WorldWideScience

Sample records for future reusable launch

  1. Navigation System for Reusable Launch Vehicle

    OpenAIRE

    Schlotterer, Markus

    2008-01-01

    PHOENIX is a downscaled experimental vehicle to demonstrate automatic landing capabilities of future Reusable Launch Vehicles (RLVs). PHOENIX has flown in May 2004 at NEAT (North European Aerospace Test range) in Vidsel, Sweden. As the shape of the vehicle has been designed for re-entry, the dynamics are very high and almost unstable. This requires a fast and precise GNC system. This paper describes the navigation system and the navigation filter of PHOENIX. The system is introduced and the h...

  2. Bantam: A Systematic Approach to Reusable Launch Vehicle Technology Development

    Science.gov (United States)

    Griner, Carolyn; Lyles, Garry

    1999-01-01

    The Bantam technology project is focused on providing a low cost launch capability for very small (100 kilogram) NASA and University science payloads. The cost goal has been set at one million dollars per launch. The Bantam project, however, represents much more than a small payload launch capability. Bantam represents a unique, systematic approach to reusable launch vehicle technology development. This technology maturation approach will enable future highly reusable launch concepts in any payload class. These launch vehicle concepts of the future could deliver payloads for hundreds of dollars per pound, enabling dramatic growth in civil and commercial space enterprise. The National Aeronautics and Space Administration (NASA) has demonstrated a better, faster, and cheaper approach to science discovery in recent years. This approach is exemplified by the successful Mars Exploration Program lead by the Jet Propulsion Laboratory (JPL) for the NASA Space Science Enterprise. The Bantam project represents an approach to space transportation technology maturation that is very similar to the Mars Exploration Program. The NASA Advanced Space Transportation Program (ASTP) and Future X Pathfinder Program will combine to systematically mature reusable space transportation technology from low technology readiness to system level flight demonstration. New reusable space transportation capability will be demonstrated at a small (Bantam) scale approximately every two years. Each flight demonstration will build on the knowledge derived from the previous flight tests. The Bantam scale flight demonstrations will begin with the flights of the X-34. The X-34 will demonstrate reusable launch vehicle technologies including; flight regimes up to Mach 8 and 250,000 feet, autonomous flight operations, all weather operations, twenty-five flights in one year with a surge capability of two flights in less than twenty-four hours and safe abort. The Bantam project will build on this initial

  3. Integrated Entry Guidance for Reusable Launch Vehicle

    Institute of Scientific and Technical Information of China (English)

    NING Guo-dong; ZHANG Shu-guang; FANG Zhen-ping

    2007-01-01

    A method for the implementation of integrated three-degree-of-freedom constrained entry guidance for reusable launch vehicle is presented. Given any feasible entry conditions, terminal area energy management interface conditions, and the reference trajectory generated onboard then, the method can generate a longitudinal guidance profile rapidly, featuring linear quadratic regular method and a proportional-integral-derivative tracking law with time-varying gains, which satisfies all the entry corridor constraints and meets the requirements with high precision. Afterwards, by utilizing special features of crossrange parameter, establishing bank-reversal corridor,and determining bank-reversals according to dynamically adjusted method, the algorithm enables the lateral entry guidance system to fly a wide range of missions and provides reliable and good performance in the presence of significant aerodynamic modeling uncertainty.Fast trajectory guidance profiles and simulations with a reusable launch vehicle model for various missions and aerodynamic uncertainties are presented to demonstrate the capacity and reliability of this method.

  4. 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.

  5. Cryopumping in Cryogenic Insulations for a Reusable Launch Vehicle

    Science.gov (United States)

    Johnson, Theodore F.; Weiser, Erik S.; Grimsley, Brian W.; Jensen, Brian J.

    2003-01-01

    Testing at cryogenic temperatures was performed to verify the material characteristics and manufacturing processes of reusable propellant tank cryogenic insulations for a Reusable Launch Vehicle (RLV). The unique test apparatus and test methods developed for the investigation of cryopumping in cryogenic insulations are described. Panel level test specimens with various types of cryogenic insulations were subjected to a specific thermal profile where the temperature varied from -262 C to 21 C. Cryopumping occurred if the interior temperature of the specimen exhibited abnormal temperature fluctuations, such as a sudden decrease in temperature during the heating phase.

  6. NASA's Reusable Launch Vehicle Technologies: A Composite Materials Overview

    Science.gov (United States)

    Clinton, R. G., Jr.; Cook, Steve; Effinger, Mike; Smith, Dennis; Swint, Shayne

    1999-01-01

    A materials overview of the NASA's Earth-to-Orbit Space Transportation Program is presented. The topics discussed are: Earth-to-Orbit Goals and Challenges; Space Transportation Program Structure; Generations of Reusable Launch Vehicles; Space Transportation Derived Requirements; X 34 Demonstrator; Fastrac Engine System; Airframe Systems; Propulsion Systems; Cryotank Structures; Advanced Materials, Fabrication, Manufacturing, & Assembly; Hot and Cooled Airframe Structures; Ceramic Matrix Composites; Ultra-High Temp Polymer Matrix Composites; Metal Matrix Composites; and PMC Lines Ducts and Valves.

  7. Future reusable space launcher systems - A European view

    Science.gov (United States)

    Reichert, Rudi G.

    Plans for future, reusable space launcher systems in Europe, beyond Ariane V/Hermes, are discussed. A family of launch vehicles, known as the European Advanced Rocket Launchers (EARLs), is presented. Technical and performance data for the EARL concept are given and the cost of development and operating the launchers is estimated. Also, the EARL concept is compared with other planned and existing concepts, including the Saenger launcher.

  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. 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.

  10. 14 CFR 431.35 - Acceptable reusable launch vehicle mission risk.

    Science.gov (United States)

    2010-01-01

    ...) Safety Review and Approval for Launch and Reentry of a Reusable Launch Vehicle § 431.35 Acceptable reusable launch vehicle mission risk. (a) To obtain safety approval for an RLV mission, an applicant must...) To obtain safety approval, an applicant shall demonstrate: (i) For public risk, the risk level to the...

  11. Reusable Launch Vehicle Control In Multiple Time Scale Sliding Modes

    Science.gov (United States)

    Shtessel, Yuri; Hall, Charles; Jackson, Mark

    2000-01-01

    A reusable launch vehicle control problem during ascent is addressed via multiple-time scaled continuous sliding mode control. The proposed sliding mode controller utilizes a two-loop structure and provides robust, de-coupled tracking of both orientation angle command profiles and angular rate command profiles in the presence of bounded external disturbances and plant uncertainties. Sliding mode control causes the angular rate and orientation angle tracking error dynamics to be constrained to linear, de-coupled, homogeneous, and vector valued differential equations with desired eigenvalues placement. Overall stability of a two-loop control system is addressed. An optimal control allocation algorithm is designed that allocates torque commands into end-effector deflection commands, which are executed by the actuators. The dual-time scale sliding mode controller was designed for the X-33 technology demonstration sub-orbital launch vehicle in the launch mode. Simulation results show that the designed controller provides robust, accurate, de-coupled tracking of the orientation angle command profiles in presence of external disturbances and vehicle inertia uncertainties. This is a significant advancement in performance over that achieved with linear, gain scheduled control systems currently being used for launch vehicles.

  12. Controls for Reusable Launch Vehicles During Terminal Area Energy Management

    Science.gov (United States)

    Driessen, Brian J.

    2005-01-01

    During the terminal energy management phase of flight (last of three phases) for a reusable launch vehicle, it is common for the controller to receive guidance commands specifying desired values for (i) the roll angle roll q(sub roll), (ii) the acceleration a(sub n) in the body negative z direction, -k(sub A)-bar, and (iii) omega(sub 3), the projection of onto the body-fixed axis k(sub A)-bar, is always indicated by guidance to be zero. The objective of the controller is to regulate the actual values of these three quantities, i.e make them close to the commanded values, while maintaining system stability.

  13. 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

  14. 14 CFR 431.43 - Reusable launch vehicle mission operational requirements and restrictions.

    Science.gov (United States)

    2010-01-01

    ... vehicle poses risk to public health and safety and the safety of property in excess of acceptable flight... LAUNCH VEHICLE (RLV) Safety Review and Approval for Launch and Reentry of a Reusable Launch Vehicle § 431... RLV mission safety approval shall submit procedures— (1) That ensure RLV mission risks do not exceed...

  15. Modeling and Simulation of Reliability & Maintainability Parameters for Reusable Launch Vehicles using Design of Experiments

    Science.gov (United States)

    Unal, Resit; Morris, W. Douglas; White, Nancy H.; Lepsch, Roger A.

    2004-01-01

    This paper describes the development of a methodology for estimating reliability and maintainability distribution parameters for a reusable launch vehicle. A disciplinary analysis code and experimental designs are used to construct approximation models for performance characteristics. These models are then used in a simulation study to estimate performance characteristic distributions efficiently. The effectiveness and limitations of the developed methodology for launch vehicle operations simulations are also discussed.

  16. Estimating Logistics Support of Reusable Launch Vehicles During Conceptual Design

    Science.gov (United States)

    Morris, W. D.; White, N. H.; Davies, W. T.; Ebeling, C. E.

    1997-01-01

    Methods exist to define the logistics support requirements for new aircraft concepts but are not directly applicable to new launch vehicle concepts. In order to define the support requirements and to discriminate among new technologies and processing choices for these systems, NASA Langley Research Center (LaRC) is developing new analysis methods. This paper describes several methods under development, gives their current status, and discusses the benefits and limitations associated with their use.

  17. Tracks for Eastern/Western European Future Launch Vehicles Cooperation

    Science.gov (United States)

    Eymar, Patrick; Bertschi, Markus

    2002-01-01

    exclusively upon Western European elements indigenously produced. Yet some private initiatives took place successfully in the second half of the nineties (Eurockot and Starsem) bringing together companies from Western and Eastern Europe. Evolution of these JV's are already envisioned. But these ventures relied mostly on already existing vehicles. broadening the bases in order to enlarge the reachable world market appears attractive, even if structural difficulties are complicating the process. had recently started to analyze, with KSRC counterparts how mixing Russian and Western European based elements would provide potential competitive edges. and RKA in the frame of the new ESA's Future Launch Preparatory Programme (FLPP). main technical which have been considered as the most promising (reusable LOx/Hydrocarbon engine, experimental reentry vehicles or demonstrators and reusable launch vehicle first stage or booster. international approach. 1 patrick.eymar@lanceurs.aeromatra.com 2

  18. NASA's Advanced Propulsion Technology Activities for Third Generation Fully Reusable Launch Vehicle Applications

    Science.gov (United States)

    Hueter, Uwe

    2000-01-01

    NASA's Office of Aeronautics and Space Transportation Technology (OASTT) established the following three major goals, referred to as "The Three Pillars for Success": Global Civil Aviation, Revolutionary Technology Leaps, and Access to Space. The Advanced Space Transportation Program Office (ASTP) at the NASA's Marshall Space Flight Center in Huntsville, Ala. focuses on future space transportation technologies under the "Access to Space" pillar. The Propulsion Projects within ASTP under the investment area of Spaceliner100, focus on the earth-to-orbit (ETO) third generation reusable launch vehicle technologies. The goals of Spaceliner 100 is to reduce cost by a factor of 100 and improve safety by a factor of 10,000 over current conditions. The ETO Propulsion Projects in ASTP, are actively developing combination/combined-cycle propulsion technologies that utilized airbreathing propulsion during a major portion of the trajectory. System integration, components, materials and advanced rocket technologies are also being pursued. Over the last several years, one of the main thrusts has been to develop rocket-based combined cycle (RBCC) technologies. The focus has been on conducting ground tests of several engine designs to establish the RBCC flowpaths performance. Flowpath testing of three different RBCC engine designs is progressing. Additionally, vehicle system studies are being conducted to assess potential operational space access vehicles utilizing combined-cycle propulsion systems. The design, manufacturing, and ground testing of a scale flight-type engine are planned. The first flight demonstration of an airbreathing combined cycle propulsion system is envisioned around 2005. The paper will describe the advanced propulsion technologies that are being being developed under the ETO activities in the ASTP program. Progress, findings, and future activities for the propulsion technologies will be discussed.

  19. RADEM: An Air Launched, Rocket Demonstrator for Future Advanced Launch Systems

    Science.gov (United States)

    Parkinson, R. C.; Skorodelov, V. A.; Serdijk, I. I.; Neiland, V. Ya.

    1995-10-01

    Critical features associated with future reusable launch vehicles include reduction of turn around effort, use of integral liquid hydrogen tanks, advanced structures and thermal protection, and re-usable LOx-hydrogen propulsion with low maintenance overheads. Many doubts associated with such designs could be removed by a sub-orbital demonstrator. An air launched vehicle would fulfil many of the objectives for such demonstration. British Aerospace, NPO Molnija, TsAGI and DB Antonov have made an initial study for ESA for such a demonstrator (RADEM), using earlier studies of operational launch systems with the An-225 /Hotol and MAKS proposals. The paper describes the results of this study, including the selection of two potential vehicle designs, and an approach to sub-system design and vehicle development to minimize the costs. It appears that such a vheicle, capable of flying to Mach 12 or beyond using currently available technology, could have a cost an order of magnitude less than that required for development of an operational vehicle.

  20. Advanced Guidance and Control Methods for Reusable Launch Vehicles: Test Results

    Science.gov (United States)

    Hanson, John M.; Jones, Robert E.; Krupp, Don R.; Fogle, Frank R. (Technical Monitor)

    2002-01-01

    There are a number of approaches to advanced guidance and control (AG&C) that have the potential for achieving the goals of significantly increasing reusable launch vehicle (RLV) safety/reliability and reducing the cost. In this paper, we examine some of these methods and compare the results. We briefly introduce the various methods under test, list the test cases used to demonstrate that the desired results are achieved, show an automated test scoring method that greatly reduces the evaluation effort required, and display results of the tests. Results are shown for the algorithms that have entered testing so far.

  1. Design of Neural Network Variable Structure Reentry Control System for Reusable Launch Vehicle

    Institute of Scientific and Technical Information of China (English)

    HU Wei-jun; ZHOU Jun

    2008-01-01

    A flight control system is designed for a reusable launch vehicle with aerodynamic control surfaces and reaction control system based on a variable-structure control and neural network theory. The control problems of coupling among the channels and the uncertainty of model parameters are solved by using the method. High precise and robust tracking of required attitude angles can be achieved in complicated air space. A mathematical model of reusable launch vehicle is pre-sented first, and then a controller of flight system is presented. Base on the mathematical model, the controller is divided into two parts: variable-structure controller and neural network module which is used to modify the parameters of con-troller. This control system decouples the lateral/directional tunnels well with a neural network sliding mode controller and provides a robust and de-coupled tracking for mission angle profiles. After this a control allocation algorithm is employed to allocate the torque moments to aerodynamic control surfaces and thrusters. The final simulation shows that the control system has a good accurate, robust and de-coupled tracking performance. The stable state error is less than 1°, and the overshoot is less than 5%.

  2. Global atmospheric response to emissions from a proposed reusable space launch system

    Science.gov (United States)

    Larson, Erik J. L.; Portmann, Robert W.; Rosenlof, Karen H.; Fahey, David W.; Daniel, John S.; Ross, Martin N.

    2017-01-01

    Modern reusable launch vehicle technology may allow high flight rate space transportation at low cost. Emissions associated with a hydrogen fueled reusable rocket system are modeled based on the launch requirements of developing a space-based solar power system that generates present-day global electric energy demand. Flight rates from 104 to 106 per year are simulated and sustained to a quasisteady state. For the assumed rocket engine, H2O and NOX are the primary emission products; this also includes NOX produced during reentry heating. For a base case of 105 flights per year, global stratospheric and mesospheric water vapor increase by approximately 10 and 100%, respectively. As a result, high-latitude cloudiness increases in the lower stratosphere and near the mesopause by as much as 20%. Increased water vapor also results in global effective radiative forcing of about 0.03 W/m2. NOX produced during reentry exceeds meteoritic production by more than an order of magnitude, and along with in situ stratospheric emissions, results in a 0.5% loss of the globally averaged ozone column, with column losses in the polar regions exceeding 2%.

  3. Closed-loop endo-atmospheric ascent guidance for reusable launch vehicle

    Science.gov (United States)

    Sun, Hongsheng

    This dissertation focuses on the development of a closed-loop endo-atmospheric ascent guidance algorithm for the 2nd generation reusable launch vehicle. Special attention has been given to the issues that impact on viability, complexity and reliability in on-board implementation. The algorithm is called once every guidance update cycle to recalculate the optimal solution based on the current flight condition, taking into account atmospheric effects and path constraints. This is different from traditional ascent guidance algorithms which operate in a simple open-loop mode inside atmosphere, and later switch to a closed-loop vacuum ascent guidance scheme. The classical finite difference method is shown to be well suited for fast solution of the constrained optimal three-dimensional ascent problem. The initial guesses for the solutions are generated using an analytical vacuum optimal ascent guidance algorithm. Homotopy method is employed to gradually introduce the aerodynamic forces to generate the optimal solution from the optimal vacuum solution. The vehicle chosen for this study is the Lockheed Martin X-33 lifting-body reusable launch vehicle. To verify the algorithm presented in this dissertation, a series of open-loop and closed-loop tests are performed for three different missions. Wind effects are also studied in the closed-loop simulations. For comparison, the solutions for the same missions are also obtained by two independent optimization softwares. The results clearly establish the feasibility of closed-loop endo-atmospheric ascent guidance of rocket-powered launch vehicles. ATO cases are also tested to assess the adaptability of the algorithm to autonomously incorporate the abort modes.

  4. Structures and Materials Technologies for Extreme Environments Applied to Reusable Launch Vehicles

    Science.gov (United States)

    Scotti, Stephen J.; Clay, Christopher; Rezin, Marc

    2003-01-01

    This paper provides an overview of the evolution of structures and materials technology approaches to survive the challenging extreme environments encountered by earth-to-orbit space transportation systems, with emphasis on more recent developments in the USA. The evolution of technology requirements and experience in the various approaches to meeting these requirements has significantly influenced the technology approaches. While previous goals were primarily performance driven, more recently dramatic improvements in costs/operations and in safety have been paramount goals. Technologies that focus on the cost/operations and safety goals in the area of hot structures and thermal protection systems for reusable launch vehicles are presented. Assessments of the potential ability of the various technologies to satisfy the technology requirements, and their current technology readiness status are also presented.

  5. Cyclic Oxidation Behavior of CuCrAl Cold-Sprayed Coatings for Reusable Launch Vehicles

    Science.gov (United States)

    Raj, Sai; Karthikeyan, J.

    2009-01-01

    The next generation of reusable launch vehicles is likely to use GRCop-84 [Cu-8(at.%)Cr-4%Nb] copper alloy combustion liners. The application of protective coatings on GRCop-84 liners can minimize or eliminate many of the environmental problems experienced by uncoated liners and significantly extend their operational lives and lower operational cost. A newly developed Cu- 23 (wt.%) Cr-5% Al (CuCrAl) coating, shown to resist hydrogen attack and oxidation in an as-cast form, is currently being considered as a protective coating for GRCop-84. The coating was deposited on GRCop-84 substrates by the cold spray deposition technique, where the CuCrAl was procured as gas-atomized powders. Cyclic oxidation tests were conducted between 773 and 1,073 K to characterize the coated substrates.

  6. A robust adaptive nonlinear fault-tolerant controller via norm estimation for reusable launch vehicles

    Science.gov (United States)

    Hu, Chaofang; Gao, Zhifei; Ren, Yanli; Liu, Yunbing

    2016-11-01

    In this paper, a reusable launch vehicle (RLV) attitude control problem with actuator faults is addressed via the robust adaptive nonlinear fault-tolerant control (FTC) with norm estimation. Firstly, the accurate tracking task of attitude angles in the presence of parameter uncertainties and external disturbances is considered. A fault-free controller is proposed using dynamic surface control (DSC) combined with fuzzy adaptive approach. Furthermore, the minimal learning parameter strategy via norm estimation technique is introduced to reduce the multi-parameter adaptive computation burden of fuzzy approximation of the lump uncertainties. Secondly, a compensation controller is designed to handle the partial loss fault of actuator effectiveness. The unknown maximum eigenvalue of actuator efficiency loss factors is estimated online. Moreover, stability analysis guarantees that all signals of the closed-loop control system are semi-global uniformly ultimately bounded. Finally, illustrative simulations show the effectiveness of the proposed method.

  7. Six-DOF trajectory optimization for reusable launch vehicles via Gauss pseudospectral method

    Institute of Scientific and Technical Information of China (English)

    Zhen Wang; Zhong Wu

    2016-01-01

    To be close to the practical flight process and in-crease the precision of optimal trajectory, a six-degree-of- freedom (6-DOF) trajectory is optimized for the reusable launch vehicle (RLV) using the Gauss pseudospectral method (GPM). Different from the traditional trajectory optimization problem which generaly considers the RLV as a point mass, the coupling between translational dynamics and rotational dynamics is taken into account. An optimization problem is formulated to minimize a performance index subject to 6-DOF equations of motion, including translational and rotational dynamics. A two-step optimal strategy is then introduced to reduce the large calculations caused by multiple variables and convergence confinement in 6-DOF trajectory optimization. The simulation results demonstrate that the 6-DOF trajectory optimal strategy for RLV is feasible.

  8. Solar thermal OTV—Applications to reusable and expendable launch vehicles

    Science.gov (United States)

    Kassler, Thomas L.; Frye, Patrick; Partch, Russ

    2000-07-01

    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 orbitto-orbit transfer systems. Solar thermal propulsion offers significant advantages for near-term expendable launch vehicles (ELVs) such as Delta IV, mid- to farterm 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 maneuvering 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

  9. Natural Atmospheric Environment Model Development for the National Aeronautics and Space Administration's Second Generation Reusable Launch Vehicle

    Science.gov (United States)

    Roberts, Barry C.; Leahy, Frank; Overbey, Glenn; Batts, Glen W.; Parker, Nelson (Technical Monitor)

    2002-01-01

    The National Aeronautics and Space Administration (NASA) recently began development of a new reusable launch vehicle. The program office is located at Marshall Space Flight Center (MSFC) and is called the Second Generation Reusable Launch Vehicle (2GRLV). The purpose of the program is to improve upon the safety and reliability of the first generation reusable launch vehicle, the Space Shuttle. Specifically, the goals are to reduce the risk of crew loss to less than 1-in-10,000 missions and decreased costs by a factor of 10 to approximately $1,000 per pound of payload launched to low Earth orbit. The program is currently in the very early stages of development and many two-stage vehicle concepts will be evaluated. Risk reduction activities are also taking place. These activities include developing new technologies and advancing current technologies to be used by the vehicle. The Environments Group at MSFC is tasked by the 2GRLV Program to develop and maintain an extensive series of analytical tools and environmental databases which enable it to provide detailed atmospheric studies in support of structural, guidance, navigation and control, and operation of the 2GRLV.

  10. Commercial suborbital reusable launch vehicles: ushering in a new era for turbopause exploration (Invited)

    Science.gov (United States)

    Smith, H. T.

