to be launched at the end of September by manufacturers Chartex. It is being welcomed by the FPA [Family Planning Association] and other family planning experts as a valuable addition to the existing range of contraceptive methods and as an alternative to the male condom in offering effective protection against sexually transmitted diseases including HIV. A lubricated, loose-fitting polyurethane sheath, Femidom is inserted into the vagina at any time before sex. An inner ring holds the condom in place beyond the pubic bone and an outer ring lies flat against the vulva. In addition to extending choice, it is under direct control of the woman. As FPA Director Doreen Massey puts it: "We have to face the fact that some women who want safer sex can't get their partners to use condoms. for the 1st time with Femidom, you can insist that if he won't use a condom, you'll use yours." In trails of self-selected couples, up to 2/3 of women and their partners found the product acceptable. a study at the Institute of Population Studies in Exeter showed that while some couples had initial misgivings about the condom's size and appearance, especially its visibility when in position, these often declined with repeated use. Researcher Dr. Nicholas Ford pointed out that if the female condom makes a woman feel unattractive, her partner's comments may well influence these feelings. Users' experience of insertion and the condom's comfort also improved with repeated use. While there are no large studies showing ranges of effectiveness, it is likely to be as effective as the male condom (about 85%-98%). In a study of 106 women at the margaret Pyke Center in London, there were 7 unplanned pregnancies: 4 were due to inconsistent use of the method and 3 were method failures. Breakages were rare. 1/3 of participants dropped out in the 1st month. Users should continue with their existing contraceptive method until they are sure that they are using

  4. The Galilean Satellites

    Science.gov (United States)

    1998-01-01

    This composite includes the four largest moons of Jupiter which are known as the Galilean satellites. The Galilean satellites were first seen by the Italian astronomer Galileo Galilei in 1610. Shown from left to right in order of increasing distance from Jupiter, Io is closest, followed by Europa, Ganymede, and Callisto.The order of these satellites from the planet Jupiter helps to explain some of the visible differences among the moons. Io is subject to the strongest tidal stresses from the massive planet. These stresses generate internal heating which is released at the surface and makes Io the most volcanically active body in our solar system. Europa appears to be strongly differentiated with a rock/iron core, an ice layer at its surface, and the potential for local or global zones of water between these layers. Tectonic resurfacing brightens terrain on the less active and partially differentiated moon Ganymede. Callisto, furthest from Jupiter, appears heavily cratered at low resolutions and shows no evidence of internal activity.North is to the top of this composite picture in which these satellites have all been scaled to a common factor of 10 kilometers (6 miles) per picture element.The Solid State Imaging (CCD) system aboard NASA's Galileo spacecraft acquired the Io and Ganymede images in June 1996, the Europa images in September 1996, and the Callisto images in November 1997.Launched in October 1989, the spacecraft's mission is to conduct detailed studies of the giant planet, its largest moons and the Jovian magnetic environment. The Jet Propulsion Laboratory, Pasadena, CA, manages the mission for NASA's Office of Space Science, Washington, DC.The Jet Propulsion Laboratory, Pasadena, CA manages the Galileo mission for NASA's Office of Space Science, Washington, DC. JPL is an operating division of California Institute of Technology (Caltech).This image and other images and data received from Galileo are posted on the World Wide Web, on the Galileo mission

  5. The Omninet mobile satellite system

    Science.gov (United States)

    Salmasi, A.; Curry, W.

    Mobile Satellite System (MSS) design offering relatively low cost voice, data, and position location services to nonmetropolitan areas of North America is proposed. The system provides spectrally efficient multiple access and modulation techniques, and flexible user interconnection to public and private switched networks. Separate UHF and L-band satellites employing two 9.1 m unfurlable antennas each, achieve a 6048 channel capacity and utilize spot beams. Mobile terminals have modular design and employ 5 dBi omnidirectional antennas. Gateway stations (with two 5 m Ku-band antennas) and base stations (with a single 1.8 m Ku-band antenna) transmit terrestrial traffic to the satellite, where traffic is then transponded via an L-band or UHF downlink to mobile users. The Network Management Center uses two 5-m antennas and incorporates the Integrated-Adaptive Mobile Access Protocol to assure demand assignment of satellite capacity. Preliminary implementation of this low-risk system involves a mobile alphanumeric data service employing receive-only terminals at Ku-band projected for 1987, and plans for the launching of L-band receive-only packages as early as 1988.

  6. CERN & Society launches donation portal

    CERN Document Server

    Cian O'Luanaigh

    2014-01-01

    The CERN & Society programme brings together projects in the areas of education and outreach, innovation and knowledge exchange, and culture and arts, that spread the CERN spirit of scientific curiosity for the inspiration and benefit of society. Today, CERN & Society is launching its "giving" website – a portal to allow donors to contribute to various projects and forge new relationships with CERN.   "The CERN & Society initiative in its embryonic form began almost three years ago, with the feeling that the laboratory could play a bigger role for the benefit of society," says Matteo Castoldi, Head of the CERN Development Office, who, with his team, is seeking supporters and ambassadors for the CERN & Society initiative. "The concept is not completely new – in some sense it is embedded in CERN’s DNA, as the laboratory helps society by creating knowledge and new technologies – but we would like to d...

  7. EADS Roadmap for Launch Vehicles

    Science.gov (United States)

    Eymar, Patrick; Grimard, Max

    2002-01-01

    still think about the future, especially at industry level in order to make the most judicious choices in technologies, vehicle types as well as human resources and facilities specialization (especially after recent merger moves). and production as prime contractor, industrial architect or stage provider have taken benefit of this expertise and especially of all the studies ran under national funding and own financing on reusable vehicles and ground/flight demonstrators have analyzed several scenarios. VEHICLES/ASTRIUM SI strategy w.r.t. launch vehicles for the two next decades. Among the main inputs taken into account of course visions of the market evolutions have been considered, but also enlargement of international cooperations and governments requests and supports (e.g. with the influence of large international ventures). 1 patrick.eymar@lanceurs.aeromatra.com 2

  8. Integrated Navigation System for the Second Generation Reusable Launch Vehicle

    Science.gov (United States)

    2002-01-01

    An array of components in a laboratory at NASA's Marshall Space Flight Center (MSFC) is being tested by the Flight Mechanics Office to develop an integrated navigation system for the second generation reusable launch vehicle. The laboratory is testing Global Positioning System (GPS) components, a satellite-based location and navigation system, and Inertial Navigation System (INS) components, sensors on a vehicle that determine angular velocity and linear acceleration at various points. The GPS and INS components work together to provide a space vehicle with guidance and navigation, like the push of the OnStar button in your car assists you with directions to a specific address. The integration will enable the vehicle operating system to track where the vehicle is in space and define its trajectory. The use of INS components for navigation is not new to space technology. The Space Shuttle currently uses them. However, the Space Launch Initiative is expanding the technology to integrate GPS and INS components to allow the vehicle to better define its position and more accurately determine vehicle acceleration and velocity. This advanced technology will lower operational costs and enhance the safety of reusable launch vehicles by providing a more comprehensive navigation system with greater capabilities. In this photograph, Dr. Jason Chuang of MSFC inspects an INS component in the laboratory.

  9. Communication Satellite Payload Special Check out Equipment (SCOE) for Satellite Testing

    Science.gov (United States)

    Subhani, Noman

    2016-07-01

    This paper presents Payload Special Check out Equipment (SCOE) for the test and measurement of communication satellite Payload at subsystem and system level. The main emphasis of this paper is to demonstrate the principle test equipment, instruments and the payload test matrix for an automatic test control. Electrical Ground Support Equipment (EGSE)/ Special Check out Equipment (SCOE) requirements, functions and architecture for C-band and Ku-band payloads are presented in details along with their interface with satellite during different phases of satellite testing. It provides test setup, in a single rack cabinet that can easily be moved from payload assembly and integration environment to thermal vacuum chamber all the way to launch site (for pre-launch test and verification).

  10. Evolved Expendable Launch Vehicle: The Air Force Needs to Adopt an Incremental Approach to Future Acquisition Planning to Enable Incorporation of Lessons Learned

    Science.gov (United States)

    2015-08-01

    Acquisitions, Technology, and Logistics directed the Air Force to introduce a competitive procurement environment for up to 14 launches.11... competition in the launch industry is a high priority for the service, and not requiring DOD-approved business systems is a key advantage of...program is the primary provider launches for military and intelligence satellites. The Air Force is working to introduce competition into the program

  11. Comparison of the GOSAT TANSO-FTS TIR CH volume mixing ratio vertical profiles with those measured by ACE-FTS, ESA MIPAS, IMK-IAA MIPAS, and 16 NDACC stations

    Directory of Open Access Journals (Sweden)

    K. S. Olsen

    2017-10-01

    Full Text Available The primary instrument on the Greenhouse gases Observing SATellite (GOSAT is the Thermal And Near infrared Sensor for carbon Observations (TANSO Fourier transform spectrometer (FTS. TANSO-FTS uses three short-wave infrared (SWIR bands to retrieve total columns of CO2 and CH4 along its optical line of sight and one thermal infrared (TIR channel to retrieve vertical profiles of CO2 and CH4 volume mixing ratios (VMRs in the troposphere. We examine version 1 of the TANSO-FTS TIR CH4 product by comparing co-located CH4 VMR vertical profiles from two other remote-sensing FTS systems: the Canadian Space Agency's Atmospheric Chemistry Experiment FTS (ACE-FTS on SCISAT (version 3.5 and the European Space Agency's Michelson Interferometer for Passive Atmospheric Sounding (MIPAS on Envisat (ESA ML2PP version 6 and IMK-IAA reduced-resolution version V5R_CH4_224/225, as well as 16 ground stations with the Network for the Detection of Atmospheric Composition Change (NDACC. This work follows an initial inter-comparison study over the Arctic, which incorporated a ground-based FTS at the Polar Environment Atmospheric Research Laboratory (PEARL at Eureka, Canada, and focuses on tropospheric and lower-stratospheric measurements made at middle and tropical latitudes between 2009 and 2013 (mid-2012 for MIPAS. For comparison, vertical profiles from all instruments are interpolated onto a common pressure grid, and smoothing is applied to ACE-FTS, MIPAS, and NDACC vertical profiles. Smoothing is needed to account for differences between the vertical resolution of each instrument and differences in the dependence on a priori profiles. The smoothing operators use the TANSO-FTS a priori and averaging kernels in all cases. We present zonally averaged mean CH4 differences between each instrument and TANSO-FTS with and without smoothing, and we examine their information content, their sensitive altitude range, their correlation, their a priori dependence, and the

  12. Validation of GOCE Satellite Gravity Gradient Observations by Orbital Analysis

    Science.gov (United States)

    Visser, P.

    The upcoming European Space Agency ESA Gravity Field and Steady-State Ocean Circular Explorer GOCE mission foreseen to be launched in 2007 will carry a highly sensitive gradiometer consisting of 3 orthogonal pairs of ultra-sensitive accelerometers A challenging calibration procedure has been developed to calibrate the gradiometer not only before launch by a series of on-ground tests but also after launch by making use of on-board cold-gas thrusters to provoke a long series of gradiometer shaking events which will provide observations for its calibration This calibration can be checked by a combined analysis of GPS Satellite-to-Satellite Tracking SST and Satellite Gravity Gradient SGG observations An assessment has been made of how well SGG calibration parameters can be estimated in a combined orbit and gravity field estimation from these observations

  13. Electric Propulsion for Low Earth Orbit Communication Satellites

    Science.gov (United States)

    Oleson, Steven R.

    1997-01-01

    Electric propulsion was evaluated for orbit insertion, satellite positioning and de-orbit applications on big (hundreds of kilograms) and little (tens of kilograms) low earth orbit communication satellite constellations. A simple, constant circumferential thrusting method was used. This technique eliminates the complex guidance and control required when shading of the solar arrays must be considered. Power for propulsion was assumed to come from the existing payload power. Since the low masses of these satellites enable multiple spacecraft per launch, the ability to add spacecraft to a given launch was used as a figure of merit. When compared to chemical propulsion ammonia resistojets, ion, Hall, and pulsed plasma thrusters allowed an additional spacecraft per launch Typical orbit insertion and de-orbit times were found to range from a few days to a few months.

  14. An Overview of JPSS-1 VIIRS Pre-Launch Testing and Performanc

    Science.gov (United States)

    Xiong, X.; McIntire, J.; Oudrari, H.; Thome, K.; Butler, J. J.; Ji, Q.; Schwarting, T.

    2015-12-01

    The Visible-Infrared Imaging Radiometer Suite (VIIRS) is a key instrument for the Suomi National Polar-orbiting Partnership (S-NPP) satellite launched in 2011 and future Joint Polar Satellite System (JPSS) satellites. The JPSS-1 (J1) spacecraft is scheduled to launch in January 2017. VIIRS instrument was designed to provide measurements of the globe twice daily. It is a cross-track scanning radiometer using a rotating telescope with spatial resolutions of 375 and 750 m at nadir for its imaging and moderate bands, respectively. It has 22 spectral bands covering wavelengths from 0.412 to 12.01 μm, including 14 reflective solar bands (RSB), 7 thermal emissive bands (TEB), and 1 day-night band (DNB). VIIRS observations are used to generate 22 environmental data products (EDRs), enabling a wide range of applications. This paper describes J1 VIIRS pre-launch testing program, instrument calibration and characterization strategies, and its projected performance based on independent analyses made by the NASA VIIRS Characterization Support Team (VCST). It also discusses the effort made the joint government team to produce sensor at-launch baseline performance parameters and the metrics needed to populate the Look-Up-Tables (LUTs) needed for the sensor data records (SDR) production. Sensor performance to be illustrated in this paper include signal-to-noise ratios (SNRs), dynamic range, spatial and spectral performance, response versus scan-angle (RVS), and polarization sensitivity.

  15. 14 CFR 415.119 - Launch plans.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Launch plans. 415.119 Section 415.119... From a Non-Federal Launch Site § 415.119 Launch plans. An applicant's safety review document must contain the plans required by § 417.111 of this chapter, except for the countdown plan of § 417.111(l) of...

  16. An SDR based AIS receiver for satellites

    DEFF Research Database (Denmark)

    Larsen, Jesper Abildgaard; Mortensen, Hans Peter; Nielsen, Jens Frederik Dalsgaard

    2011-01-01

    For a few years now, there has been a high interest in monitoring the global ship traffic from space. A few satellite, capable of listening for ship borne AIS transponders have already been launched, and soon the AAUSAT3, carrying two different types of AIS receivers will also be launched. One...... of the AIS receivers onboard AAUSAT3 is an SDR based AIS receiver. This paper serves to describe the background of the AIS system, and how the SDR based receiver has been integrated into the AAUSAT3 satellite. Amongst some of the benefits of using an SDR based receiver is, that due to its versatility, new...... detection algorithms are easily deployed, and it is easily adapted the new proposed AIS transmission channels....

  17. Launch processing system concept to reality

    Science.gov (United States)

    Bailey, W. W.

    1985-01-01

    The Launch Processing System represents Kennedy Space Center's role in providing a major integrated hardware and software system for the test, checkout and launch of a new space vehicle. Past programs considered the active flight vehicle to ground interfaces as part of the flight systems and therefore the related ground system was provided by the Development Center. The major steps taken to transform the Launch Processing System from a concept to reality with the successful launches of the Shuttle Programs Space Transportation System are addressed.

  18. Launch Control System Message Reduction

    Science.gov (United States)

    Nguyen, Uyen

    2014-01-01

    System Monitoring and Control (SMC) message browsers receive many messages daily that operators do not need to see. My job is to reduce the number of messages so that warning and emergency messages can be seen easily and therefore, responded to promptly. There are two methods to reduce messages: duplicate and state-based message correlations. With duplicate message correlation, SMC display the message the first time it shows up. The next times it occurs, a duplicate number will count the number of times the message appears. State-based message correlation is a process in which more informative messages acknowledge less useful ones and send them to history. I also work on correcting the severity level and text formats of messages. I follow two SMC message filtering tenets as I'm working on this project. Firstly, before filtering an offending message, a non-conformance (NC) must be created in order to attempt fixing that message through hardware or software. Only after the NC assessment states that it cannot fix an offending message, it can be filtered by SMC. Secondly, per Launch Control System (LCS) Coding Standards, SMC does not send information messages to the active message browser unless it's a response to an operator action.

  19. Data Collection Satellite Application in Precision Agriculture

    Science.gov (United States)

    Durào, O.

    2002-01-01

    Agricultural Instrumentation Research Center, Brazilian Agricultural Research Corporation; Space Programs Brazil launched in 1993 its first satellite partially built and entirely designed, integrated, tested and operated in the country. It was the SCD-1 satellite, a small (115 kg. and an octagonal prism with 80 cm. height and an external diameter of 100 cm.) with a payload transponder that receives data from ground platforms spread all over the country (including its sea shore). These data are then retransmitted to a receiving station at every satellite pass. Data collected and received are processed at Data Collection Mission Center for distribution via internet at most 30 min after the satellite pass. The ground platforms are called PCD's and differ in the parameters measured according to its purpose and location. Thus, they are able to measure temperature, rain level, wind direction, solar radiation, carbon monoxide as well as many others, beyond its own location. SCD- 1 had a nominal designed life of one year, but is still functioning. It is a LEO satellite with inclination of 25°. In 1998, the country launched SCD-2, with the same purpose, but in phase with SCD-1 . Other differences were a higher index of Brazilian made components and an active attitude control subsystem for the spin rate provided by the magnetic torque coils (these in accordance with a development strategy previously planned). In 1999 the country launched in cooperation with China a remote sensing satellite (mass of 1.4 ton.) called CBERS-1. This satellite is sun synchronous (98° inclination) and also carries a transponder for data collection/transmission as a secondary payload. Thus, the country has now three satellites with data collection/transmission capabilities, two in low inclination phased orbits and one in polar orbit, providing a nice coverage both geographical and temporal not only to its territory but also to other regions of the world.. At first there were not too many PCD

  20. Arianespace Launch Service Operator Policy for Space Safety (Regulations and Standards for Safety)

    Science.gov (United States)

    Jourdainne, Laurent

    2013-09-01

    Since December 10, 2010, the French Space Act has entered into force. This French Law, referenced as LOS N°2008-518 ("Loi relative aux Opérations Spatiales"), is compliant with international rules. This French Space Act (LOS) is now applicable for any French private company whose business is dealing with rocket launch or in orbit satellites operations. Under CNES leadership, Arianespace contributed to the consolidation of technical regulation applicable to launch service operators.Now for each launch operation, the operator Arianespace has to apply for an authorization to proceed to the French ministry in charge of space activities. In the files issued for this purpose, the operator is able to justify a high level of warranties in the management of risks through robust processes in relation with the qualification maintenance, the configuration management, the treatment of technical facts and relevant conclusions and risks reduction implementation when needed.Thanks to the historic success of Ariane launch systems through its more than 30 years of exploitation experience (54 successes in a row for latest Ariane 5 launches), Arianespace as well as European public and industrial partners developed key experiences and knowledge as well as competences in space security and safety. Soyuz-ST and Vega launch systems are now in operation from Guiana Space Center with identical and proved risks management processes. Already existing processes have been slightly adapted to cope with the new roles and responsibilities of each actor contributing to the launch preparation and additional requirements like potential collision avoidance with inhabited space objects.Up to now, more than 12 Ariane 5 launches and 4 Soyuz-ST launches have been authorized under the French Space Act regulations. Ariane 5 and Soyuz- ST generic demonstration of conformity have been issued, including exhaustive danger and impact studies for each launch system.This article will detail how Arianespace

  1. Experience and Methodology gained from 4 years of Student Satellite Projects

    DEFF Research Database (Denmark)

    Alminde, Lars; Bisgaard, Morten; Bhanderi, Dan

    2005-01-01

    The AAU Cubesat student satellite project at Aalborg University was initiated in September 2001 and led to the launch of the satellite on the 30th of June 2003 with a “Rockot” rocket from Plesetsk in Russia. The satellite survived three months in orbit and based on the experiences gained the next...... student satellite project was commenced called AAUSAT II which is due for launch early 2006. This paper presents the experiences gained and lessons learned from the work with student satellite projects at Aalborg University as well as the methodology used to manage these projects. First an introduction...... to the concept of student satellite projects is given and the two student satellite projects are introduced. Then an introduction and description of the Problem Based Learning concept used at Aalborg University is given and advantages of applying it to these projects are discussed. The benets of student...