    2013-12-01

    Multiple companies are in the process of developing commercial suborbital reusable launch vehicles (sRLV's). While these companies originally targeted space tourism as the primary customer base, it is rapidly becoming apparent that this dramatic increase in low cost access to space could provide revolutionary opportunities for scientific research, engineering/instrument development and STEM education. These burgeoning capabilities will offer unprecedented opportunities regarding access to space with frequent low-cost access to the region of space from the ground to the boundary of near-Earth space at ~100 km. In situ research of this region is difficult because it is too high for aircraft and balloons and yet too low for orbital satellites and spacecraft. However, this region is very significant because it represents the tenuous boundary of Earth's Atmosphere and Space. It contains a critical portion of the atmosphere where the regime transitions from collisional to non-collisional physics and includes complex charged and neutral particle interactions. These new launch vehicles are currently designed for manned and unmanned flights that reach altitudes up to 110 km for 5K-500K per flight with payload capacity exceeding 600 kg. Considering the much higher cost per flight for a sounding rocket with similar capabilities, high flight cadence, and guaranteed return of payload, commercial spacecraft has the potential to revolutionize access to near space. This unprecedented access to space allows participation at all levels of research, engineering, education and the public at large. For example, one can envision a model where students can conduct complete end to end projects where they design, build, fly and analyze data from individual research projects for thousands of dollars instead of hundreds of thousands. Our community is only beginning to grasp the opportunities and impactions of these new capabilities but with operational flights anticipated in 2014, it is

  11. Onboard planning of constrained longitudinal trajectory for reusable launch vehicles in terminal area

    Science.gov (United States)

    Liang, Zixuan; Li, Qingdong; Ren, Zhang

    2016-02-01

    A rapid planning algorithm is developed to generate a constrained longitudinal trajectory onboard for reusable launch vehicles (RLVs) in the terminal area energy management (TAEM) phase. The longitudinal trajectory is planned in the flight-path angle vs. altitude space. This flight-path angle profile is designed with required altitude, flight-path angle and range-to-go, and then optimized as a one-parameter search problem to meet the velocity constraint. Considering the dynamic pressure constraint, a dynamic pressure protection (DPP) method is designed. With the DPP, the highly constrained longitudinal trajectory is generated by tracking the planned flight-path angle profile. Finally, the TAEM trajectory planning algorithm is tested on the X-33 vehicle model in different cases. The algorithm is shown to be effective and robust to generate longitudinal flight trajectories with all constraints satisfied in high precision. In each case, the constrained trajectory is planned within 1 s on a PC, which indicates that the algorithm is feasible to be employed onboard.

  12. Reusable Launch Vehicle Attitude Control Using a Time-Varying Sliding Mode Control Technique

    Science.gov (United States)

    Shtessel, Yuri B.; Zhu, J. Jim; Daniels, Dan; Jackson, Scott (Technical Monitor)

    2002-01-01

    In this paper we present a time-varying sliding mode control (TVSMC) technique for reusable launch vehicle (RLV) attitude control in ascent and entry flight phases. In ascent flight the guidance commands Euler roll, pitch and yaw angles, and in entry flight it commands the aerodynamic angles of bank, attack and sideslip. The controller employs a body rate inner loop and the attitude outer loop, which are separated in time-scale by the singular perturbation principle. The novelty of the TVSMC is that both the sliding surface and the boundary layer dynamics can be varied in real time using the PD-eigenvalue assignment technique. This salient feature is used to cope with control command saturation and integrator windup in the presence of severe disturbance or control effector failure, which enhances the robustness and fault tolerance of the controller. The TV-SMC ascent and descent designs are currently being tested with high fidelity, 6-DOF dispersion simulations. The test results will be presented in the final version of this paper.

  13. Experimental investigation of a graphite-composite wing-box section for a reusable launch vehicle

    Science.gov (United States)

    Sawyer, James Wayne; Bush, Harold; Sutter, Tom

    1997-01-01

    The use of graphite-composites as primary structure is essential for the development of a cost effective single-stage-to-orbit reusable launch vehicle (RLV) to replace the Space Shuttle. A full-scale segment of a graphite-composite wing was designed and fabricated by an industry team and tested at NASA Langley Research Center as a part of the RLV technology development program. The wing-box test component was 1.5 m wide by 3.0 m long and 1.1 m deep. It was construction from honeycomb sandwich panels with graphite-bisaleimide composite skins. The test component was loaded to design limit load in reverse bending followed by a test to design ultimate load, also in reverse bending. It was then loaded to failure. Resistance and fiber optic gages were used to measure strains in the wing box section during the test. A comprehensive finite element analysis of the specimen was performed. The test results verified the structural integrity of the wing-box component for RLV design loads, and good correlation between test and analysis was obtained. Both the failure location and the failure load were accurately predicted by the analysis.

  14. Robust adaptive constrained backstepping flight controller design for re-entry reusable launch vehicle under input constraint

    Directory of Open Access Journals (Sweden)

    Qin Zou

    2015-09-01

    Full Text Available A nonlinear constrained controller is designed for a reusable launch vehicle during re-entry phase in the presence of model uncertainty, external disturbance, and input constraint, via combining sliding mode control and adaptive backstepping control. Since the complex coupling between the translational and rotational dynamics of reusable launch vehicle, a control-oriented model derived from rotational dynamic is used for controller design. During the virtual control input design procedure, a dynamic robust term is utilized to compensate for the uncertainty. In addition, a filter is applied to handle “explosion of terms” problem during the actual control input design. To reduce the computational burden, adaptive law is used to evaluate the unknown norm bound of the lumped uncertainty. An auxiliary system is constructed to compensate for the input constraint effect. The stability of the closed-loop system is analyzed based on Lyapunov theory. Simulation results demonstrate the validity of the developed controller in providing stable tracking of the guidance command by numerical simulation on the 6-degree-of-freedom model of reusable launch vehicle.

  15. In-Space Repair and Refurbishment of Thermal Protection System Structures for Reusable Launch Vehicles

    Science.gov (United States)

    Singh, M.

    2007-01-01

    Advanced repair and refurbishment technologies are critically needed for the thermal protection system of current space transportation systems as well as for future launch and crew return vehicles. There is a history of damage to these systems from impact during ground handling or ice during launch. In addition, there exists the potential for in-orbit damage from micrometeoroid and orbital debris impact as well as different factors (weather, launch acoustics, shearing, etc.) during launch and re-entry. The GRC developed GRABER (Glenn Refractory Adhesive for Bonding and Exterior Repair) material has shown multiuse capability for repair of small cracks and damage in reinforced carbon-carbon (RCC) material. The concept consists of preparing an adhesive paste of desired ceramic with appropriate additives and then applying the paste to the damaged/cracked area of the RCC composites with an adhesive delivery system. The adhesive paste cures at 100-120 C and transforms into a high temperature ceramic during reentry conditions. A number of plasma torch and ArcJet tests were carried out to evaluate the crack repair capability of GRABER materials for Reinforced Carbon-Carbon (RCC) composites. For the large area repair applications, Integrated Systems for Tile and Leading Edge Repair (InSTALER) have been developed and evaluated under various ArcJet testing conditions. In this presentation, performance of the repair materials as applied to RCC is discussed. Additionally, critical in-space repair needs and technical challenges are reviewed.

  16. 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

  17. Coating Development for GRCop-84 Liners for Reusable Launch Vehicles Aided by Modeling Studies

    Science.gov (United States)

    Raj, Sai V.; Ghosn, Louis J.

    2004-01-01

    The design of the next generation of reusable launch vehicles calls for using GRCop-84 copper alloy liners based on a composition invented at the NASA Glenn Research Center. Despite its considerable advantage over other copper alloys, it is expected that GRCop-84 will suffer from environmental degradation depending on the type of rocket fuels used and on thermomechanical fatigue. Applying protective coatings on GRCop-84 substrates can minimize or eliminate many of these problems and extend the operational life of the combustion liner. This could increase component reliability, shorten depot maintenance turnaround times, and lower operating costs. Therefore, Glenn is actively pursuing the development of advanced coatings technology for GRCop-84 liners. Technology is being developed in four major areas: (1) new metallic coating compositions, (2) application techniques, (3) test methods, and (4) life prediction design methodology using finite element analysis. The role of finite element analysis in guiding the coating effort is discussed in this report. Thermal analyses were performed at Glenn for different combinations of top- and bondcoat compositions to determine the temperature variation across the coated cross section with the thickness of the top coat. These calculations were conducted for simulated LH2/LO2 booster engine conditions assuming that the bond coat had a constant thickness of 50 m. The preceding graphs show the predicted temperatures at the outer surface of the top coat (hot wall), at the top-coat/bond-coat interface, at the bond-coat/GRCop-84 interface, and at the GRCop-84 cold wall as a function of top-coat thickness for Cu- 26(wt%)Cr top coat (top graph), Ni-17(wt%)Cr-6%Al-0.5%Y top coat and Cu-26%Cr bond coat, and NiAl top coat and Ni bond coat. In all cases, the temperature of the top coat at the hot wall increased with increasing top-coat thickness and with corresponding decreases in the temperatures at the two interfaces and the cold wall

  18. Second Generation Reusable Launch Vehicle Development and Global Competitiveness of US Space Transportation Industry: Critical Success Factors Assessment

    Science.gov (United States)

    Enyinda, Chris I.

    2002-01-01

    In response to the unrelenting call in both public and private sectors fora to reduce the high cost associated with space transportation, many innovative partially or fully RLV (Reusable Launch Vehicles) designs (X-34-37) were initiated. This call is directed at all levels of space missions including scientific, military, and commercial and all aspects of the missions such as nonrecurring development, manufacture, launch, and operations. According to Wertz, tbr over thirty years, the cost of space access has remained exceedingly high. The consensus in the popular press is that to decrease the current astronomical cost of access to space, more safer, reliable, and economically viable second generation RLVs (SGRLV) must be developed. Countries such as Brazil, India, Japan, and Israel are now gearing up to enter the global launch market with their own commercial space launch vehicles. NASA and the US space launch industry cannot afford to lag behind. Developing SGRLVs will immeasurably improve the US's space transportation capabilities by helping the US to regain the global commercial space markets while supporting the transportation capabilities of NASA's space missions, Developing the SGRLVs will provide affordable commercial space transportation that will assure the competitiveness of the US commercial space transportation industry in the 21st century. Commercial space launch systems are having difficulty obtaining financing because of the high cost and risk involved. Access to key financial markets is necessary for commercial space ventures. However, public sector programs in the form of tax incentives and credits, as well as loan guarantees are not yet available. The purpose of this paper is to stimulate discussion and assess the critical success factors germane for RLVs development and US global competitiveness.

  19. Determining Logistics Ground Support Manpower Requirements for a Reusable Military Launch Vehicle

    Science.gov (United States)

    2007-03-01

    Force Link, 28 February 2005. n. pag. 28 December 2006 http://www.af.mil/news/story.asp?storyID=123009914. Leedy , P. D., & Ormrod , J. E...nature” of providing logistics support to a newly-emerging space launch platform ( Leedy , 2005: 94). As such, the research process exhibited the...requirements can only be “easily divided into discrete, measurable variables” ( Leedy , 2005: 96) based upon historical data for a platform. Since

  20. Quick Access Rocket Exhaust Rig Testing of Coated GRCop-84 Sheets Used to Aid Coating Selection for Reusable Launch Vehicles

    Science.gov (United States)

    Raj, Sai V.; Robinson, Raymond C.; Ghosn, Louis J.

    2005-01-01

    The design of the next generation of reusable launch vehicles calls for using GRCop-84 copper alloy liners based on a composition1 invented at the NASA Glenn Research Center: Cu-8(at.%)Cr-4%Nb. Many of the properties of this alloy have been shown to be far superior to those of other conventional copper alloys, such as NARloy-Z. Despite this considerable advantage, it is expected that GRCop-84 will suffer from some type of environmental degradation depending on the type of rocket fuel utilized. In a liquid hydrogen (LH2), liquid oxygen (LO2) booster engine, copper alloys undergo repeated cycles of oxidation of the copper matrix and subsequent reduction of the copper oxide, a process termed "blanching". Blanching results in increased surface roughness and poor heat-transfer capabilities, local hot spots, decreased engine performance, and premature failure of the liner material. This environmental degradation coupled with the effects of thermomechanical stresses, creep, and high thermal gradients can distort the cooling channel severely, ultimately leading to its failure.

  1. Near-term U.S. military and commercial launch systems. A post cold war assessment of future needs

    Science.gov (United States)

    Whitehair, C. L.; Wolfe, M. G.

    In late 1992, the Vice President's Space Policy Advisory Board made a number of major space policy recommendations that impact the United States launch industry. These recommendations included greater cooperation and synergism and less duplication between the National Aeronautics and Space Administration (NASA) and the Department of Defense (DOD); development of a new, more efficient space launch capability to replace the aging and operationally expensive current launch systems that are finding it increasingly difficult to compete in the global commercial market place; transition to more cost-effective ways of meeting both unmanned and manned space transportation needs in the 21st century; prudent relaxation of security regulations to foster increased world trade; sharing of capabilities with allies and friendly states; and expansion of efforts to forge partnerships with other nations in carefully selected areas. The recommendations were intended to aid the incoming administration and the new president in making funding decisions for near-term future launch systems. In the light of these recommendations, this paper examines the limitations of the current U.S. expendable launch fleet; the performance, operability, reliability, and cost-effectiveness enhancement options available; the availability of new technologies and design changes that can be applied to current systems; the requirements that would have to be met to make U.S. systems more competitive in the global market place; and the advisability of replacing or augmenting current systems with a new "Spacelift" vehicle or family of vehicles. The Spacelift concept is described and assessed against projected domestic and global mission requirements, including possible manned missions. Expendable options are compared with current launch systems and with near-term future systems such as Ariane 5. Alternative design approaches, such as partially reusable concepts; fully reusable systems; and the possibility of using

  2. Space Shuttle Launch Probability Analysis: Understanding History so We Can Predict the Future

    Science.gov (United States)

    Cates, Grant R.

    2014-01-01

    The Space Shuttle was launched 135 times and nearly half of those launches required 2 or more launch attempts. The Space Shuttle launch countdown historical data of 250 launch attempts provides a wealth of data that is important to analyze for strictly historical purposes as well as for use in predicting future launch vehicle launch countdown performance. This paper provides a statistical analysis of all Space Shuttle launch attempts including the empirical probability of launch on any given attempt and the cumulative probability of launch relative to the planned launch date at the start of the initial launch countdown. This information can be used to facilitate launch probability predictions of future launch vehicles such as NASA's Space Shuttle derived SLS. Understanding the cumulative probability of launch is particularly important for missions to Mars since the launch opportunities are relatively short in duration and one must wait for 2 years before a subsequent attempt can begin.

  3. A New Way of Doing Business: Reusable Launch Vehicle Advanced Thermal Protection Systems Technology Development: NASA Ames and Rockwell International Partnership

    Science.gov (United States)

    Carroll, Carol W.; Fleming, Mary; Hogenson, Pete; Green, Michael J.; Rasky, Daniel J. (Technical Monitor)

    1995-01-01

    NASA Ames Research Center and Rockwell International are partners in a Cooperative Agreement (CA) for the development of Thermal Protection Systems (TPS) for the Reusable Launch Vehicle (RLV) Technology Program. This Cooperative Agreement is a 30 month effort focused on transferring NASA innovations to Rockwell and working as partners to advance the state-of-the-art in several TPS areas. The use of a Cooperative Agreement is a new way of doing business for NASA and Industry which eliminates the traditional customer/contractor relationship and replaces it with a NASA/Industry partnership.

  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. Development of the Architectural Simulation Model for Future Launch Systems and its Application to an Existing Launch Fleet

    Science.gov (United States)

    Rabadi, Ghaith

    2005-01-01

    A significant portion of lifecycle costs for launch vehicles are generated during the operations phase. Research indicates that operations costs can account for a large percentage of the total life-cycle costs of reusable space transportation systems. These costs are largely determined by decisions made early during conceptual design. Therefore, operational considerations are an important part of vehicle design and concept analysis process that needs to be modeled and studied early in the design phase. However, this is a difficult and challenging task due to uncertainties of operations definitions, the dynamic and combinatorial nature of the processes, and lack of analytical models and the scarcity of historical data during the conceptual design phase. Ultimately, NASA would like to know the best mix of launch vehicle concepts that would meet the missions launch dates at the minimum cost. To answer this question, we first need to develop a model to estimate the total cost, including the operational cost, to accomplish this set of missions. In this project, we have developed and implemented a discrete-event simulation model using ARENA (a simulation modeling environment) to determine this cost assessment. Discrete-event simulation is widely used in modeling complex systems, including transportation systems, due to its flexibility, and ability to capture the dynamics of the system. The simulation model accepts manifest inputs including the set of missions that need to be accomplished over a period of time, the clients (e.g., NASA or DoD) who wish to transport the payload to space, the payload weights, and their destinations (e.g., International Space Station, LEO, or GEO). A user of the simulation model can define an architecture of reusable or expendable launch vehicles to achieve these missions. Launch vehicles may belong to different families where each family may have it own set of resources, processing times, and cost factors. The goal is to capture the required

  6. A future data environment - reusability vs. citability and synchronisation vs. ingestion

    Science.gov (United States)

    Fleischer, D.

    2012-04-01

    During the last decades data managers dedicated their work to the pursuit for importable data. In the recent years this chase seams to come to an end while funding organisations assume that the approach of data publications with citable data sets will eliminate denial of scientists to commit their data. But is this true for all problems we are facing at the edge of a data avalanche and data intensive science? The concept of citable data is a logical consequence from the connection of points. Potential data providers in the past complained usually about the missing of a credit assignment for data providers and they still do. The selected way of DOI captured data sets is perfectly fitting into the credit system of publisher driven publications with countable citations. This system is well known by scientists for approximately 400 years now. Unfortunately, there is a double bind situation between citeability and reusability. While cooperation of publishers and data archives are coming into existence, it is necessary to get one question clear: "Is it really worth while in the twenty-first century to force data into the publication process of the seventeenth century?" Data publications enable easy citability, but do not support easy data reusability for future users. Additional problems occur in such an environment while taking into account the chances of collaborative data corrections in the institutional repository. The future with huge amounts of data connected with publications makes reconsideration towards a more integrated approach reasonable. In the past data archives were the only infrastructures taking care of long-term data retrievability and availability. Nevertheless, they were never a part of the scientific process from data creation, analysis, interpretation and publication. Data archives were regarded as isolated islands in the sea of scientific data. Accordingly scientists considered data publications like a stumbling stone in their daily routines and

  7. Improved Re-Configurable Sliding Mode Controller for Reusable Launch Vehicle of Second Generation Addressing Aerodynamic Surface Failures and Thrust Deficiencies

    Science.gov (United States)

    Shtessel, Yuri B.

    2002-01-01

    In this report we present a time-varying sliding mode control (TV-SMC) technique for reusable launch vehicle (RLV) attitude control in ascent and entry flight phases. In ascent flight the guidance commands Euler roll, pitch and yaw angles, and in entry flight it commands the aerodynamic angles of bank, attack and sideslip. The controller employs a body rate inner loop and the attitude outer loop, which are separated in time-scale by the singular perturbation principle. The novelty of the TVSMC is that both the sliding surface and the boundary layer dynamics can be varied in real time using the PD-eigenvalue assignment technique. This salient feature is used to cope with control command saturation and integrator windup in the presence of severe disturbance or control effector failure, which enhances the robustness and fault tolerance of the controller. The TV-SMC is developed and tuned up for the X-33 sub-orbital technology demonstration vehicle in launch and re-entry modes. A variety of nominal, dispersion and failure scenarios have tested via high fidelity 6DOF simulations using MAVERIC/SLIM simulation software.

  8. Motivation for Air-Launch: Past, Present, and Future

    Science.gov (United States)

    Kelly, John W.; Rogers, Charles E.; Brierly, Gregory T.; Martin, J Campbell; Murphy, Marshall G.

    2017-01-01

    Air-launch is defined as two or more air-vehicles joined and working together, that eventually separate in flight, and that have a combined performance greater than the sum of the individual parts. The use of the air-launch concept has taken many forms across civil, commercial, and military contexts throughout the history of aviation. Air-launch techniques have been applied for entertainment, movement of materiel and personnel, efficient execution of aeronautical research, increasing aircraft range, and enabling flexible and efficient launch of space vehicles. For each air-launch application identified in the paper, the motivation for that application is discussed.

  9. Alternatives for Future U.S. Space-Launch Capabilities

    Science.gov (United States)

    2006-10-01

    as the crew carrier and the similarly derived top-mounted super-heavy launcher as the cargo carrier—that is, the shuttle-derived super-heavy alterna ...tive considered by CBO. Through 2017, CBO’s estimate of the budgetary resources needed to execute that alterna - tive on the more ambitious schedule...U.S. launch capacity exclude the Sea Launch system operated by Boeing in partnership with RSC- Energia (based in Moscow), Kvaerner ASA (based in Oslo

  10. Space Launch System: Building the Future of Space Exploration

    Science.gov (United States)

    Morgan, Markeeva

    2016-01-01

    NASA has begun a new era of human space exploration, with the goal of landing humans on Mars. To carry out that mission, NASA is building the Space Launch System, the world's most powerful rocket. Space Launch System is currently under construction, with substantial amounts of hardware already created and testing well underway. Because of its unrivaled power, SLS can perform missions no other rocket can, like game-changing science and human landings on Mars. The Journey to Mars has begun; NASA has begun a series of missions that will result in astronauts taking the first steps on the Red Planet.

  11. Launch Processing System operations with a future look to Operations Analyst (OPERA)

    Science.gov (United States)

    Heard, Astrid E.

    1987-01-01

    The Launch Processing System architecture and the ground support operations required to provide Shuttle System engineers with the capability to safely process and launch an Orbiter are described. The described ground operations are the culmination of eleven years of experience and redesign. Some of the 'lessons learned' are examined, and problem areas which ground support operations have identified over the years as the Shuttle and Launch Processing Systems continue to grow in complexity are discussed. The Operational Analyst for Distributed Systems (OPERA), a proposed set of expert systems for the Launch Processing System Operational assistance, is discussed along with its extensions to prospective future configurations and components for the Launch Processing System.

  12. Launch Processing System operations with a future look to Operations Analyst (OPERA)

    Science.gov (United States)

    Heard, Astrid E.

    1987-01-01

    The Launch Processing System architecture and the ground support operations required to provide Shuttle System engineers with the capability to safely process and launch an Orbiter are described. The described ground operations are the culmination of eleven years of experience and redesign. Some of the 'lessons learned' are examined, and problem areas which ground support operations have identified over the years as the Shuttle and Launch Processing Systems continue to grow in complexity are discussed. The Operational Analyst for Distributed Systems (OPERA), a proposed set of expert systems for the Launch Processing System Operational assistance, is discussed along with its extensions to prospective future configurations and components for the Launch Processing System.

  13. Reusable Military Launch Systems (RMLS)

    Science.gov (United States)

    2008-02-01

    Thermal barriers , a kind of seal, are used around openings into the vehicle and in the closeout areas between major components. Aerothermal seals...into the windward side of the vehicle. The thermal barriers are split into the high temperature (nose gear door), low temperature (main gear door...area. The high temperature region is approximately above 2000 degrees F. This area requires the most complicated thermal barriers . The low

  14. Magnetic Launch Assist: NASA's Vision for the Future

    Science.gov (United States)

    Jacobs, William A.; Montenegro, Justino (Technical Monitor)

    2000-01-01

    With the ever-increasing cost of getting to space and the need for safe, reliable, and inexpensive ways to access space. The National Aeronautics and Space Administration (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 generated electricity 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 been developed. Where NASA's MagLev diverges from the traditional train is in the immense amount of power required to propel this vehicle to 183 meters per second in less than 10 seconds. New technologies or the upgrade of existing technologies will need to be investigated in the areas of energy storage and power switching. An added difficulty is the separation of a very large mass (the space vehicle) from the track and the aerodynamics of that vehicle while on the track. These are of great concern and require considerable study and testing. NASA's plan is to mature these technologies in the next 25 years to achieve our goal of launching a full sized space vehicle for under $300 a kilogram.

  15. RLV自主着陆航迹设计与控制研究%Autolanding Trajectory Design and Control for Reusable Launch Vehicle

    Institute of Scientific and Technical Information of China (English)

    罗欢; 侯明善; 刘文风; 唐成师

    2012-01-01

    研究了重复使用运载器(RLV)自主着陆陡下滑捕获-陡下滑-圆弧拉起-指数拉平模式航迹生成算法设计;为解决不同着陆段航迹控制指令跳变问题,提出了航迹指令自适应平滑算法;以捕获点法向过载跳变最小为指标研究了三次多项式陡下滑捕获点的优化方法;给出了完整的在线航迹生成算法;基于法向过载的开环加闭环复合控制指令跟踪方案,使用simulink进行数值仿真,结果显示文章提出的航迹生成算法可以自动生成有效航迹,控制方法可以保证航迹平滑过渡且对初始扰动具有良好的鲁棒性,从而验证了方法的可行性和有效性.%Autolanding trajectory generation algorithm for reusable launch vehicle (RLV) is investigated, the trajectory includes four parts: steep glideslope capture, steep glideslope. Circular pull-up and exponential flare. The trajectory command adaptive smoothing algorithm is proposed to reduce the command jumps between different trajectory sections. The optimization method based minimum normal acceleration jumps for the capture point in steep glideslope and complete on-line trajectory generation algorithm are presented. Numerical simulations were performed using an open and closed-loop composite control scheme, the results show trajectory generation algorithm can generate effective trajectory autonomy, control method can guarantee a smooth transition and robustness against initial disturbance. It verifies the feasibility and effectiveness of this method.

  16. Space Ops 2002: Bringing Space Operations into the 21st Century. Track 3: Operations, Mission Planning and Control. 2nd Generation Reusable Launch Vehicle-Concepts for Flight Operations

    Science.gov (United States)

    Hagopian, Jeff

    2002-01-01

    With the successful implementation of the International Space Station (ISS), the National Aeronautics and Space Administration (NASA) enters a new era of opportunity for scientific research. The ISS provides a working laboratory in space, with tremendous capabilities for scientific research. Utilization of these capabilities requires a launch system capable of routinely transporting crew and logistics to/from the ISS, as well as supporting ISS assembly and maintenance tasks. The Space Shuttle serves as NASA's launch system for performing these functions. The Space Shuttle also serves as NASA's launch system for supporting other science and servicing missions that require a human presence in space. The Space Shuttle provides proof that reusable launch vehicles are technically and physically implementable. However, a couple of problems faced by NASA are the prohibitive cost of operating and maintaining the Space Shuttle and its relative inability to support high launch rates. The 2nd Generation Reusable Launch Vehicle (2nd Gen RLV) is NASA's solution to this problem. The 2nd Gen RLV will provide a robust launch system with increased safety, improved reliability and performance, and less cost. The improved performance and reduced costs of the 2nd Gen RLV will free up resources currently spent on launch services. These resource savings can then be applied to scientific research, which in turn can be supported by the higher launch rate capability of the 2nd Gen RLV. The result is a win - win situation for science and NASA. While meeting NASA's needs, the 2nd Gen RLV also provides the United States aerospace industry with a commercially viable launch capability. One of the keys to achieving the goals of the 2nd Gen RLV is to develop and implement new technologies and processes in the area of flight operations. NASA's experience in operating the Space Shuttle and the ISS has brought to light several areas where automation can be used to augment or eliminate functions

  17. Reusable Software.

    Science.gov (United States)

    1984-03-01

    overseeing reusable software, the Reusable Software Organization ( RUSO ). This author does not feel at this time that establishment of such a specific...49] have not been accompanied by establishment of RUSO -like activities. There is need, however, for assurance that functions which a RUSO might be...assurance 6. establishment and maintenance of reuse archival facilities and activities. Actual establishment of a RUSO is best dictated by size of the

  18. Ares V and Future Very Large Launch Vehicles to Enable Major Astronomical Missions

    Science.gov (United States)

    Thronson, Harley; Langhoff, Stephanie; Stahl, H. Philip; Lester, Daniel

    2008-01-01

    The current NASA architecture planned to return humans to the lunar surface includes the Ares V heavy lift launch vehicle designed primarily to carry the Altair lunar lander and to be available before about 2020. However. the capabilities of this system (and its variants) are such that adapting the vehicle to launch very large optical systems could achieve major scientific goals that are not otherwise possible. For example, an 8-m monolith UV/visual/IR telescope appears able to be launched to the Sun-Earth L2 location by an Ares V with a 10-m fairing. Even larger apertures that are deployed or assembled in space seem possible, which may take advantage of other elements of NASA's future human spaceflight architecture. Alternatively. multiple elements of a spatial array or two or three astronomical observatories might he launched simultaneously. That is, Ares V appears to offer the astronomy communities an opportunity to put into orbit extremely capable observatories, in addition to being a key element of NASA's current architecture for human spaceflight. For the past year, a number of scientists and engineers have been eva1uating concepts for astronomical observatories that take advantage of future large launch vehicles, including the science goals of such missions and design modifications to the vehicle to enable the observatories. In parallel, members of the Solar System science communities have likewise been considering what major science goals can be achieved if new, extremely capable launch systems become available.

  19. Launch processing system operations with a future look to operations analyst (OPERA)

    Science.gov (United States)

    Heard, Astrid E.

    The launch processing system at Kennedy Space Center is used to process a Shuttle vehicle from its initial arrival in an Orbiter processing facility to a launch pad. This paper describes the launch processing system architecture and the ground support operations required to provide Shuttle system engineers with the capability to safely process and launch an Orbiter. The described ground operations are the culmination of 11 years of experience and redesign. In this paper, I examine some of the "lessons learned" and discuss problem areas which ground support operations have identified over the years as the Shuttle and launch processing systems continue to grow in complexity. As we strive to maintain the efficient level of support currently provided, some benefits have been gained through standard information management and automation techniques. However, problems requiring complex correlational analyses of information have defied resolution until artificial intelligence research developed expert system applications technology. The operational analyst for distributed systems (OPERA), a proposed set of expert systems for launch processing system operational assistance, is discussed along with its extensions to prospective future configurations and components for the launch processing system.

  20. Saenger - European reusability

    Science.gov (United States)

    Hoegenauer, E.

    1988-06-01

    An account is given of the design features and performance capabilities of the Saenger two-stage-to-orbit reusable launch vehicle. Saenger, in addition to employing a novel, airbreathing lower-stage propulsion system, is unique in its alternative employment of either a manned, reentry-capable upper stage or an expendable, unmanned cargo-carrying one. This configuration is also noted to offer the use of the lower stage as a hypersonic-cruise passenger aircraft. It is in the choice of a propulsion system configuration that Saenger's designers face the most critical challenge.

  1. Methodology for Assessing Reusability of Spaceflight Hardware

    Science.gov (United States)

    Childress-Thompson, Rhonda; Thomas, L. Dale; Farrington, Phillip

    2017-01-01

    In 2011 the Space Shuttle, the only Reusable Launch Vehicle (RLV) in the world, returned to earth for the final time. Upon retirement of the Space Shuttle, the United States (U.S.) no longer possessed a reusable vehicle or the capability to send American astronauts to space. With the National Aeronautics and Space Administration (NASA) out of the RLV business and now only pursuing Expendable Launch Vehicles (ELV), not only did companies within the U.S. start to actively pursue the development of either RLVs or reusable components, but entities around the world began to venture into the reusable market. For example, SpaceX and Blue Origin are developing reusable vehicles and engines. The Indian Space Research Organization is developing a reusable space plane and Airbus is exploring the possibility of reusing its first stage engines and avionics housed in the flyback propulsion unit referred to as the Advanced Expendable Launcher with Innovative engine Economy (Adeline). Even United Launch Alliance (ULA) has announced plans for eventually replacing the Atlas and Delta expendable rockets with a family of RLVs called Vulcan. Reuse can be categorized as either fully reusable, the situation in which the entire vehicle is recovered, or partially reusable such as the National Space Transportation System (NSTS) where only the Space Shuttle, Space Shuttle Main Engines (SSME), and Solid Rocket Boosters (SRB) are reused. With this influx of renewed interest in reusability for space applications, it is imperative that a systematic approach be developed for assessing the reusability of spaceflight hardware. The partially reusable NSTS offered many opportunities to glean lessons learned; however, when it came to efficient operability for reuse the Space Shuttle and its associated hardware fell short primarily because of its two to four-month turnaround time. Although there have been several attempts at designing RLVs in the past with the X-33, Venture Star and Delta Clipper

  2. Assessment of the Feasibility of Innovative Reusable Launchers

    Science.gov (United States)

    Chiesa, S.; Corpino, S.; Viola, N.

    The demand for getting access to space, in particular to Low Earth Orbit, is increasing and fully reusable launch vehicles (RLVs) are likely to play a key role in the development of future space activities. Up until now this kind of space systems has not been successfully carried out: in fact today only the Space Shuttle, which belongs to the old generation of launchers, is operative and furthermore it is not a fully reusable system. In the nineties many studies regarding advanced transatmospheric planes were started, but no one was accomplished because of the technological problems encountered and the high financial resources required with the corresponding industrial risk. One of the most promising project was the Lockheed Venture Star, which seemed to have serious chances to be carried out. Anyway, if this ever happens, it will take quite a long time thus the operative life of Space Shuttle will have to be extended for the International Space Station support. The purpose of the present work is to assess the feasibility of different kinds of advanced reusable launch vehicles to gain access to space and to meet the requirements of today space flight needs, which are mainly safety and affordability. Single stage to orbit (SSTO), two stage to orbit (TSTO) and the so called "one and a half" stage to orbit vehicles are here taken into account to highlight their advantages and disadvantages. The "one and a half" stage to orbit vehicle takes off and climbs to meet a tanker aircraft to be aerially refuelled and then, after disconnecting from the tanker, it flies to reach the orbit. In this case, apart from the space vehicle, also the tanker aircraft needs a dedicated study to examine the problems related to the refuelling at high subsonic speeds and at a height near the tropopause. Only winged vehicles which take off and land horizontally are considered but different architectural layouts and propulsive configurations are hypothesised. Unlike the Venture Star, which

  3. Ada (Trademark) Reusability Guidelines.

    Science.gov (United States)

    1985-04-01

    to do if a Problem Occurs 61 6.1.10 Examples of Reuse 61 6.2 INTERFACE DESCRIPTION 61 6.2.1 Reusable Component Called Via Subprogram Call by Reuser 62...6.2.2 Reusable Component Calls Subprogram of Reuser 62 6.2.3 Reusable Component is a Task with an Entry Called by Rouser 62 6.2.4 Reusable Component...is a Task that Calls an Entry of Reuser 62 6.2.5 Reusable Component Shares Memory with Subprogram of Reuser 63 6.2.6 Reusable Component is a Task

  4. The application of large scale hybrids to NLS and future personnel launch vehicles

    Science.gov (United States)

    McKinney, Bevin C.

    1992-07-01

    Two new space transportation concepts are being investigated in the United States. One, the National Launch System (NLS), is designed to launch unmanned payloads. Another, the Personnel Launch System (PLS), is a small spacecraft designed exclusively for personnel transport. Consideration is being given to launching the PLS using an element of the NLS booster. Because of the demanding requirements for crew safety and safe return after abort, the PLS may be better served by a launcher optimized for crew safety, leaving the NLS to be optimized for its unmanned cargo carrying role. The unique safety characteristics of hybrid propulsion could be invaluable in this manned launch role. This paper reviews the characteristics of hybrid propulsion as they apply to the PLS mission, and describes the features of an example hybrid PLS launcher. The paper suggests that booster elements of this hybrid PLS launcher could be used to augment NLS core performance for missions that require heavier payloads.

  5. Reusable Rapid Prototyped Blunt Impact Simulator

    Science.gov (United States)

    2016-08-01

    RP technology to create a custom reusable projectile for air-cannon-launched impact research. Several projectile configurations with varying frontal... impact area geometries were manufactured using selective laser sintering RP technology . These projectiles were launched with a compressed air cannon...connector interface for analysis. The objective of this report is to inform the audience of a novel use of RP technology to fabricate projectiles

  6. Technology developments for thrust chambers of future launch vehicle liquid rocket engines

    Energy Technology Data Exchange (ETDEWEB)

    Immich, H.; Alting, J.; Kretschmer, J.; Preclik, D. [Astrium GmbH, Space Infrastructure Div. Advanced Programs and System Engineering, Munich (Germany)

    2003-11-01

    In this paper an overview of recent technology developments for thrust chambers of future launch vehicle liquid rocket engines at Astrium, Space Infrastructure Division (SI), is shown. The main technology developments shown in this paper are: Technologies for enhanced heat transfer to the coolant for expander cycle engines. Advanced injector head technologies. Advanced combustion chamber manufacturing technologies. The main technologies for enhanced heat transfer investigated by subscale chamber hot-firing tests are: Increase of chamber length. Hot gas side ribs in the chamber. Artificially increased surface roughness. The developments for advanced injector head technologies were focused on the design of a new modular subscale chamber injector head. This injector head allows for an easy exchange of different injection elements: By this, cost effective hot-fire tests with different injection element concepts can be performed. The developments for advanced combustion chamber manufacturing technologies are based on subscale chamber tests with a new design of the Astrium subscale chamber. The subscale chamber has been modified by introduction of a segmented cooled cylindrical section which gives the possibility to test different manufacturing concepts for cooled chamber technologies by exchanging the individual segments. The main technology efforts versus advanced manufacturing technologies shown in this paper are: Soldering techniques. Thermal barrier coatings for increased chamber life. A new technology effort is dedicated especially to LOX/Hydrocarbon propellant combinations. Recent hot fire tests on the sub scale chamber with Kerosene and Methane as fuel have already been performed. A comprehensive engine system trade-off between the both propellant combinations (Kerosene vs. Methane) is presently under preparation. (Author)

  7. Technology developments for thrust chambers of future launch vehicle liquid rocket engines

    Science.gov (United States)

    Immich, H.; Alting, J.; Kretschmer, J.; Preclik, D.

    2003-08-01

    In this paper an overview of recent technology developments for thrust chambers of future launch vehicle liquid rocket engines at Astrium, Space Infrastructure Division (SI), is shown. The main technology. developments shown in this paper are: Technologies Technologies for enhanced heat transfer to the coolant for expander cycle engines Advanced injector head technologies Advanced combustion chamber manufacturing technologies. The main technologies for enhanced heat transfer investigated by subscale chamber hot-firing tests are: Increase of chamber length Hot gas side ribs in the chamber Artificially increased surface roughness. The developments for advanced injector head technologies were focused on the design of a new modular subscale chamber injector head. This injector head allows for an easy exchange of different injection elements: By this, cost effective hot-fire tests with different injection element concepts can be performed. The developments for advanced combustion chamber manufacturing technologies are based on subscale chamber tests with a new design of the Astrium subscale chamber. The subscale chamber has been modified by introduction of a segmented cooled cylindrical section which gives the possibility to test different manufacturing concepts for cooled chamber technologies by exchanging the individual segments. The main technology efforts versus advanced manufacturing technologies shown in this paper are: Soldering techniques Thermal barrier coatings for increased chamber life. A new technology effort is dedicated especially to LOX/Hydrocarbon propellant combinations. Recent hot fire tests on the subscale chamber with Kerosene and Methane as fuel have already been performed. A comprehensive engine system trade-off between the both propellant combinations (Kerosene vs. Methane) is presently under preparation.

  8. The 4th Annual"A Legend of the Future China's Leading Enterprises of Tomorrow Award"was Launched

    Institute of Scientific and Technical Information of China (English)

    Guo Yan

    2009-01-01

    @@ Standard Chartered Bank(China)Limited("Standard Chartered China")announced the launch of the 4th"A Legend of the Future-China's Leading Enterprises of Tomorrow Award"("SME Awards")on June 10,2009,in Beijing.Against the backdrop of the global financial tsunami,the 4th SME Award aims to help Small and Medium Enterprises(SMEs)ride out the financial storm and thrive despite the adverse economic environment.

  9. Multidisciplinary design optimization method for suborbital reusable launch vehicle%亚轨道重复使用运载器总体多学科优化方法

    Institute of Scientific and Technical Information of China (English)

    龚春林; 谷良贤; 粟华

    2012-01-01

    In order to figure out tight-coupling overall design problem of Suborbital Reusable Launch Vehicle (SRLV) , the crucial technologies of Multidisciplinary Design Optimization (MDO) were investigated,namely task planning,discipline modeling,integration and solving strategy. A SRLV concept serving as the booster of orbital vehicle was selected as the baseline. First, the overall design task of SRLV was decomposed into seven disciplinary components including geometry,aerodynamics,structure, propulsion, trajectory, aero-heating, and thermal conduction/TPS design. The functions of disciplines and dataflow between them were defined. Then,the computational models of these disciplines were established,which met the requirements of overall design. Based on the task of SRLV,the MDO problems were presented,including objectives,constraints and variables. Within multidisciplinary framework software,the architecture of Multi-Disciplinary Feasible (MDF) was created. By integrating seven disciplinary models into MDF architecture,a MDO software system for SRLV overall design was established. Genetic Algorithm was chosen to optimize the take-off weight of SRLV. The obtained results show that the mass of propulsion structure and TPS parts both increase slightly,but the fuel mass and airframe structural mass decrease,and the take-off weight decreases about 2.4%.%针对亚轨道运载器总体设计多学科耦合的特点,从任务规划、学科建模、集成和求解策略等方面对多学科优化方法进行了研究.以助推亚轨道飞行器为对象,确定了学科模块组成、功能和数据耦合关系.建立了与总体设计过程相适应的7个学科模型,包括几何主模型、气动、推进、弹道、气动热、传热/热防护系统、结构.结合飞行器任务要求和基准方案,从系统级定义了多学科优化问题,包括目标函数、约束条件和设计变量.基于多学科软件框架集成学科模型,采用多学科可行法作为求解框

  10. Aerodynamic flight control to increase payload capability of future launch vehicles

    Science.gov (United States)

    Cochran, John E., Jr.; Cheng, Y.-M.; Leleux, Todd; Bigelow, Scott; Hasbrook, William

    1993-01-01

    In this report, we provide some examples of French, Russian, Chinese, and Japanese launch vehicles that have utilized fins in their designs. Next, the aerodynamic design of the fins is considered in Section 3. Some comments on basic static stability and control theory are followed by a brief description of an aerodynamic characteristics prediction code that was used to estimate the characteristics of a modified NLS 1.5 Stage vehicle. Alternative fin designs are proposed and some estimated aerodynamic characteristics presented and discussed. Also included in Section 3 is a discussion of possible methods of enhancement of the aerodynamic efficiency of fins, such as vortex generators and jet flaps. We consider the construction of fins for launch vehicles in Section 4 and offer an assessment of the state-of-the-art in the use of composites for aerodynamic control surfaces on high speed vehicles. We also comment on the use of smart materials for launch vehicle fins. The dynamic stability and control of a launch vehicle that utilizes both thrust vector control (engine nozzle gimballing) and movable fins is the subject addressed in Section 5. We give a short derivation of equations of motion for a launch vehicle moving in a vertical plane above a spherical earth, discuss the use of a gravity-turn nominal trajectory, and give the form of the period equations linearized about such a nominal. We then consider feedback control of vehicle attitude using both engine gimballing and fin deflection. Conclusions are stated and recommendations made in Section 6. An appendix contains aerodynamic data in tabular and graphical formats.

  11. STARS Reusability Guidelines

    Science.gov (United States)

    1990-04-30

    on the body of the reusable component. Since this effect is usually unexpected, take care to insure that the reuser is aware of the compilation issues...code to depend on the body of the reusable component. Since this effect is usually unexpected, take care to insure that the reuser is aware of the

  12. Highly reusable space transportation system study

    Science.gov (United States)

    Haney, J. W.

    1997-01-01

    To significantly increase demand for launch services by stimulating existing and planned markets as well as enabling new markets, the cost to orbit needs to be reduced a factor of ten below projected Reusable Launch Vehicle (RLV) goals. This will place the recurring operations cost around 200 per payload pound to low earth orbit (LEO). Methods for reducing the cost include: increasing relative vehicle performance, increasing vehicle reusability, and decreasing recurring operations. A study was conducted for NASA in support of its Highly Reusable Space Transportation (HRST) initiative to identify for further assessment and development, those launch strategies that hold the greatest potential with respect to meeting this goal. During this study a number of candidate strategies were evaluated associated with access to space. Both technical and cost trades were performed, and concluded that there are two airbreathing propulsion concepts utilizing launch assist that appear promising in achieving the HRST-cost goals. These concepts employ both turbine based combine cycle (TBCC) and rocket based combine cycle (RBCC) propulsion systems. The launch assist selected uses electromagnetic propulsion and a guideway to provide both delta velocity and altitude. A first order investigation of system level requirements associated with HRST launch assist for a magnetically launched vehicle including guideway concept and requirements as well as magnetic levitation and propulsion concepts and requirements were also conducted. This study concluded that the HRST goals of total recurring operations cost of 200 per payload pound to Low Earth Orbit based on a ten year operational period were feasible if the required technology was matured. The most promising concept to achieve these goals is based on a RBCC powered vehicle with electromagnetic launch assist.

  13. Reusable Launch Vehicles: Rethinking Access to Space (cover title: Reusable Launch Vehicles and Space Operations)

    Science.gov (United States)

    2000-05-01

    to $l billion. See Jamie G. G. Varni, —Space Operations: Through the Looking Glass ,“ 2025 Study (Maxwell Air Force Base, AL: Air University Press...Aviation, 1945 - 1950 (Washington DC: Naval Historical Center, 1994), p. 121. 134. Jamie G.G Varni et al, —Space Operations: Through the Looking Glass ,“ 2025

  14. ICFA announces launch of technology recommendation process for future linear collider

    CERN Multimedia

    2003-01-01

    The International Committee for Future Accelerators has announced the membership and chair of the 12-person International Technology Recommendation Panel. The ITRP, with four members each from Europe, North America and Asia, is charged with recommending which of two leading accelerating technologies will form the best choice for a future international linear collider (1 page).

  15. 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

  16. Reliable, Reusable Cryotank Project

    Data.gov (United States)

    National Aeronautics and Space Administration — Microcracking issues have significantly limited the reusability of state-of-the-art (SOA) composite cryotanks. While developers have made some progress addressing...

  17. Reusable Component Services

    Data.gov (United States)

    U.S. Environmental Protection Agency — The Reusable Component Services (RCS) is a super-catalog of components, services, solutions and technologies that facilitates search, discovery and collaboration in...

  18. Conceptual Design of an APT Reusable Spaceplane

    Science.gov (United States)

    Corpino, S.; Viola, N.

    Safety characteristics. Several applications of this conceptual design methodology have been carried out in order to validate it. Here we will show one of the most challenging case studies: the APT73 spaceplane. Today the demand for getting access to space is increasing and fully reusable launch vehicles are likely to play a key role in future space activities, but up until now this kind of space system has not been successfully developed. The ideal reusable launcher should be a vehicle able to maintain physical integrity during its mission, to takeoff and land at any conventional airport, to be operated with a minimum maintenance effort and to guarantee an adequate safety level. Thanks to its flexibility it should be able to enter the desired orbital plane and to abort its mission any time in case of mishap. Moreover considerable cost reduction could be expected only by having extremely high launch rates comparable to today's aircraft fleets in the commercial airlines business. In our opinion the solution which better meets these specifications is the Aerial Propellant Transfer spaceplane concept, the so called "one stage and a half" space vehicle, which takes off and climbs to meet a tanker aircraft to be aerially re-fuelled and then, after disconnecting from the tanker, it flies to reach the orbit. The APT73 has been designed to reach the Low Earth Orbit to perform two kinds of mission: 1) to release payloads; 2) to be flown as crew return vehicle from the ISS. The concept has emerged from a set of preliminary choices established at the beginning of the project: Possible variants to the basic plan have been investigated and a trade off analysis has been carried out in order to obtain the optimum configuration. Listed below are the options that have been evaluated: This paper provides a technical description of the APT73 and illustrates the design challenges encountered in the development of the project.

  19. 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.

  20. Single reusable spacecraft

    Data.gov (United States)

    National Aeronautics and Space Administration — Design of a my single person reusable spacecraft. It can carry one person and it has to be dropped from an aircraft at an altitude of 40,000 - 45,000 feet. Can be...