  2. Launch Will Create a Radio Telescope Larger than Earth

    Science.gov (United States)

    NASA and the National Radio Astronomy Observatory are joining with an international consortium of space agencies to support the launch of a Japanese satellite next week that will create the largest astronomical "instrument" ever built -- a radio telescope more than two-and-a-half times the diameter of the Earth that will give astronomers their sharpest view yet of the universe. The launch of the Very Long Baseline Interferometry (VLBI) Space Observatory Program (VSOP) satellite by Japan's Institute of Space and Astronautical Science (ISAS) is scheduled for Feb. 10 at 11:50 p.m. EST (1:50 p.m. Feb. 11, Japan time.) The satellite is part of an international collaboration led by ISAS and backed by Japan's National Astronomical Observatory; NASA's Jet Propulsion Laboratory (JPL), Pasadena, CA; the National Science Foundation's National Radio Astronomy Observatory (NRAO), Socorro, NM; the Canadian Space Agency; the Australia Telescope National Facility; the European VLBI Network and the Joint Institute for Very Long Baseline Interferometry in Europe. Very long baseline interferometry is a technique used by radio astronomers to electronically link widely separated radio telescopes together so they work as if they were a single instrument with extraordinarily sharp "vision," or resolving power. The wider the distance between telescopes, the greater the resolving power. By taking this technique into space for the first time, astronomers will approximately triple the resolving power previously available with only ground-based telescopes. The satellite system will have resolving power almost 1,000 times greater than the Hubble Space Telescope at optical wavelengths. The satellite's resolving power is equivalent to being able to see a grain of rice in Tokyo from Los Angeles. "Using space VLBI, we can probe the cores of quasars and active galaxies, believed to be powered by super massive black holes," said Dr. Robert Preston, project scientist for the U.S. Space Very Long

  3. Geostationary Satellite (GOES) Images

    Data.gov (United States)

    National Oceanic and Atmospheric Administration, Department of Commerce — Visible and Infrared satellite imagery taken from radiometer instruments on SMS (ATS) and GOES satellites in geostationary orbit. These satellites produced...

  4. 14 CFR 417.13 - Agreement with Federal launch range.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Agreement with Federal launch range. 417.13... Agreement with Federal launch range. Before conducting a licensed launch from a Federal launch range, a launch operator must— (a) Enter into an agreement with a Federal launch range to provide access to...

  5. Neptune's small satellites

    Science.gov (United States)

    Thomas, P.

    1992-04-01

    The small satellites of Neptune and other planets discovered during the Voyager 2 mission are discussed in terms of their composition and relationship to the planetary systems. The satellite Proteus is described in terms of its orbit, five other satellites are described, and they are compared to ther small satellites and systems. Neptune's satellites are hypothesized to be related to the ring system, and the satellite Galatea is related to the confinement of the rings.

  6. Plan of advanced satellite communications experiment using ETS-VI

    Science.gov (United States)

    Shiomi, Tadashi

    1988-01-01

    Communications Research Laboratory (CRL, Ministry of Posts and Telecommunications, Japan) has been engaged in development of three advanced satellite communication payloads aiming at experiments by Japan's 2-ton class Engineering Test Satellite VI (ETS-VI) which is to be launched in H-II rocket by NASDA in August 1992. CRL's three experimental systems are: (1) S-band inter-satellite communications; (2) millimeter-wave inter-satellite and personal-satellite communications; and (3) optical inter-satellite communications. CRL develops experimental optical communication system with telescope of 75 mm diameter which has gimbal mirror beam pointing/tracking mechanism. The onboard system has fundamental optical communication functions with laser diode transmitter of wavelength 0.83 micron, laser beam point-ahead mechanism, receiver of wavelength 0.51 micron, modulation/demodulation subsystem, and so on.

  7. Development of environmental monitoring satellite systems in China

    Institute of Scientific and Technical Information of China (English)

    2010-01-01

    With the increase in global environmental problems,the necessity and urgency of remote sensing technology being applied to environmental monitoring has been widely recognized around the world.China has launched the environment and disaster monitoring and forecasting small satellite constellation HJ-1A/B and the FY3 atmosphere and environmental satellite,but they still cannot fully satisfy requirements for environmental monitoring.This paper summarizes the current status of satellite environmental monitoring in China and the existing problems of inadequate load design and low data utilization efficiency,and discusses the demand for environmental monitoring satellites.Based on the development of foreign satellite systems for environmental monitoring,the future development and key tasks of the environmental monitoring satellite system in China is discussed,as are some related initiatives.

  8. Review and Development on the Studies of Chinese Meteorological Satellite and Satellite Meteorology

    Institute of Scientific and Technical Information of China (English)

    FANG Zongyi; XU Jianmin; ZHAO Fengsheng

    2006-01-01

    Meteorological satellite and satellite meteorology are the fastest developing new branches in the atmospheric sciences. Today the meteorological satellite has become a key element in the global atmospheric sounding system while the satellite meteorology is covering the main components of earth's system science.This article describes the major achievements that China has made in these fields in the past 30 years.The following contents are involved: (1) History and present status of China's meteorological satellites. It covers the development, launch, operation, technical parameters of China's polar and geostationary meteorological satellites. (2) Major achievements on remote sensing principle and method. It describes the retrieval of atmospheric temperature and humidity profiles, cloud character retrieval, aerosol character retrieval, precipitation retrieval as well as the generation of cloud wind. (3) Achievement on the studies of meteorological satellite data application. This part covers the applications of meteorological satellite data to weather analysis and forecast, numerical forecast, climate monitoring, and prediction of short-term climate change. Besides, the new results on data assimilation, climate monitoring, and forecast are also included.

  9. The Second Young Engineers' Satellite: Innovative Technology through Education

    Science.gov (United States)

    Fujii, Hironori A.; Kruijff, Michiel; van der Heide, Erik J.; Watanabe, Takeo

    The second Young Engineers' Satellite,YES2, is the longest manmade structure launched in 2007 and is space piggybacked on the Foton-M3 microgravity platform with the objective of a controlled deployment of a 32km tether. This paper introduces the object and the flight results of YES2 and the performance of the satellite is studied in comparison of the simulations and ground tests with respect to the flight results.

  10. Mini-RPV Launch System Conceptual Study

    Science.gov (United States)

    1978-12-01

    are needed to produce total launch forces sufficient to launch mini-RPV’s. 4. Votta , F. A. Jr.;THE THEORY AND DESIGN OF LONG DEFLECTION, CONSTANT...Amendment 1, 29 September 1966. 4. Votta , F. A., Jr., THE THEORY AND DESIGN OF LONG DEFLECTION, CONSTANT FORCE SPRING ELEMENTS, Transactions of the ASME

  11. The Sketch of a New Generation Launch Vehicle of Long-March Family

    Science.gov (United States)

    Tang, Yihua; Wang, Xiaojun; Cheng, Tangming

    2002-01-01

    To meet the ever-expanding requirements of satellite customers, a new generation launch vehicle of Long-March (LM) family is being studied according to theprinciples of low-cost, high-reliability, and maximum flexibility. With reducing prelaunch processing times, the launch system will strengthen the capability of providing international commercial launching services in the future. The new generation launch system is constructed with some standard modules, while featuring two types of newly developed engines and three new modules with non-toxic, non-polluting propellant. Based on the three modules, 5-m module powered by two 50-ton-thrust engines which burn liquid hydrogen (LH2) and liquid oxygen (LO2), 3.35-m module powered by two 120-ton-thrust engines which burn LO2 and kerosene (KO), and 2.25-m module powered by one 120-ton-thrust engine, first can combine into a serial large-scale launch vehicles with 5-m-dia common core. By modified the modules, next combine into medium launch vehicles with 3.35-m-dia core and a small launch vehicle with 2.25-m-dia core. Then a new group of launch vehicles will be formed to accommodate a wide range of performance requirements, which provide a capable of delivering payloads ranging from 1.5-14 ton to geosynchronous transfer orbit (GTO) and up to 25 ton to low earth orbit (LEO). This paper will highlight the design principles, system concept and serial configurations for the new generation launch system.

  12. Model of load distribution for earth observation satellite

    Science.gov (United States)

    Tu, Shumin; Du, Min; Li, Wei

    2017-03-01

    For the system of multiple types of EOS (Earth Observing Satellites), it is a vital issue to assure that each type of payloads carried by the group of EOS can be used efficiently and reasonably for in astronautics fields. Currently, most of researches on configuration of satellite and payloads focus on the scheduling for launched satellites. However, the assignments of payloads for un-launched satellites are bit researched, which are the same crucial as the scheduling of tasks. Moreover, the current models of satellite resources scheduling lack of more general characteristics. Referring the idea about roles-based access control (RBAC) of information system, this paper brings forward a model based on role-mining of RBAC to improve the generality and foresight of the method of assignments of satellite-payload. By this way, the assignment of satellite-payload can be mapped onto the problem of role-mining. A novel method will be introduced, based on the idea of biclique-combination in graph theory and evolutionary algorithm in intelligence computing, to address the role-mining problem of satellite-payload assignments. The simulation experiments are performed to verify the novel method. Finally, the work of this paper is concluded.

  13. 14 CFR 417.17 - Launch reporting requirements and launch specific updates.

    Science.gov (United States)

    2010-01-01

    ... flight safety analysis products, using previously approved methodologies, for each launch no later than...) May not change an analysis product within the final 30 days before flight unless the launch operator... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Launch reporting requirements and...

  14. 76 FR 52694 - National Environmental Policy Act: Launch of NASA Routine Payloads on Expendable Launch Vehicles

    Science.gov (United States)

    2011-08-23

    ... SPACE ADMINISTRATION National Environmental Policy Act: Launch of NASA Routine Payloads on Expendable... availability and request for comments on the draft environmental assessment (``Draft EA'') for launch of NASA routine payloads on expendable launch vehicles. SUMMARY: Pursuant to the National Environmental Policy...

  15. 14 CFR 420.29 - Launch site location review for unproven launch vehicles.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Launch site location review for unproven... AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION LICENSING LICENSE TO OPERATE A LAUNCH SITE Criteria and Information Requirements for Obtaining a License § 420.29 Launch site location review for...

  16. 14 CFR 420.30 - Launch site location review for permitted launch vehicles.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Launch site location review for permitted... AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION LICENSING LICENSE TO OPERATE A LAUNCH SITE Criteria and Information Requirements for Obtaining a License § 420.30 Launch site location review...

  17. The 10th BeiDou 2 Navigation Satellite Flew into Space

    Institute of Scientific and Technical Information of China (English)

    2011-01-01

    LM launch vehicles established a new record by successfully performing the 16th successful flight this year.A LM-3A launched the 10th BeiDou 2 satellite into its predetermined transfer orbit on December 2 from the XSLC in Sichuan Province.

  18. Using ocean-glint scattered sunlight as a diagnostic tool for satellite remote sensing of greenhouse gases

    Directory of Open Access Journals (Sweden)

    A. Butz

    2013-09-01

    Full Text Available Spectroscopic measurements of sunlight backscattered by the Earth's surface is a technique widely used for remote sensing of atmospheric constituent concentrations from space. Thereby, remote sensing of greenhouse gases poses particularly challenging accuracy requirements for instrumentation and retrieval algorithms which, in general, suffer from various error sources. Here, we investigate a method that helps disentangle sources of error for observations of sunlight backscattered from the glint spot on the ocean surface. The method exploits the backscattering characteristics of the ocean surface, which is bright for glint geometry but dark for off-glint angles. This property allows for identifying a set of clean scenes where light scattering due to particles in the atmosphere is negligible such that uncertain knowledge of the lightpath can be excluded as a source of error. We apply the method to more than 3 yr of ocean-glint measurements by the Thermal And Near infrared Sensor for carbon Observation (TANSO Fourier Transform Spectrometer (FTS onboard the Greenhouse Gases Observing Satellite (GOSAT, which aims at measuring carbon dioxide (CO2 and methane (CH4 concentrations. The proposed method is able to clearly monitor recent improvements in the instrument calibration of the oxygen (O2 A-band channel and suggests some residual uncertainty in our knowledge about the instrument. We further assess the consistency of CO2 retrievals from several absorption bands between 6400 cm−1 (1565 nm and 4800 cm−1 (2100 nm and find that the absorption bands commonly used for monitoring of CO2 dry air mole fractions from GOSAT allow for consistency better than 1.5 ppm. Usage of other bands reveals significant inconsistency among retrieved CO2 concentrations pointing at inconsistency of spectroscopic parameters.

  19. Using ocean-glint scattered sunlight as a diagnostic tool for satellite remote sensing of greenhouse gases

    Directory of Open Access Journals (Sweden)

    A. Butz

    2013-05-01

    Full Text Available Spectroscopic measurements of sunlight backscattered by the Earth's surface is a technique widely used for remote sensing of atmospheric constituent concentrations from space. Thereby, remote sensing of greenhouse gases poses particularly challenging accuracy requirements for instrumentation and retrieval algorithms which, in general, suffer from various error sources. Here, we investigate a method that helps disentangle sources of error for observations of sunlight backscattered from the glint spot on the ocean surface. The method exploits the backscattering characteristics of the ocean surface which is bright for glint geometry but dark for off-glint angles. This property allows for identifying a set of clean scenes where light scattering due to particles in the atmosphere is negligible such that uncertain knowledge of the lightpath can be excluded as a source of error. We apply the method to more than 3 yr of ocean-glint measurements by the Thermal And Near infrared Sensor for carbon Observation (TANSO – Fourier Transform Spectrometer (FTS onboard the Greenhouse Gases Observing Satellite (GOSAT which aims at measuring carbon dioxide (CO2 and methane (CH4 concentrations. The proposed method is able to clearly monitor recent improvements in the instrument calibration of the oxygen (O2 A-band channel and suggests some residual uncertainty in our knowledge about the instrument. We further assess the consistency of CO2 retrievals from several absorption bands between 6400 cm−1 (1565 nm and 4800 cm−1 (2100 nm and find that the absorption bands commonly used for monitoring of CO2 dry air mole fractions from GOSAT allow for consistency better than 1.5 ppm. Usage of other bands reveals significant inconsistency among retrieved CO2 concentrations pointing at inconsistency of spectroscopic parameters.

  20. GHRSST 2 Level 2P Global Skin Sea Surface Temperature from the Visible Infrared Imaging Radiometer Suite (VIIRS) on the Suomi NPP satellite created by the NOAA Advanced Clear-Sky Processor for Ocean (ACSPO) (GDS version 2)

    Data.gov (United States)

    National Oceanic and Atmospheric Administration, Department of Commerce — The Joint Polar Satellite System (JPSS), starting with S-NPP launched on 28 October 2011, is the new generation of the US Polar Operational Environmental Satellites...

  1. COLD-SAT orbital experiment configured for Atlas launch

    Science.gov (United States)

    Shuster, J. R.; Bennett, F. O.; Wachter, J. P.

    1989-01-01

    The design and requirements for the proposed cryogenic on-orbit liquid depot storage, acquisition, and transfer (COLD-SAT) satellite experiment, which is to be launched by Atlas I, are examined. The COLD-SAT experiments are categorized as class I and II; class I involves technology related to space transportation missions and class II represents alternative fluid management operations and data. The hardware for the COLD-SAT experiments consists of three hydrogen tanks contained in the experimental module; the experimental module is connected to a three-axis-controlled spacecraft bus, and thrusters are positioned on the forward and aft ends of the spacecraft and on the cylindrical portion of the experimental module. The components and systems of the experiment module and the types of experiments that can be conducted in each tank are described. Diagrams of the spacecraft configuration are provided.

  2. Global Monitoring of Terrestrial Chlorophyll Fluorescence from Moderate-spectral-resolution Near-infrared Satellite Measurements: Methodology, Simulations, and Application to GOME-2

    Science.gov (United States)

    Joiner, J.; Gaunter, L.; Lindstrot, R.; Voigt, M.; Vasilkov, A. P.; Middleton, E. M.; Huemmrich, K. F.; Yoshida, Y.; Frankenberg, C.

    2013-01-01

    Globally mapped terrestrial chlorophyll fluorescence retrievals are of high interest because they can provide information on the functional status of vegetation including light-use efficiency and global primary productivity that can be used for global carbon cycle modeling and agricultural applications. Previous satellite retrievals of fluorescence have relied solely upon the filling-in of solar Fraunhofer lines that are not significantly affected by atmospheric absorption. Although these measurements provide near-global coverage on a monthly basis, they suffer from relatively low precision and sparse spatial sampling. Here, we describe a new methodology to retrieve global far-red fluorescence information; we use hyperspectral data with a simplified radiative transfer model to disentangle the spectral signatures of three basic components: atmospheric absorption, surface reflectance, and fluorescence radiance. An empirically based principal component analysis approach is employed, primarily using cloudy data over ocean, to model and solve for the atmospheric absorption. Through detailed simulations, we demonstrate the feasibility of the approach and show that moderate-spectral-resolution measurements with a relatively high signal-to-noise ratio can be used to retrieve far-red fluorescence information with good precision and accuracy. The method is then applied to data from the Global Ozone Monitoring Instrument 2 (GOME-2). The GOME-2 fluorescence retrievals display similar spatial structure as compared with those from a simpler technique applied to the Greenhouse gases Observing SATellite (GOSAT). GOME-2 enables global mapping of far-red fluorescence with higher precision over smaller spatial and temporal scales than is possible with GOSAT. Near-global coverage is provided within a few days. We are able to show clearly for the first time physically plausible variations in fluorescence over the course of a single month at a spatial resolution of 0.5 deg × 0.5 deg

  3. JPSS-1 VIIRS Radiometric Characterization and Calibration Based on Pre-Launch Testing

    Directory of Open Access Journals (Sweden)

    Hassan Oudrari

    2016-01-01

    Full Text Available The Visible Infrared Imaging Radiometer Suite (VIIRS on-board the first Joint Polar Satellite System (JPSS completed its sensor level testing on December 2014. The JPSS-1 (J1 mission is scheduled to launch in December 2016, and will be very similar to the Suomi-National Polar-orbiting Partnership (SNPP mission. VIIRS instrument has 22 spectral bands covering the spectrum between 0.4 and 12.6 μm. It is a cross-track scanning radiometer capable of providing global measurements twice daily, through observations at two spatial resolutions, 375 m and 750 m at nadir for the imaging and moderate bands, respectively. This paper will briefly describe J1 VIIRS characterization and calibration performance and methodologies executed during the pre-launch testing phases by the government independent team to generate the at-launch baseline radiometric performance and the metrics needed to populate the sensor data record (SDR Look-Up-Tables (LUTs. This paper will also provide an assessment of the sensor pre-launch radiometric performance, such as the sensor signal to noise ratios (SNRs, radiance dynamic range, reflective and emissive bands calibration performance, polarization sensitivity, spectral performance, response-vs-scan (RVS, and scattered light response. A set of performance metrics generated during the pre-launch testing program will be compared to both the VIIRS sensor specification and the SNPP VIIRS pre-launch performance.

  4. Artificial Satellites and How to Observe Them

    CERN Document Server

    Schmude, Jr , Richard

    2012-01-01

    Astronomers' Observing Guides provide up-to-date information for amateur astronomers who want to know all about what it is they are observing. This is the basis for the first part of the book. The second part details observing techniques for practical astronomers, working with a range of different instruments. Every amateur astronomer sees "stars" that aren't natural objects steadily slide across the background of the sky. Artificial satellites can be seen on any night, and some are as bright as the planets. But can you identify which satellite or spent launch vehicle casing you are seeing? Do you know how to image it? Artificial Satellites and How to Observe Them describes all of the different satellites that can be observed, including communication, scientific, spy satellites, and of course, the International Space Station. Richard Schmude describes how to recognize them and even how to predict their orbits. The book tells how to observe artificial satellites with the unaided eye, binoculars and with telesc...

  5. Satellite Ocean Biology: Past, Present, Future

    Science.gov (United States)

    McClain, Charles R.

    2012-01-01

    Since 1978 when the first satellite ocean color proof-of-concept sensor, the Nimbus-7 Coastal Zone Color Scanner, was launched, much progress has been made in refining the basic measurement concept and expanding the research applications of global satellite time series of biological and optical properties such as chlorophyll-a concentrations. The seminar will review the fundamentals of satellite ocean color measurements (sensor design considerations, on-orbit calibration, atmospheric corrections, and bio-optical algorithms), scientific results from the Sea-viewing Wide Field-of-view Sensor (SeaWiFS) and Moderate resolution Imaging Spectroradiometer (MODIS) missions, and the goals of future NASA missions such as PACE, the Aerosol, Cloud, Ecology (ACE), and Geostationary Coastal and Air Pollution Events (GeoCAPE) missions.

  6. Characterizing Epistemic Uncertainty for Launch Vehicle Designs

    Science.gov (United States)

    Novack, Steven D.; Rogers, Jim; Al Hassan, Mohammad; Hark, Frank

    2016-01-01

    NASA Probabilistic Risk Assessment (PRA) has the task of estimating the aleatory (randomness) and epistemic (lack of knowledge) uncertainty of launch vehicle loss of mission and crew risk, and communicating the results. Launch vehicles are complex engineered systems designed with sophisticated subsystems that are built to work together to accomplish mission success. Some of these systems or subsystems are in the form of heritage equipment, while some have never been previously launched. For these cases, characterizing the epistemic uncertainty is of foremost importance, and it is anticipated that the epistemic uncertainty of a modified launch vehicle design versus a design of well understood heritage equipment would be greater. For reasons that will be discussed, standard uncertainty propagation methods using Monte Carlo simulation produce counter intuitive results, and significantly underestimate epistemic uncertainty for launch vehicle models. Furthermore, standard PRA methods, such as Uncertainty-Importance analyses used to identify components that are significant contributors to uncertainty, are rendered obsolete, since sensitivity to uncertainty changes are not reflected in propagation of uncertainty using Monte Carlo methods. This paper provides a basis of the uncertainty underestimation for complex systems and especially, due to nuances of launch vehicle logic, for launch vehicles. It then suggests several alternative methods for estimating uncertainty and provides examples of estimation results. Lastly, the paper describes how to implement an Uncertainty-Importance analysis using one alternative approach, describes the results, and suggests ways to reduce epistemic uncertainty by focusing on additional data or testing of selected components.

  7. Tabletop Experimental Track for Magnetic Launch Assist

    Science.gov (United States)

    2000-01-01

    Marshall Space Flight Center's (MSFC's) Advanced Space Transportation Program has developed the Magnetic Launch Assist System, formerly known as the Magnetic Levitation (MagLev) technology that could give a space vehicle a running start to break free from Earth's gravity. A Magnetic Launch Assist system would use magnetic fields to levitate and accelerate a vehicle along a track at speeds up to 600 mph. The vehicle would shift to rocket engines for launch into orbit. Similar to high-speed trains and roller coasters that use high-strength magnets to lift and propel a vehicle a couple of inches above a guideway, a Magnetic Launch Assist system would electromagnetically propel a space vehicle along the track. The tabletop experimental track for the system shown in this photograph is 44-feet long, with 22-feet of powered acceleration and 22-feet of passive braking. A 10-pound carrier with permanent magnets on its sides swiftly glides by copper coils, producing a levitation force. The track uses a linear synchronous motor, which means the track is synchronized to turn the coils on just before the carrier comes in contact with them, and off once the carrier passes. Sensors are positioned on the side of the track to determine the carrier's position so the appropriate drive coils can be energized. MSFC engineers have conducted tests on the indoor track and a 50-foot outdoor track. The major advantages of launch assist for NASA launch vehicles is that it reduces the weight of the take-off, the landing gear, the wing size, and less propellant resulting in significant cost savings. The US Navy and the British MOD (Ministry of Defense) are planning to use magnetic launch assist for their next generation aircraft carriers as the aircraft launch system. The US Army is considering using this technology for launching target drones for anti-aircraft training.

  8. Magnetic Launch Assist System Demonstration Test

    Science.gov (United States)

    2001-01-01

    Engineers at the Marshall Space Flight Center (MSFC) have been testing Magnetic Launch Assist Systems, formerly known as Magnetic Levitation (MagLev) technologies. To launch spacecraft into orbit, a Magnetic Launch Assist system would use magnetic fields to levitate and accelerate a vehicle along a track at a very high speed. Similar to high-speed trains and roller coasters that use high-strength magnets to lift and propel a vehicle a couple of inches above a guideway, the launch-assist system would electromagnetically drive a space vehicle along the track. A full-scale, operational track would be about 1.5-miles long and capable of accelerating a vehicle to 600 mph in 9.5 seconds. This photograph shows a subscale model of an airplane running on the experimental track at MSFC during the demonstration test. This track is an advanced linear induction motor. Induction motors are common in fans, power drills, and sewing machines. Instead of spinning in a circular motion to turn a shaft or gears, a linear induction motor produces thrust in a straight line. Mounted on concrete pedestals, the track is 100-feet long, about 2-feet wide, and about 1.5- feet high. The major advantages of launch assist for NASA launch vehicles is that it reduces the weight of the take-off, the landing gear, the wing size, and less propellant resulting in significant cost savings. The US Navy and the British MOD (Ministry of Defense) are planning to use magnetic launch assist for their next generation aircraft carriers as the aircraft launch system. The US Army is considering using this technology for launching target drones for anti-aircraft training.

  9. DLR HABLEG- High Altitude Balloon Launched Experimental Glider

    Science.gov (United States)

    Wlach, S.; Schwarzbauch, M.; Laiacker, M.

    2015-09-01

    The group Flying Robots at the DLR Institute of Robotics and Mechatronics in Oberpfaffenhofen conducts research on solar powered high altitude aircrafts. Due to the high altitude and the almost infinite mission duration, these platforms are also denoted as High Altitude Pseudo-Satellites (HAPS). This paper highlights some aspects of the design, building, integration and testing of a flying experimental platform for high altitudes. This unmanned aircraft, with a wingspan of 3 m and a mass of less than 10 kg, is meant to be launched as a glider from a high altitude balloon in 20 km altitude and shall investigate technologies for future large HAPS platforms. The aerodynamic requirements for high altitude flight included the development of a launch method allowing for a safe transition to horizontal flight from free-fall with low control authority. Due to the harsh environmental conditions in the stratosphere, the integration of electronic components in the airframe is a major effort. For regulatory reasons a reliable and situation dependent flight termination system had to be implemented. In May 2015 a flight campaign was conducted. The mission was a full success demonstrating that stratospheric research flights are feasible with rather small aircrafts.

  10. Structural dynamics for new launch vehicles

    Science.gov (United States)

    Neighbors, Joyce; Ryan, Robert S.

    1992-01-01

    An overview is presented of current studies that will permit more robust designs and reduce the safety hazards of maximum dynamic pressure during launches. Key considerations in the assessment of future operable launch capabilities are the dynamics problems that arise during the initial minutes of transition from the static configuration on the launch pad to the attainment of orbital velocity. Attention is given to a typical attempt to achieve robustness that involves creating a design in which the first bending mode will have a high enough frequency to allow decoupling between the autopilot design and the flexible body dynamics.

  11. Space Solar Power Satellite Systems, Modern Small Satellites, and Space Rectenna

    Science.gov (United States)

    Bergsrud, Corey Alexis Marvin

    Space solar power satellite (SSPS) systems is the concept of placing large satellite into geostationary Earth orbit (GEO) to harvest and convert massive amounts of solar energy into microwave energy, and to transmit the microwaves to a rectifying antenna (rectenna) array on Earth. The rectenna array captures and converts the microwave power into usable power that is injected into the terrestrial electric grid for use. This work approached the microwave power beam as an additional source of power (with solar) for lower orbiting satellites. Assuming the concept of retrodirectivity, a GEO-SSPS antenna array system tracks and delivers microwave power to lower orbiting satellites. The lower orbiting satellites are equipped with a stacked photovoltaic (PV)/rectenna array hybrid power generation unit (HPGU) in order to harvest solar and/or microwave energy for on-board use during orbit. The area, and mass of the PV array part of the HPGU was reduced at about 32% beginning-of-life power in order to achieve the spacecraft power requirements. The HPGU proved to offer a mass decrease in the PGU, and an increase in mission life due to longer living component life of the rectenna array. Moreover, greater mission flexibility is achieved through a track and power delivery concept. To validate the potential advantages offered by a HPGU, a mission concept was presented that utilizes modern small satellites as technology demonstrators. During launch, a smaller power receiving "daughter" satellite sits inside a larger power transmitting "mother" satellite. Once separated from the launch vehicle the daughter satellite is ejected away from the mother satellite, and each satellite deploys its respective power transmitting or power receiving hardware's for experimentation. The concept of close proximity mission operations between the satellites is considered. To validate the technology of the space rectenna array part of the HPGU, six milestones were completed in the design. The first

  12. Shallow-earth rheology from glacial isostasy and satellite gravity: a sensitivity analysis for GOCE

    NARCIS (Netherlands)

    Schotman, H.H.A.

    2008-01-01

    In recent years, satellite gravity missions have been launched that probe the earth's long- to mediumwavelength (1000 - 500 km) gravity field. The upcoming ESA satellite gravity mission GOCE is predicted to measure the gravity field with an accuracy of a few centimeters at spatial scales of 100 km.

  13. Lessons learned after one year in space for the AAUSAT3 satellite

    DEFF Research Database (Denmark)

    Larsen, Jesper Abildgaard; Mortensen, Hans Peter; Jessen, Troels

    2014-01-01

    The AAUSAT3 satellite is a 1U cubesat, which has been developed by students at Aalborg University, Denmark in collaboration with the Danish Maritime Authority. The satellite was launched into a polar DD-SSO orbit of 800 km altitude on February 25th 2013 on a mission to monitor ships from space...

  14. Satellite data compression

    CERN Document Server

    Huang, Bormin

    2011-01-01

    Satellite Data Compression covers recent progress in compression techniques for multispectral, hyperspectral and ultra spectral data. A survey of recent advances in the fields of satellite communications, remote sensing and geographical information systems is included. Satellite Data Compression, contributed by leaders in this field, is the first book available on satellite data compression. It covers onboard compression methodology and hardware developments in several space agencies. Case studies are presented on recent advances in satellite data compression techniques via various prediction-

  15. Trends in communications satellites

    CERN Document Server

    Curtin, Denis J

    1979-01-01

    Trends in Communications Satellites offers a comprehensive look at trends and advances in satellite communications, including experimental ones such as NASA satellites and those jointly developed by France and Germany. The economic aspects of communications satellites are also examined. This book consists of 16 chapters and begins with a discussion on the fundamentals of electrical communications and their application to space communications, including spacecraft, earth stations, and orbit and wavelength utilization. The next section demonstrates how successful commercial satellite communicati

  16. Mapping man-made CO2 emissions using satellite-observed nighttime lights

    Science.gov (United States)

    Oda, T.; Maksyutov, S. S.; Andres, R. J.; Elvidge, C.; Baugh, K.; Hsu, F. C.; Roman, M. O.

    2015-12-01

    The Open-Data Inventory for Anthropogenic Carbon dioxide (ODIAC) is a global high spatial resolution (1x1km) emission dataset for CO2 emissions from fossil fuel combustion. The original version of ODIAC was developed at the Japanese Greenhouse Gas Observing Satellite (GOSAT) project to prescribe their inverse model. ODIAC first introduced the combined use of satellite-observed nighttime light data and individual power plant emission/geolocation information to estimate the spatial extent of fossil fuel CO2. The ODIAC emission data has been widely used by the international carbon cycle research community and appeared in a number of publications in the literature. Since its original publication in 2011, we have made numerous modifications to the ODIAC emission model and the emission data have been updated on annual basis. We are switching from BP statistical data based emission estimates to estimates made by Carbon Dioxide Information Analysis Center (CDIAC) at Oak Ridge National Laboratory. In recent versions of ODIAC data, the emission seasonality has been adopted from the CDIAC monthly emission dataset. The emissions from international bunkers, which are not included in the CDIAC gridded emission data, are estimated using the UN Energy Database and included with the spatial distributions. In the next version of ODIAC emission model, we will explore the use of satellite data collected by the NASA's Suomi National Polar-orbiting Partnership (NPP) satellite. We will estimate emission spatial distributions using global 500x500m nighttime lights data created from VIIRS data. We will also utilize a combustion detection algorithm Nightfire developed at NOAA National Geophysical Data Center to map gas flaring emissions. We also plan to expand our two emission sector emission distributing approach (power plant emission and non-point source emissions) by introducing a transportation emission sector which should improve emission distributions in urban and rural areas.

  17. The Soyuz launch vehicle the two lives of an engineering triumph

    CERN Document Server

    Lardier, Christian

    2013-01-01

    The Soyuz launch vehicle has had a long and illustrious history. Built as the world's first intercontinental missile, it took the first man into space in April 1961, before becoming the workhorse of Russian spaceflight, launching satellites, interplanetary probes, every cosmonaut from Gagarin onwards, and, now, the multinational crews of the International Space Station. This remarkable book gives a complete and accurate description of the two lives of Soyuz, chronicling the cooperative space endeavor of Europe and Russia. First, it takes us back to the early days of astronautics, when technology served politics. From archives found in the Soviet Union the authors describe the difficulty of designing a rocket in the immediate post-war period. Then, in Soyuz's golden age, it launched numerous scientific missions and manned flights which were publicized worldwide while the many more numerous military missions were kept highly confidential! The second part of the book tells the contemporary story of the second li...

  18. Using satellite data in map design and production

    Science.gov (United States)

    Hutchinson, John A.

    2002-01-01

    Satellite image maps have been produced by the U.S. Geological Survey (USGS) since shortly after the launch of the first Landsat satellite in 1972. Over the years, the use of image data to design and produce maps has developed from a manual and photographic process to one that incorporates geographic information systems, desktop publishing, and digital prepress techniques. At the same time, the content of most image-based maps produced by the USGS has shifted from raw image data to land cover or other information layers derived from satellite imagery, often portrayed in combination with shaded relief.

  19. Technical comparison of several global mobile satellite communications systems

    Science.gov (United States)

    Comparetto, Gary M.

    The era of satellite-based mobile satellite communications (MSC) systems started with the first MARISAT satellite which was launched into a geostationary orbit over the Pacific Ocean in 1976 to provide communications between ships and shore stations. The combination of high cost and unacceptably large equipment has kept the space-based MSC systems from appealing to the wider market of personal mobile communications. The progress made over the last ten years, however, in digital voice processing, satellite technology, and component miniaturization has resulted in the viability of satellite-based mobile satellite communications systems to meet the growing market in personal mobile communications using handsets similar to those currently in use with land-based cellular systems. Three of the more mature LEO/MEO satellite systems are addressed in this paper including GLOBALSTAR, Iridium, and Odyssey. The system architectures of each system are presented along with a description of the satellite and user handset designs and the multiaccess techniques employed. It will be shown that, although a number of similarities exist among the system addressed, each system is unique in a variety of significant design areas. It is concluded that the technical feasibility of satellite-based mobile satellite communications systems seems to be secure. It will be challenging, however, for the vendors to actually develop and deploy these systems in a cost effective, timely, and reliable way that meets a continually evolving set of requirements based upon a rapidly changing technology base.

  20. Planning for a data base system to support satellite conceptual design

    Science.gov (United States)

    Claydon, C. R.

    1976-01-01

    The conceptual design of an automated satellite design data base system is presented. The satellite catalog in the system includes data for all earth orbital satellites funded to the hardware stage for launch between 1970 and 1980, and provides a concise compilation of satellite capabilities and design parameters. The cost of satellite subsystems and components will be added to the base. Data elements are listed and discussed. Sensor and science and applications opportunities catalogs will be included in the data system. Capabilities of the BASIS storage, retrieval, and analysis system are used in the system design.

  1. CTS United States experiments - A progress report. [Communications Technology Satellite for high power broadcasting

    Science.gov (United States)

    Robbins, W. H.; Donoughe, P. L.

    1976-01-01

    The Communications Technology Satellite (CTS) is a high-power broadcast satellite launched by NASA on January 17, 1976. CTS is the first satellite to operate at a frequency of 12 gigahertz and incorporates technology making possible new satellite telecommunications services. CTS is a cooperative program of the United States and Canada. This paper presents the results of the United States experimental activity to date. Wide segments of the population are involved in the Experiments Program, including the scientific community, other government agencies, industry, and the education and health entities. The experiments are associated with both technological objectives and the demonstration of new community and social services via satellite.

  2. Minimum Cost Nanosatellite Launch System Project

    Data.gov (United States)

    National Aeronautics and Space Administration — Delta Velocity Corporation proposes the development of a very low cost, highly responsive nanosat launch system. We propose to develop an integrated propulsion...

  3. Launch Pad Flame Trench Refractory Materials

    Science.gov (United States)

    Calle, Luz M.; Hintze, Paul E.; Parlier, Christopher R.; Bucherl, Cori; Sampson, Jeffrey W.; Curran, Jerome P.; Kolody, Mark; Perusich, Steve; Whitten, Mary

    2010-01-01

    The launch complexes at NASA's John F. Kennedy Space Center (KSC) are critical support facilities for the successful launch of space-based vehicles. These facilities include a flame trench that bisects the pad at ground level. This trench includes a flame deflector system that consists of an inverted, V-shaped steel structure covered with a high temperature concrete material five inches thick that extends across the center of the flame trench. One side of the "V11 receives and deflects the flames from the orbiter main engines; the opposite side deflects the flames from the solid rocket boosters. There are also two movable deflectors at the top of the trench to provide additional protection to shuttle hardware from the solid rocket booster flames. These facilities are over 40 years old and are experiencing constant deterioration from launch heat/blast effects and environmental exposure. The refractory material currently used in launch pad flame deflectors has become susceptible to failure, resulting in large sections of the material breaking away from the steel base structure and creating high-speed projectiles during launch. These projectiles jeopardize the safety of the launch complex, crew, and vehicle. Post launch inspections have revealed that the number and frequency of repairs, as well as the area and size of the damage, is increasing with the number of launches. The Space Shuttle Program has accepted the extensive ground processing costs for post launch repair of damaged areas and investigations of future launch related failures for the remainder of the program. There currently are no long term solutions available for Constellation Program ground operations to address the poor performance and subsequent failures of the refractory materials. Over the last three years, significant liberation of refractory material in the flame trench and fire bricks along the adjacent trench walls following Space Shuttle launches have resulted in extensive investigations of

  4. The second Ariane launch complex (ELA-2)

    Science.gov (United States)

    Dana, C.