  1. Development and flight test of metal-lined CFRP cryogenic tank for reusable rocket

    Science.gov (United States)

    Higuchi, Ken; Takeuchi, Shinsuke; Sato, Eiichi; Naruo, Yoshihiro; Inatani, Yoshifumi; Namiki, Fumiharu; Tanaka, Kohtaro; Watabe, Yoko

    2005-07-01

    A cryogenic tank made of carbon fiber reinforced plastic (CFRP) shell with aluminum thin liner has been designed as a liquid hydrogen (LH2) tank for an ISAS reusable launch vehicle, and the function of it has been proven by repeated flights onboard the test vehicle called reusable vehicle testing (RVT) in October 2003. The liquid hydrogen tank has to be a pressure vessel, because the fuel of the engine of the test vehicle is supplied by fuel pressure. The pressure vessel of a combination of the outer shell of CFRP for strength element at a cryogenic temperature and the inner liner of aluminum for gas barrier has shown excellent weight merit for this purpose. Interfaces such as tank outline shape, bulk capacity, maximum expected operating pressure (MEOP), thermal insulation, pipe arrangement, and measurement of data are also designed to be ready onboard. This research has many aims, not only development of reusable cryogenic composite tank but also the demonstration of repeated operation including thermal cycle and stress cycle, familiarization with test techniques of operation of cryogenic composite tanks, and the accumulation of data for future design of tanks, vehicle structures, safety evaluation, and total operation systems.

  2. Reusable Security Requirements

    Science.gov (United States)

    2016-06-13

    2003 by Carnegie Mellon University page 1 Carnegie Mellon Software Engineering Institute Reusable Security Requirements RE’2003 RHAS’03 Workshop...PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) Carnegie Mellon University , Software Engineering Institute,Pittsburgh,PA,15213 8. PERFORMING...Carnegie Mellon University page 2 Carnegie Mellon Software Engineering Institute In a Nut Shell • Similar Assets, Attackers, and Threats • Security

  3. A Survey of Software Reusability

    OpenAIRE

    Rohit Patidar; Prof. Virendra Singh

    2014-01-01

    Reusability is an only one best direction to increase developing productivity and maintainability of application. One must first search for good tested software component and reusable. Developed Application software by one programmer can be shown useful for others also component. This is proving that code specifics to application requirements can be also reused in develop projects related with same requirements. The main aim of this paper proposed a way for reusable module. An...

  4. 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...

  5. A Survey of Software Reusability

    Directory of Open Access Journals (Sweden)

    Rohit Patidar

    2014-08-01

    Full Text Available Reusability is an only one best direction to increase developing productivity and maintainability of application. One must first search for good tested software component and reusable. Developed Application software by one programmer can be shown useful for others also component. This is proving that code specifics to application requirements can be also reused in develop projects related with same requirements. The main aim of this paper proposed a way for reusable module. An process that takes source code as a input that will helped to take the decision approximately which particular software, reusable artefacts should be reused or not.

  6. Authoring Systems Delivering Reusable Learning Objects

    Directory of Open Access Journals (Sweden)

    George Nicola Sammour

    2009-10-01

    Full Text Available A three layer e-learning course development model has been defined based on a conceptual model of learning content object. It starts by decomposing the learning content into small chunks which are initially placed in a hierarchic structure of units and blocks. The raw content components, being the atomic learning objects (ALO, were linked to the blocks and are structured in the database. We set forward a dynamic generation of LO's using re-usable e-learning raw materials or ALO’s In that view we need a LO authoring/ assembling system fitting the requirements of interoperability and reusability and starting from selecting the raw learning content from the learning materials content database. In practice authoring systems are used to develop e-learning courses. The company EDUWEST has developed an authoring system that is database based and will be SCORM compliant in the near future.

  7. Integration of reusable systems

    CERN Document Server

    Rubin, Stuart

    2014-01-01

    Software reuse and integration has been described as the process of creating software systems from existing software rather than building software systems from scratch. Whereas reuse solely deals with the artifacts creation, integration focuses on how reusable artifacts interact with the already existing parts of the specified transformation. Currently, most reuse research focuses on creating and integrating adaptable components at development or at compile time. However, with the emergence of ubiquitous computing, reuse technologies that can support adaptation and reconfiguration of architectures and components at runtime are in demand. This edited book includes 15 high quality research papers written by experts in information reuse and integration to cover the most recent advances in the field. These papers are extended versions of the best papers which were presented at IEEE International Conference on Information Reuse and Integration and IEEE International Workshop on Formal Methods Integration, which wa...

  8. Viability of a Reusable In-Space Transportation System

    Science.gov (United States)

    Jefferies, Sharon A.; McCleskey, Carey M.; Nufer, Brian M.; Lepsch, Roger A.; Merrill, Raymond G.; North, David D.; Martin, John G.; Komar, David R.

    2015-01-01

    The National Aeronautics and Space Administration (NASA) is currently developing options for an Evolvable Mars Campaign (EMC) that expands human presence from Low Earth Orbit (LEO) into the solar system and to the surface of Mars. The Hybrid in-space transportation architecture is one option being investigated within the EMC. The architecture enables return of the entire in-space propulsion stage and habitat to cis-lunar space after a round trip to Mars. This concept of operations opens the door for a fully reusable Mars transportation system from cis-lunar space to a Mars parking orbit and back. This paper explores the reuse of in-space transportation systems, with a focus on the propulsion systems. It begins by examining why reusability should be pursued and defines reusability in space-flight context. A range of functions and enablers associated with preparing a system for reuse are identified and a vision for reusability is proposed that can be advanced and implemented as new capabilities are developed. Following this, past reusable spacecraft and servicing capabilities, as well as those currently in development are discussed. Using the Hybrid transportation architecture as an example, an assessment of the degree of reusability that can be incorporated into the architecture with current capabilities is provided and areas for development are identified that will enable greater levels of reuse in the future. Implications and implementation challenges specific to the architecture are also presented.

  9. Research of a Reusable Application

    Institute of Scientific and Technical Information of China (English)

    QiangWang; WanhuaQiu

    2004-01-01

    We will present the concept and definition about software architecture and software reuse. And then discuss the software architecture that can be reused. Finally we present a demo of reusable software system in a MIS project.

  10. Reusable Launch Vehicle Design Implications for Regeneration Time

    Science.gov (United States)

    2009-03-01

    Michalski & Johnson, 2007). The problem with developing a generic model is that the vehicle does not yet exist; therefore, recovery, maintenance, and...Assessment For the second objective of gaining insight into ground operations using the model) many studies were performed (Johnson et al, 2006; Michalski ...2007; Michalski and Johnson, 2007; Michalski and Johnson 2008; Johnson and Jackson 2008, Johnson et al, 2008). Although the baseline MILEPOST

  11. Process Time Refinement for Reusable Launch Vehicle Regeneration Modeling

    Science.gov (United States)

    2008-03-01

    Adjustments / Calibrations / Post-Repair QC 138 HLV systems check Inspections / Checks / Diagnosis / Troubleshooting 131 139 Waterproof TPS Adjustments...stenciling, lettering, installing decals, instrument range marking, etc., and painting for cosmetic purposes only). Do Not Use This Code For Treating...painting for cosmetic purposes only). Do Not Use This Code For Treating Corrosion or Painting of Parts/Assemblies/Equipment For Corrosion Prevention

  12. Quality Initiatives in the Commercial Development of Reusable Launch Vehicles

    Science.gov (United States)

    2015-03-01

    them, made some observers cynical about NASA’s capacity to create a second-generation RLV—the Space Shuttle was the first generation RLV. a. First...and material transactions and decisions, especially at process and organizational interfaces. Let Customers Pull The customer pulls products from...programs in recent years. The principal attributes of the IPPD management approach include: (1) aligning the organizational structure with the work

  13. Cryogenic Composite Tank Fabrication for Reusable Launch Vehicles Project

    Data.gov (United States)

    National Aeronautics and Space Administration — XCOR has conducted extensive research and development, and material characterization analysis of a nonflammable, high-strength, lightweight thermoplastic...

  14. SPECIAL COLLOQUIUM : Building a Commercial Space Launch System and the Role of Space Tourism in the Future (exceptionally on Tuesday)

    CERN Document Server

    CERN. Geneva

    2010-01-01

    The talk will explore a little of the history of space launch systems and rocketry, will explain why commercial space tourism did not take off after Apollo, and what is happening right now with commercial space systems such as Virgin's, utilising advances in aerospace technology not exploited by conventional ground-based rocket systems. I will then explain the Virgin Galactic technology, its business plan as a US-regulated space tourism company, and the nature of its applications. I will then go on to say a little of how our system can be utilised for sub-orbital space science based on a commercial business plan

  15. Fast, linked, and open – the future of taxonomic publishing for plants: launching the journal PhytoKeys

    Directory of Open Access Journals (Sweden)

    Lyubomir Penev

    2010-11-01

    Full Text Available The paper describes the focus, scope and the rationale of PhytoKeys, a newly established, peer-reviewed, open-access journal in plant systematics. PhytoKeys is launched to respond to four main challenges of our time: (1 Appearance of electronic publications as amendments or even alternatives to paper publications; (2 Open Access (OA as a new publishing model; (3 Linkage of electronic registers, indices and aggregators that summarize information on biological species through taxonomic names or their persistent identifiers (Globally Unique Identifiers or GUIDs; currently Life Science Identifiers or LSIDs; (4 Web 2.0 technologies that permit the semantic markup of, and semantic enhancements to, published biological texts. The journal will pursue cutting-edge technologies in publication and dissemination of biodiversity information while strictly following the requirements of the current International Code of Botanical Nomenclature (ICBN.

  16. RBCC可重复使用运载器上升段轨迹优化设计%Since the multi-phase and multi-control-variable trajectory of the reusable launch vehicle ( RLV) which is coupled with the thrust powered by rocket based combined cycle (RBCC) is difficult to solve,the numerical optimization model and method based on Gau

    Institute of Scientific and Technical Information of China (English)

    龚春林; 韩璐

    2012-01-01

    Since the multi-phase and multi-control-variable trajectory of the reusable launch vehicle ( RLV) which is coupled with the thrust powered by rocket based combined cycle (RBCC) is difficult to solve,the numerical optimization model and method based on Gauss Pseudospectral Method (CPM) were proposed,and the optimal-fuel ascent trajectory was obtained. Hie trajectory is divided into three phases powered by rocket,ramjet and scramjet in sequence. The angle of attack and fuel flow are control variables,and according to the trajectory mission,the ignition and work condition of the each mode,the optimization model was built,the terminal and path constraints were imposed. The optimal trajectory was solved by using GPM and the boundary control variables were solved by a special method. Compared with the result by traditional method,the optimization model and GPM can solve trajectory optimization problems effectively, and the optimal result accords with the characteristic of the RBCC-powered RLV and satisfies all the constraints.%针对火箭基组合动力(RBCC)可重复使用运载器(RLV)轨迹多段、多控制变量、推力与飞行轨迹耦合,飞行轨迹设计困难的问题,提出了基于高斯伪光谱方法的数值优化求解模型和求解方法,并获得满足要求的上升段燃料最省轨迹.将该轨迹分为3部分,分别由引射火箭、亚燃冲压和超燃冲压发动机提供动力,以攻角和燃料秒流量为控制变量,根据轨迹任务和各模态发动机启动及工作条件建立优化模型、设定各段末端和路径约束,利用高斯伪谱法求解最优轨迹并利用特殊方法计算边界控制变量.通过与传统方法所得轨迹的对比表明,所建立的优化模型和方法可快速求解出RBCC运载器上升段最优轨迹,优化结果符合RBCC运载器工作特点.

  17. 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

  18. Synthetic studies on reusable propulsion system: (1) Study on the reliability design method (2) General planning of the reusable propulsion system

    OpenAIRE

    Kuratani, Naoshi; Taguchi, Hideyuki; Himeno, Takehiro; Hasegawa, Takuya; Aoki, Hiroshi; 倉谷 尚志; 田口 秀之; 姫野 武洋; 長谷川 卓也; 青木 宏

    2004-01-01

    Synthetic studies on the reusable and future propulsion systems are presented in this paper. Especially, focused are the high reliability design methodology for the liquid rocket engine at conceptual phase, the flight demonstration project SubLEO that is propelled by the existing propulsion system, the propellant management of the liquid propellant behavior in the fuselage tank for the reusable vehicle testing and existing rocket under the accelerated environment and the health monitoring sen...

  19. Self-Healing Nanocomposites for Reusable Composite Cryotanks

    Science.gov (United States)

    Eberly, Daniel; Ou, Runqing; Karcz, Adam; Skandan, Ganesh

    2013-01-01

    Composite cryotanks, or composite overwrapped pressure vessels (COPVs), offer advantages over currently used aluminum-lithium cryotanks, particularly with respect to weight savings. Future NASA missions are expected to use COPVs in spaceflight propellant tanks to store fuels, oxidizers, and other liquids for launch and space exploration vehicles. However, reliability, reparability, and reusability of the COPVs are still being addressed, especially in cryogenic temperature applications; this has limited the adoption of COPVs in reusable vehicle designs. The major problem with composites is the inherent brittleness of the epoxy matrix, which is prone to microcrack formation, either from exposure to cryogenic conditions or from impact from different sources. If not prevented, the microcracks increase gas permeation and leakage. Accordingly, materials innovations are needed to mitigate microcrack damage, and prevent damage in the first place, in composite cryotanks. The self-healing technology being developed is capable of healing the microcracks through the use of a novel engineered nanocomposite, where a uniquely designed nanoparticle additive is incorporated into the epoxy matrix. In particular, this results in an enhancement in the burst pressure after cryogenic cycling of the nanocomposite COPVs, relative to the control COPVs. Incorporating a novel, self-healing, epoxy-based resin into the manufacture of COPVs allows repeatable self-healing of microcracks to be performed through the simple application of a low-temperature heat source. This permits COPVs to be reparable and reusable with a high degree of reliability, as microcracks will be remediated. The unique phase-separated morphology that was imparted during COPV manufacture allows for multiple self-healing cycles. Unlike single-target approaches where one material property is often improved at the expense of another, robustness has been introduced to a COPV by a combination of a modified resin and

  20. Design of launch systems using continuous improvement process

    Science.gov (United States)

    Brown, Richard W.

    1995-01-01

    The purpose of this paper is to identify a systematic process for improving ground operations for future launch systems. This approach is based on the Total Quality Management (TQM) continuous improvement process. While the continuous improvement process is normally identified with making incremental changes to an existing system, it can be used on new systems if they use past experience as a knowledge base. In the case of the Reusable Launch Vehicle (RLV), the Space Shuttle operations provide many lessons. The TQM methodology used for this paper will be borrowed from the United States Air Force 'Quality Air Force' Program. There is a general overview of the continuous improvement process, with concentration on the formulation phase. During this phase critical analyses are conducted to determine the strategy and goals for the remaining development process. These analyses include analyzing the mission from the customers point of view, developing an operations concept for the future, assessing current capabilities and determining the gap to be closed between current capabilities and future needs and requirements. A brief analyses of the RLV, relative to the Space Shuttle, will be used to illustrate the concept. Using the continuous improvement design concept has many advantages. These include a customer oriented process which will develop a more marketable product and a better integration of operations and systems during the design phase. But, the use of TQM techniques will require changes, including more discipline in the design process and more emphasis on data gathering for operational systems. The benefits will far outweigh the additional effort.

  1. Reusable Reentry Satellite (RRS) system design study

    Science.gov (United States)

    1991-01-01

    The Reusable Reentry Satellite (RRS) is intended to provide investigators in several biological disciplines with a relatively inexpensive method to access space for up to 60 days with eventual recovery on Earth. The RRS will permit totally intact, relatively soft, recovery of the vehicle, system refurbishment, and reflight with new and varied payloads. The RRS is to be capable of three reflights per year over a 10-year program lifetime. The RRS vehicle will have a large and readily accessible volume near the vehicle center of gravity for the Payload Module (PM) containing the experiment hardware. The vehicle is configured to permit the experimenter late access to the PM prior to launch and rapid access following recovery. The RRS will operate in one of two modes: (1) as a free-flying spacecraft in orbit, and will be allowed to drift in attitude to provide an acceleration environment of less than 10(exp -5) g. the acceleration environment during orbital trim maneuvers will be less than 10(exp -3) g; and (2) as an artificial gravity system which spins at controlled rates to provide an artificial gravity of up to 1.5 Earth g. The RRS system will be designed to be rugged, easily maintained, and economically refurbishable for the next flight. Some systems may be designed to be replaced rather than refurbished, if cost effective and capable of meeting the specified turnaround time. The minimum time between recovery and reflight will be approximately 60 days. The PMs will be designed to be relatively autonomous, with experiments that require few commands and limited telemetry. Mass data storage will be accommodated in the PM. The hardware development and implementation phase is currently expected to start in 1991 with a first launch in late 1993.

  2. Launch Options for the Future

    Science.gov (United States)

    1988-01-01

    B. Callaham Stephen W. Korthals-Altes Gordon Law Ray A- Williamson Administrative Staff Jannie Home Cecile Parker Jackie Robinson...more than half of current U.S. payload mass to low earth orbit. Coilgun for Cargo - Electric catapults and guns have been studied since the 1930s, but

  3. Reusable rocket engine optical condition monitoring

    Science.gov (United States)

    Wyett, L.; Maram, J.; Barkhoudarian, S.; Reinert, J.

    1987-01-01

    Plume emission spectrometry and optical leak detection are described as two new applications of optical techniques to reusable rocket engine condition monitoring. Plume spectrometry has been used with laboratory flames and reusable rocket engines to characterize both the nominal combustion spectra and anomalous spectra of contaminants burning in these plumes. Holographic interferometry has been used to identify leaks and quantify leak rates from reusable rocket engine joints and welds.

  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

  5. 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

  6. 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

  7. The K-1 reusable aerospace vehicle: managing to achieve low cost.

    Science.gov (United States)

    Mueller (HM), George E.; Lepore, Debra Facktor

    2000-03-01

    Kistler Aerospace Corporation is developing the world's first privately funded, fully reusable aerospace vehicle, the K-1. This vehicle represents a new implementation of proven technologies, designed by an elite, experienced team of engineers and managers and implemented by the best manufacturing capability in the United States. Kistler Aerospace expects to begin commercial operations of the K-1 in 2000. Market researchers predict that during the next decade telecommunications satellite ventures will require launch services for over 1,400 payloads to LEO. This prediction greatly exceeds the current available industry capacity. The K-1 was designed primarily to meet this anticipated growth in demand. Significant progress has been made in constructing the K-1 vehicle fleet. The fully reusable K-1 vehicle is designed to lower the cost of access to space, increase launch reliability, and reduce lead-time-to-launch requirements. The K-1 will offer significant cost benefits and aircraft type reliability based on a proven flight record.

  8. Russian aluminum-lithium alloys for advanced reusable spacecraft

    Science.gov (United States)

    Charette, Ray O.; Leonard, Bruce G.; Bozich, William F.; Deamer, David A.

    1998-01-01

    Cryotanks that are cost-affordable, robust, fuel-compatible, and lighter weight than current aluminum design are needed to support next-generation launch system performance and operability goals. The Boeing (McDonnell Douglas Aerospace-MDA) and NASA's Delta Clipper-Experimental Program (DC-XA) flight demonstrator test bed vehicle provided the opportunity for technology transfer of Russia's extensive experience base with weight-efficient, highly weldable aluminum-lithium (Al-Li) alloys for cryogenic tank usage. As part of NASA's overall reusable launch vehicle (RLV) program to help provide technology and operations data for use in advanced RLVs, MDA contracted with the Russian Academy of Sciences (RAS/IMASH) for design, test, and delivery of 1460 Al-Li alloy liquid oxygen (LO2) cryotanks: one for development, one for ground tests, and one for DC-XA flight tests. This paper describes the development of Al-Li 1460 alloy for reusable LO2 tanks, including alloy composition tailoring, mechanical properties database, forming, welding, chemical milling, dissimilar metal joining, corrosion protection, completed tanks proof, and qualification testing. Mechanical properties of the parent and welded materials exceeded expectations, particularly the fracture toughness, which promise excellent reuse potential. The LO2 cryotank was successfully demonstrated in DC-XA flight tests.

  9. REUSABLE PROPULSION ARCHITECTURE FOR SUSTAINABLE LOW-COST ACCESS TO SPACE

    Science.gov (United States)

    Bonometti, J. A.; Dankanich, J. W.; Frame, K. L.

    2005-01-01

    The primary obstacle to any space-based mission is, and has always been, the cost of access to space. Even with impressive efforts toward reusability, no system has come close to lowering the cost a significant amount. It is postulated here, that architectural innovation is necessary to make reusability feasible, not incremental subsystem changes. This paper shows two architectural approaches of reusability that merit further study investments. Both #inherently# have performance increases and cost advantages to make affordable access to space a near term reality. A rocket launched from a subsonic aircraft (specifically the Crossbow methodology) and a momentum exchange tether, reboosted by electrodynamics, offer possibilities of substantial reductions in the total transportation architecture mass - making access-to-space cost-effective. They also offer intangible benefits that reduce risk or offer large growth potential. The cost analysis indicates that approximately a 50% savings is obtained using today#s aerospace materials and practices.

  10. RL-10 Based Combined Cycle For A Small Reusable Single-Stage-To-Orbit Launcher

    Science.gov (United States)

    Balepin, Vladimir; Price, John; Filipenco, Victor

    1999-01-01

    This paper discusses a new application of the combined propulsion known as the KLIN(TM) cycle, consisting of a thermally integrated deeply cooled turbojet (DCTJ) and liquid rocket engine (LRE). If based on the RL10 rocket engine family, the KLIN (TM) cycle makes a small single-stage-to-orbit (SSTO) reusable launcher feasible and economically very attractive. Considered in this paper are the concept and parameters of a small SSTO reusable launch vehicle (RLV) powered by the KLIN (TM) cycle (sSSTO(TM)) launcher. Also discussed are the benefits of the small launcher, the reusability, and the combined cycle application. This paper shows the significant reduction of the gross take off weight (GTOW) and dry weight of the KLIN(TM) cycle-powered launcher compared to an all-rocket launcher.

  11. The Reusable Astronomy Portal (TRAP)

    Science.gov (United States)

    Donaldson, T.; Rogers, A.; Wallace, G.

    2012-09-01

    The Reusable Astronomy Portal (TRAP) aims to provide a common platform for rapidly deploying Astronomy Archives to the web. TRAP is currently under development for both the VAO Data Discovery Portal and the MAST Multi-Mission Portal (Figure 1). TRAP consists of 2 major software packages: the TRAP Client and the TRAP Server. The TRAP framework allows developers to deploy the Server, connect to data resources, then focus on building custom tools for the Client. TRAP is built upon proven industry technologies including the Ext/JS JavaScript Component Library, Mono.NET Web Services, and JSON message based APIs. The multi-layered architecture of TRAP decouples each layer: Client, Service and Data Access, enabling each to evolve independently over time. Although currently deployed to provide astronomy science data access, the TRAP architecture is flexible enough to thrive in any distributed data environment.

  12. 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.

  13. 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.

  14. Using PHM to measure equipment usable life on the Air Force's next generation reusable space booster

    Science.gov (United States)

    Blasdel, A.

    The U.S. Air Force procures many launch vehicles and launch vehicle services to place their satellites at their desired location in space. The equipment on-board these satellite and launch vehicle often suffer from premature failures that result in the total loss of the satellite or a shortened mission life sometimes requiring the purchase of a replacement satellite and launch vehicle. The Air Force uses its EELV to launch its high priority satellites. Due to a rise in the cost of purchasing a launch using the Air Force's EELV from 72M in 1997 to as high as 475M per launch today, the Air Force is working to replace the EELV with a reusable space booster (RSB). The RSB will be similar in design and operations to the recently cancelled NASA reusable space booster known as the Space Shuttle. If the Air Force uses the same process that procures the EELV and other launch vehicles and satellites, the RSB will also suffer from premature equipment failures thus putting the payloads at a similar high risk of mission failure. The RSB is expected to lower each launch cost by 50% compared to the EELV. The development of the RSB offers the Air Force an opportunity to use a new reliability paradigm that includes a prognostic and health management program and a condition-based maintenance program. These both require using intelligent, decision making self-prognostic equipment The prognostic and health management program and its condition-based maintenance program allows increases in RSB equipment usable life, lower logistics and maintenance costs, while increasing safety and mission assurance. The PHM removes many decisions from personnel that, in the past resulted in catastrophic failures and loss of life. Adding intelligent, decision-making self-prognostic equipment to the RSB will further decrease launch costs while decreasing risk and increasing safety and mission assurance.

  15. Health Monitoring Technology for Thermal Protection Systems on Reusable Hypersonic Vehicles

    Science.gov (United States)

    Milos, Frank S.; Watters, D. G.; Heinemann, J. M.; Karunaratne, K. S.; Arnold, Jim (Technical Monitor)

    2001-01-01

    Integrated subsystem health diagnostics is an area where major improvements have been identified for potential implementation into the design of new reusable launch vehicles (RLVs) in order to reduce life cycle costs, to increase safety margins, and to improve mission reliability. This talk summarizes a joint effort between NASA Ames and industry partners to develop rapid non-contact diagnostic tools for health and performance monitoring of thermal protection systems (TPS) on future RLVs. The specific goals for TPS health monitoring are to increase the speed and reliability of TPS inspections for improved operability at lower cost. The technology being developed includes a 3-D laser scanner for examining the exterior surface of the TPS, and a subsurface microsensor suite for monitoring the health and performance of the TPS. The sensor suite consists of passive overlimit sensors and sensors for continuous parameter monitoring in flight. The sensors are integrated with radio-frequency identification (RFID) microchips to enable wireless communication of-the sensor data to an external reader that may be a hand-held scanner or a large portal. Prototypes of the laser system and both types of subsurface sensors have been developed. The laser scanner was tested on Shuttle Orbiter Columbia and was able to dimension surface chips and holes on a variety of TPS materials. The temperature-overlimit microsensor has a diameter under 0.05 inch (suitable for placement in gaps between ceramic TPS tiles) and can withstand 700 F for 15 minutes.

  16. Reusable shape memory polymer mandrels

    Science.gov (United States)

    Everhart, Matthew C.; Stahl, Jaime

    2005-05-01

    Cornerstone Research Group, Inc. (CRG) has recently demonstrated the feasibility of filament winding complex compound-curved composite shapes on shape memory polymer (SMP) mandrels. Under thermal stimuli, SMPs can exhibit a radical change from a rigid polymer to a flexible, elastic state, and then back to a rigid state again. SMP tubes were fabricated using CRG's Veriflex, a thermoset SMP resin system. The SMP tubes were raised above the transition temperature, the temperature at which the SMP becomes pliable and rubber-like and inflated inside a clamshell master metal mold with a cavity in the shape of the desired mandrel. The SMP was then cooled; the lowering of the temperature allows the SMP to become a rigid structure again, resulting in an exact replica of the cavity without the need of air pressure. A composite part was filament wound onto the SMP mandrel and after curing of the composite, the SMP mandrel is again raised above the transition temperature. This allows the mandrel to return to its memory shape for easy extraction. This paper will demonstrate and discuss the feasibility of SMP mandrels for filament winding and fiber placement composite manufacturing techniques allowing for quick, easy, and low cost mandrels that are dimensionally accurate, autoclave-tolerant, rapidly removable, and reusable .

  17. Reusable State Machine Code Generator

    Science.gov (United States)

    Hoffstadt, A. A.; Reyes, C.; Sommer, H.; Andolfato, L.

    2010-12-01

    The State Machine model is frequently used to represent the behaviour of a system, allowing one to express and execute this behaviour in a deterministic way. A graphical representation such as a UML State Chart diagram tames the complexity of the system, thus facilitating changes to the model and communication between developers and domain experts. We present a reusable state machine code generator, developed by the Universidad Técnica Federico Santa María and the European Southern Observatory. The generator itself is based on the open source project architecture, and uses UML State Chart models as input. This allows for a modular design and a clean separation between generator and generated code. The generated state machine code has well-defined interfaces that are independent of the implementation artefacts such as the middle-ware. This allows using the generator in the substantially different observatory software of the Atacama Large Millimeter Array and the ESO Very Large Telescope. A project-specific mapping layer for event and transition notification connects the state machine code to its environment, which can be the Common Software of these projects, or any other project. This approach even allows to automatically create tests for a generated state machine, using techniques from software testing, such as path-coverage.

  18. SCASim: A Flexible and Reusable Detector Simulator for the MIRI instrument of the JWST

    Science.gov (United States)

    Beard, S.; Morin, J.; Gastaud, R.; Azzollini, R.; Bouchet, P.; Chaintreuil, S.; Lahuis, F.; Littlejohns, O.; Nehme, C.; Pye, J.

    2012-09-01

    The JWST Mid Infrared Instrument (MIRI) operates in the 5-28μm wavelength range and can be configured for imaging, coronographic imaging, long-slit, low-resolution spectroscopy or medium resolution spectroscopy with an integral field unit. SCASim is one of a suite of simulators which operate together to simulate all the different modes of the instrument. These simulators are essential for the efficient operation of MIRI; allowing more accurate planning of MIRI observations on sky or during the pre-launch testing of the instrument. The data generated by the simulators are essential for testing the data pipeline software. The simulators not only need to reproduce the behaviour of the instrument faithfully, they also need to be adaptable so that information learned about the instrument during the pre-launch testing and in-orbit commissioning can be fed back into the simulation. SCASim simulates the behaviour of the MIRI detectors, taking into account cosmetic effects, quantum efficiency, shot noise, dark current, read noise, amplifier layout, cosmic ray hits, etc... The software has benefited from three major design choices. First, the development of a suite of MIRI simulators, rather than single simulator, has allowed MIRI simulators to be developed in parallel by different teams, with each simulator able to concentrate on one particular area. SCASim provides a facility common to all the other simulators and saves duplication of effort. Second, SCASim has a Python-based object-oriented design which makes it easier to adapt as new information about the instrument is learned during testing. Third, all simulator parameters are maintained in external files, rather than being hard coded in the software. These design choices have made SCASim highly reusable. In its present form it can be used to simulate any JWST detector, and it can be adapted for future instruments with similar, photon-counting detectors.

  19. Technical and Economical study of New Technologies and Reusable Space Vehicles promoting Space Tourism.

    Science.gov (United States)

    Srivastav, Deepanshu; Malhotra, Sahil

    2012-07-01

    For many of us space tourism is an extremely fascinating and attractive idea. But in order for these to start we need vehicles that will take us to orbit and bring us back. Current space vehicles clearly cannot. Only the Space Shuttle survives past one use, and that's only if we ignore the various parts that fall off on the way up. So we need reusable launch vehicles. Launch of these vehicles to orbit requires accelerating to Mach 26, and therefore it uses a lot of propellant - about 10 tons per passenger. But there is no technical reason why reusable launch vehicles couldn't come to be operated routinely, just like aircraft. The main problem about space is how much it costs to get there, it's too expensive. And that's mainly because launch vehicles are expendable - either entirely, like satellite launchers, or partly, like the space shuttle. The trouble is that these will not only reduce the cost of launch - they'll also put the makers out of business, unless there's more to launch than just a few satellites a year, as there are today. Fortunately there's a market that will generate far more launch business than satellites ever well - passenger travel. This paper assesses this emerging market as well as technology that will make space tourism feasible. The main conclusion is that space vehicles can reduce the cost of human transport to orbit sufficiently for large new commercial markets to develop. Combining the reusability of space vehicles with the high traffic levels of space tourism offers the prospect of a thousandfold reduction in the cost per seat to orbit. The result will be airline operations to orbit involving dozens of space vehicles, each capable of more than one flight per day. These low costs will make possible a rapid expansion of space science and exploration. Luckily research aimed at developing low-cost reusable launch vehicles has increased recently. Already there are various projects like Spaceshipone, Spaceshiptwo, Spacebus, X-33 NASA etc. The

  20. A Business Analysis of a SKYLON-based European Launch Service Operator

    Science.gov (United States)

    Hempsell, Mark; Aprea, Julio; Gallagher, Ben; Sadlier, Greg

    2016-04-01

    Between 2012 and 2014 an industrial consortium led by Reaction Engines conducted a feasibility study for the European Space Agency with the objective to explore the feasibility of SKYLON as the basis for a launcher that meets the requirements established for the Next Generation European Launcher. SKYLON is a fully reusable single stage to orbit launch system that is enabled by the unique performance characteristic of the Synergetic Air-Breathing Rocket Engine and is under active development. The purpose of the study which was called "SKYLON-based European Launch Service Operator (S-ELSO)" was to support ESA decision making on launch service strategy by exploring the potential implications of this new launch system on future European launch capability and the European industry that supports it. The study explored both a SKYLON operator (S-ELSO) and SKYLON manufacturer as separate business ventures. In keeping with previous studies, the only strategy that was found that kept the purchase price of the SKYLON low enough for a viable operator business was to follow an "airline" business model where the manufacturer sells SKYLONs to other operators in addition to S-ELSO. With the assumptions made in the study it was found that the SKYLON manufacturer with a total production run of between 30 and 100 SKYLONs could expect an Internal Rate of Return of around 10%. This was judged too low for all the funding to come from commercial funding sources, but is sufficiently high for a Public Private Partnership. The S-ELSO business model showed that the Internal Rate of Return would be high enough to consider operating without public support (i.e. commercial in operation, irrespective of any public funding of development), even when the average launch price is lowered to match the lowest currently quoted price for expendable systems.

  1. 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

  2. Technology development for metallic hot structures in aerodynamic control surfaces of reusable launchers

    NARCIS (Netherlands)

    Sudmeijer, K.J.; Wentzel, C.; Lefeber, B.M.; Kloosterman, A.

    2002-01-01

    In this paper a summary is presented of the technology development in the Netherlands focussed on the design and development of a metallic aerodynamic control surface for the future European reusable launcher. The applied materials are mainly Oxide Dispersion Strengthened (ODS) alloys produced by

  3. 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

  4. Normalized Specifications for Identifying Reusable Software

    OpenAIRE

    Luqi

    1987-01-01

    An approach to retrieving reusable software components by means of module specifications is described. The approach depends on normalizing specifications to reduce the variations in the representation of software concepts. The concept is illustrated in terms of both formal and informal approaches to component specifications.

  5. Supporting software reusability with polymorphic types

    NARCIS (Netherlands)

    Laverman, Bert

    1995-01-01

    This thesis concerns the technical problems of software reuse and the -related- problem of constructing highly reusable software. Although several of the problems of software reuse are to be found in the fields of psychology and/or economics, the technica plroblems are there to be solved as well. On

  6. 14 CFR 437.67 - Tracking a reusable suborbital rocket.

    Science.gov (United States)

    2010-01-01

    ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Tracking a reusable suborbital rocket. 437... a reusable suborbital rocket. A permittee must— (a) During permitted flight, measure in real time the position and velocity of its reusable suborbital rocket; and (b) Provide position and...

  7. Futurism.

    Science.gov (United States)

    Foy, Jane Loring

    The objectives of this research report are to gain insight into the main problems of the future and to ascertain the attitudes that the general population has toward the treatment of these problems. In the first section of this report the future is explored socially, psychologically, and environmentally. The second section describes the techniques…

  8. Air Force Reusable Booster System: A Quick-look, Design Focused Modeling and Cost Analysis Study

    Science.gov (United States)

    Zapata, Edgar

    2011-01-01

    This paper presents a method and an initial analysis of the costs of a reusable booster system (RBS) as envisioned by the US Department of Defense (DoD) and numerous initiatives that form the concept of Operationally Responsive Space (ORS). This paper leverages the knowledge gained from decades of experience with the semi-reusable NASA Space Shuttle to understand how the costs of a military next generation semi-reusable space transport might behave in the real world - and how it might be made as affordable as desired. The NASA Space Shuttle had a semi-expendable booster, that being the reusable Solid Rocket MotorslBoosters (SRMlSRB) and the expendable cryogenic External Tank (ET), with a reusable cargo and crew capable orbiter. This paper will explore DoD concepts that invert this architectural arrangement, using a reusable booster plane that flies back to base soon after launch, with the in-space elements of the launch system being the expendable portions. Cost estimating in the earliest stages of any potential, large scale program has limited usefulness. As a result, the emphasis here is on developing an approach, a structure, and the basic concepts that could continue to be matured as the program gains knowledge. Where cost estimates are provided, these results by necessity carry many caveats and assumptions, and this analysis becomes more about ways in which drivers of costs for diverse scenarios can be better understood. The paper is informed throughout with a design-for-cost philosophy whereby the design and technology features of the proposed RBS (who and what, the "architecture") are taken as linked at the hip to a desire to perform a certain mission (where and when), and together these inform the cost, responsiveness, performance and sustainability (how) of the system. Concepts for developing, acquiring, producing or operating the system will be shown for their inextricable relationship to the "architecture" of the system, and how these too relate to costs

  9. 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.

  10. An Approach to Design Reusable Workflow Engine

    Institute of Scientific and Technical Information of China (English)

    2005-01-01

    Developers still need design workflow system according to users' specific needs, though workflow management coalition standardized the five kinds of abstract interfaces in workflow reference model. Specific business process characteristics are still supported by specific workflow system. A set of common functionalities of workflow engine are abstracted from business component, so the reusability of business component is extended into workflow engine and composition method is proposed. Needs of different business requirements and characteristics are met by reusing the workflow engine.

  11. Multigraph: Reusable Interactive Data Graphs

    Science.gov (United States)

    Phillips, M. B.

    2010-12-01

    There are surprisingly few good software tools available for presenting time series data on the internet. The most common practice is to use a desktop program such as Excel or Matlab to save a graph as an image which can be included in a web page like any other image. This disconnects the graph from the data in a way that makes updating a graph with new data a cumbersome manual process, and it limits the user to one particular view of the data. The Multigraph project defines an XML format for describing interactive data graphs, and software tools for creating and rendering those graphs in web pages and other internet connected applications. Viewing a Multigraph graph is extremely simple and intuitive, and requires no instructions; the user can pan and zoom by clicking and dragging, in a familiar "Google Maps" kind of way. Creating a new graph for inclusion in a web page involves writing a simple XML configuration file. Multigraph can read data in a variety of formats, and can display data from a web service, allowing users to "surf" through large data sets, downloading only those the parts of the data that are needed for display. The Multigraph XML format, or "MUGL" for short, provides a concise description of the visual properties of a graph, such as axes, plot styles, data sources, labels, etc, as well as interactivity properties such as how and whether the user can pan or zoom along each axis. Multigraph reads a file in this format, draws the described graph, and allows the user to interact with it. Multigraph software currently includes a Flash application for embedding graphs in web pages, a Flex component for embedding graphs in larger Flex/Flash applications, and a plugin for creating graphs in the WordPress content management system. Plans for the future include a Java version for desktop viewing and editing, a command line version for batch and server side rendering, and possibly Android and iPhone versions. Multigraph is currently in use on several web

  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. Portability and Reusability, Standardized Programming for Present and Future Computers

    Science.gov (United States)

    Dumont, Jean-Jacques; Tomassini, Marco

    Unstructured sequential programming in Fortran, together with a top down approach for problem analysis, have always been and still are the usual physicists favorite methods as far as computing is concerned. This unfortunate fact of life is causing a tremendous amount of efficiency loss for code development and maintenance, which could easily be avoided by evolving to a more modern, bottom up programming style, based on the new emerging standards (system interfaces, communication between computational nodes, object-oriented C-extensions, user graphical interfaces, data structures etc.). We are reaching the historical point where this evolution becomes mandatory if one wants to tackle properly the problem of programming in a reasonably efficient way the highly parallel machines which are now appearing on the market, to the delight of numerous scientists who are badly in need of more computation power.

  15. 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.

  16. Mars Conjunction Crewed Missions With a Reusable Hybrid Architecture

    Science.gov (United States)

    Merrill, Raymond G.; Strange, Nathan J.; Qu, Min; Hatten, Noble

    2015-01-01

    A new crew Mars architecture has been developed that provides many potential benefits for NASA-led human Mars moons and surface missions beginning in the 2030s or 2040s. By using both chemical and electric propulsion systems where they are most beneficial and maintaining as much orbital energy as possible, the Hybrid spaceship that carries crew round trip to Mars is pre-integrated before launch and can be delivered to orbit by a single launch. After check-out on the way to cis-lunar space, it is refueled and can travel round trip to Mars in less than 1100 days, with a minimum of 300 days in Mars vicinity (opportunity dependent). The entire spaceship is recaptured into cis-lunar space and can be reused. The spaceship consists of a habitat for 4 crew attached to the Hybrid propulsion stage which uses long duration electric and chemical in-space propulsion technologies that are in use today. The hybrid architecture's con-ops has no in-space assembly of the crew transfer vehicle and requires only rendezvous of crew in a highly elliptical Earth orbit for arrival at and departure from the spaceship. The crew transfer vehicle does not travel to Mars so it only needs be able to last in space for weeks and re-enter at lunar velocities. The spaceship can be refueled and resupplied for multiple trips to Mars (every other opportunity). The hybrid propulsion stage for crewed transits can also be utilized for cargo delivery to Mars every other opportunity in a reusable manner to pre-deploy infrastructure required for Mars vicinity operations. Finally, the Hybrid architecture provides evolution options for mitigating key long-duration space exploration risks, including crew microgravity and radiation exposure.

  17. A literature review on business process modelling: new frontiers of reusability

    Science.gov (United States)

    Aldin, Laden; de Cesare, Sergio

    2011-08-01

    Business process modelling (BPM) has become fundamental for modern enterprises due to the increasing rate of organisational change. As a consequence, business processes need to be continuously (re-)designed as well as subsequently aligned with the corresponding enterprise information systems. One major problem associated with the design of business processes is reusability. Reuse of business process models has the potential of increasing the efficiency and effectiveness of BPM. This article critically surveys the existing literature on the problem of BPM reusability and more specifically on that State-of-the-Art research that can provide or suggest the 'elements' required for the development of a methodology aimed at discovering reusable conceptual artefacts in the form of patterns. The article initially clarifies the definitions of business process and business process model; then, it sets out to explore the previous research conducted in areas that have an impact on reusability in BPM. The article concludes by distilling directions for future research towards the development of apatterns-based approach to BPM; an approach that brings together the contributions made by the research community in the areas of process mining and discovery, declarative approaches and ontologies.

  18. Aerosciences, Aero-Propulsion and Flight Mechanics Technology Development for NASA's Next Generation Launch Technology Program

    Science.gov (United States)

    Cockrell, Charles E., Jr.

    2003-01-01

    The Next Generation Launch Technology (NGLT) program, Vehicle Systems Research and Technology (VSR&T) project is pursuing technology advancements in aerothermodynamics, aeropropulsion and flight mechanics to enable development of future reusable launch vehicle (RLV) systems. The current design trade space includes rocket-propelled, hypersonic airbreathing and hybrid systems in two-stage and single-stage configurations. Aerothermodynamics technologies include experimental and computational databases to evaluate stage separation of two-stage vehicles as well as computational and trajectory simulation tools for this problem. Additionally, advancements in high-fidelity computational tools and measurement techniques are being pursued along with the study of flow physics phenomena, such as boundary-layer transition. Aero-propulsion technology development includes scramjet flowpath development and integration, with a current emphasis on hypervelocity (Mach 10 and above) operation, as well as the study of aero-propulsive interactions and the impact on overall vehicle performance. Flight mechanics technology development is focused on advanced guidance, navigation and control (GN&C) algorithms and adaptive flight control systems for both rocket-propelled and airbreathing vehicles.

  19. Building Reusable Software Component For Optimization Check in ABAP Coding

    Directory of Open Access Journals (Sweden)

    P.Shireesha

    2010-07-01

    Full Text Available Software component reuse is the software engineering practice of developing newsoftware products from existing components. A reuse library or component reuserepository organizes stores and manages reusable components. This paper describeshow a reusable component is created, how it reuses the function and checking ifoptimized code is being used in building programs and applications. Finally providingcoding guidelines, standards and best practices used for creating reusable componentsand guidelines and best practices for making configurable and easy to use.

  20. Building Reusable Software Component For Optimization Check in ABAP Coding

    CERN Document Server

    Shireesha, P; 10.5121/ijsea.2010.1303

    2010-01-01

    Software component reuse is the software engineering practice of developing new software products from existing components. A reuse library or component reuse repository organizes stores and manages reusable components. This paper describes how a reusable component is created, how it reuses the function and checking if optimized code is being used in building programs and applications. Finally providing coding guidelines, standards and best practices used for creating reusable components and guidelines and best practices for making configurable and easy to use.

  1. An Approach to Calculate Reusability in Source Code Using Metrics

    OpenAIRE

    Rohit Patidar; Prof. Virendra Singh

    2015-01-01

    Reusability is an only one best direction to increase developing productivity and maintainability of application. One must first search for good tested software component and reusable. Developed Application software by one programmer can be shown useful for others also component. This is proving that code specifics to application requirements can be also reused in develop projects related with same requirements. The main aim of this paper proposed a way for reusable module. An pro...

  2. Building Reusable Software Component For Optimization Check in ABAP Coding

    OpenAIRE

    Shireesha, P.; S.S.V.N.Sharma

    2010-01-01

    Software component reuse is the software engineering practice of developing new software products from existing components. A reuse library or component reuse repository organizes stores and manages reusable components. This paper describes how a reusable component is created, how it reuses the function and checking if optimized code is being used in building programs and applications. Finally providing coding guidelines, standards and best practices used for creating reusable components and ...

  3. 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

  4. An Approach to Calculate Reusability in Source Code Using Metrics

    Directory of Open Access Journals (Sweden)

    Rohit Patidar

    2015-02-01

    Full Text Available Reusability is an only one best direction to increase developing productivity and maintainability of application. One must first search for good tested software component and reusable. Developed Application software by one programmer can be shown useful for others also component. This is proving that code specifics to application requirements can be also reused in develop projects related with same requirements. The main aim of this paper proposed a way for reusable module. An process that takes source code as a input that will helped to take the decision approximately which particular software, reusable artefacts should be reused or not.

  5. Simulated meteoroid penetration of reusable surface insulation

    Science.gov (United States)

    Lehman, J. K.; Christensen, H. E.

    1973-01-01

    Meteoroid impact simulation test results on insulation tiles were used to determine penetration resistance of reusable surface insulation attached to simulated shuttle structures. The probability of no meteoroid damage to a typical shuttle orbiter was determined. Specimens were plasma jet tested to determine effects of various size meteoroid cavities on their thermal performance. None of the tiles failed catastrophically, but large, egg-shaped craters did result from meteoroid penetration. The metallic side of a specimen that was completely penetrated showed a petalled hole typical for thin gage shielded structures.

  6. Reusable Reentry Satellite (RRS) system design study: System cost estimates document

    Science.gov (United States)

    1991-01-01

    The Reusable Reentry Satellite (RRS) program was initiated to provide life science investigators relatively inexpensive, frequent access to space for extended periods of time with eventual satellite recovery on earth. The RRS will provide an on-orbit laboratory for research on biological and material processes, be launched from a number of expendable launch vehicles, and operate in Low-Altitude Earth Orbit (LEO) as a free-flying unmanned laboratory. SAIC's design will provide independent atmospheric reentry and soft landing in the continental U.S., orbit for a maximum of 60 days, and will sustain three flights per year for 10 years. The Reusable Reentry Vehicle (RRV) will be 3-axis stabilized with artificial gravity up to 1.5g's, be rugged and easily maintainable, and have a modular design to accommodate a satellite bus and separate modular payloads (e.g., rodent module, general biological module, ESA microgravity botany facility, general botany module). The purpose of this System Cost Estimate Document is to provide a Life Cycle Cost Estimate (LCCE) for a NASA RRS Program using SAIC's RRS design. The estimate includes development, procurement, and 10 years of operations and support (O&S) costs for NASA's RRS program. The estimate does not include costs for other agencies which may track or interface with the RRS program (e.g., Air Force tracking agencies or individual RRS experimenters involved with special payload modules (PM's)). The life cycle cost estimate extends over the 10 year operation and support period FY99-2008.