    1985-05-01

    ELA-2 will, in 1986, become the primary Ariane launch complex, with ELA-1 being relegated to back-up roles. Both Ariane 3 and Ariane 4 vehicles can lift-off from ELA 2, but not ELA-1. In the Preparation Zone, spacecraft, launch vehicles and propellant are unloaded from shipment, stored and assembled in a one month process. The assembly building is equipped with stored ice to ensure continued air conditioning and cooling of electronic equipment and stored fuels in case of power outage. The launch gantry to which the Ariane is transported by rail is equipped with blast channels to redirect the rocket exhausts. The control center has remote cameras and sensors for monitoring launch pad activities and an underground, concrete bunker for the safety of up to 200 personnel.

  5. Launching PPARC's five year strategy programme

    CERN Multimedia

    2003-01-01

    "Over one hundred delegates from Parliament, Whitehall and Industry attended a reception on Tuesday night (25 November) to mark the launch the Particle Physics and Astronomy Research Council's (PPARC) Five Year Plan" (1 page).

  6. Metric Tracking of Launch Vehicles Project

    Data.gov (United States)

    National Aeronautics and Space Administration — NASA needs reliable, accurate navigation for launch vehicles and other missions. GPS is the best world-wide navigation system, but operates at low power making it...

  7. GPS Attitude Determination for Launch Vehicles Project

    Data.gov (United States)

    National Aeronautics and Space Administration — Toyon Research Corporation proposes to develop a family of compact, low-cost GPS-based attitude (GPS/A) sensors for launch vehicles. In order to obtain 3-D attitude...

  8. Strategies Behind The Successful Industrial Product Launch

    OpenAIRE

    Choffray, Jean-Marie; Gary L. Lilien

    1984-01-01

    In this paper, we discuss a newly-developed microcomputer decision support system useful for predicting sales growth and testing launch strategies prior to an industrial product market introduction. Peer reviewed

  9. Alstom launches new mini hydro range

    Institute of Scientific and Technical Information of China (English)

    2002-01-01

    LSTOM POWER HYDRO has announced the launch of a complete mini hydro solution. Named Mini-Aqua, the product has been developed to integrate the hydro turbine, generator and control system in a single and optimised product.

  10. National Launch System comparative economic analysis

    Science.gov (United States)

    Prince, A.

    1992-01-01

    Results are presented from an analysis of economic benefits (or losses), in the form of the life cycle cost savings, resulting from the development of the National Launch System (NLS) family of launch vehicles. The analysis was carried out by comparing various NLS-based architectures with the current Shuttle/Titan IV fleet. The basic methodology behind this NLS analysis was to develop a set of annual payload requirements for the Space Station Freedom and LEO, to design launch vehicle architectures around these requirements, and to perform life-cycle cost analyses on all of the architectures. A SEI requirement was included. Launch failure costs were estimated and combined with the relative reliability assumptions to measure the effects of losses. Based on the analysis, a Shuttle/NLS architecture evolving into a pressurized-logistics-carrier/NLS architecture appears to offer the best long-term cost benefit.

  11. Electrospun jets launched from polymeric bubbles

    Directory of Open Access Journals (Sweden)

    J.S. Varabhas

    2009-12-01

    Full Text Available In this paper the launching of liquid polymer jetsfrom the apex of gas bubbles on thepolyvinylpyrrolidone in ethanol (PVP solutionsurface due to an applied electrical potential isinvestigated. Jets of polymer launched from bubbleprovide an alternative method for electrospinningpolymer nanofibers that may be scalable forcommercial production. Bubbles were experimentallycreated on the surface of a polymer solution byforcing air through a syringe into the polymersolution. An electric potential was applied to thesolution to launch the jets. The polymer solutionconcentration was varied to determine the optimumconcentration. The semi-angle of the apex of bubblejust prior to jet launch was observed to be close to thetheoretical value of 49.3 degrees for a pendant drop.

  12. STS-114: Discovery Launch Readiness Press Conference

    Science.gov (United States)

    2005-01-01

    This press conference, attended by representatives from the national, Florida, and aerospace media, addresses launch, weather, and safety issues related to Space Shuttle Discovery prior to its launch on the STS-114 Return to Flight mission. The Master of Ceremonies is George Diller from NASA Public Affairs, and the panelists are: Space Shuttle Program Manager Bill Parsons, ISS Program Manager (JSC) Bill Gerstenmaier, Space Shuttle Deputy Program Manager Wayne Hale, Director of Shuttle Processing Mike Wetmore, ISS Program Manager (JAXA) Dr. Kuniaki Shiraki, and Launch Weather Officer (USAF) Mindy Chavez. Questions included the following topics: predicted weather conditions at launch, contingency rescue plans, countdown procedures, and risk management, as well as implications of the Return to Flight for the International Space Station (ISS).

  13. STS-114: Post Launch Press Conference

    Science.gov (United States)

    2005-01-01

    Dean Acosta, Deputy Assistant Administrator for Public Affairs hosted this post launch press conference. Present were Mike Griffin, NASA Administrator; William Ready, Associate Administrator for Space Operations; Bill Parsons, Space Shuttle Program Manager; Mike Leinbach, NASA Launch Director; and Wayne Hill, Deputy Program Manager for Space Shuttle Program. Each expressed thanks to all of NASA Officials and employees, contractors, vendors and the crew for their hard work the past two and a half years that resulted the successful and pristine launch of Space Shuttle Discovery. The Panel emphasized that through extensive technical analysis, thorough planning and tremendous amount of public support brought them full circle again to return to flight. Flight safety, debris during rocket separation, sensors, observations from the mission control, launch conditions were some of the topics discussed with the News media.

  14. Visits Service Launches New Seminar Series

    CERN Multimedia

    2001-01-01

    The CERN Visits Service is launching a new series of seminars for guides, and they are open to everyone. The series kicks off next week with a talk by Konrad Elsener on the CERN neutrinos to Gran Sasso, CNGS, project.

  15. ALSAT-2A power subsystem behavior during launch, early operation, and in-orbit test

    Science.gov (United States)

    Larbi, N.; Attaba, M.; Beaufume, E.

    2012-09-01

    In 2006, Algerian Space Agency (ASAL) decided to design and built two optical Earth observation satellites. The first one, ALSAT-2A, was integrated and tested as a training and cooperation program with EADS Astrium. The second satellite ALSAT-2B will be integrated by ASAL engineers in the Satellite Development Center (CDS) at Oran in Algeria. On 12th July 2010, Algeria has launched ALSAT-2A onboard an Indian rocket PSLV-C15 from the Sriharikota launch base, Chennaï. ALSAT-2A is the first Earth observation satellite of the AstroSat-100 family; the design is based on the Myriade platform and comprising the first flight model of the New Astrosat Observation Modular Instrument (NAOMI). This Instrument offers a 2.5m ground resolution for the PAN channel and a 10m ground resolution for four multi-spectral channels which provides high imaging quality. The operations are performed from ALSAT-2 ground segment located in Ouargla (Algeria) and after the test phase ALSAT-2A provides successful images. ALSAT-2A electrical power subsystem (EPS) is composed of a Solar Array Generator (SAG ), a Li-ion battery dedicated to power storage and energy source during eclipse or high consumption phases and a Power Conditioning and Distribution Unit (PCDU). This paper focuses primarily on ALSAT-2A electrical power subsystem behavior during Launch and Early OPeration (LEOP) as well as In Orbit Test (IOT). The telemetry data related to the SAG voltage, current and temperature will be analyzed in addition to battery temperature, voltage, charge and discharge current. These parameters will be studied in function of satellite power consumption.

  16. NASA-GSFC ionospheric corrections to satellite tracking data

    Science.gov (United States)

    Schmid, P. E.; Bent, R. B.; Llewellyn, S. K.; Nesterczuk, G.; Rangaswamy, S.

    1971-01-01

    An overview is presented of the development, verification, and recent implementation of the NASA-GSFC ionospheric model for satellite tracking data corrections. This model was incorporated into the Goddard Trajectory Determination System which is providing continuous trajectory computation support for the lunar orbiting Radio Astronomy Explorer-B launched on 10 June 1973.

  17. Cultures in orbit: Satellite technologies, global media and local practice

    Science.gov (United States)

    Parks, Lisa Ann

    Since the launch of Sputnik in 1957, satellite technologies have had a profound impact upon cultures around the world. "Cultures in Orbit" examines these seemingly disembodied, distant relay machines in relation to situated social and cultural processes on earth. Drawing upon a range of materials including NASA and UNESCO documents, international satellite television broadcasts, satellite 'development' projects, documentary and science fiction films, remote sensing images, broadcast news footage, World Wide Web sites, and popular press articles I delineate and analyze a series of satellite mediascapes. "Cultures in Orbit" analyzes uses of satellites for live television relay, surveillance, archaeology and astronomy. The project examines such satellite media as the first live global satellite television program Our World, Elvis' Aloha from Hawaii concert, Aboriginal Australian satellite programs, and Star TV's Asian music videos. In addition, the project explores reconnaissance images of mass graves in Bosnia, archaeological satellite maps of Cleopatra's underwater palace in Egypt, and Hubble Space Telescope images. These case studies are linked by a theoretical discussion of the satellite's involvement in shifting definitions of time, space, vision, knowledge and history. The satellite fosters an aesthetic of global realism predicated on instantaneous transnational connections. It reorders linear chronologies by revealing traces of the ancient past on the earth's surface and by searching in deep space for the "edge of time." On earth, the satellite is used to modernize and develop "primitive" societies. Satellites have produced new electronic spaces of international exchange, but they also generate strategic maps that advance Western political and cultural hegemony. By technologizing human vision, the satellite also extends the epistemologies of the visible, the historical and the real. It allows us to see artifacts and activities on earth from new vantage points

  18. Former astronaut Armstrong witnesses STS-83 launch

    Science.gov (United States)

    1997-01-01

    Apollo l1 Commander Neil A. Armstrong and his wife, Carol, were among the many special NASA STS-83 launch guests who witnessed the liftoff of the Space Shuttle Columbia April 4 at the Banana Creek VIP Viewing Site at KSC. Columbia took off from Launch Pad 39A at 2:20:32 p.m. EST to begin the 16-day Microgravity Science Laboratory-1 (MSL-1) mission.

  19. Space Launching Site Protection against Lightning Hazards

    OpenAIRE

    Issac, F.; Bachelier, E.; Prost, D.; Enjalbert, V.; Mohedano, L.

    2012-01-01

    International audience; A launching pad, because of its activity, is particularly sensitive to the risk of lightning. The use of Standard IEC62305 "Protection against lightning" establishes the general framework for the Lightning Protection System (LPS). However, the specific activity of a launching pad requires special analysis on specific points of the LPS. Indeed, it is necessary to take into account the lightning conductor system particularity on the one hand, and the launcher electromagn...

  20. Atmospheric environment for ASTP (SA-210) launch

    Science.gov (United States)

    Johnson, D. L.

    1976-01-01

    A summary is presented of selected atmospheric conditions observed near ASTP/SA-210 launch time on July 15, 1975, at Kennedy Space Center, Florida. Values of ambient pressure, temperature, moisture, ground winds, visual observations (cloud), density, index of refraction, and wind/wind shear aloft are included. A final meteorological data tape for the ASTP launch, consisting of wind and thermodynamic parameters versus altitude, has been constructed.

  1. Comparison of Two Recent Launch Abort Platforms

    Science.gov (United States)

    Dittemore, Gary D.; Harding, Adam

    2011-01-01

    The development of new and safer manned space vehicles is a top priority at NASA. Recently two different approaches of how to accomplish this mission of keeping astronauts safe was successfully demonstrated. With work already underway on an Apollo-like launch abort system for the Orion Crew Exploration Vehicle (CEV), an alternative design concept named the Max Launch Abort System, or MLAS, was developed as a parallel effort. The Orion system, managed by the Constellation office, is based on the design of a single solid launch abort motor in a tower positioned above the capsule. The MLAS design takes a different approach placing the solid launch abort motor underneath the capsule. This effort was led by the NASA Engineering and Safety Center (NESC). Both escape systems were designed with the Ares I Rocket as the launch vehicle and had the same primary requirement to safely propel a crew module away from any emergency event either on the launch pad or during accent. Beyond these two parameters, there was little else in common between the two projects, except that they both concluded in successful launches that will further promote the development of crew launch abort systems. A comparison of these projects from the standpoint of technical requirements; program management and flight test objectives will be done to highlight the synergistic lessons learned by two engineers who worked on each program. This comparison will demonstrate how the scope of the project architecture and management involvement in innovation should be tailored to meet the specific needs of the system under development.

  2. National Security Space Launch at a Crossroads

    Science.gov (United States)

    2016-05-13

    critical” breach occurs when the program acquisition or the procurement unit cost increases 25% or more over the current baseline estimate or 50% or more...Force’s ability to continue with its current three-phase EELV acquisition strategy. These include ongoing concerns over program and launch costs ...space for national security missions. The current strategy for the EELV (Evolved Expendable Launch Vehicle) program dates from the 1990s and has since

  3. Attitude control of a small satellite using magnetic bearing momentum wheel

    OpenAIRE

    Terui, Fuyuto; Nakajima, Atsushi; 照井 冬人; 中島 厚

    1996-01-01

    An attitude controller for a 50 kg-class micro satellite which could be launched by H-2 rocket as a piggyback payload of a main satellite is considered. The survey of the proposals of the mission using a micro satellite from national institutes, universities and private companies shows that the development of a small, light and inexpensive three axis attitude controller is widely expected. One of the candidate configurations for such an attitude controller is bias momentum control using a mag...

  4. Clouds and the Earth's Radiant Energy System (CERES) Visualization Single Satellite Footprint (SSF) Plot Generator

    Science.gov (United States)

    Barsi, Julia A.

    1995-01-01

    The first Clouds and the Earth's Radiant Energy System (CERES) instrument will be launched in 1997 to collect data on the Earth's radiation budget. The data retrieved from the satellite will be processed through twelve subsystems. The Single Satellite Footprint (SSF) plot generator software was written to assist scientists in the early stages of CERES data analysis, producing two-dimensional plots of the footprint radiation and cloud data generated by one of the subsystems. Until the satellite is launched, however, software developers need verification tools to check their code. This plot generator will aid programmers by geolocating algorithm result on a global map.

  5. A Covert Disruptive Technology: Test and Development of the Corona Satellite

    Science.gov (United States)

    Peebles, Curtis

    2008-01-01

    The launching by the Soviet Union of the Sputnik satellite in 19457 was an impetuous to the United States. The Intercontinental ballistic Missile (ICBM) that launched the Earth's first satellite, could have been armed with a nuclear warhead, that could destroy an American city. The primary intelligence requirement that the US had was to determine the actual size of the Soviet missile program. To this end, a covert, high-risk photoreconnaissance satellite was developed. The code name of this program was "Corona." This article describes the trials and eventual successes of the Corona program.

  6. A Covert Disruptive Technology: Test and Development of the Corona Satellite

    Science.gov (United States)

    Peebles, Curtis

    2008-01-01

    The launching by the Soviet Union of the Sputnik satellite in 19457 was an impetuous to the United States. The Intercontinental ballistic Missile (ICBM) that launched the Earth's first satellite, could have been armed with a nuclear warhead, that could destroy an American city. The primary intelligence requirement that the US had was to determine the actual size of the Soviet missile program. To this end, a covert, high-risk photoreconnaissance satellite was developed. The code name of this program was "Corona." This article describes the trials and eventual successes of the Corona program.

  7. Copernicus Sentinel-1 Satellite And C-SAR Instrument

    Science.gov (United States)

    Panetti, Aniceto; Rostan, Friedhelm; L'Abbate, Michelangelo; Bruno, Claudio; Bauleo, Antonio; Catalano, Toni; Cotogni, Marco; Galvagni, Luigi; Pietropaolo, Andrea; Taini, Giacomo; Venditti, Paolo; Huchler, Markus; Torres, Ramon; Lokaas, Svein; Bibby, David

    2013-12-01

    The Copernicus Sentinel-1 Earth Radar Observatory, a mission funded by the European Union and developed by ESA, is a constellation of two C-band radar satellites. The satellites have been conceived to be a continuous and reliable source of C-band SAR imagery for operational applications such as mapping of global landmasses, coastal zones and monitoring of shipping routes. The Sentinel-1 satellites are built by an industrial consortium led by Thales Alenia Space Italia as Prime Contractor and with Astrium GmbH as SAR Instrument Contractor. The paper describes the general satellite architecture, the spacecraft subsystems, AIT flow and the satellite key performances. It provides also an overview on the C-SAR Instrument, its development status and pre- launch SAR performance prediction.

  8. Analysis and optimization of an air-launch-to-orbit separation

    Science.gov (United States)

    Sohier, Henri; Piet-Lahanier, Helene; Farges, Jean-Loup

    2015-03-01

    In an air-launch-to-orbit, a space rocket is launched from a carrier aircraft. Air-launch-to-orbit appears as particularly interesting for nano- and microsatellites which are generally launched as secondary loads, that is, placed in the conventional launch vehicle's payload section with a larger primary satellite. In an air-launch-to-orbit, a small satellite can be launched alone as a primary load, away from a carrier aircraft, aboard a smaller rocket vehicle, and in doing so, benefit from more flexible dates and trajectories. One of the most important phases of the mission is the separation between the carrier aircraft and the space rocket. A flight simulator including a large number of factors of uncertainties has been especially developed to study the separation, and a safety criteria has been defined with respect to store collision avoidance. It is used for a sensitivity analysis and an optimization of the possible trajectories. The sensitivity analysis first requires a screening method to select unessential factors that can be held constant. The Morris method is amongst the most popular screening methods. It requires limited calculations, but may result in keeping constant an essential factor which would greatly affect the results of the sensitivity analysis. This paper shows that this risk can be important in spite of recent improvements of the Morris method. It presents an adaptation of this method which divides this risk by a factor of ten on a standard test function. It is based on the maximum of the elementary effects instead of their average. The method focuses the calculations on the factors with a low impact, checking the convergence of this set of factors, and uses two different factor variations instead of one. This adaptation of the Morris method is used to limit the amount of the air-launch-to-orbit simulations and simplify the uncertainty domain for analysis by Sobol's method. The aerodynamic perturbations due to wind, the parameters defining the

  9. Toward a new spacecraft optimal design lifetime? Impact of marginal cost of durability and reduced launch price

    Science.gov (United States)

    Snelgrove, Kailah B.; Saleh, Joseph Homer

    2016-10-01

    The average design lifetime of satellites continues to increase, in part due to the expectation that the satellite cost per operational day decreases monotonically with increased design lifetime. In this work, we challenge this expectation by revisiting the durability choice problem for spacecraft in the face of reduced launch price and under various cost of durability models. We first provide a brief overview of the economic thought on durability and highlight its limitations as they pertain to our problem (e.g., the assumption of zero marginal cost of durability). We then investigate the merging influence of spacecraft cost of durability and launch price, and we identify conditions that give rise cost-optimal design lifetimes that are shorter than the longest lifetime technically achievable. For example, we find that high costs of durability favor short design lifetimes, and that under these conditions the optimal choice is relatively robust to reduction in launch prices. By contrast, lower costs of durability favor longer design lifetimes, and the optimal choice is highly sensitive to reduction in launch price. In both cases, reduction in launch prices translates into reduction of the optimal design lifetime. Our results identify a number of situations for which satellite operators would be better served by spacecraft with shorter design lifetimes. Beyond cost issues and repeat purchases, other implications of long design lifetime include the increased risk of technological slowdown given the lower frequency of purchases and technology refresh, and the increased risk for satellite operators that the spacecraft will be technologically obsolete before the end of its life (with the corollary of loss of value and competitive advantage). We conclude with the recommendation that, should pressure to extend spacecraft design lifetime continue, satellite manufacturers should explore opportunities to lease their spacecraft to operators, or to take a stake in the ownership

  10. Space Launch System for Exploration and Science

    Science.gov (United States)

    Klaus, K.