  7. Learning Objects Reusability Effectiveness Metric (LOREM

    Directory of Open Access Journals (Sweden)

    Torky Ibrahim Sultan

    2014-03-01

    Full Text Available In this research we aim to propose an advanced metric to evaluate the effectiveness of learning objects in order to be reused in new contexts. By the way learning objects reusability is achieving economic benefits from educational technology as it saving time and improving quality, but in case of choosing unsuitable learning object it may be less benefit than creating the learning object from scratch. Actually learning objects reusability can facilitate systems development and adaptation. By surveying the current evaluation metrics, we found that while they cover essential aspects, they enables all reviewers of learning objects to evaluate all criteria without paying attention to their roles in creating the learning object which affect their capability to evaluate specific criteria. Our proposed Approach (LOREM is evaluating learning objects based on a group of Aspects which measure their level of effectiveness in order to be reused in other contexts. LOREM classifies reviewers into 3 categories; 1. Academic Group: (Subject Expert Matter “SME” and Instructor. 2. Technical Group: (Instructional Designer “ID”, LO Developer and LO Designer. 3. Students group. The authorization of reviewers in these several categories are differentiated according to reviewer's type, e.g., (Instructor, LO Developer and their area of expert (their expertise subjects for academic and students reviewers.

  8. Methodology for Evaluating Quality and Reusability of Learning Objects

    Science.gov (United States)

    Kurilovas, Eugenijus; Bireniene, Virginija; Serikoviene, Silvija

    2011-01-01

    The aim of the paper is to present the scientific model and several methods for the expert evaluation of quality of learning objects (LOs) paying especial attention to LOs reusability level. The activities of eQNet Quality Network for a European Learning Resource Exchange (LRE) aimed to improve reusability of LOs of European Schoolnet's LRE…

  9. Characteristic model based control of the X-34 reusable launch vehicle in its climbing phase

    Institute of Scientific and Technical Information of China (English)

    MENG Bin; WU HongXin; LIN ZongLi; LI Guo

    2009-01-01

    In this paper,a characteristic model based longitudinal control design for the trans-aerosphere vehicle X-34 In its transonic and hypersonic climbing phase is proposed.The design is based on the dynamic characteristics of the vehicle and the curves it is to track in this climbing phase.Through a detailed analysis of the aerodynamics and vehicle dynamics during this climbing phase,an explicit description of the tracking curve for the flight path angle is derived.On the basis of this tracking curve,the tracking curves for the two short-period variables,the angle of attack and the pitch rate,are designed.An all-coefficient adaptive controller is then designed,based on the characteristic modeling,to cause these two short-period variables to follow their respective tracking curves.The proposed design does not require multiple working points,making the design procedure simple.Numerical simulation is performed to validate the performance of the controller.The simulation results Indicate that the resulting control law ensures that the vehicle climbs up successfully under the restrictions on the pitch angle and overloading.

  10. Automated System Checkout to Support Predictive Maintenance for the Reusable Launch Vehicle

    Science.gov (United States)

    Patterson-Hine, Ann; Deb, Somnath; Kulkarni, Deepak; Wang, Yao; Lau, Sonie (Technical Monitor)

    1998-01-01

    The Propulsion Checkout and Control System (PCCS) is a predictive maintenance software system. The real-time checkout procedures and diagnostics are designed to detect components that need maintenance based on their condition, rather than using more conventional approaches such as scheduled or reliability centered maintenance. Predictive maintenance can reduce turn-around time and cost and increase safety as compared to conventional maintenance approaches. Real-time sensor validation, limit checking, statistical anomaly detection, and failure prediction based on simulation models are employed. Multi-signal models, useful for testability analysis during system design, are used during the operational phase to detect and isolate degraded or failed components. The TEAMS-RT real-time diagnostic engine was developed to utilize the multi-signal models by Qualtech Systems, Inc. Capability of predicting the maintenance condition was successfully demonstrated with a variety of data, from simulation to actual operation on the Integrated Propulsion Technology Demonstrator (IPTD) at Marshall Space Flight Center (MSFC). Playback of IPTD valve actuations for feature recognition updates identified an otherwise undetectable Main Propulsion System 12 inch prevalve degradation. The algorithms were loaded into the Propulsion Checkout and Control System for further development and are the first known application of predictive Integrated Vehicle Health Management to an operational cryogenic testbed. The software performed successfully in real-time, meeting the required performance goal of 1 second cycle time.

  11. High-Fidelity Real-Time Trajectory Optimization for Reusable Launch Vehicles

    Science.gov (United States)

    2006-12-01

    Pure Teleoperations Adaptive Behaviors Situational AwarenessFeature ID Mission PlanningPath Planning Obstacle Detection/ Disturbance Estimation Path...Following Obstacle Detection/ Disturbance Rejection Figure 1.8 Autonomy Spectrum Adapted from Ref. [92]. Since optimal solutions are rarely...these angular relationships. The first approach consists of using trigonometry based on the physical geometry of the flight angles. This is done by

  12. Technology transfer metrics: Measurement and verification of data/reusable launch vehicle business analysis

    Science.gov (United States)

    Trivoli, George W.

    1996-01-01

    Congress and the Executive Branch have mandated that all branches of the Federal Government exert a concentrated effort to transfer appropriate government and government contractor-developed technology to the industrial use in the U.S. economy. For many years, NASA has had a formal technology transfer program to transmit information about new technologies developed for space applications into the industrial or commercial sector. Marshall Space Flight Center (MSFC) has been in the forefront of the development of U.S. industrial assistance programs using technologies developed at the Center. During 1992-93, MSFC initiated a technology transfer metrics study. The MSFC study was the first of its kind among the various NASA centers. The metrics study is a continuing process, with periodic updates that reflect on-going technology transfer activities.

  13. Integrated G and C Implementation within IDOS: A Simulink Based Reusable Launch Vehicle Simulation

    Science.gov (United States)

    Fisher, Joseph E.; Bevacqua, Tim; Lawrence, Douglas A.; Zhu, J. Jim; Mahoney, Michael

    2003-01-01

    The implementation of multiple Integrated Guidance and Control (IG&C) algorithms per flight phase within a vehicle simulation poses a daunting task to coordinate algorithm interactions with the other G&C components and with vehicle subsystems. Currently being developed by Universal Space Lines LLC (USL) under contract from NASA, the Integrated Development and Operations System (IDOS) contains a high fidelity Simulink vehicle simulation, which provides a means to test cutting edge G&C technologies. Combining the modularity of this vehicle simulation and Simulink s built-in primitive blocks provide a quick way to implement algorithms. To add discrete-event functionality to the unfinished IDOS simulation, Vehicle Event Manager (VEM) and Integrated Vehicle Health Monitoring (IVHM) subsystems were created to provide discrete-event and pseudo-health monitoring processing capabilities. Matlab's Stateflow is used to create the IVHM and Event Manager subsystems and to implement a supervisory logic controller referred to as the Auto-commander as part of the IG&C to coordinate the control system adaptation and reconfiguration and to select the control and guidance algorithms for a given flight phase. Manual creation of the Stateflow charts for all of these subsystems is a tedious and time-consuming process. The Stateflow Auto-builder was developed as a Matlab based software tool for the automatic generation of a Stateflow chart from information contained in a database. This paper describes the IG&C, VEM and IVHM implementations in IDOS. In addition, this paper describes the Stateflow Auto-builder.

  14. Performance Study of Staging Variables on Two-Stage-to-Orbit Reusable Launch Vehicles

    Science.gov (United States)

    2005-03-01

    Milton E. Franke (Chairman) date ____________________________________ Ralph A. Anthenien (Member... Milton Franke, for his guidance and support throughout the course of this thesis effort. The insight and experience was certainly appreciated. I...Management, Air Force Institute of Technology (AU), Wright- Patterson AFB OH, March 2004. 2. Murphy, Kelly J. Gary Erickson , and Scott Goodliff

  15. The Development of Reusable Luggage Tag with the Internet of Things for Mobile Tracking and Environmental Sustainability

    Directory of Open Access Journals (Sweden)

    Eugene Y. C. Wong

    2016-12-01

    Full Text Available With more than two billion passengers worldwide travelling by air each year, vast amounts of lost luggage and disposable paper adhesive luggage tags are pushing the aviation industry to improve luggage tracking and reduce the one-off adhesive luggage paper tags. This paper reviews the current application of Radio Frequency Identification (RFID in the luggage handling system and proposes the Internet of Things’ (IoT development of the reusable luggage tag to facilitate aviation luggage handling, the tracking process and environmental conservation. A framework of IoT and its RFID components for the proposed reusable tag are presented. An integrated cyber-physical system, including a database management system and mobile app, for the reusable luggage tag is developed. Future studies will enhance the methodology of integrating the retail system, luggage tag, airport check-in counter, luggage handling system, aircraft, and the destination airport through the use of the tag, readers, antenna, and mobile devices.

  16. Reproducibility and reusability of scientific software

    Science.gov (United States)

    Shamir, Lior

    2017-01-01

    Information science and technology has been becoming an integral part of astronomy research, and due to the consistent growth in the size and impact of astronomical databases, that trend is bound to continue. While software is a vital part information systems and data analysis processes, in many cases the importance of the software and the standards of reporting on the use of source code has not yet elevated in the scientific communication process to the same level as other parts of the research. The purpose of the discussion is to examine the role of software in the scientific communication process in the light of transparency, reproducibility, and reusability of the research, as well as discussing software in astronomy in comparison to other disciplines.

  17. 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.

  18. 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.

  19. Condition monitoring helps make the Space Shuttle Main Engine reusable

    Science.gov (United States)

    Lacroix, W. P.

    1973-01-01

    The Space Shuttle Main Engine (SSME) is a reusable, high-performance liquid-propellant rocket engine being developed for the Space Shuttle Orbiter Vehicle. The SSME has been designed for long life, rapid postflight maintenance, and a fast vehicle turnaround cycle of 160 hours. To meet the unique reusability requirements, the SSME considers maintainability and condition monitoring much as airlines do today. The condition monitoring capabilities designed into this engine are discussed with major emphasis on internal inspection and techniques which ensure the reusability of the SSME.

  20. Recent Advances in Near-Net-Shape Fabrication of Al-Li Alloy 2195 for Launch Vehicles

    Science.gov (United States)

    Wagner, John; Domack, Marcia; Hoffman, Eric

    2007-01-01

    Recent applications in launch vehicles use 2195 processed to Super Lightweight Tank specifications. Potential benefits exist by tailoring heat treatment and other processing parameters to the application. Assess the potential benefits and advocate application of Al-Li near-net-shape technologies for other launch vehicle structural components. Work with manufacturing and material producers to optimize Al-Li ingot shape and size for enhanced near-net-shape processing. Examine time dependent properties of 2195 critical for reusable applications.

  1. 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)

  2. 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

  3. 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.

  4. 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.

  5. 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...

  6. 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.

  7. Two hundred endoscopic extraperitoneal inguinal hernioplasties: cost containment by reusable instruments

    Institute of Scientific and Technical Information of China (English)

    2002-01-01

    Objective To report our experience of 200 endoscopic totally extraperitoneal inguinal hernioplasties utilizing reusable instruments.Results A total of 196 (98%) endoscopic extraperitoneal inguinal hernioplasties were successfully performed. Conversion rates to transabdominal preperitoneal and open repairs were 1.5% (n=3) and 0.5% (n=1), respectively. There were no other intraoperative complications. Postoperative morbidity included retention of urine (n=7), wound bruising (n=2), atelectasis (n=2) and gouty arthritis (n=1). The mean visual analogue pain scores at rest were 2.3, 1.6 and 1.9 on postoperative days 0, 1 and 2, respectively. The mean length of hospital stay was 1.9 days. 113 patients (69%) returned to normal activities within one week. Of the 35 patients who experienced both open and laparoscopic repair, 80% expressed preference for endoscopic hernioplasty in the event of future recurrence.Conclusions Endoscopic extraperitoneal inguinal hernioplasty can be safely performed utilizing reusable trocars. Substantial reduction of operative cost could be achieved by the elimination of disposable instruments. Deficiencies of the reusable metallic trocar, namely peri-cannula air-leak and sliding movements of the trocar, can be overcome by purse-string suture of the fascial opening.

  8. 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.

  9. Intelligent, Reusable Software for Plug and Play Space Avionics Project

    Data.gov (United States)

    National Aeronautics and Space Administration — Space Micro proposes to build upon our existing space processing and hardening technologies and products e.g (Proton 200K), to research and develop reusable software...

  10. Technical Concept Document. Central Archive for Reusable Defense Software (CARDS)

    Science.gov (United States)

    1994-02-28

    component and therefore lost to the reuser . Typically, components selected for reuse Page 1 STARS-VC.BO09/001/00 28 Feiwuay 1994 are taken from the...underlying services that the component may have relied upon are no longer present for the reuser . Certainly the reusability of a component is enhanced...built, and maintained to house reusable components. reuser One who implements a system through the reuse process. rule base A collection of rules

  11. Considerations for the design of Ada reusable packages

    Science.gov (United States)

    Nise, Norman S.; Giffin, Chuck

    1986-01-01

    Two important considerations that precede the design of Ada reusable packages (commonality and programming standards) are discuessed. First, the importance of designing packages to yield widespread commonality is expressed. A means of measuring the degree of applicability of packages both within and across applications areas is presented. Design consideration that will improve commonality are also discussed. Second, considerations for the development of programming standards are set forth. These considerations will lead to standards that will improve the reusability of Ada packages.

  12. Reusable space tug concept and mission

    Science.gov (United States)

    Cresto Aleina, Sara; Viola, Nicole; Stesina, Fabrizio; Viscio, Maria Antonietta; Ferraris, Simona

    2016-11-01

    The paper deals with the conceptual design of a space tug to be used in support to Earth satellites transfer manoeuvres. Usually Earth satellites are released in a non-definitive low orbit, depending on the adopted launcher, and they need to be equipped with an adequate propulsion system able to perform the transfer to their final operational location. In order to reduce the mass at launch of the satellite system, an element pre-deployed on orbit, i.e. the space tug, can be exploited to perform the transfer manoeuvres; this allows simplifying the propulsion requirements for the satellite, with a consequent decrease of mass and volume, in favour of larger payloads. The space tug here presented is conceived to be used for the transfer of a few satellites from low to high orbits, and vice versa, if needed. To support these manoeuvres, dedicated refuelling operations are envisaged. The paper starts from on overview of the mission scenario, the concept of operations and the related architecture elements. Then it focuses on the detailed definition of the space tug, from the requirements' assessment up to the budgets' development, through an iterative and recursive design process. The overall mission scenario has been derived from a set of trade-off analyses that have been performed to choose the mission architecture and operations that better satisfy stakeholder expectations: the most important features of these analyses and their results are described within the paper. Eventually, in the last part of the work main conclusions are drawn on the selected mission scenario and space tug and further utilizations of this innovative system in the frame of future space exploration are discussed. Specifically, an enhanced version of the space tug that has been described in the paper could be used to support on orbit assembly of large spacecraft for distant and long exploration missions. The Space Tug development is an activity carried on in the frame of the SAPERE project (Space

  13. Improvement of Reusable Surface Insulation (RSI) materials

    Science.gov (United States)

    Blome, J. C.

    1972-01-01

    The mullite fiber based hardened compacted fibers (HCF) type of reusable surface insulation was further developed for use in the Space Shuttle Program. Two hundred fifty formulations of fiber mixtures, fillers, binders, and organic processing aids were made using mullite fibers as the basic ingredient. Most of the work was accomplished on 15-lb/cu ft material. It was established that higher density materials are stronger with strength values as high as 250 lb/sq in. in tension. New measurement techniques and equipment were developed for accurate determination of strength and strain to failure. Room temperature to 2300 F stress-strain relationships were made. The room temperature tensile modulus of elasticity is 61,700 lb/sq in. and the strain at failure is 0.165 percent, typically, when measured longitudinally parallel to the long axes of the fibers. Thermal insulating effectiveness was increased 20 percent by reducing the diameter of some of the fibers in the material. Improvements were made in density uniformity and strength uniformity in a block of HCF by mixing improvements and by the use of organic additives. Specifications were established on the materials and processes used in making the insulation.

  14. Reusable Solid Rocket Motor - Accomplishment, Lessons, and a Culture of Success

    Science.gov (United States)

    Moore, D. R.; Phelps, W. J.

    2011-01-01

    The Reusable Solid Rocket Motor (RSRM) represents the largest solid rocket motor (SRM) ever flown and the only human-rated solid motor. High reliability of the RSRM has been the result of challenges addressed and lessons learned. Advancements have resulted by applying attention to process control, testing, and postflight through timely and thorough communication in dealing with all issues. A structured and disciplined approach was taken to identify and disposition all concerns. Careful consideration and application of alternate opinions was embraced. Focus was placed on process control, ground test programs, and postflight assessment. Process control is mandatory for an SRM, because an acceptance test of the delivered product is not feasible. The RSRM maintained both full-scale and subscale test articles, which enabled continuous improvement of design and evaluation of process control and material behavior. Additionally RSRM reliability was achieved through attention to detail in post flight assessment to observe any shift in performance. The postflight analysis and inspections provided invaluable reliability data as it enables observation of actual flight performance, most of which would not be available if the motors were not recovered. RSRM reusability offered unique opportunities to learn about the hardware. NASA is moving forward with the Space Launch System that incorporates propulsion systems that takes advantage of the heritage Shuttle and Ares solid motor programs. These unique challenges, features of the RSRM, materials and manufacturing issues, and design improvements will be discussed in the paper.

  15. 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

  16. Is It Worth It? - the Economics of Reusable Space Transportation

    Science.gov (United States)

    Webb, Richard

    2016-01-01

    Over the past several decades billions of dollars have been invested by governments and private companies in the pursuit of lower cost access to space through earth-to-orbit (ETO) space transportation systems. Much of that investment has been focused on the development and operation of various forms of reusable transportation systems. From the Space Shuttle to current efforts by private commercial companies, the overarching belief of those making such investments has been that reusing system elements will be cheaper than utilizing expendable systems that involve throwing away costly engines, avionics, and other hardware with each flight. However, the view that reusable systems are ultimately a "better" approach to providing ETO transportation is not held universally by major stakeholders within the space transportation industry. While the technical feasibility of at least some degree of reusability has been demonstrated, there continues to be a sometimes lively debate over the merits and drawbacks of reusable versus expendable systems from an economic perspective. In summary, is it worth it? Based on our many years of direct involvement with the business aspects of several expendable and reusable transportation systems, it appears to us that much of the discussion surrounding reusability is hindered by a failure to clearly define and understand the financial and other metrics by which the financial "goodness" of a reusable or expandable approach is measured. As stakeholders, the different users and suppliers of space transportation have a varied set of criteria for determining the relative economic viability of alternative strategies, including reusability. Many different metrics have been used to measure the affordability of space transportation, such as dollars per payload pound (kilogram) to orbit, cost per flight, life cycle cost, net present value/internal rate of return, and many others. This paper will examine the key considerations that influence

  17. 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.

  18. Dynamic Reusable Workflows for Ocean Science

    Directory of Open Access Journals (Sweden)

    Richard P. Signell

    2016-10-01

    Full Text Available Digital catalogs of ocean data have been available for decades, but advances in standardized services and software for catalog searches and data access now make it possible to create catalog-driven workflows that automate—end-to-end—data search, analysis, and visualization of data from multiple distributed sources. Further, these workflows may be shared, reused, and adapted with ease. Here we describe a workflow developed within the US Integrated Ocean Observing System (IOOS which automates the skill assessment of water temperature forecasts from multiple ocean forecast models, allowing improved forecast products to be delivered for an open water swim event. A series of Jupyter Notebooks are used to capture and document the end-to-end workflow using a collection of Python tools that facilitate working with standardized catalog and data services. The workflow first searches a catalog of metadata using the Open Geospatial Consortium (OGC Catalog Service for the Web (CSW, then accesses data service endpoints found in the metadata records using the OGC Sensor Observation Service (SOS for in situ sensor data and OPeNDAP services for remotely-sensed and model data. Skill metrics are computed and time series comparisons of forecast model and observed data are displayed interactively, leveraging the capabilities of modern web browsers. The resulting workflow not only solves a challenging specific problem, but highlights the benefits of dynamic, reusable workflows in general. These workflows adapt as new data enter the data system, facilitate reproducible science, provide templates from which new scientific workflows can be developed, and encourage data providers to use standardized services. As applied to the ocean swim event, the workflow exposed problems with two of the ocean forecast products which led to improved regional forecasts once errors were corrected. While the example is specific, the approach is general, and we hope to see increased

  19. Dynamic reusable workflows for ocean science

    Science.gov (United States)

    Signell, Richard; Fernandez, Filipe; Wilcox, Kyle

    2016-01-01

    Digital catalogs of ocean data have been available for decades, but advances in standardized services and software for catalog search and data access make it now possible to create catalog-driven workflows that automate — end-to-end — data search, analysis and visualization of data from multiple distributed sources. Further, these workflows may be shared, reused and adapted with ease. Here we describe a workflow developed within the US Integrated Ocean Observing System (IOOS) which automates the skill-assessment of water temperature forecasts from multiple ocean forecast models, allowing improved forecast products to be delivered for an open water swim event. A series of Jupyter Notebooks are used to capture and document the end-to-end workflow using a collection of Python tools that facilitate working with standardized catalog and data services. The workflow first searches a catalog of metadata using the Open Geospatial Consortium (OGC) Catalog Service for the Web (CSW), then accesses data service endpoints found in the metadata records using the OGC Sensor Observation Service (SOS) for in situ sensor data and OPeNDAP services for remotely-sensed and model data. Skill metrics are computed and time series comparisons of forecast model and observed data are displayed interactively, leveraging the capabilities of modern web browsers. The resulting workflow not only solves a challenging specific problem, but highlights the benefits of dynamic, reusable workflows in general. These workflows adapt as new data enters the data system, facilitate reproducible science, provide templates from which new scientific workflows can be developed, and encourage data providers to use standardized services. As applied to the ocean swim event, the workflow exposed problems with two of the ocean forecast products which led to improved regional forecasts once errors were corrected. While the example is specific, the approach is general, and we hope to see increased use of dynamic

  20. 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.

  1. New Approaches in Reusable Booster System Life Cycle Cost Modeling

    Science.gov (United States)

    Zapata, Edgar

    2013-01-01

    This paper presents the results of a 2012 life cycle cost (LCC) study of hybrid Reusable Booster Systems (RBS) conducted by NASA Kennedy Space Center (KSC) and the Air Force Research Laboratory (AFRL). The work included the creation of a new cost estimating model and an LCC analysis, building on past work where applicable, but emphasizing the integration of new approaches in life cycle cost estimation. Specifically, the inclusion of industry processes/practices and indirect costs were a new and significant part of the analysis. The focus of LCC estimation has traditionally been from the perspective of technology, design characteristics, and related factors such as reliability. Technology has informed the cost related support to decision makers interested in risk and budget insight. This traditional emphasis on technology occurs even though it is well established that complex aerospace systems costs are mostly about indirect costs, with likely only partial influence in these indirect costs being due to the more visible technology products. Organizational considerations, processes/practices, and indirect costs are traditionally derived ("wrapped") only by relationship to tangible product characteristics. This traditional approach works well as long as it is understood that no significant changes, and by relation no significant improvements, are being pursued in the area of either the government acquisition or industry?s indirect costs. In this sense then, most launch systems cost models ignore most costs. The alternative was implemented in this LCC study, whereby the approach considered technology and process/practices in balance, with as much detail for one as the other. This RBS LCC study has avoided point-designs, for now, instead emphasizing exploring the trade-space of potential technology advances joined with potential process/practice advances. Given the range of decisions, and all their combinations, it was necessary to create a model of the original model

  2. On the Concepts of Usability and Reusability of Learning Objects

    Directory of Open Access Journals (Sweden)

    Miguel-Angel Sicilia

    2003-10-01

    Full Text Available “Reusable learning objects” oriented towards increasing their potential reusability are required to satisfy concerns about their granularity and their independence of concrete contexts of use. Such requirements also entail that the definition of learning object “usability,” and the techniques required to carry out their “usability evaluation” must be substantially different from those commonly used to characterize and evaluate the usability of conventional educational applications. In this article, a specific characterization of the concept of learning object usability is discussed, which places emphasis on “reusability,” the key property of learning objects residing in repositories. The concept of learning object reusability is described as the possibility and adequacy for the object to be usable in prospective educational settings, so that usability and reusability are considered two interrelated – and in many cases conflicting – properties of learning objects. Following the proposed characterization of two characteristics or properties of learning objects, a method to evaluate usability of specific learning objects will be presented.