    2013-12-01

    Introduction: The Space Launch System (SLS) is the most powerful rocket ever built and provides a critical heavy-lift launch capability enabling diverse deep space missions. The exploration class vehicle launches larger payloads farther in our solar system and faster than ever before. The vehicle's 5 m to 10 m fairing allows utilization of existing systems which reduces development risks, size limitations and cost. SLS lift capacity and superior performance shortens mission travel time. Enhanced capabilities enable a myriad of missions including human exploration, planetary science, astrophysics, heliophysics, planetary defense and commercial space exploration endeavors. Human Exploration: SLS is the first heavy-lift launch vehicle capable of transporting crews beyond low Earth orbit in over four decades. Its design maximizes use of common elements and heritage hardware to provide a low-risk, affordable system that meets Orion mission requirements. SLS provides a safe and sustainable deep space pathway to Mars in support of NASA's human spaceflight mission objectives. The SLS enables the launch of large gateway elements beyond the moon. Leveraging a low-energy transfer that reduces required propellant mass, components are then brought back to a desired cislunar destination. SLS provides a significant mass margin that can be used for additional consumables or a secondary payloads. SLS lowers risks for the Asteroid Retrieval Mission by reducing mission time and improving mass margin. SLS lift capacity allows for additional propellant enabling a shorter return or the delivery of a secondary payload, such as gateway component to cislunar space. SLS enables human return to the moon. The intermediate SLS capability allows both crew and cargo to fly to translunar orbit at the same time which will simplify mission design and reduce launch costs. Science Missions: A single SLS launch to Mars will enable sample collection at multiple, geographically dispersed locations and a

  11. Nigeria's Satellite Programme Development: Prospects and Challenges

    Science.gov (United States)

    Akinyede, Joseph

    Nigeria's desire to maximize the benefits of space technology for its sustainable development, has become a reality with the establishment of the National Space Research and Development Agency (NASRDA) in May 1999 and the approval of the national Space Policy and Programmes in July 2001. In November, 2000, the Federal Government took a bold step with the signing of an agreement with the Surrey Satellite Technology Limited (SSTL) of United Kingdom (UK) for the design, construction and launch of a medium resolution micro-satellite - NigeriaSat-1 with a Ground Sampling Distance of thirty-two (32) meters. The agreement also covers the Know-How-Technology-Training (KHTT) to Nigerian Engineers and Scientists for a period of 18th months at SSTL‘s facility in the U.K.. NigeriaSat-1 was successfully launched into Leo Earth Orbit on 27th September, 2003. NigeriaSat- 1 is one of the five (5) satellites belonging to Nigeria, Algeria, Turkey, United Kingdom and China being operated in a Disaster Monitoring Constellation (DMC). The launch of NigeriaSat-1 has promoted access to information which has become a strategy for mass socio-economic development, as information underscores all developmental effort be it in education, provision of health services, marketing, construction industry, tourism, defense, etc. As a follow-up to the successful launch of NigeriaSat-1, the government of Nigeria started the implementation of a Nigerian communication satellite (NigcomSat-1) to address the problem of communication which is the greatest drawbacks to the socio-economic development of the country, particularly in the areas of rural telephone, tele-education, tele-medicine, egovernment, e-commerce and real-time monitoring services. NigcomSat-1, which carries 40- hybrid transponders in the C, KU, KA and L bands, has a 15 years life span and coverage of the African continent, Middle East and part of Europe was launched in May 2007. To satisfy geospatial data needs in sectors such as survey

  12. Digital frequency control of satellite frequency standards. [Defense Navigation Satellites

    Science.gov (United States)

    Nichols, S. A.

    1973-01-01

    In the Frequency and Time Standard Development Program of the TIMATION System, a new miniaturized rubidium vapor frequency standard has been tested and analyzed for possible use on the TIMATION 3A launch, as part of the Defense Navigation Satellite Development Program. The design and construction of a digital frequency control was required to remotely control this rubidium vapor frequency standard as well as the quartz oscillator in current use. This control must be capable of accepting commands from a satellite telemetry system, verify that the correct commands have been sent and control the frequency to the requirements of the system. Several modifications must be performed to the rubidium vapor frequency standard to allow it to be compatible with the digital frequency control. These include the addition of a varactor to voltage tune the coarse range of the flywheel oscillator, and a modification to supply the C field current externally. The digital frequency control for the rubidium vapor frequency standard has been successfully tested in prototype form.

  13. Preface: BeiDou Navigation Satellite System (BDS)/GNSS+: Recent progress and new applications

    Science.gov (United States)

    Jin, Shuanggen

    2017-02-01

    Nowadays, the new China's BeiDou Navigation Satellite System (BDS) has been developed well. At the end of 2016, over 23 BDS satellites were launched, including five geostationary Earth orbit (GEO) satellites, five inclined geosynchronous orbit (IGSO) satellites and nine medium Earth orbit (MEO) satellites. The current BDS service covers China and most Asia-Pacific regions with accuracy of better than 10 m in positioning, 0.2 m/s in velocity and 50 ns in timing. The BDS with global coverage will be completely established by 2020 with five GEO satellites and 30 MEO satellites. The main function of BDS is the positioning, navigation and timing (PNT) as well as short message communications. Together with the United States' GPS, Russia's GLONASS and the European Union's Galileo system as well as other regional augmentation systems, more new applications of multi-Global Navigation Satellite Systems (GNSS) will be exploited and realized in the next decades.

  14. Strategy of Khrunichev's Launch Vehicles Further Evolution

    Science.gov (United States)

    Medvedev, A. A.; Kuzin, A. I.; Karrask, V. K.

    2002-01-01

    vehicles and it is concerned with a further evolution of its launcher fleet in order to meet arising demands of their services customers. Continuing to provide an operation of current "Proton" heavy launch vehicle and "Rockot" small launch vehicle, Khrunichev is carrying out a permanent improvement of these launchers as well as is developing new advanced launch systems. Thus, the `Proton' just has the improved "Proton-M" version, which was successfully tested in a flight, while an improvement of the "Rockot" is provided by a permanent modernization of its "Breeze-KM" upper stage and a payload fairing. Enhancing of the "Proton/Proton-M's" lift capabilities and flexibility of operation is being provided by introduction of advanced upper stages, the "Breeze- M", which was just put into service, and KVRB being in the development. "Angara-1.1" small launcher is scheduled to a launch in 2003. A creation of this family foresees not only a range of small, medium and heavy launch vehicles based on a modular principle of design but also a construction of high-automated launch site at the Russian Plesetsk spaceport. An operation of the "Angara" family's launchers will allow to inject payloads of actually all classes from Russian national territory into all range of applicable orbits with high technical and economic indices. ecological safety of drop zones, Khrunichev is developing the "Baikal" fly-back reusable booster. This booster would replace expendable first stages of small "Angaras" and strap-ons of medium/heavy launchers, which exert a most influence on the Earth's environment. intercontinental ballistic missiles to current and advanced space launch vehicles of various classes. A succession of the gained experience and found technological solutions are shown.

  15. System Critical Design Audit (CDA). Books 1, 2 and 3; [Small Satellite Technology Initiative (SSTI Lewis Spacecraft Program)

    Science.gov (United States)

    1995-01-01

    Small Satellite Technology Initiative (SSTI) Lewis Spacecraft Program is evaluated. Spacecraft integration, test, launch, and spacecraft bus are discussed. Payloads and technology demonstrations are presented. Mission data management system and ground segment are also addressed.

  16. Post-Decadal White Paper: A Dual-Satellite Dark-Energy/Microlensing NASA-ESA Mission

    CERN Document Server

    Gould, Andrew

    2010-01-01

    A confluence of scientific, financial, and political factors imply that launching two simpler, more narrowly defined dark-energy/microlensing satellites will lead to faster, cheaper, better (and more secure) science than the present EUCLID and WFIRST designs. The two satellites, one led by ESA and the other by NASA, would be explicitly designed to perform complementary functions of a single, dual-satellite dark-energy/microlensing ``mission''. One would be a purely optical wide-field camera, with large format and small pixels, optimized for weak-lensing, which because of its simple design, could be launched by ESA on relatively short timescales. The second would be a purely infrared satellite with marginally-sampled or under-sampled pixels, launched by NASA. Because of budget constraints, this would be launched several years later. The two would complement one another in 3 dark energy experiments (weak lensing, baryon oscillations, supernovae) and also in microlensing planet searches. Signed international agr...

  17. Galileo satellite antenna modeling

    Science.gov (United States)

    Steigenberger, Peter; Dach, Rolf; Prange, Lars; Montenbruck, Oliver

    2015-04-01

    The space segment of the European satellite navigation system Galileo currently consists of six satellites. Four of them belong to the first generation of In-Orbit Validation (IOV) satellites whereas the other two are Full Operational Capability (FOC) satellites. High-precision geodetic applications require detailed knowledge about the actual phase center of the satellite and receiver antenna. The deviation of this actual phase center from a well-defined reference point is described by phase center offsets (PCOs) and phase center variations (PCVs). Unfortunately, no public information is available about the Galileo satellite antenna PCOs and PCVs, neither for the IOV, nor the FOC satellites. Therefore, conventional values for the IOV satellite antenna PCOs have been adopted for the Multi-GNSS experiment (MGEX) of the International GNSS Service (IGS). The effect of the PCVs is currently neglected and no PCOs for the FOC satellites are available yet. To overcome this deficiency in GNSS observation modeling, satellite antenna PCOs and PCVs are estimated for the Galileo IOV satellites based on global GNSS tracking data of the MGEX network and additional stations of the legacy IGS network. Two completely independent solutions are computed with the Bernese and Napeos software packages. The PCO and PCV values of the individual satellites are analyzed and the availability of two different solutions allows for an accuracy assessment. The FOC satellites are built by a different manufacturer and are also equipped with another type of antenna panel compared to the IOV satellites. Signal transmission of the first FOC satellite has started in December 2014 and activation of the second satellite is expected for early 2015. Based on the available observations PCO estimates and, optionally PCVs of the FOC satellites will be presented as well. Finally, the impact of the new antenna model on the precision and accuracy of the Galileo orbit determination is analyzed.

  18. Advantages of Hybrid Global Navigation Satellite Systems

    Directory of Open Access Journals (Sweden)

    Asim Bilajbegović

    2007-05-01

    Full Text Available In a decision-making situation, what kind of GPS equipment to purchase, one always has a dilemma, tobuy hybrid (GPS+GLONASS or only GPS receivers? In the case of completeness of the GLONASS satellite system, this dilemma probably would not have existed. The answer to this dilemma is given in the present paper, but for the constellation of the GLONASS satellites in summer 2006 (14 satellites operational. Due to the short operational period of these satellites (for example GLONASS-M, 5 years, and not launching new ones, at this moment (February 25, 2007, only 10 satellites are operational. For the sake of research and giving answers to these questions, about 252 RTK measurements have been done using (GPS and GNSS receivers, on points with different obstructions of horizon. Besides that, initialisation time has been investigated for both systems from about 480 measurements, using rover's antenna with metal cover, during a time interval of 0.5, 2 and 5 seconds. Moreover, accuracy, firmware declared accuracy and redundancy of GPS and GNSS RTK measurements have been investigating.  

  19. Use of Advanced Solar Cells for Commercial Communication Satellites

    Science.gov (United States)

    Bailey, Sheila G.; Landis, Geoffrey A.

    1995-01-01

    The current generation of communications satellites are located primarily in geosynchronous Earth orbit (GEO). Over the next decade, however, a new generation of communications satellites will be built and launched, designed to provide a world-wide interconnection of portable telephones. For this mission, the satellites must be positioned in lower polar and near-polar orbits. To provide complete coverage, large numbers of satellites will be required. Because the required number of satellites decreases as the orbital altitude is increased, fewer satellites would be required if the orbit chosen were raised from low to intermediate orbit. However, in intermediate orbits, satellites encounter significant radiation due to trapped electrons and protons. Radiation tolerant solar cells may be necessary to make such satellites feasible. We analyze the amount of radiation encountered in low and intermediate polar orbits at altitudes of interest to next-generation communication satellites, calculate the expected degradation for silicon, GaAs, and InP solar cells, and show that the lifetimes can be significantly increased by use of advanced solar cells.

  20. Flight Testing of Wireless Networking for Nanosat Launch Vehicles Project

    Data.gov (United States)

    National Aeronautics and Space Administration — The innovation proposed here addresses the testing and evaluation of wireless networking technologies for small launch vehicles by leveraging existing nanosat launch...

  1. Launch Vehicle Demonstrator Using Shuttle Assets

    Science.gov (United States)

    Threet, Grady E., Jr.; Creech, Dennis M.; Philips, Alan D.; Water, Eric D.

    2011-01-01

    The Marshall Space Flight Center Advanced Concepts Office (ACO) has the leading role for NASA s preliminary conceptual launch vehicle design and performance analysis. Over the past several years the ACO Earth-to-Orbit Team has evaluated thousands of launch vehicle concept variations for a multitude of studies including agency-wide efforts such as the Exploration Systems Architecture Study (ESAS), Constellation, Heavy Lift Launch Vehicle (HLLV), Heavy Lift Propulsion Technology (HLPT), Human Exploration Framework Team (HEFT), and Space Launch System (SLS). NASA plans to continue human space exploration and space station utilization. Launch vehicles used for heavy lift cargo and crew will be needed. One of the current leading concepts for future heavy lift capability is an inline one and a half stage concept using solid rocket boosters (SRB) and based on current Shuttle technology and elements. Potentially, the quickest and most cost-effective path towards an operational vehicle of this configuration is to make use of a demonstrator vehicle fabricated from existing shuttle assets and relying upon the existing STS launch infrastructure. Such a demonstrator would yield valuable proof-of-concept data and would provide a working test platform allowing for validated systems integration. Using shuttle hardware such as existing RS-25D engines and partial MPS, propellant tanks derived from the External Tank (ET) design and tooling, and four-segment SRB s could reduce the associated upfront development costs and schedule when compared to a concept that would rely on new propulsion technology and engine designs. There are potentially several other additional benefits to this demonstrator concept. Since a concept of this type would be based on man-rated flight proven hardware components, this demonstrator has the potential to evolve into the first iteration of heavy lift crew or cargo and serve as a baseline for block upgrades. This vehicle could also serve as a demonstration

  2. Operational Analysis in the Launch Environment

    Science.gov (United States)

    James, George; Kaouk, Mo; Cao, Tim; Fogt, Vince; Rocha, Rodney; Schultz, Ken; Tucker, Jon-Michael; Rayos, Eli; Bell,Jeff; Alldredge, David; Howsman, Tom

    2012-01-01

    The launch environment is a challenging regime to work due to changing system dynamics, changing environmental loading, joint compression loads that cannot be easily applied on the ground, and control effects. Operational testing is one of the few feasible approaches to capture system level dynamics since ground testing cannot reproduce all of these conditions easily. However, the most successful applications of Operational Modal Testing involve systems with good stationarity and long data acquisition times. This paper covers an ongoing effort to understand the launch environment and the utility of current operational modal tools. This work is expected to produce a collection of operational tools that can be applied to non-stationary launch environment, experience dealing with launch data, and an expanding database of flight parameters such as damping. This paper reports on recent efforts to build a software framework for the data processing utilizing existing and specialty tools; understand the limits of current tools; assess a wider variety of current tools; and expand the experience with additional datasets as well as to begin to address issues raised in earlier launch analysis studies.

  3. Quality function deployment in launch operations

    Science.gov (United States)

    Portanova, P. L.; Tomei, E. J., Jr.

    1990-11-01

    The goal of the Advanced Launch System (ALS) is a more efficient launch capability that provides a highly reliable and operable system at substantially lower cost than current launch systems. Total Quality Management (TQM) principles are being emphasized throughout the ALS program. A continuous improvement philosophy is directed toward satisfying users' and customer's requirements in terms of quality, performance, schedule, and cost. Quality Function Deployment (QFD) is interpreted as the voice of the customer (or user), and it is an important planning tool in translating these requirements throughout the whole process of design, development, manufacture, and operations. This report explores the application of QFD methodology to launch operations, including the modification and addition of events (operations planning) in the engineering development cycle, and presents an informal status of study results to date. QFD is a technique for systematically analyzing the customer's (Space Command) perceptions of what constitutes a highly reliable and operable system and functionally breaking down those attributes to identify the critical characteristics that determine an efficient launch system capability. In applying the principle of QFD, a series of matrices or charts are developed with emphasis on the one commonly known as the House of Quality (because of its roof-like format), which identifies and translates the most critical information.

  4. Vibro-acoustic launch protection experiment (VALPE)

    Science.gov (United States)

    Henderson, Benjamin; Gerhart, Charlotte; Lane, Steven; Jensen, Elizabeth; Griffin, Steve; Lazzaro, Anthony

    2003-10-01

    Launch acoustic and vibration loads have the potential to damage sensitive payloads within a payload fairing, often requiring more structural mass to withstand these loads than would otherwise be necessary to survive launch. Experiments demonstrating several vibro-acoustic mitigation technologies developed by AFRL/VS and its contractors flew on the Vibro-Acoustic Launch Protection Experiment 2 (VALPE-2) aboard a Terrier-Improved Orion sounding rocket from Wallops Island Flight Facility in August 2003. Flight data collected in November 2002 from a nearly identical launch (VALPE-1) was used to characterize the fairing environment for comparison. Preparations for the flight experiments are discussed along with the performance of the various experiments in flight. The several experiments include an Adaptive Vibro-Acoustic Device (AVAD) to mitigate acoustic loads, an active/passive hybrid vibration isolation system using voice-coil actuation and a ShockRing passive component, a voice-coil regenerative electronics vibration isolation system to absorb a portion of the vibration energy during launch and use it to power an active isolation system during a staging event, and a ChamberCore composite fairing with implications for passive acoustic performance.

  5. Arianespace: Launch Solutions for Scientific Endeavours

    Science.gov (United States)

    Le Gall, J.-Y.

    Arianespace was established 25 years ago and currently stands as the European operator offering launch services from the Guiana Space Centre CSG according to the mandate given by the European Member States through the European Space Agency ESA While guaranteeing access to space through commercially sustained capabilities Arianespace is first and foremost dedicated to satisfy scientific requests to orbit any mission providing reliable and available market-priced solutions to the scientific community In this regard among the 232 spacecraft deployed by Arianespace include all European space observatories such as Giotto 1985 Hipparcos 1989 ISO 1995 XMM 1999 Envisat 2002 Mars Express 2003 Rosetta 2004 Venus Express 2005 This longstanding heritage illustrates the Arianespace steady commitment toward its scientific customers to tailor launch solutions according to their requirements Arianespace operates a fleet of launch vehicles optimized for each and every scientific mission including the heavy-lift Ariane 5 the mid-size Soyuz currently launched from Baikonur and available from CSG beginning in 2008 and the light Vega starting in 2008 More than a launch Arianespace provides consummate and adapted solutions paving the way for cost-effective and target-oriented scientific endeavours

  6. Satellite-Delivered Learning.

    Science.gov (United States)

    Arnall, Gail C.

    1987-01-01

    Discusses the application of satellite information delivery to training. Describes a new trend, horizontal programming. Also discusses vertical programming and in-house production of training materials. Lists vendors of satellite-based training. (CH)

  7. GPS Satellite Simulation Facility

    Data.gov (United States)

    Federal Laboratory Consortium — The GPS satellite simulation facility consists of a GPS satellite simulator controlled by either a Silicon Graphics Origin 2000 or PC depending upon unit under test...

  8. Satellite Tags- Hawaii EEZ

    Data.gov (United States)

    National Oceanic and Atmospheric Administration, Department of Commerce — Satellite tagging was implemented in 2013. Satellite tagging is conducted using a Dan Inject air rifle and deployment arrows designed by Wildlife Computers. Two...

  9. Satellite communication engineering

    CERN Document Server

    Kolawole, Michael Olorunfunmi

    2013-01-01

    An undeniably rich and thorough guide to satellite communication engineering, Satellite Communication Engineering, Second Edition presents the fundamentals of information communications systems in a simple and succinct way. This book considers both the engineering aspects of satellite systems as well as the practical issues in the broad field of information transmission. Implementing concepts developed on an intuitive, physical basis and utilizing a combination of applications and performance curves, this book starts off with a progressive foundation in satellite technology, and then moves on

  10. High-precision satellite relative-trajectory simulating servosystem for inter-satellite laser communications

    Science.gov (United States)

    Zhang, Lei; Liu, Liren; Luan, Zhu; Liu, Hongzhan; Xu, Rongwei

    2004-10-01

    Because PAT (pointing-acquisition-tracking) parameters and integrated technical specifications of laser communication terminals for inter-satellite link must be pre-verified and assessed thoroughly on a ground-based test-bed before launched into the space, it is necessary to develop a system as a primary part of the test bed to simulate the relative trajectory between the satellites. In this paper, an original high-precision satellite relative-trajectory simulating servosystem is introduced in detail as well as its structures and characteristics. The system is used to simulate the motion of relative-trajectory between satellites in different orbits. The principle of the system is to import the data of two satellites" orbits into a computer-based control system in advance. After processed and analyzed, the data is transformed into the angular displacement of the servomotor which drives the gimbal directly. The angular displacement of the two axes of the gimbal can simulate precisely the relative-trajectory, namely elevation angle and azimuth angle of the two satellites in communication. A laser communication terminal mounted on the gimbal then performs the PAT mechanisms to evaluate the system"s capacity.

  11. Effectiveness of Loan Guarantees versus Tax Incentives for Space Launch Ventures

    Science.gov (United States)

    Scottoline, S.; Coleman, R.

    1999-01-01

    Over the course of the past few years, several new and innovative fully or partiailly reusable launch vehicle designs have been initiated with the objective of reducing the cost of space transportation. These new designs are in various stages hardware development for technology and system demonstrators. The larger vehicles include the Lockheed Martin X-33 technology demonstrator for VentureStar and the Space Access launcher. The smaller launcher ventures include Kelly Space and Technology and Rotary Rocket Company. A common denominator between the new large and small commercial launch systems is the ability to obtain project financing and at an affordable cost. Both are having or will have great difficulty in obtaining financing in the capital markets because of the dollar amounts and the risk involved. The large established companies are pursuing multi-billion dollar developments which are a major challenge to finance because of the size and risk of the projects. The smaller start-up companies require less capital for their smaller systems, however, their lack of corporate financial muscle and launch vehicle track record results in a major challenge to obtain financing also because of high risk. On Wall Street, new launch system financing is a question of market, technical, organizational, legal/regulatory and financial risk. The current limit of acceptable financial risk for Space businesses on Wall Street are the telecommunications and broadcast satellite projects, of which many in number are projected for the future. Tbc recent problems with Iridium market and financial performance are casting a long shadow over new satellite project financing, making it increasingly difficult for the new satellite projects to obtain needed financing.

  12. Cyber security with radio frequency interferences mitigation study for satellite systems

    Science.gov (United States)

    Wang, Gang; Wei, Sixiao; Chen, Genshe; Tian, Xin; Shen, Dan; Pham, Khanh; Nguyen, Tien M.; Blasch, Erik

    2016-05-01

    Satellite systems including the Global Navigation Satellite System (GNSS) and the satellite communications (SATCOM) system provide great convenience and utility to human life including emergency response, wide area efficient communications, and effective transportation. Elements of satellite systems incorporate technologies such as navigation with the global positioning system (GPS), satellite digital video broadcasting, and information transmission with a very small aperture terminal (VSAT), etc. The satellite systems importance is growing in prominence with end users' requirement for globally high data rate transmissions; the cost reduction of launching satellites; development of smaller sized satellites including cubesat, nanosat, picosat, and femtosat; and integrating internet services with satellite networks. However, with the promising benefits, challenges remain to fully develop secure and robust satellite systems with pervasive computing and communications. In this paper, we investigate both cyber security and radio frequency (RF) interferences mitigation for satellite systems, and demonstrate that they are not isolated. The action space for both cyber security and RF interferences are firstly summarized for satellite systems, based on which the mitigation schemes for both cyber security and RF interferences are given. A multi-layered satellite systems structure is provided with cross-layer design considering multi-path routing and channel coding, to provide great security and diversity gains for secure and robust satellite systems.

  13. Geodetic Secor Satellite

    Science.gov (United States)

    1974-06-01

    simple, and had low-power lem. 17 14. Satellite Orientation . The satellite was designed to maintain a constant relationship between the antenna...the same satellite orientation . Further considerations were Th oscillations, however, when higher orbital ranges (500-2500 nautical miles) -, 3 a

  14. TC-2 Satellite Delivered

    Institute of Scientific and Technical Information of China (English)

    2005-01-01

    On April 18, 2005, TC-2, the second satellite of Double Star Program (DSP), which was jointly developed by CNSA and ESA, was approved to be delivered to the user after the on-board test and trial operation. The satellite is working well and the performance can meet the user's need. The satellite has collected large amount of valuable scientific data

  15. Direct launch using the electric rail gun

    Science.gov (United States)

    Barber, J. P.

    1983-01-01

    The concept explored involves using a large single stage electric rail gun to achieve orbital velocities. Exit aerodynamics, launch package design and size, interior ballistics, system and component sizing and design concepts are treated. Technology development status and development requirements are identified and described. The expense of placing payloads in Earth orbit using conventional chemical rockets is considerable. Chemical rockets are very inefficient in converting chemical energy into payload kinetic energy. A rocket motor is relatively expensive and is usually expended on each launch. In addition specialized and expensive forms of fuel are required. Gun launching payloads directly to orbit from the Earth's surface is a possible alternative. Guns are much more energy efficient than rockets. The high capital cost of the gun installation can be recovered by reusing it over and over again. Finally, relatively inexpensive fuel and large quantities of energy are readily available to a fixed installation on the Earth's surface.

  16. The continuing challenge of electromagnetic launch

    Energy Technology Data Exchange (ETDEWEB)

    Cowan, M.; Cnare, E.C.; Duggin, B.W.; Kaye, R.J.; Marder, B.M.; Shokair, I.R.

    1993-07-01

    Interest in launching payloads through the atmosphere to ever higher velocity is robust. For hundreds of years, guns and rockets have been improved for this purpose until they are now considered to be near to their performance limits. While the potential of electromagnetic technology to increase launch velocity has been known since late in the nineteenth century, it was not until about 1980 that a sustained and large-scale effort was started to exploit it. Electromagnetic launcher technology is restricted here to mean only that technology which establishes both a current density, J, and a magnetic field, B, within a part of the launch package, called the armature, so that J {times} B integrated over the volume of the armature is the launching force. Research and development activity was triggered by the discovery that high velocity can be produced with a simple railgun which uses an arc for its armature. This so called ``plasma-armature railgun`` has been the launcher technology upon which nearly all of the work has focused. Still, a relatively small parallel effort has also been made to explore the potential of electromagnetic launchers which do not use sliding contacts on stationary rails to establish current in the armature. One electromagnetic launcher of this type is called an induction coilgun because armature current is established by electromagnetic induction. In this paper, we first establish terminology which we will use not only to specify requirements for successful endoatmospheric launch but also to compare different launcher types. Then, we summarize the statuses of the railgun and induction coilgun technologies and discuss the issues which must be resolved before either of these launchers can offer substantial advantage for endoatomospheric launch.

  17. Atomic hydrogen as a launch vehicle propellant

    Energy Technology Data Exchange (ETDEWEB)

    Palaszewski, B.A.

    1990-01-01

    An analysis of several atomic hydrogen launch vehicles was conducted. A discussion of the facilities and the technologies that would be needed for these vehicles is also presented. The Gross Liftoff Weights (GLOW) for two systems were estimated; their specific impulses (I{sub sp}) were 750 and 1500 lb{sub f}/s/lb{sub m}. The atomic hydrogen launch vehicles were also compared to the currently planned Advanced Launch System design concepts. Very significant GLOW reductions of 52 to 58 percent are possible over the Advanced Launch System designs. Applying atomic hydrogen propellants to upper stages was also considered. Very high I{sub sp} (greater than 750 lb{sub f}/s/lb{sub m}) is needed to enable a mass savings over advanced oxygen/hydrogen propulsion. Associated with the potential benefits of high I(sub sp) atomic hydrogen are several challenging problems. Very high magnetic fields are required to maintain the atomic hydrogen in a solid hydrogen matrix. The magnetic field strength was estimated to be 30 kilogauss (3 Tesla). Also the storage temperature of the propellant is 4 K. This very low temperature will require a large refrigeration facility for the launch vehicle. The design considerations for a very high recombination rate for the propellant are also discussed. A recombination rate of 210 cm/s is predicted for atomic hydrogen. This high recombination rate can produce very high acceleration for the launch vehicle. Unique insulation or segmentation to inhibit the propellant may be needed to reduce its recombination rate.

  18. Space Launch System Mission Flexibility Assessment

    Science.gov (United States)

    Monk, Timothy; Holladay, Jon; Sanders, Terry; Hampton, Bryan

    2012-01-01

    The Space Launch System (SLS) is envisioned as a heavy lift vehicle that will provide the foundation for future beyond low Earth orbit (LEO) missions. While multiple assessments have been performed to determine the optimal configuration for the SLS, this effort was undertaken to evaluate the flexibility of various concepts for the range of missions that may be required of this system. These mission scenarios include single launch crew and/or cargo delivery to LEO, single launch cargo delivery missions to LEO in support of multi-launch mission campaigns, and single launch beyond LEO missions. Specifically, we assessed options for the single launch beyond LEO mission scenario using a variety of in-space stages and vehicle staging criteria. This was performed to determine the most flexible (and perhaps optimal) method of designing this particular type of mission. A specific mission opportunity to the Jovian system was further assessed to determine potential solutions that may meet currently envisioned mission objectives. This application sought to significantly reduce mission cost by allowing for a direct, faster transfer from Earth to Jupiter and to determine the order-of-magnitude mass margin that would be made available from utilization of the SLS. In general, smaller, existing stages provided comparable performance to larger, new stage developments when the mission scenario allowed for optimal LEO dropoff orbits (e.g. highly elliptical staging orbits). Initial results using this method with early SLS configurations and existing Upper Stages showed the potential of capturing Lunar flyby missions as well as providing significant mass delivery to a Jupiter transfer orbit.

  19. Launch Pad Escape System Design (Human Spaceflight)

    Science.gov (United States)

    Maloney, Kelli

    2011-01-01

    A launch pad escape system for human spaceflight is one of those things that everyone hopes they will never need but is critical for every manned space program. Since men were first put into space in the early 1960s, the need for such an Emergency Escape System (EES) has become apparent. The National Aeronautics and Space Administration (NASA) has made use of various types of these EESs over the past 50 years. Early programs, like Mercury and Gemini, did not have an official launch pad escape system. Rather, they relied on a Launch Escape System (LES) of a separate solid rocket motor attached to the manned capsule that could pull the astronauts to safety in the event of an emergency. This could only occur after hatch closure at the launch pad or during the first stage of flight. A version of a LES, now called a Launch Abort System (LAS) is still used today for all manned capsule type launch vehicles. However, this system is very limited in that it can only be used after hatch closure and it is for flight crew only. In addition, the forces necessary for the LES/LAS to get the capsule away from a rocket during the first stage of flight are quite high and can cause injury to the crew. These shortcomings led to the development of a ground based EES for the flight crew and ground support personnel as well. This way, a much less dangerous mode of egress is available for any flight or ground personnel up to a few seconds before launch. The early EESs were fairly simple, gravity-powered systems to use when thing's go bad. And things can go bad very quickly and catastrophically when dealing with a flight vehicle fueled with millions of pounds of hazardous propellant. With this in mind, early EES designers saw such a passive/unpowered system as a must for last minute escapes. This and other design requirements had to be derived for an EES, and this section will take a look at the safety design requirements had to be derived for an EES, and this section will take a look at

  20. An Overview of Advanced Concepts for Launch

    Science.gov (United States)

    2012-02-09

    Assist •Gas Dynamic Guns • Railguns Mechanical Assistance •Space Platforms and Towers •Space Elevator Breakthrough Physics Not Covered •Skyhook...30 Exemplar Status Envisioned Design Launch Assist Railguns Concept Description Pros Eval. Cons IAT-UT LCA LMS LTF nCA nMS nTF •V > 7.5km...Combining, Propagation, µW conversion. --- Gun Launch High gees, Power Sources, Aerothermal Loads. Rapid, Robust Payload Railgun High gees, Power Sources

  1. Wireless Instrumentation Use on Launch Vehicles

    Science.gov (United States)

    Sherman, Aaron

    2010-01-01

    This slide presentation reviews the results of a study on the use of wireless instrumentation and sensors on future launch vehicles. The use of wireless technologies would if feasible would allow for fewer wires, and allow for more flexibility. However, it was generally concluded that wireless solutions are not currently ready to replace wired technologies for launch vehicles. The recommendations of the study were to continue to use wired sensors as the primary choice for vehicle instrumentation, and to continue to assess needs and use wireless instrumentation where appropriate. The future work includes support efforts for wireless technologies, and continue to monitor the development of wireless solutions.

  2. Space Launch System (SLS) Mission Planner's Guide

    Science.gov (United States)

    Smith, David Alan

    2017-01-01

    The purpose of this Space Launch System (SLS) Mission Planner's Guide (MPG) is to provide future payload developers/users with sufficient insight to support preliminary SLS mission planning. Consequently, this SLS MPG is not intended to be a payload requirements document; rather, it organizes and details SLS interfaces/accommodations in a manner similar to that of current Expendable Launch Vehicle (ELV) user guides to support early feasibility assessment. Like ELV Programs, once approved to fly on SLS, specific payload requirements will be defined in unique documentation.

  3. Sentinel-5 Precursor: First Copernicus Atmospheric Chemistry Mission ready for Launch

    Science.gov (United States)

    McMullan, Kevin; Nett, Herbert

    2017-04-01

    Sentinel-5 Precursor (S-5P) will be the first of a series of atmospheric chemistry missions to be launched within the European Commission's Copernicus (former GMES) Programme. With the current launch window of June 2017 and a nominal lifetime of 7 years, S-5P is expected to provide continuity in the availability of global atmospheric data products between its predecessor missions SCIAMACHY (Envisat) and OMI (AURA) and the future Sentinel-4 and -5 series. S-5P will deliver unique data regarding the sources and sinks of trace gases with a focus on the lower Troposphere including the planet boundary layer due to its enhanced spatial, temporal and spectral sampling capabilities as compared to its predecessors. The S-5P satellite will carry a single payload, TROPOMI (TROPOspheric Monitoring Instrument) which is jointly developed by The Netherlands and ESA. Covering spectral channels in the UV, visible, near- and short-wave infrared, it will measure various key species including tropospheric/stratospheric ozone, NO2, SO2, CO, CH4, CH2O as well as cloud and aerosol parameters. The S-5P Project successfully passed the Ground Segment Acceptance Review (GS-AR) and the satellite-level Qualification Acceptance Review (QAR) in March and April 2016, respectively. Remaining pre-launch tasks focus on the detailed planning of Phase E1 activities and the training of the operations teams. The paper includes descriptions of the S-5p spacecraft, the TROPOMI instrument, data products and applications, Level-1b and Level-2 processing, Ground Segment, launch preparation, launch and in-orbit commissioning and in-flight calibration and validation.

  4. B-52 Launch Aircraft in Flight

    Science.gov (United States)

    2001-01-01

    NASA's venerable B-52 mothership is seen here photographed from a KC-135 Tanker aircraft. The X-43 adapter is visible attached to the right wing. The B-52, used for launching experimental aircraft and for other flight research projects, has been a familiar sight in the skies over Edwards for more than 40 years and is also both the oldest B-52 still flying and the aircraft with the lowest flight time of any B-52. NASA B-52, Tail Number 008, is an air launch carrier aircraft, 'mothership,' as well as a research aircraft platform that has been used on a variety of research projects. The aircraft, a 'B' model built in 1952 and first flown on June 11, 1955, is the oldest B-52 in flying status and has been used on some of the most significant research projects in aerospace history. Some of the significant projects supported by B-52 008 include the X-15, the lifting bodies, HiMAT (highly maneuverable aircraft technology), Pegasus, validation of parachute systems developed for the space shuttle program (solid-rocket-booster recovery system and the orbiter drag chute system), and the X-38. The B-52 served as the launch vehicle on 106 X-15 flights and flew a total of 159 captive-carry and launch missions in support of that program from June 1959 to October 1968. Information gained from the highly successful X-15 program contributed to the Mercury, Gemini, and Apollo human spaceflight programs as well as space shuttle development. Between 1966 and 1975, the B-52 served as the launch aircraft for 127 of the 144 wingless lifting body flights. In the 1970s and 1980s, the B-52 was the launch aircraft for several aircraft at what is now the Dryden Flight Research Center, Edwards, California, to study spin-stall, high-angle-of attack, and maneuvering characteristics. These included the 3/8-scale F-15/spin research vehicle (SRV), the HiMAT (Highly Maneuverable Aircraft Technology) research vehicle, and the DAST (drones for aerodynamic and structural testing). The aircraft supported

  5. ESTABLISHMENT OF SATELLITE FORMATION WITH INITIAL UNCERTAINTY BY CONTROL LYAPUNOV FUNCTION APPROACH

    Directory of Open Access Journals (Sweden)

    M. Navabi

    2012-03-01

    Full Text Available In recent years, dynamics and control of satellite formation flying have been active areas of research. From the mission planning perspective, three main areas namely formation establishment, maintenance and reconfiguration have been discussed. In this paper, a study of formation establishment under initial uncertainty is presented. In this regard, dynamics of low Earth orbit satellite formation is discussed. Control Lyapunov function approach is adopted to bring a deputy satellite, with perturbed initial conditions into formation with a chief satellite. In order to take account of the initial orbit insertion error, uncertainty in initial conditions of the deputy satellite is considered. For a case study, a relatively small formation is adopted, with air-launched Pegasus as the launch vehicle. For several initial conditions, control function and required time to achieve a given mission accuracy are determined, and results are provided as illustration.