  3. Inheritance Hierarchy Based Reuse & Reusability Metrics in OOSD

    Directory of Open Access Journals (Sweden)

    Nasib S. Gill,

    2011-06-01

    Full Text Available Reuse and reusability are two major aspects in object oriented software which can be measured from inheritance hierarchy. Reusability is the prerequisite of reuse but both may or may not bemeasured using same metric. This paper characterizes metrics of reuse and reusability in Object Oriented Software Development (OOSD. Reuse metrics compute the extent to which classes have been reused and reusability metrics computes the extent to which classes can be reused. In this paper five new metrics namely- Breadth of Inheritance Tree (BIT, Method Reuse Per Inheritance Relation (MRPIR,Attribute Reuse Per Inheritance Relation (ARPIR, Generality of Class (GC and Reuse Probability (RP have been proposed. These metrics help to evaluate reuse and reusability of object oriented software.Four extensively validated existing object oriented metrics, namely- Depth of Inheritance Tree (DIT, Number of Children (NOC, Method Inheritance Factor (MIF and Attribute Inheritance Factor (AIFhave been selected and investigated for comparison with proposed metrics. All metrics can be computed from inheritance hierarchies and classified according to their characteristics. Further, metrics areevaluated against a case study. These metrics are helpful in comparing alternative inheritance hierarchies at design time to select best alternative, so that the development time and cost can be reduced.

  4. The Falcon Launch Vehicle - An Attempt at Making Access to Space More Affordable, Reliable and Pleasant

    OpenAIRE

    Musk, Elon; Koenigsmann, Hans; Gurevich, Gwynne

    2003-01-01

    Falcon is a mostly reusable, two stage, liquid oxygen and kerosene powered launch vehicle being built by Space Exploration Technologies (SpaceX) from the ground up. The vehicle is designed above all for high reliability, followed by low cost and a benign flight environment. Launched from Vandenberg, a standard Falcon can carry over 470 kg to a 700 km sun-synchronous orbit and a heavy Falcon can deliver 1450 kg to the same orbit. To minimize failure modes, the vehicle has the minimum pragmatic...

  5. 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

  6. Ares V: Game Changer for National Security Launch

    Science.gov (United States)

    Sumrall, Phil; Morris, Bruce

    2009-01-01

    NASA is designing the Ares V cargo launch vehicle to vastly expand exploration of the Moon begun in the Apollo program and enable the exploration of Mars and beyond. As the largest launcher in history, Ares V also represents a national asset offering unprecedented opportunities for new science, national security, and commercial missions of unmatched size and scope. The Ares V is the heavy-lift component of NASA's dual-launch architecture that will replace the current space shuttle fleet, complete the International Space Station, and establish a permanent human presence on the Moon as a stepping-stone to destinations beyond. During extensive independent and internal architecture and vehicle trade studies as part of the Exploration Systems Architecture Study (ESAS), NASA selected the Ares I crew launch vehicle and the Ares V to support future exploration. The smaller Ares I will launch the Orion crew exploration vehicle with four to six astronauts into orbit. The Ares V is designed to carry the Altair lunar lander into orbit, rendezvous with Orion, and send the mated spacecraft toward lunar orbit. The Ares V will be the largest and most powerful launch vehicle in history, providing unprecedented payload mass and volume to establish a permanent lunar outpost and explore significantly more of the lunar surface than was done during the Apollo missions. The Ares V consists of a Core Stage, two Reusable Solid Rocket Boosters (RSRBs), Earth Departure Stage (EDS), and a payload shroud. For lunar missions, the shroud would cover the Lunar Surface Access Module (LSAM). The Ares V Core Stage is 33 feet in diameter and 212 feet in length, making it the largest rocket stage ever built. It is the same diameter as the Saturn V first stage, the S-IC. However, its length is about the same as the combined length of the Saturn V first and second stages. The Core Stage uses a cluster of five Pratt & Whitney Rocketdyne RS-68B rocket engines, each supplying about 700,000 pounds of thrust

  7. Moon-Based Advanced Reusable Transportation Architecture: The MARTA Project

    Science.gov (United States)

    Alexander, R.; Bechtel, R.; Chen, T.; Cormier, T.; Kalaver, S.; Kirtas, M.; Lewe, J.-H.; Marcus, L.; Marshall, D.; Medlin, M.; McIntire, J.; Nelson, D.; Remolina, D.; Scott, A.; Weglian, J.; Olds, J.

    2000-01-01

    The Moon-based Advanced Reusable Transportation Architecture (MARTA) Project conducted an in-depth investigation of possible Low Earth Orbit (LEO) to lunar surface transportation systems capable of sending both astronauts and large masses of cargo to the Moon and back. This investigation was conducted from the perspective of a private company operating the transportation system for a profit. The goal of this company was to provide an Internal Rate of Return (IRR) of 25% to its shareholders. The technical aspect of the study began with a wide open design space that included nuclear rockets and tether systems as possible propulsion systems. Based on technical, political, and business considerations, the architecture was quickly narrowed down to a traditional chemical rocket using liquid oxygen and liquid hydrogen. However, three additional technologies were identified for further investigation: aerobraking, in-situ resource utilization (ISRU), and a mass driver on the lunar surface. These three technologies were identified because they reduce the mass of propellant used. Operational costs are the largest expense with propellant cost the largest contributor. ISRU, the production of materials using resources on the Moon, was considered because an Earth to Orbit (ETO) launch cost of 1600 per kilogram made taking propellant from the Earth's surface an expensive proposition. The use of an aerobrake to circularize the orbit of a vehicle coming from the Moon towards Earth eliminated 3, 100 meters per second of velocity change (Delta V), eliminating almost 30% of the 11,200 m/s required for one complete round trip. The use of a mass driver on the lunar surface, in conjunction with an ISRU production facility, would reduce the amount of propellant required by eliminating using propellant to take additional propellant from the lunar surface to Low Lunar Orbit (LLO). However, developing and operating such a system required further study to identify if it was cost effective. The

  8. 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.

  9. 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.

  10. 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

  11. 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.

  12. 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.

  13. Reusables get high marks in adult incontinence care market.

    Science.gov (United States)

    Tison-Rossman, J

    1992-11-01

    The adult incontinence care market is coming of age. As environmental concerns gradually erode the popularity of disposables, nursing homes and hospitals are looking at reusables in a new light. In addition, the aging of the U.S. population is expected to increase the demand for incontinence care products. A recent study found that the sales of reusable cloth diapers and pads accounted for $385 million annually. All of these factors add up to a lucrative market for textile rental companies that can supply these products.

  14. Wound dressing with reusable electronics for wireless monitoring

    KAUST Repository

    Shamim, Atif

    2016-10-20

    A wound dressing device with reusable electronics for wireless monitoring and a method of making the same are provided. The device can be a smart device. In an embodiment, the device has a disposable portion including one or more sensors and a reusable portion including wireless electronics. The one or more sensors can be secured to a flexible substrate and can be printed by non-contact printing on the substrate. The disposable portion can be removably coupled to the one or more sensors. The device can include one or more sensors for wireless monitoring of a wound, a wound dressing, a body fluid exuded by the wound and/or wearer health.

  15. Evolution of the Florida Launch Site Architecture: Embracing Multiple Customers, Enhancing Launch Opportunities

    Science.gov (United States)

    Colloredo, Scott; Gray, James A.

    2011-01-01

    The impending conclusion of the Space Shuttle Program and the Constellation Program cancellation unveiled in the FY2011 President's budget created a large void for human spaceflight capability and specifically launch activity from the Florida launch Site (FlS). This void created an opportunity to re-architect the launch site to be more accommodating to the future NASA heavy lift and commercial space industry. The goal is to evolve the heritage capabilities into a more affordable and flexible launch complex. This case study will discuss the FlS architecture evolution from the trade studies to select primary launch site locations for future customers, to improving infrastructure; promoting environmental remediation/compliance; improving offline processing, manufacturing, & recovery; developing range interface and control services with the US Air Force, and developing modernization efforts for the launch Pad, Vehicle Assembly Building, Mobile launcher, and supporting infrastructure. The architecture studies will steer how to best invest limited modernization funding from initiatives like the 21 st elSe and other potential funding.

  16. 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

  17. Reusable Hot-Wire Cable Cutter

    Science.gov (United States)

    Pauken, Michael T.; Steinkraus, Joel M.

    2010-01-01

    During the early development stage of balloon deployment systems for missions, nichrome wire cable cutters were often used in place of pyro-actuated cutters. Typically, a nichrome wire is wrapped around a bundle of polymer cables with a low melting point and connected to a relay-actuated electric circuit. The heat from the nichrome reduces the strength of the cable bundle, which quickly breaks under a mechanical load and can thus be used as a release mechanism for a deployment system. However, the use of hand-made heated nichrome wire for cutters is not very reliable. Often, the wrapped nichrome wire does not cut through the cable because it either pulls away from its power source or does not stay in contact with the cable being cut. Because nichrome is not readily soldered to copper wire, unreliable mechanical crimps are often made to connect the nichrome to an electric circuit. A self-contained device that is reusable and reliable was developed to sever cables for device release or deployment. The nichrome wire in this new device is housed within an enclosure to prevent it from being damaged by handling. The electric power leads are internally connected within the unit to the nichrome wire using a screw terminal connection. A bayonet plug, a quick and secure method of connecting the cutter to the power source, is used to connect the cutter to the power leads similar to those used in pyro-cutter devices. A small ceramic tube [0.25-in. wide 0.5-in. long (.6.4-mm wide 13-mm long)] houses a spiraled nichrome wire that is heated when a cable release action is required. The wire is formed into a spiral coil by wrapping it around a mandrel. It is then laid inside the ceramic tube so that it fits closely to the inner surface of the tube. The ceramic tube provides some thermal and electrical insulation so that most of the heat generated by the wire is directed toward the cable bundle in the center of the spiral. The ceramic tube is cemented into an aluminum block, which

  18. Web Service Component Reusability Evaluation: A Fuzzy Multi-Criteria Approach

    Directory of Open Access Journals (Sweden)

    Aditya Pratap Singh

    2016-01-01

    Full Text Available The service oriented architecture supports reusable components. Component reusability is one of the important features while designing web services for reuse. The reusability is an ideal and key factor to improve the quality and production rate of software. It becomes very helpful for quality assurance, if such quality parameters can be quantified. Non functional quality parameters like reusability are not easy to measure and quantify. This paper attempts to quantify reusability using fuzzy multi criteria approach. This approach is considered due to the unpredictable nature of reusability attributes. For the estimation of reusability, the paper identifies 5 key attributes of reusability i.e. Coupling, Interface Complexity, Security, Response Time and Statelessness in context of web service components.

  19. 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,

  20. 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.

  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. 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

  4. 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.

  5. Architectures Toward Reusable Science Data Systems

    Science.gov (United States)

    Moses, J. F.

    2014-12-01

    Science Data Systems (SDS) comprise an important class of data processing systems that support product generation from remote sensors and in-situ observations. These systems enable research into new science data products, replication of experiments and verification of results. NASA has been building ground systems for satellite data processing since the first Earth observing satellites launched and is continuing development of systems to support NASA science research, NOAA's weather satellites and USGS's Earth observing satellite operations. The basic data processing workflows and scenarios continue to be valid for remote sensor observations research as well as for the complex multi-instrument operational satellite data systems being built today. System functions such as ingest, product generation and distribution need to be configured and performed in a consistent and repeatable way with an emphasis on scalability. This paper will examine the key architectural elements of several NASA satellite data processing systems currently in operation and under development that make them suitable for scaling and reuse. Examples of architectural elements that have become attractive include virtual machine environments, standard data product formats, metadata content and file naming, workflow and job management frameworks, data acquisition, search, and distribution protocols. By highlighting key elements and implementation experience the goal is to recognize architectures that will outlast their original application and be readily adaptable for new applications. Concepts and principles are explored that lead to sound guidance for SDS developers and strategists.

  6. Unconditionally-secure and reusable public-key authentication

    CERN Document Server

    Ioannou, Lawrence M

    2011-01-01

    We present a quantum-public-key identification protocol and show that it is secure against a computationally-unbounded adversary. This demonstrates for the first time that unconditionally-secure and reusable public-key authentication is possible in principle with (pure-state) public keys.

  7. Research Data Reusability: Conceptual Foundations, Barriers and Enabling Technologies

    Directory of Open Access Journals (Sweden)

    Costantino Thanos

    2017-01-01

    Full Text Available High-throughput scientific instruments are generating massive amounts of data. Today, one of the main challenges faced by researchers is to make the best use of the world’s growing wealth of data. Data (reusability is becoming a distinct characteristic of modern scientific practice. By data (reusability, we mean the ease of using data for legitimate scientific research by one or more communities of research (consumer communities that is produced by other communities of research (producer communities. Data (reusability allows the reanalysis of evidence, reproduction and verification of results, minimizing duplication of effort, and building on the work of others. It has four main dimensions: policy, legal, economic and technological. The paper addresses the technological dimension of data reusability. The conceptual foundations of data reuse as well as the barriers that hamper data reuse are presented and discussed. The data publication process is proposed as a bridge between the data author and user and the relevant technologies enabling this process are presented.

  8. Mobile Authoring of Open Educational Resources as Reusable Learning Objects

    Science.gov (United States)

    Kinshuk; Jesse, Ryan

    2013-01-01

    E-learning technologies have allowed authoring and playback of standardized reusable learning objects (RLO) for several years. Effective mobile learning requires similar functionality at both design time and runtime. Mobile devices can play RLO using applications like SMILE, mobile access to a learning management system (LMS), or other systems…

  9. Reusable neoprene jacket protects parts for chemical milling

    Science.gov (United States)

    1965-01-01

    Reusable neoprene jacket is used to prepare metal part or panel for chemical milling. Jacket covers back and upper rim of part and is sealed before the masking solution is applied to surface to be milled. This reduces amount of masking material required for milling identical parts and increases production.

  10. 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

  11. 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.

  12. Future launchers strategy : the ariane 2010 initiative

    Science.gov (United States)

    Bonnal, Ch.; Eymard, M.; Soccodato, C.

    2001-03-01

    With the new cryogenic upper stage ESC, the European heavy launcher Ariane 5+ is perfectly suited to the space market envisioned for the coming decade: flexible to cope with any payload and commercially attractive despite a fierce competition. Current Arianespace projections for the following years 2010-2020 indicate two major trends: satellites may still become larger and may require very different final orbits; today's market largely dominated by GEO may well evolve, influenced by LEO operations such as those linked to ISS or by constellations, to remain competitive, the launch cost has to be reduced. The future generation of the European heavy launcher has therefore to focus on an ever increased flexibility with a drastic cost reduction. Two strategies are possible to achieve this double goal: reusable launchers, either partially or totally, may ease the access to space, limiting costly expendable stages; the assessment of their technical feasibility and financial viability is undergoing in Europe under the Future Launchers Technology Program (FLTP), expendable launchers, derived from the future Ariane 5+. This second way started by CNES at the end of year 1999 is called the "Ariane 2010 initiative". The main objectives are simultaneously an increase of 25% in performance and a reduction of 30% in launch cost wrt Ariane 5+. To achieve these very ambitious goals, numerous major modifications are studied: technical improvements : modifications of the Solid Rocket Boosters may consist in filament winding casing, increased loading, simplified casting, improved grain, simplified Thrust Vector Control, … evolution of the Vulcain engine leading to higher efficiency despite a simplified design, flow separation controlled nozzle extension, propellant management of the two cryogenic stages, simplified electrical system, increased standardization, for instance on flanged interfaces and manufacturing processes, operational improvements such as launch cycle simplification

  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. New Future for Stock Trading

    Institute of Scientific and Technical Information of China (English)

    LAN XINZHEN

    2010-01-01

    @@ For three years Wang Liangguang,an cxperienced stock investor,waited patiently for the trading of stock index futures.And now,that day has arrived-stock index futures will soon be launched on Chinese financial market.The China Securities Regulatory Commission (CSRC) may officially launch stock index futures as soon as May.

  16. 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

  17. 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

  18. A Reusable Component Retrieval System for Prototyping

    Science.gov (United States)

    1991-09-01

    for a prototyped software system. 20 graphic editor -Protte Edit Font Pattem FqCalor 39Color lign ption Select Se move Modify q Specif ? Streas M...CAPS the designer uses a graphical editor to design and decompose the prototype’s operators [Ref 19]. Future versions of CAPS will also allow for...spec_1ext (): SB TEXTO -03.1 ECT *imip-body-text ( SBTEXTOBJ CT *illformal-descript ioni( SB.TEXTOBJECT *formal-description(); SBJTEXTOBJ ECT *norn-forml

  19. Software Library: A Reusable Software Issue.

    Science.gov (United States)

    1984-06-01

    hopefully, this will benefit the future developmental soft- ware Ircducts. E. ECCICBICS OF THE SOETWAIE lIBRABY It aas teen stated in [Bef. 5], that...issues around entity size. That is, in cider to maintain the size of entities, a hierarchical approach to prcgram creation and modizicatioc should be...1roduced ty the preiiccesscr is combnined with any FOFIBAN the user may have written, and tbeL it is CcoMiled, linked, and exEcuted. In cider to reuse t

  20. Near-Optimal Operation of Dual-Fuel Launch Vehicles

    Science.gov (United States)

    Ardema, M. D.; Chou, H. C.; Bowles, J. V.

    1996-01-01

    A near-optimal guidance law for the ascent trajectory from earth surface to earth orbit of a fully reusable single-stage-to-orbit pure rocket launch vehicle is derived. Of interest are both the optimal operation of the propulsion system and the optimal flight path. A methodology is developed to investigate the optimal throttle switching of dual-fuel engines. The method is based on selecting propulsion system modes and parameters that maximize a certain performance function. This function is derived from consideration of the energy-state model of the aircraft equations of motion. Because the density of liquid hydrogen is relatively low, the sensitivity of perturbations in volume need to be taken into consideration as well as weight sensitivity. The cost functional is a weighted sum of fuel mass and volume; the weighting factor is chosen to minimize vehicle empty weight for a given payload mass and volume in orbit.

  1. 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.

  2. A Framework for Assessing the Software Reusability using Fuzzy Logic Approach for Aspect Oriented Software

    Directory of Open Access Journals (Sweden)

    Pradeep Kumar Singh

    2015-01-01

    Full Text Available Software reusability is very important and crucial attribute to evaluate the system software. Due to incremental growth of software development, the software reusability comes under attention of many researcher and practitioner. It is pretty easier to reuse the software than developing the new software. Software reusability reduces the development time, cost and effort of software product. Software reusability define the depth to which a module can be reused again with very little or no modification. However the prediction of this quality attribute is cumbersome process. Aspect oriented software development is new approach that introduce the concerns to overcome the issues with modular programming and object oriented programming. However many researcher worked on accessing the software reusability on object oriented system but the software reusability of aspect oriented system is not completely explored. This paper explores the various metric that affects the reusability of aspect oriented software and estimate it using fuzzy logic approach.

  3. 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.

  4. 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.

  5. 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.

  6. 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.

  7. 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.

  8. 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...

  9. 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

  10. ANFIS Approach for Optimal Selection of Reusable Components

    Directory of Open Access Journals (Sweden)

    K.S. Ravichandran

    2012-12-01

    Full Text Available In a growing world, the development of modern software system requires large-scale manpower, high development cost, larger completion time and high risk of maintaining the software quality. Component- Based Software Development (CBSD approach is based on the concept of developing modern software systems by selecting the appropriate reusable components or COTS (Commercial Off-The-Shelf components and then assembling them with well-defined software architecture. The proper selection of COTS components will really reduce the manpower, development cost, product completion time, risk, maintenance cost and also it addresses the high quality software product. In this paper, we develop an automated process of component selection by using Adaptive Neuro-Fuzzy Inference Systems (ANFIS based technique by using 14 reusable components’ parameters as a first time in this field. Again, for increasing the accuracy of a model, Fuzzy- Weighted-Relational-Coefficient (FWRC matrix is derived between the components and CBS development with the help of 14 component parameters, namely, Reliability, Stability, Portability, Consistency, Completeness, Interface & Structural Complexity, Understandability of Software Documents, Security, Usability, Accuracy, Compatibility, Performance, Serviceability and Customizable. In the recent literature studies reveals that almost all the researchers have been designed a general fuzzy-design rule for a component selection problem of all kinds of software architecture; but it leads to a poor selection of components and this paper suggests adoption of a specific fuzzy-design rule for every software architecture application for the selection of reusable components. Finally, it is concluded that the selection of reusable components through ANFIS performs better than the other models discussed so far.

  11. An Approach for Constructing Reusable Software Components in Ada

    Science.gov (United States)

    1990-09-01

    Cognitive Issues in Reusing Software Artifacts. Software Reusability, Volume 11: Applications and Experience, ed. Ted J. Biggerstaff and Alan J...Terms with Terminology for Software Reuse. Pittsburgh, PA: position paper for the Reuse in Practice Workshop, SEI. Prieto -Diaz87a Prieto -Diaz, Rubdn...Novak GE/SEI Carnegie Mellon University Pittsburgh, PA 15213-3890 Frank Poslajko SDC MS CSSD-SP 206 Wynn Drive Huntsville, AL 35807 Ruben Prieto -Diaz SPC

  12. Reusable Solid Rocket Motor - Accomplishments, Lessons, and a Culture of Success

    Science.gov (United States)

    Moore, Dennis R.; Phelps, Willie J.

    2011-01-01

    The Reusable Solid Rocket Motor represents the largest solid rocket motor ever flown and the only human rated solid motor. Each Reusable Solid Rocket Motor (RSRM) provides approximately 3-million lb of thrust to lift the integrated Space Shuttle vehicle from the launch pad. The motors burn out approximately 2 minutes later, separate from the vehicle and are recovered and refurbished. The size of the motor and the need for high reliability were challenges. Thrust shaping, via shaping of the propellant grain, was needed to limit structural loads during ascent. The motor design evolved through several block upgrades to increase performance and to increase safety and reliability. A major redesign occurred after STS-51L with the Redesigned Solid Rocket Motor. Significant improvements in the joint sealing systems were added. Design improvements continued throughout the Program via block changes with a number of innovations including development of low temperature o-ring materials and incorporation of a unique carbon fiber rope thermal barrier material. Recovery of the motors and post flight inspection improved understanding of hardware performance, and led to key design improvements. Because of the multidecade program duration material obsolescence was addressed, and requalification of materials and vendors was sometimes needed. Thermal protection systems and ablatives were used to protect the motor cases and nozzle structures. Significant understanding of design and manufacturing features of the ablatives was developed during the program resulting in optimization of design features and processing parameters. The project advanced technology in eliminating ozone-depleting materials in manufacturing processes and the development of an asbestos-free case insulation. Manufacturing processes for the large motor components were unique and safety in the manufacturing environment was a special concern. Transportation and handling approaches were also needed for the large

  13. A CORBA BASED ARCHITECTURE FOR ACCESSING REUSABLE SOFTWARE COMPONENTS ON THE WEB.

    Directory of Open Access Journals (Sweden)

    R. Cenk ERDUR

    2003-01-01

    Full Text Available In a very near future, as a result of the continious growth of Internet and advances in networking technologies, Internet will become the common software repository for people and organizations who employ component based reuse approach in their software development life cycles. In order to use the reusable components such as source codes, analysis, designs, design patterns during new software development processes, environments that support the identification of the components over Internet are needed. Basic elements of such an environment are the coordinator programs which deliver user requests to appropriate component libraries, user interfaces for querying, and programs that wrap the component libraries. First, a CORBA based architecture is proposed for such an environment. Then, an alternative architecture that is based on the Java 2 platform technologies is given for the same environment. Finally, the two architectures are compared.