  6. Meteorological satellite systems

    CERN Document Server

    Tan, Su-Yin

    2014-01-01

    “Meteorological Satellite Systems” is a primer on weather satellites and their Earth applications. This book reviews historic developments and recent technological advancements in GEO and polar orbiting meteorological satellites. It explores the evolution of these remote sensing technologies and their capabilities to monitor short- and long-term changes in weather patterns in response to climate change. Satellites developed by various countries, such as U.S. meteorological satellites, EUMETSAT, and Russian, Chinese, Japanese and Indian satellite platforms are reviewed. This book also discusses international efforts to coordinate meteorological remote sensing data collection and sharing. This title provides a ready and quick reference for information about meteorological satellites. It serves as a useful tool for a broad audience that includes students, academics, private consultants, engineers, scientists, and teachers.

  7. Theory of geostationary satellites

    CERN Document Server

    Zee, Chong-Hung

    1989-01-01

    Geostationary or equatorial synchronous satellites are a daily reminder of our space efforts during the past two decades. The nightly television satellite weather picture, the intercontinental telecommunications of television transmissions and telephone conversations, and the establishrnent of educational programs in remote regions on Earth are constant reminders of the presence of these satellites. As used here, the term 'geo­ stationary' must be taken loosely because, in the long run, the satellites will not remain 'stationary' with respect to an Earth-fixed reference frame. This results from the fact that these satellites, as is true for all satellites, are incessantly subject to perturbations other than the central-body attraction of the Earth. Among the more predominant pertur­ bations are: the ellipticity of the Earth's equator, the Sun and Moon, and solar radiation pressure. Higher harmonics of the Earth's potential and tidal effects also influence satellite motion, but they are of second­ order whe...

  8. Effect of Ionosphere on Geostationary Communication Satellite Signals

    Science.gov (United States)

    Erdem, Esra; Arikan, Feza; Gulgonul, Senol

    2016-07-01

    ionosphere using IRI-Plas-G software. One of the outstanding features of IONOLAB-RAY is the opportunity of Global Ionospheric Map-Total Electron Content (GIM-TEC) assimilation. This feature enables more realistic representation of ionosphere, especially for the times when ionosphere deviates from the generalized models, such as during geomagnetic storms. This feature is critical to examine the effect of ionosphere on satellite signals under ionospheric storm conditions. In this study TURKSAT satellite data is used to compare the results of IONOLAB-RAY and evaluate the effect of ionosphere. TURKSAT is one of the world's leading companies providing all sorts of satellite communications through the satellites of TURKSAT as well as the other satellites. Providing services for voice, data, internet, TV, and radio broadcasting through the satellites across a wide area extending from Europe to Asia. The latest satellite of TURKSAT, namely Turksat 4B was launched on October 2015, before that various versions of TURKSAT satellites are launched since 1994. In the future enlargement of broadcasting area towards equatorial region is aimed, where the ionospheric anomalies and storms are highly expected. In the future this study can be applied to the satellite signals in equatorial regions and effects of ionosphere especially under storm conditions can be discussed. This study is supported by TUBITAK 114E541, 115E915 and Joint TUBITAK 114E092 and AS CR 14/001 projects.

  9. Secondary Payload Opportunities on NASA's Space Launch System (SLS) Enable Science and Deep Space Exploration

    Science.gov (United States)

    Singer, Jody; Pelfrey, Joseph; Norris, George

    2016-01-01

    For the first time in almost 40 years, a NASA human-rated launch vehicle has completed its Critical Design Review (CDR). With this milestone, NASA's Space Launch System (SLS) and Orion spacecraft are on the path to launch a new era of deep space exploration. This first launch of SLS and the Orion Spacecraft is planned no later than November 2018 and will fly along a trans-lunar trajectory, testing the performance of the SLS and Orion systems for future missions. NASA is making investments to expand the science and exploration capability of the SLS by developing the capability to deploy small satellites during the trans-lunar phase of the mission trajectory. Exploration Mission 1 (EM-1) will include thirteen 6U Cubesat small satellites to be deployed beyond low earth orbit. By providing an earth-escape trajectory, opportunities are created for the advancement of small satellite subsystems, including deep space communications and in-space propulsion. This SLS capability also creates low-cost options for addressing existing Agency strategic knowledge gaps and affordable science missions. A new approach to payload integration and mission assurance is needed to ensure safety of the vehicle, while also maintaining reasonable costs for the small payload developer teams. SLS EM-1 will provide the framework and serve as a test flight, not only for vehicle systems, but also payload accommodations, ground processing, and on-orbit operations. Through developing the requirements and integration processes for EM-1, NASA is outlining the framework for the evolved configuration of secondary payloads on SLS Block upgrades. The lessons learned from the EM-1 mission will be applied to processes and products developed for future block upgrades. In the heavy-lift configuration of SLS, payload accommodations will increase for secondary opportunities including small satellites larger than the traditional Cubesat class payload. The payload mission concept of operations, proposed payload

  10. DPJ Editorial: Launching the new journal

    Directory of Open Access Journals (Sweden)

    Eugene Matusov

    2013-01-01

    Full Text Available We welcome and invite new readers, authors, reviewers and editors to the new journal.  A short history of the journal foundation is given along with the reasons for launching this publication. A long, but not finished, list is provided of important and interesting themes and areas of interest for dialogic educational practice, research and theory.

  11. Control of NASA's Space Launch System

    Science.gov (United States)

    VanZwieten, Tannen S.

    2014-01-01

    The flight control system for the NASA Space Launch System (SLS) employs a control architecture that evolved from Saturn, Shuttle & Ares I-X while also incorporating modern enhancements. This control system, baselined for the first unmanned launch, has been verified and successfully flight-tested on the Ares I-X rocket and an F/A-18 aircraft. The development of the launch vehicle itself came on the heels of the Space Shuttle retirement in 2011, and will deliver more payload to orbit and produce more thrust than any other vehicle, past or present, opening the way to new frontiers of space exploration as it carries the Orion crew vehicle, equipment, and experiments into new territories. The initial 70 metric ton vehicle consists of four RS-25 core stage engines from the Space Shuttle inventory, two 5- segment solid rocket boosters which are advanced versions of the Space Shuttle boosters, and a core stage that resembles the External Tank and carries the liquid propellant while also serving as the vehicle's structural backbone. Just above SLS' core stage is the Interim Cryogenic Propulsion Stage (ICPS), based upon the payload motor used by the Delta IV Evolved Expendable Launch Vehicle (EELV).

  12. CERF Launches CESN En Espanol in 2012

    Science.gov (United States)

    CERF launched Coastal and Estuarine Science News (CESN) in 2003 as an electronic companion to the journal Estuaries and Coasts. CESN serves to strengthen the link between science and management of coastal systems by reaching out to a wider audience with accessible summaries of 4...

  13. SMAP Post-launch Field Campaign Planning

    Science.gov (United States)

    The SMAP post-launch Cal/Val activities are intended both to assess the quality of the mission products and to support analyses that lead to their improvement. A suite of complementary methodologies will be employed that will result in a robust global assessment. Much of the work will occur in the C...

  14. Air loads on solar panels during launch

    NARCIS (Netherlands)

    Beltman, W.M.; van der Hoogt, Peter; Spiering, R.M.E.J.; Tijdeman, H.

    1996-01-01

    The dynamical behaviour of solar panels during launch is significantly affected by the thin layers of air trapped between the panels. For narrow gaps the air manifests itself not only as a considerable added mass, but its viscosity can result in a substantial amount of damping. A model has been

  15. Illustration of Launching Samples Home from Mars

    Science.gov (United States)

    2005-01-01

    One crucial step in a Mars sample return mission would be to launch the collected sample away from the surface of Mars. This artist's concept depicts a Mars ascent vehicle for starting a sample of Mars rocks on their trip to Earth.

  16. CAS Launches Website for Scientific Education

    Institute of Scientific and Technical Information of China (English)

    2004-01-01

    @@ CAS member Wang Shouguan and SecretaryGeneral of the Ministry of Science and Technology Zhang Jing'an jointly push the button on August 26 in Beijing to launch a CAS website for scientific education (http ://www.fipse. cn/).

  17. Launching a Projectile into Deep Space

    Science.gov (United States)

    Maruszewski, Richard F., Jr.

    2004-01-01

    As part of the discussion about Newton's work in a history of mathematics course, one of the presentations calculated the amount of energy necessary to send a projectile into deep space. Afterwards, the students asked for a recalculation with two changes: First the launch under study consisted of a single stage, but the students desired to…

  18. Ares Launch Vehicles Lean Practices Case Study

    Science.gov (United States)

    Doreswamy, Rajiv; Self, Timothy A.

    2007-01-01

    The Ares launch vehicles team, managed by the Ares Projects Office (APO) at NASA Marshall Space Flight Center, has completed the Ares I Crew Launch Vehicle System Requirements Review and System Definition Review and early design work for the Ares V Cargo Launch Vehicle. This paper provides examples of how Lean Manufacturing, Kaizen events, and Six Sigma practices are helping APO deliver a new space transportation capability on time and within budget, while still meeting stringent technical requirements. For example, Lean philosophies have been applied to numerous process definition efforts and existing process improvement activities, including the Ares I-X test flight Certificate of Flight Readiness (CoFR) process, risk management process, and review board organization and processes. Ares executives learned Lean practices firsthand, making the team "smart buyers" during proposal reviews and instilling the team with a sense of what is meant by "value-added" activities. Since the goal of the APO is to field launch vehicles at a reasonable cost and on an ambitious schedule, adopting Lean philosophies and practices will be crucial to the Ares Project's long-term SUCCESS.

  19. Satellite data for geomagnetic field modeling

    Science.gov (United States)

    Langel, R. A.; Baldwin, R. T.

    1992-06-01

    Satellite measurements of the geomagnetic fields began with the launch of Sputnik 3 in May of 1958 and have continued sporadically. Spacecraft making significant contributions to main field geomagnetism will be reviewed and the characteristics of their data discussed, including coverage, accuracy, resolution and data availability. Of particular interest are Vanguard 3; Cosmos 49, Ogo's -2, -4, and -6; Magsat; DE-2; and POGS. Spacecraft make measurements on a moving platfrom above the ionosphere as opposed to measurements from fixed observatories and surveys, both below the ionosphere. Possible future missions, such as Aristoteles and GOS are reviewed.

  20. Satellite Data for Geomagnetic Field Modeling

    Science.gov (United States)

    Langel, R. A.; Baldwin, R. T.

    1992-01-01

    Satellite measurements of the geomagnetic fields began with the launch of Sputnik 3 in May of 1958 and have continued sporadically. Spacecraft making significant contributions to main field geomagnetism will be reviewed and the characteristics of their data discussed, including coverage, accuracy, resolution and data availability. Of particular interest are Vanguard 3; Cosmos 49, Ogo's -2, -4, and -6; Magsat; DE-2; and POGS. Spacecraft make measurements on a moving platfrom above the ionosphere as opposed to measurements from fixed observatories and surveys, both below the ionosphere. Possible future missions, such as Aristoteles and GOS are reviewed.

  1. JPSS Preparations at the Satellite Proving Ground for Marine, Precipitation, and Satellite Analysis

    Science.gov (United States)

    Folmer, M. J.; Berndt, E.; Clark, J.; Orrison, A.; Kibler, J.; Sienkiewicz, J. M.; Nelson, J. A., Jr.; Goldberg, M.

    2016-12-01

    The National Oceanic and Atmospheric Administration (NOAA) Satellite Proving Ground (PG) for Marine, Precipitation, and Satellite Analysis (MPS) has been demonstrating and evaluating Suomi National Polar-orbiting Partnership (S-NPP) products along with other polar-orbiting satellite platforms in preparation for the Joint Polar Satellite System - 1 (JPSS-1) launch in March 2017. The first S-NPP imagery was made available to the MPS PG during the evolution of Hurricane Sandy in October 2012 and has since been popular in operations. Since this event the MPS PG Satellite Liaison has been working with forecasters on ways to integrate single-channel and multispectral imagery from the Visible Infrared Imaging Radiometer Suite (VIIRS), the Moderate Resolution Imaging Spectroradiometer (MODIS), and the Advanced Very High Resolution Radiometer (AVHRR)into operations to complement numerical weather prediction and geostationary satellite savvy National Weather Service (NWS) National Centers. Additional unique products have been introduced to operations to address specific forecast challenges, including the Cooperative Institute for Research in the Atmosphere (CIRA) Layered Precipitable Water, the National Environmental Satellite, Data, and Information Service (NESDIS) Snowfall Rate product, NOAA Unique Combined Atmospheric Processing System (NUCAPS) Soundings, ozone products from the Atmospheric Infrared Sounder (AIRS), Cross-track Infrared Sounder/Advanced Technology Microwave Sounder (CrIS/ATMS), and Infrared Atmospheric Sounding Interferometer (IASI). In addition, new satellite domains have been created to provide forecasters at the NWS Ocean Prediction Center and Weather Prediction Center with better quality imagery at high latitudes. This has led to research projects that are addressing forecast challenges such as tropical to extratropical transition and explosive cyclogenesis. This presentation will provide examples of how the MPS PG has been introducing and integrating

  2. ECHAM5-wiso water vapour isotopologues simulation and its comparison with WS-CRDS measurements and retrievals from GOSAT and ground-based FTIR spectra in the atmosphere of Western Siberia

    Directory of Open Access Journals (Sweden)

    K. Gribanov

    2013-01-01

    Full Text Available Water stable isotopes provide integrated tracers of the atmospheric water cycle, affected by changes in air mass origin, non-convective and convective processes and continental recycling. Novel remote sensing and in situ measuring techniques have recently offered opportunities for monitoring atmospheric water vapour isotopic composition. Recently developed infrared laser spectrometers allow for continuous in situ measurements of surface water vapour δDv and δ18Ov. So far, very few intercomparison of measurements conducted using different techniques have been achieved at a given location, due to difficulties intrinsic to the comparison of integrated with local measurements. Nudged simulations conducted with high resolution isotopically enabled GCMs provide a consistent framework for comparison with the different types of observations. Here, we compare simulations conducted with the ECHAM5-wiso model with three types of water vapour isotopic data obtained during summer 2012 at the forest site of Kourovka, Western Siberia: daily mean GOSAT δDv soundings, hourly ground-based FTIR total atmospheric columnar δDv amounts, and in situ hourly Picarro δDv measurements. There is an excellent correlation between observed and predicted δDv at surface while the comparison between water column values derived from the model compares well with FTIR and GOSAT estimates.

    This research was supported by the grant of Russian government under the contract 11.G34.31.0064.

  3. The Infrared Astronomical Satellite (IRAS) mission

    Science.gov (United States)

    Neugebauer, G.; Habing, H. J.; Van Duinen, R.; Aumann, H. H.; Beichman, C. A.; Baud, B.; Beintema, D. A.; Boggess, N.; Clegg, P. E.; De Jong, T.

    1984-01-01

    The Infrared Astronomical Satellite (IRAS) consists of a spacecraft and a liquid helium cryostat that contains a cooled IR telescope. The telescope's focal plane assembly is cooled to less than 3 K, and contains 62 IR detectors in the survey array which are arranged so that every source crossing the field of view can be seen by at least two detectors in each of four wavelength bands. The satellite was launched into a 900 km-altitude near-polar orbit, and its cryogenic helium supply was exhausted on November 22, 1983. By mission's end, 72 percent of the sky had been observed with three or more hours-confirming scans, and 95 percent with two or more hours-confirming scans. About 2000 stars detected at 12 and 25 microns early in the mission, and identified in the SAO (1966) catalog, have a positional uncertainty ellipse whose axes are 45 x 9 arcsec for an hours-confirmed source.

  4. Maglev Launch: Ultra-low Cost, Ultra-high Volume Access to Space for Cargo and Humans

    Science.gov (United States)

    Powell, James; Maise, George; Rather, John

    2010-01-01

    . Passenger spacecraft enter the atmosphere at 70,000 feet, where deceleration is acceptable. A levitated evacuated launch tube is used, with the levitation force generated by magnetic interaction between superconducting cables on the levitated launch tube and superconducting cables on the ground beneath. The Gen-2 system could launch 100's of thousands of passengers per year, and operate by 2030 AD. Maglev launch will enable large human scale exploration of space, thousands of gigawatts of space solar power satellites for beamed power to Earth, a robust defense against asteroids and comets, and many other applications not possible now.

  5. Launching a world-class joint venture.

    Science.gov (United States)

    Bamford, James; Ernst, David; Fubini, David G

    2004-02-01

    More than 5,000 joint ventures, and many more contractual alliances, have been launched worldwide in the past five years. Companies are realizing that JVs and alliances can be lucrative vehicles for developing new products, moving into new markets, and increasing revenues. The problem is, the success rate for JVs and alliances is on a par with that for mergers and acquisitions--which is to say not very good. The authors, all McKinsey consultants, argue that JV success remains elusive for most companies because they don't pay enough attention to launch planning and execution. Most companies are highly disciplined about integrating the companies they target through M&A, but they rarely commit sufficient resources to launching similarly sized joint ventures or alliances. As a result, the parent companies experience strategic conflicts, governance gridlock, and missed operational synergies. Often, they walk away from the deal. The launch phase begins with the parent companies' signing of a memorandum of understanding and continues through the first 100 days of the JV or alliance's operation. During this period, it's critical for the parents to convene a team dedicated to exposing inherent tensions early. Specifically, the launch team must tackle four basic challenges. First, build and maintain strategic alignment across the separate corporate entities, each of which has its own goals, market pressures, and shareholders. Second, create a shared governance system for the two parent companies. Third, manage the economic interdependencies between the corporate parents and the JV. And fourth, build a cohesive, high-performing organization (the JV or alliance)--not a simple task, since most managers come from, will want to return to, and may even hold simultaneous positions in the parent companies. Using real-world examples, the authors offer their suggestions for meeting these challenges.

  6. Solar thermal OTV - applications to reusable and expendable launch vehicles

    Energy Technology Data Exchange (ETDEWEB)

    Kessler, Thomas L. [Boeing Co., Phantom Works (United States); Frye, Patrick [Boeing Co., Rocketdyne Propulsion and Power (United States); Partch, Russ [Air Force Research Lab. (United States)

    2000-11-01

    The Solar Orbit Transfer Vehicle (SOTV) program being sponsored by the U.S. Air Force Research Laboratory (AFRL) is developing technology that will engender revolutionary benefits to satellites and orbit-to-orbit transfer systems. Solar thermal propulsion offers significant advantages for near-term expendable launch vehicles (ELVs) such as Delta IV, mid- to far-term reusable launch vehicles (RLVs) and ultimately to manned exploration of the Moon and Mars. Solar thermal propulsion uses a relatively large mirrored concentrator to focus solar energy onto a compact absorber, which is in turn heated to >2200 K. This heat can then be used in two major ways. By flowing hydrogen or another working fluid through the absorber, high efficiency thrust can be generated with 800 sec or more specific impulse (Isp), almost twice that of conventional cryogenic stages and comparable with typical solid-core nuclear thermal stages. Within a decade, advances in materials and fabrication processes hold the promise of the Isp ranging up to 1,100 sec. In addition, attached thermionic or alkali metal thermoelectric converter (AMTEC) power converters can be used to generate 20 to 100 kilowatts (kW) of electricity. The SOTV Space Experiment (SOTV-SE), planned to be flown in 2003, will demonstrate both hydrogen propulsion and thermionic power generation, including advanced lightweight deployable concentrators suitable for large-scale applications. Evolutionary geosynchronous-transfer orbit/geosynchronous-Earth orbit (GTO/GEO) payload lift capability improvements of 50% or more to the Delta IV launch vehicles could be implemented as part of the Delta IV P4I plan shortly thereafter. Beyond that, SOTV technology should allow long-term storage of stages in orbits up to GEO with tremendous manoeuvring capability, potentially 4 to 5 km/sec or more. Servicing of low-Earth orbit (LEO) and GEO assets and reusable (ROTVs) are other possible applications. Offering a combination of high Isp and high

  7. A Low-Cost Launch Assistance System for Orbital Launch Vehicles

    Directory of Open Access Journals (Sweden)

    Oleg Nizhnik

    2012-01-01

    Full Text Available The author reviews the state of art of nonrocket launch assistance systems (LASs for spaceflight focusing on air launch options. The author proposes an alternative technologically feasible LAS based on a combination of approaches: air launch, high-altitude balloon, and tethered LAS. Proposed LAS can be implemented with the existing off-the-shelf hardware delivering 7 kg to low-earth orbit for the 5200 USD per kg. Proposed design can deliver larger reduction in price and larger orbital payloads with the future advances in the aerostats, ropes, electrical motors, and terrestrial power networks.

  8. Satellite-based Tropical Cyclone Monitoring Capabilities

    Science.gov (United States)

    Hawkins, J.; Richardson, K.; Surratt, M.; Yang, S.; Lee, T. F.; Sampson, C. R.; Solbrig, J.; Kuciauskas, A. P.; Miller, S. D.; Kent, J.

    2012-12-01

    Satellite remote sensing capabilities to monitor tropical cyclone (TC) location, structure, and intensity have evolved by utilizing a combination of operational and research and development (R&D) sensors. The microwave imagers from the operational Defense Meteorological Satellite Program [Special Sensor Microwave/Imager (SSM/I) and the Special Sensor Microwave Imager Sounder (SSMIS)] form the "base" for structure observations due to their ability to view through upper-level clouds, modest size swaths and ability to capture most storm structure features. The NASA TRMM microwave imager and precipitation radar continue their 15+ yearlong missions in serving the TC warning and research communities. The cessation of NASA's QuikSCAT satellite after more than a decade of service is sorely missed, but India's OceanSat-2 scatterometer is now providing crucial ocean surface wind vectors in addition to the Navy's WindSat ocean surface wind vector retrievals. Another Advanced Scatterometer (ASCAT) onboard EUMETSAT's MetOp-2 satellite is slated for launch soon. Passive microwave imagery has received a much needed boost with the launch of the French/Indian Megha Tropiques imager in September 2011, basically greatly supplementing the very successful NASA TRMM pathfinder with a larger swath and more frequent temporal sampling. While initial data issues have delayed data utilization, current news indicates this data will be available in 2013. Future NASA Global Precipitation Mission (GPM) sensors starting in 2014 will provide enhanced capabilities. Also, the inclusion of the new microwave sounder data from the NPP ATMS (Oct 2011) will assist in mapping TC convective structures. The National Polar orbiting Partnership (NPP) program's VIIRS sensor includes a day night band (DNB) with the capability to view TC cloud structure at night when sufficient lunar illumination exits. Examples highlighting this new capability will be discussed in concert with additional data fusion efforts.

  9. Atmospheric CH4 and CO2 enhancements and biomass burning emission ratios derived from satellite observations of the 2015 Indonesian fire plumes

    Science.gov (United States)

    Parker, Robert J.; Boesch, Hartmut; Wooster, Martin J.; Moore, David P.; Webb, Alex J.; Gaveau, David; Murdiyarso, Daniel

    2016-08-01

    The 2015-2016 strong El Niño event has had a dramatic impact on the amount of Indonesian biomass burning, with the El Niño-driven drought further desiccating the already-drier-than-normal landscapes that are the result of decades of peatland draining, widespread deforestation, anthropogenically driven forest degradation and previous large fire events. It is expected that the 2015-2016 Indonesian fires will have emitted globally significant quantities of greenhouse gases (GHGs) to the atmosphere, as did previous El Niño-driven fires in the region. The form which the carbon released from the combustion of the vegetation and peat soils takes has a strong bearing on its atmospheric chemistry and climatological impacts. Typically, burning in tropical forests and especially in peatlands is expected to involve a much higher proportion of smouldering combustion than the more flaming-characterised fires that occur in fine-fuel-dominated environments such as grasslands, consequently producing significantly more CH4 (and CO) per unit of fuel burned. However, currently there have been no aircraft campaigns sampling Indonesian fire plumes, and very few ground-based field campaigns (none during El Niño), so our understanding of the large-scale chemical composition of these extremely significant fire plumes is surprisingly poor compared to, for example, those of southern Africa or the Amazon.Here, for the first time, we use satellite observations of CH4 and CO2 from the Greenhouse gases Observing SATellite (GOSAT) made in large-scale plumes from the 2015 El Niño-driven Indonesian fires to probe aspects of their chemical composition. We demonstrate significant modifications in the concentration of these species in the regional atmosphere around Indonesia, due to the fire emissions.Using CO and fire radiative power (FRP) data from the Copernicus Atmosphere Service, we identify fire-affected GOSAT soundings and show that peaks in fire activity are followed by subsequent large

  10. Soviet satellite communications science and technology

    Energy Technology Data Exchange (ETDEWEB)

    Birch, J.N.; Campanella, S.J.; Gordon, G.D.; McElroy, D.R.; Pritchard, W.L.; Stamminger, R.

    1991-08-01

    This is a report by six US scientists and engineers concerning the current state of the art and projections of future Soviet satellite communications technologies. The panel members are experts in satellite stabilization, spacecraft environments, space power generation, launch systems, spacecraft communications sciences and technologies, onboard processing, ground stations, and other technologies that impact communications. The panel assessed the Soviet ability to support high-data-rate space missions at 128 Mbps by evaluating current and projected Soviet satellite communications technologies. A variety of space missions were considered, including Earth-to-Earth communications via satellites in geostationary or highly elliptical orbits, those missions that require space-to-Earth communications via a direct path and those missions that require space-to-Earth communications via a relay satellite. Soviet satellite communications capability, in most cases, is 10 years behind that of the United States and other industrialized nations. However, based upon an analysis of communications links needed to support these missions using current Soviet capabilities, it is well within the current Soviet technology to support certain space missions outlined above at rates of 128 Mbps or higher, although published literature clearly shows that the Soviet Union has not exceeded 60 Mbps in its current space system. These analyses are necessary but not sufficient to determine mission data rates, and other technologies such as onboard processing and storage could limit the mission data rate well below that which could actually be supported via the communications links. Presently, the Soviet Union appears to be content with data rates in the low-Earth-orbit relay via geostationary mode of 12 Mbps. This limit is a direct result of power amplifier limits, spacecraft antenna size, and the utilization of K{sub u}-band frequencies. 91 refs., 16 figs., 15 tabs.

  11. Plasma-satellite interaction driven magnetic field perturbations

    Energy Technology Data Exchange (ETDEWEB)

    Saeed-ur-Rehman, E-mail: surehman@ualberta.ca [Department of Physics, University of Alberta, Edmonton, Alberta T6G 2E1 (Canada); Theoretical Physics Division, PINSTECH, Nilore Islamabad 44000 (Pakistan); Marchand, Richard, E-mail: Richard.Marchand@ualberta.ca [Department of Physics, University of Alberta, Edmonton, Alberta T6G 2E1 (Canada)

    2014-09-15

    We report the first fully kinetic quantitative estimate of magnetic field perturbations caused by the interaction of a spacecraft with space environment. Such perturbations could affect measurements of geophysical magnetic fields made with very sensitive magnetometers on-board satellites. Our approach is illustrated with a calculation of perturbed magnetic fields near the recently launched Swarm satellites. In this case, magnetic field perturbations do not exceed 20 pT, and they are below the sensitivity threshold of the on-board magnetometers. Anticipating future missions in which satellites and instruments would be subject to more intense solar UV radiation, however, it appears that magnetic field perturbations associated with satellite interaction with space environment, might approach or exceed instruments' sensitivity thresholds.

  12. Tidal Models In A New Era of Satellite Gravimetry

    Science.gov (United States)

    Ray, Richard D.; Rowlings, David D.; Edbert, G. D.; Chao, Benjamin F. (Technical Monitor)

    2002-01-01

    The high precision gravity measurements to be made by recently launched (and recently approved) satellites place new demands on models of Earth, atmospheric, and oceanic tides. The latter is the most problematic. The ocean tides induce variations in the Earth's geoid by amounts that far exceed the new satellite sensitivities, and tidal models must be used to correct for this. Two methods are used here to determine the standard errors in current ocean tide models. At long wavelengths these errors exceed the sensitivity of the GRACE mission. Tidal errors will not prevent the new satellite missions from improving our knowledge of the geopotential by orders of magnitude, but the errors may well contaminate GRACE estimates of temporal variations in gravity. Solar tides are especially problematic because of their long alias periods. The satellite data may be used to improve tidal models once a sufficiently long time series is obtained. Improvements in the long-wavelength components of lunar tides are especially promising.

  13. The Cyclone Global Navigation Satellite System (CYGNSS) - Analysis and Data Assimilation for Tropical Convection

    Science.gov (United States)

    Li, Xuanli; Lang, Timothy J.; Mecikalski, John; Castillo, Tyler; Hoover, Kacie; Chronis, Themis

    2017-01-01

    Cyclone Global Navigation Satellite System (CYGNSS): a constellation of 8 micro-satellite observatories launched in November 2016, to measure near-surface oceanic wind speed. Main goal: To monitor surface wind fields of the Tropical Cyclones' inner core, including regions beneath the intense eye wall and rain bands that could not previously be measured from space; Cover 38 deg S -38 deg N with unprecedented temporal resolution and spatial coverage, under all precipitating conditions Low flying satellite: Pass over ocean surface more frequently than one large satellite. A median(mean) revisit time of 2.8(7.2) hrs.

  14. Design and implementation of an experiment scheduling system for the ACTS satellite

    Science.gov (United States)

    Ringer, Mark J.

    1994-01-01

    The Advanced Communication Technology Satellite (ACTS) was launched on the 12th of September 1993 aboard STS-51. All events since that time have proceeded as planned with user operations commencing on December 6th, 1993. ACTS is a geosynchronous satellite designed to extend the state of the art in communication satellite design and is available to experimenters on a 'time/bandwidth available' basis. The ACTS satellite requires the advance scheduling of experimental activities based upon a complex set of resource, state, and activity constraints in order to ensure smooth operations. This paper describes the software system developed to schedule experiments for ACTS.

  15. Optimization of Determinant Factors of Satellite Electrical Power System with Particle Swarm Optimization (PSO Algorithm

    Directory of Open Access Journals (Sweden)

    Mojtaba Biglarahmadi

    2014-03-01

    Full Text Available Weight and dimension, cost, and performance are determinant factors for design, fabrication, and launch the satellites which are related to the mission type of the satellites. Each satellite includes several subsystems such as Electrical Power Subsystem (EPS, Navigation Subsystem, Thermal Subsystem, etc. The purpose of this paper is to optimize these determinant factors by Particle Swarm Optimization (PSO algorithm, for Electrical Power Subsystem. This paper considers the effects of selecting various types of Photovoltaic (PV cells and batteries on weight and dimension, cost, and performance of the satellite. We have used two various types of PVs and two various type of batteries in optimization of the Electrical Power Subsystem (EPS

  16. Hail Disrometer Array for Launch Systems Support

    Science.gov (United States)

    Lane, John E.; Sharp, David W.; Kasparis, Takis C.; Doesken, Nolan J.

    2008-01-01

    Prior to launch, the space shuttle might be described as a very large thermos bottle containing substantial quantities of cryogenic fuels. Because thermal insulation is a critical design requirement, the external wall of the launch vehicle fuel tank is covered with an insulating foam layer. This foam is fragile and can be damaged by very minor impacts, such as that from small- to medium-size hail, which may go unnoticed. In May 1999, hail damage to the top of the External Tank (ET) of STS-96 required a rollback from the launch pad to the Vehicle Assembly Building (VAB) for repair of the insulating foam. Because of the potential for hail damage to the ET while exposed to the weather, a vigilant hail sentry system using impact transducers was developed as a hail damage warning system and to record and quantify hail events. The Kennedy Space Center (KSC) Hail Monitor System, a joint effort of the NASA and University Affiliated Spaceport Technology Development Contract (USTDC) Physics Labs, was first deployed for operational testing in the fall of 2006. Volunteers from the Community Collaborative Rain. Hail, and Snow Network (CoCoRaHS) in conjunction with Colorado State University were and continue to be active in testing duplicate hail monitor systems at sites in the hail prone high plains of Colorado. The KSC Hail Monitor System (HMS), consisting of three stations positioned approximately 500 ft from the launch pad and forming an approximate equilateral triangle (see Figure 1), was deployed to Pad 39B for support of STS-115. Two months later, the HMS was deployed to Pad 39A for support of STS-116. During support of STS-117 in late February 2007, an unusual hail event occurred in the immediate vicinity of the exposed space shuttle and launch pad. Hail data of this event was collected by the HMS and analyzed. Support of STS-118 revealed another important application of the hail monitor system. Ground Instrumentation personnel check the hail monitors daily when a

  17. NASA's Space Launch System Progress Report

    Science.gov (United States)

    Singer, Joan A.; Cook, Jerry R.; Lyles, Garry M.; Beaman, David E.

    2011-01-01

    Exploration beyond Earth will be an enduring legacy for future generations, confirming America's commitment to explore, learn, and progress. NASA's Space Launch System (SLS) Program, managed at the Marshall Space Flight Center, is responsible for designing and developing the first exploration-class rocket since the Apollo Program's Saturn V that sent Americans to the Moon. The SLS offers a flexible design that may be configured for the MultiPurpose Crew Vehicle and associated equipment, or may be outfitted with a payload fairing that will accommodate flagship science instruments and a variety of high-priority experiments. Both options support a national capability that will pay dividends for future generations. Building on legacy systems, facilities, and expertise, the SLS will have an initial lift capability of 70 metric tons (mT) and will be evolvable to 130 mT. While commercial launch vehicle providers service the International Space Station market, this capability will surpass all vehicles, past and present, providing the means to do entirely new missions, such as human exploration of asteroids and Mars. With its superior lift capability, the SLS can expand the interplanetary highway to many possible destinations, conducting revolutionary missions that will change the way we view ourselves, our planet and its place in the cosmos. To perform missions such as these, the SLS will be the largest launch vehicle ever built. It is being designed for safety and affordability - to sustain our journey into the space age. Current plans include launching the first flight, without crew, later this decade, with crewed flights beginning early next decade. Development work now in progress is based on heritage space systems and working knowledge, allowing for a relatively quick start and for maturing the SLS rocket as future technologies become available. Together, NASA and the U.S. aerospace industry are partnering to develop this one-of-a-kind asset. Many of NASA's space

  18. Laser Communication Experiments with Artemis Satellite

    Science.gov (United States)

    Kuzkov, Sergii; Sodnik, Zoran; Kuzkov, Volodymyr

    2013-10-01

    In November 2001, the European Space Agency (ESA) established the world-first inter-satellite laser communication link between the geostationary ARTEMIS satellite and the low Earth orbiting (LEO) SPOT-4 Earth observation satellite, demonstrating data rates of 50 Mbps. In 2006, the Japanese Space Agency launched the KIRARI (OICETS) LEO satellite with a compatible laser communication terminal and bidirectional laser communication links (50 Mbps and 2 Mbps) were successfully realized between KIRARI and ARTEMIS. ESA is now developing the European Data Relay Satellite (EDRS) system, which will use laser communication technology to transmit data between the Sentinel 1 and 2 satellites in LEO to two geostationary satellites (EDRS-A and EDRS-C) at data rates of 1.8 Gbps. As the data handling capabilities of state-of-the-art telecommunication satellites in GEO increase so is the demand for the feeder-link bandwidth to be transmitted from ground. This is why there is an increasing interest in developing high bandwidth ground-to-space laser communication systems working through atmosphere. In 2002, the Main Astronomical Observatory (MAO) started the development of its own laser communication system for its 0.7m AZT-2 telescope, located in Kyiv, Ukraine. The work was supported by the National Space Agency of Ukraine and by ESA. MAO developed a highly accurate computerized tracking system for AZT-2 telescope and a compact laser communication package called LACES (Laser Atmosphere and Communication Experiments with Satellites). The LACES instrument includes a camera of the pointing and tracking subsystems, a receiver module, a laser transmitter module, a tip/tilt atmospheric turbulence compensation subsystem, a bit error rate tester module and other optical and electronic components. The principal subsystems are mounted on a platform, which is located at the Cassegrain focus of the AZT-2 telescope. All systems were tested with the laser communication payload on-board ARTEMIS and

  19. LQG controller designs from reduced order models for a launch vehicle

    Indian Academy of Sciences (India)

    Ashwin Dhabale; R N Banavar; M V Dhekane

    2008-02-01

    The suppression of liquid fuel slosh motion is critical in a launch vehicle (LV). In particular, during certain stages of the launch, the dynamics of the fuel interacts adversely with the rigid body dynamics of the LV and the feedback controller must attentuate these effects. This paper describes the effort of a multivariable control approach applied to the Geosynchronous Satellite Launch Vehicle (GSLV) of the Indian Space Research Organization (ISRO) during a certain stage of its launch. The fuel slosh dynamics are modelled using a pendulum model analogy. We describe two design methodologies using the Linear-Quadratic Gaussian (LQG) technique. The novelty of the technique is that we apply the LQG design for models that are reduced in order through inspection alone. This is possible from a perspective that the LV could be viewed as many small systems attached to a main body and the interactions of some of these smaller systems could be neglected at the controller design stage provided sufficient robustness is ensured by the controller. The first LQG design is carried out without the actuator dynamics incorporated at the design stage and for the second design we neglect the slosh dynamics as well.

  20. Resonant mode controllers for launch vehicle applications

    Science.gov (United States)

    Schreiner, Ken E.; Roth, Mary Ellen

    Electro-mechanical actuator (EMA) systems are currently being investigated for the National Launch System (NLS) as a replacement for hydraulic actuators due to the large amount of manpower and support hardware required to maintain the hydraulic systems. EMA systems in weight sensitive applications, such as launch vehicles, have been limited to around 5 hp due to system size, controller efficiency, thermal management, and battery size. Presented here are design and test data for an EMA system that competes favorably in weight and is superior in maintainability to the hydraulic system. An EMA system uses dc power provided by a high energy density bipolar lithium thionyl chloride battery, with power conversion performed by low loss resonant topologies, and a high efficiency induction motor controlled with a high performance field oriented controller to drive a linear actuator.