  14. Characterizing and Modeling the Cost of Rework in a Library of Reusable Software Components

    Science.gov (United States)

    Basili, Victor R.; Condon, Steven E.; ElEmam, Khaled; Hendrick, Robert B.; Melo, Walcelio

    1997-01-01

    In this paper we characterize and model the cost of rework in a Component Factory (CF) organization. A CF is responsible for developing and packaging reusable software components. Data was collected on corrective maintenance activities for the Generalized Support Software reuse asset library located at the Flight Dynamics Division of NASA's GSFC. We then constructed a predictive model of the cost of rework using the C4.5 system for generating a logical classification model. The predictor variables for the model are measures of internal software product attributes. The model demonstrates good prediction accuracy, and can be used by managers to allocate resources for corrective maintenance activities. Furthermore, we used the model to generate proscriptive coding guidelines to improve programming, practices so that the cost of rework can be reduced in the future. The general approach we have used is applicable to other environments.

  15. 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

  16. 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

  17. 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.

  18. STS-112 Commander Ashby suits up for launch

    Science.gov (United States)

    2002-01-01

    KENNEDY SPACE CENTER, FLA. -- STS-112 Commander Jeffrey Ashby finishes suiting up for launch. STS-112 is the 15th assembly flight to the International Space Station, carrying the S1 Integrated Truss Structure and the Crew and Equipment Translation Aid (CETA) Cart A. The CETA is the first of two human-powered carts that will ride along the ISS railway, providing mobile work platforms for future spacewalking astronauts. On the 11-day mission, three spacewalks are planned to attach the S1 truss to the Station. Launch is scheduled for 3:46 p.m. EDT from Launch Pad 39B.

  19. STS-112 M.S. Magnus suits up before launch

    Science.gov (United States)

    2002-01-01

    KENNEDY SPACE CENTER, FLA. -- STS-112 Mission Specialist Sandra Magnus finishes suiting up before launch. STS-112 is the 15th assembly flight to the International Space Station, carrying the S1 Integrated Truss Structure and the Crew and Equipment Translation Aid (CETA) Cart A. The CETA is the first of two human-powered carts that will ride along the ISS railway, providing mobile work platforms for future spacewalking astronauts. On the 11-day mission, three spacewalks are planned to attach the S1 truss to the Station. Launch is scheduled for 3:46 p.m. EDT from Launch Pad 39B.

  20. STS-112 M.S. Sellers suits up for launch

    Science.gov (United States)

    2002-01-01

    KENNEDY SPACE CENTER, FLA. - During suitup for launch, STS-112 Mission Specialist Piers Sellers smiles in anticipation of his first Shuttle flight. STS-112 is the 15th assembly flight to the International Space Station, carrying the S1 Integrated Truss Structure and the Crew and Equipment Translation Aid (CETA) Cart A. The CETA is the first of two human-powered carts that will ride along the ISS railway, providing mobile work platforms for future spacewalking astronauts. On the 11-day mission, three spacewalks are planned to attach the S1 truss to the Station. Launch is scheduled for 3:46 p.m. EDT from Launch Pad 39B.

  1. Reusable Reentry Satellite (RRS) system design study. Phase B, appendix E: Attitude control system study

    Science.gov (United States)

    1991-01-01

    A study which consisted of a series of design analyses for an Attitude Control System (ACS) to be incorporated into the Re-usable Re-entry Satellite (RRS) was performed. The main thrust of the study was associated with defining the control laws and estimating the mass and power requirements of the ACS needed to meet the specified performance goals. The analyses concentrated on the different on-orbit control modes which start immediately after the separation of the RRS from the launch vehicle. The three distinct on-orbit modes considered for these analyses are as follows: (1) Mode 1 - A Gravity Gradient (GG) three-axis stabilized spacecraft with active magnetic control; (2) Mode 2 - A GG stabilized mode with a controlled yaw rotation rate ('rotisserie') using three-axis magnetic control and also incorporating a 10 N-m-s momentum wheel along the (Z) yaw axis; and (3) Mode 3 - A spin stabilized mode of operation with the spin about the pitch (Y) axis, incorporating a 20 N-m-s momentum wheel along the pitch (Y) axis and attitude control via thrusters. To investigate the capabilities of the different controllers in these various operational modes, a series of computer simulations and trade-off analyses have been made to evaluate the achievable performance levels, and the necessary mass and power requirements.

  2. New Future for Stock Trading

    Institute of Scientific and Technical Information of China (English)

    2010-01-01

    Securities regulators formulated the risk-control mechanism prior to launch of stock index futures in China For three years Wang Liangguang, an experienced stock investor, waited patiently for the trading of stock index futures. And now, that day has

  3. Impact of Re-launching the Treasury Bonds Futures on the Volatility Market Interest Rates%重推国债期货对利率市场波动性的影响研究

    Institute of Scientific and Technical Information of China (English)

    夏秀相; 侯擎天; 周敦辉

    2015-01-01

    With the data of treasury bond futures ( 09/06/2013—04/11/2014 ) and the government bond index ( 01/04/2013—04/11/2014 ) , we establish some dummy variable for lunching treasury bond futures to set up the GARCH , GJR models to analyze the role of treasury bonds futures .The result shows that negative leverage effect was improved , investors become more ra-tional, market risk was reduced.However, the effect of the futures trading to the market volatility rate is extremely limited .The pa-per explains the inconsistency of the experimental data with the old theory which holds that the transmission of market information would be slowdown .In this paper , we proved that the treasury bond futures would contribute to development of basic interest rate of financial market , and can provide a hedge against interest rate changes .%选择“2013年9月6日至2014年4月11日国债期货数据”和“2013年1月4日至2014年4月11日国债指数”数据,对国债期货推出设立虚拟变量,建立GARCH、GJR等模型定量分析了国债期货发挥的作用,得出了在引入国债期货交易之后,国债现货市场中信息的“负杠杆效应”有所改善,投资者由非理性趋向理性,国债现货市场中的市场风险有效地降低,但国债期货对国债现货市场波动性的影响十分有限等结论,并结合中国国债市场实际情况分析解释了重推国债期货后市场上信息的传递速度变慢这一与理论不符的结果,证明了国债期货合约的功能发挥有助于市场形成完善的基准收益率体系并有助于有效规避利率风险。

  4. A Discrete-Event Simulation Model for Evaluating Air Force Reusable Military Launch Vehicle Post-Landing Operations

    Science.gov (United States)

    2006-06-01

    safety pin prevents inadvertent firing of the gun on the aircraft. The chaff-flare safety pin prevents the accidental dispensing of chaff and...flares. All of these actions protect the ground crew and other personnel that may be in the area. 16 Following the safety pin installation, the...link allows the ground crew to confirm with the aircrew the condition of the EPU prior to installing the EPU ground safety pin . The EPU ground

  5. 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).

  6. 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...

  7. Representation and Adaptive Transformation of Reusable Software Components

    Institute of Scientific and Technical Information of China (English)

    2001-01-01

    The key ingredient for promoting software reuse in arepository-base integrated development environment, is to provide support for the software develo per who wants to search the repository to locate and retrieve suitable software components for reuse. This paper presents that reusable software components form a base to provide a flexible representation of component adaptability to any re pository with a specific classification. As an alternative, it proposes to autom atically identify and convert the component source code with all its information into a standard form, so that components can be transferred from one type of li brary to another.

  8. Aquarius, a reusable water-based interplanetary human spaceflight transport

    Science.gov (United States)

    Adamo, Daniel R.; Logan, James S.

    2016-11-01

    Attributes of a reusable interplanetary human spaceflight transport are proposed and applied to example transits between the Earth/Moon system and Deimos, the outer moon of Mars. Because the transport is 54% water by mass at an interplanetary departure, it is christened Aquarius. In addition to supporting crew hydration/hygiene, water aboard Aquarius serves as propellant and as enhanced crew habitat radiation shielding during interplanetary transit. Key infrastructure and technology supporting Aquarius operations include pre-emplaced consumables and subsurface habitat at Deimos with crew radiation shielding equivalent to sea level on Earth, resupply in a selenocentric distant retrograde orbit, and nuclear thermal propulsion.

  9. 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.

  10. 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.

  11. 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.

  12. Lunar launch and landing facilities and operations

    Science.gov (United States)

    1987-01-01

    The Florida Institute of Technology established an Interdisciplinary Design Team to design a lunar based facility whose primary function involves launch and landing operations for future moon missions. Both manned and unmanned flight operations were considered in the study with particular design emphasis on the utilization (or reutilization) of all materials available on the moon. This resource availability includes man-made materials which might arrive in the form of expendable landing vehicles as well as in situ lunar minerals. From an engineering standpoint, all such materials are considered as to their suitability for constructing new lunar facilities and/or repairing or expanding existing structures. Also considered in this design study was a determination of the feasibility of using naturally occurring lunar materials to provide fuel components to support lunar launch operations. Conventional launch and landing operations similar to those used during the Apollo Program were investigated as well as less conventional techniques such as rail guns and electromagnetic mass drivers. The Advanced Space Design team consisted of students majoring in Physics and Space Science as well as Electrical, Mechanical, Chemical and Ocean Engineering.

  13. Optimization of a Future RLV Business Case using Multiple Strategic Market Prices

    Science.gov (United States)

    Charania, A.; Olds, J. R.

    2002-01-01

    There is a lack of depth in the current paradigm of conceptual level economic models used to evaluate the value and viability of future capital projects such as a commercial reusable launch vehicle (RLV). Current modeling methods assume a single price is charged to all customers, public or private, in order to optimize the economic metrics of interest. This assumption may not be valid given the different utility functions for space services of public and private entities. The government's requirements are generally more inflexible than its commercial counterparts. A government's launch schedules are much more rigid, choices of international launch services restricted, and launch specifications generally more stringent as well as numerous. These requirements generally make the government's demand curve more inelastic. Subsequently, a launch vehicle provider will charge a higher price (launch price per kg) to the government and may obtain a higher level of financial profit compared to an equivalent a commercial payload. This profit is not a sufficient condition to enable RLV development by itself but can help in making the financial situation slightly better. An RLV can potentially address multiple payload markets; each market has a different price elasticity of demand for both the commercial and government customer. Thus, a more resilient examination of the economic landscape requires optimization of multiple prices in which each price affects a different demand curve. Such an examination is performed here using the Cost and Business Analysis Module (CABAM), an MS-Excel spreadsheet-based model that attempts to couple both the demand and supply for space transportation services in the future. The demand takes the form of market assumptions (both near-term and far-term) and the supply comes from user-defined vehicles that are placed into the model. CABAM represents RLV projects as commercial endeavors with the possibility to model the effects of government

  14. 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

  15. A comparison of reusable and disposable perioperative textiles: sustainability state-of-the-art 2012.

    Science.gov (United States)

    Overcash, Michael

    2012-05-01

    Contemporary comparisons of reusable and single-use perioperative textiles (surgical gowns and drapes) reflect major changes in the technologies to produce and reuse these products. Reusable and disposable gowns and drapes meet new standards for medical workers and patient protection, use synthetic lightweight fabrics, and are competitively priced. In multiple science-based life cycle environmental studies, reusable surgical gowns and drapes demonstrate substantial sustainability benefits over the same disposable product in natural resource energy (200%-300%), water (250%-330%), carbon footprint (200%-300%), volatile organics, solid wastes (750%), and instrument recovery. Because all other factors (cost, protection, and comfort) are reasonably similar, the environmental benefits of reusable surgical gowns and drapes to health care sustainability programs are important for this industry. Thus, it is no longer valid to indicate that reusables are better in some environmental impacts and disposables are better in other environmental impacts. It is also important to recognize that large-scale studies of comfort, protection, or economics have not been actively pursued in the last 5 to 10 years, and thus the factors to improve both reusables and disposable systems are difficult to assess. In addition, the comparison related to jobs is not well studied, but may further support reusables. In summary, currently available perioperative textiles are similar in comfort, safety, and cost, but reusable textiles offer substantial opportunities for nurses, physicians, and hospitals to reduce environmental footprints when selected over disposable alternatives. Evidenced-based comparison of environmental factors supports the conclusion that reusable gowns and drapes offer important sustainability improvements. The benefit of reusable systems may be similar for other reusables in anesthesia, such as laryngeal mask airways or suction canisters, but life cycle studies are needed to

  16. 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,

  17. Distributed Health Monitoring System for Reusable Liquid Rocket Engines

    Science.gov (United States)

    Lin, C. F.; Figueroa, F.; Politopoulos, T.; Oonk, S.

    2009-01-01

    The ability to correctly detect and identify any possible failure in the systems, subsystems, or sensors within a reusable liquid rocket engine is a major goal at NASA John C. Stennis Space Center (SSC). A health management (HM) system is required to provide an on-ground operation crew with an integrated awareness of the condition of every element of interest by determining anomalies, examining their causes, and making predictive statements. However, the complexity associated with relevant systems, and the large amount of data typically necessary for proper interpretation and analysis, presents difficulties in implementing complete failure detection, identification, and prognostics (FDI&P). As such, this paper presents a Distributed Health Monitoring System for Reusable Liquid Rocket Engines as a solution to these problems through the use of highly intelligent algorithms for real-time FDI&P, and efficient and embedded processing at multiple levels. The end result is the ability to successfully incorporate a comprehensive HM platform despite the complexity of the systems under consideration.

  18. Thermally Stable and Sterilizable Polymer Transistors for Reusable Medical Devices.

    Science.gov (United States)

    Kyaw, Aung Ko Ko; Jamalullah, Feroz; Vaithieswari, Loga; Tan, Mein Jin; Zhang, Lian; Zhang, Jie

    2016-04-20

    We realize a thermally stable polymer thin film transistor (TFT) that is able to endure the standard autoclave sterilization for reusable medical devices. A thermally stable semiconducting polymer poly[4-(4,4-dihexadecyl-4Hcyclopenta[1,2-b:5,4-b]dithiophen-2-yl)-alt[1,2,5]thiadiazolo [3,4c] pyridine], which is stable up to 350 °C in N2 and 200 °C in air, is used as channel layer, whereas the biocompatible SU-8 polymer is used as a flexible dielectric layer, in addition to conventional SiO2 dielectric layer. Encapsulating with in-house designed composite film laminates as moisture barrier, both TFTs using either SiO2 or SU-8 dielectric layer exhibit good stability in sterilized conditions without significant change in mobility and threshold voltage. After sterilization for 30 min in autoclave, the mobility drops only 15%; from as-fabricated mobility of 1.4 and 1.3 cm(2) V(-1) s(-1) to 1.2 and 1.1 cm(2) V(-1) s(-1) for TFTs with SiO2 and SU-8 dielectric layer, respectively. Our TFT design along with experimental results reveal the opportunity on organic/polymer flexible TFTs in sterilizable/reusable medical device application.

  19. Novel reusable porous polyimide fibers for hot-oil adsorption.

    Science.gov (United States)

    Tian, Lidong; Zhang, Chongyin; He, Xiaowei; Guo, Yongqiang; Qiao, Mingtao; Gu, Junwei; Zhang, Qiuyu

    2017-10-15

    The development of oil sorbents with high thermal stability, adsorption capacity, reusability and recoverability is of great significance for hot oil leakage protection, especially for oil spillage of oil refinery, petrochemical industry and cars. In our work, highly efficient hot oil adsorption of polyimide (PI) fibers with excellent thermal stability was successfully prepared by a facile electrospinning method followed by post-treatment. The corresponding morphologies, structures and oil adsorption properties of as-prepared PI fibers at different temperatures were analyzed and characterized. Results showed that PI fibers presented a stable morphology and pore structure at 200°C. The oil adsorption capacity of porous PI fibers for hot motor oil (200°C) was about 57.4gg(-1), higher than that of PI fibers (32.7gg(-1)) with non-porous structure for the motor oil at room temperature. Even after ten adsorption cycles, porous PI fibers still maintained a comparable oil sorption capacity (oil retention of 4.2%). The obtained porous PI fibers exhibited excellent hot oil adsorption capacity, reusability and recoverability, which would broaden the application of electrospun fibers in oil spill cleanup and further provide a versatile platform for exploring the technologies of nanofibers in hot oil adsorption field. Copyright © 2017. Published by Elsevier B.V.

  20. Reducing the Cost of Laparoscopy: Reusable versus Disposable Laparoscopic Instruments

    Directory of Open Access Journals (Sweden)

    Dimitrios K. Manatakis

    2014-01-01

    Full Text Available Cost-effectiveness in health care management is critical. The situation in debt-stricken Greece is further aggravated by the financial crisis and constant National Health System expense cut-downs. In an effort to minimize the cost of laparoscopy, our department introduced reusable laparoscopic instruments in December 2011. The aim of this study was to assess potential cost reduction of laparoscopic operations in the field of general surgery. Hospital records, invoice lists, and operative notes between January 2012 and December 2013, were retrospectively reviewed and data were collected on laparoscopic procedures, instrument failures, and replacement needs. Initial acquisition cost of 5 basic instrument sets was €21,422. Over the following 24 months, they were used in 623 operations, with a total maintenance cost of €11,487. Based on an average retail price of €490 per set, projected cost with disposable instruments would amount to €305,270, creating savings of €272,361 over the two-year period under study. Despite the seemingly high purchase price, each set amortized its acquisition cost after only 9 procedures and instrument cost depreciated to less than €55 per case. Disposable instruments cost 9 times more than reusable ones, and their high price would almost equal the total hospital reimbursement by social security funds for many common laparoscopic procedures.

  1. Study on Alternative Cargo Launch Options from the Lunar Surface

    Energy Technology Data Exchange (ETDEWEB)

    Cheryl A. Blomberg; Zamir A. Zulkefli; Spencer W. Rich; Steven D. Howe

    2013-07-01

    In the future, there will be a need for constant cargo launches from Earth to Mars in order to build, and then sustain, a Martian base. Currently, chemical rockets are used for space launches. These are expensive and heavy due to the amount of necessary propellant. Nuclear thermal rockets (NTRs) are the next step in rocket design. Another alternative is to create a launcher on the lunar surface that uses magnetic levitation to launch cargo to Mars in order to minimize the amount of necessary propellant per mission. This paper investigates using nuclear power for six different cargo launching alternatives, as well as the orbital mechanics involved in launching cargo to a Martian base from the moon. Each alternative is compared to the other alternative launchers, as well as compared to using an NTR instead. This comparison is done on the basis of mass that must be shipped from Earth, the amount of necessary propellant, and the number of equivalent NTR launches. Of the options, a lunar coil launcher had a ship mass that is 12.7% less than the next best option and 17 NTR equivalent launches, making it the best of the presented six options.

  2. Evolution of computational chemistry, the "launch pad" to scientific computational models: The early days from a personal account, the present status from the TACC-2012 congress, and eventual future applications from the global simulation approach

    Science.gov (United States)

    Clementi, Enrico

    2012-06-01

    This is the introductory chapter to the AIP Proceedings volume "Theory and Applications of Computational Chemistry: The First Decade of the Second Millennium" where we discuss the evolution of "computational chemistry". Very early variational computational chemistry developments are reported in Sections 1 to 7, and 11, 12 by recalling some of the computational chemistry contributions by the author and his collaborators (from late 1950 to mid 1990); perturbation techniques are not considered in this already extended work. Present day's computational chemistry is partly considered in Sections 8 to 10 where more recent studies by the author and his collaborators are discussed, including the Hartree-Fock-Heitler-London method; a more general discussion on present day computational chemistry is presented in Section 14. The following chapters of this AIP volume provide a view of modern computational chemistry. Future computational chemistry developments can be extrapolated from the chapters of this AIP volume; further, in Sections 13 and 15 present an overall analysis on computational chemistry, obtained from the Global Simulation approach, by considering the evolution of scientific knowledge confronted with the opportunities offered by modern computers.

  3. RAGE Reusable Game Software Components and Their Integration into Serious Game Engines

    NARCIS (Netherlands)

    Van der Vegt, Wim; Nyamsuren, Enkhbold; Westera, Wim

    2016-01-01

    This paper presents and validates a methodology for integrating reusable software components in diverse game engines. While conforming to the RAGE com-ponent-based architecture described elsewhere, the paper explains how the interac-tions and data exchange processes between a reusable software

  4. RAGE Reusable Game Software Components and Their Integration into Serious Game Engines

    NARCIS (Netherlands)

    Van der Vegt, Wim; Nyamsuren, Enkhbold; Westera, Wim

    2016-01-01

    This paper presents and validates a methodology for integrating reusable software components in diverse game engines. While conforming to the RAGE com-ponent-based architecture described elsewhere, the paper explains how the interac-tions and data exchange processes between a reusable software compo

  5. RAGE Reusable Game Software Components and Their Integration into Serious Game Engines

    NARCIS (Netherlands)

    Van der Vegt, Wim; Nyamsuren, Enkhbold; Westera, Wim

    2016-01-01

    This paper presents and validates a methodology for integrating reusable software components in diverse game engines. While conforming to the RAGE com-ponent-based architecture described elsewhere, the paper explains how the interac-tions and data exchange processes between a reusable software compo

  6. New Pedagogies and Re-Usable Learning Objects: Toward a Different Role for an LMS.

    Science.gov (United States)

    Collis, Betty; Strijker, Allard

    While the idea of reusing objects in digital learning environments is not new, continual strides are being made toward improving the prospects of reusability. A major trend in company training settings is to think of reusability in terms of a LMS (learning management system), but instructor use and pedagogies are little considered. This paper…

  7. Gun Launch System: efficient and low-cost means of research and real-time monitoring

    Science.gov (United States)

    Degtyarev, Alexander; Ventskovsky, Oleg; Korostelev, Oleg; Yakovenko, Peter; Kanevsky, Valery; Tselinko, Alexander

    2005-08-01

    The Gun Launch System with a reusable sub-orbital launch vehicle as a central element is proposed by a consortium of several Ukrainian high-tech companies as an effective, fast-response and low-cost means of research and real-time monitoring. The system is described in details, with the emphasis on its most important advantages. Multiple applications of the system are presented, including ones for the purposes of microgravity research; chemical, bacteriological and radiation monitoring and research of atmosphere and ionosphere; operational monitoring of natural and man-made disasters, as well as for some other areas of great practical interest. The current level of the system development is given, and the way ahead towards full system's implementation is prescribed.

  8. Oxidatively Stable Flexible Aerogel Composites for Reusable TPS Project

    Data.gov (United States)

    National Aeronautics and Space Administration — NASA?s Next Generation Launch Vehicle Technology Program has an interest in robust TPS materials with the highest level of thermal performance at the lowest possible...

  9. The Application of the NASA Advanced Concepts Office, Launch Vehicle Team Design Process and Tools for Modeling Small Responsive Launch Vehicles

    Science.gov (United States)

    Threet, Grady E.; Waters, Eric D.; Creech, Dennis M.

    2012-01-01

    The Advanced Concepts Office (ACO) Launch Vehicle Team at the NASA Marshall Space Flight Center (MSFC) is recognized throughout NASA for launch vehicle conceptual definition and pre-phase A concept design evaluation. The Launch Vehicle Team has been instrumental in defining the vehicle trade space for many of NASA s high level launch system studies from the Exploration Systems Architecture Study (ESAS) through the Augustine Report, Constellation, and now Space Launch System (SLS). The Launch Vehicle Team s approach to rapid turn-around and comparative analysis of multiple launch vehicle architectures has played a large role in narrowing the design options for future vehicle development. Recently the Launch Vehicle Team has been developing versions of their vetted tools used on large launch vehicles and repackaged the process and capability to apply to smaller more responsive launch vehicles. Along this development path the LV Team has evaluated trajectory tools and assumptions against sounding rocket trajectories and air launch systems, begun altering subsystem mass estimating relationships to handle smaller vehicle components, and as an additional development driver, have begun an in-house small launch vehicle study. With the recent interest in small responsive launch systems and the known capability and response time of the ACO LV Team, ACO s launch vehicle assessment capability can be utilized to rapidly evaluate the vast and opportune trade space that small launch vehicles currently encompass. This would provide a great benefit to the customer in order to reduce that large trade space to a select few alternatives that should best fit the customer s payload needs.

  10. 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

  11. End-To-End Simulation of Launch Vehicle Trajectories Including Stage Separation Dynamics

    Science.gov (United States)

    Albertson, Cindy W.; Tartabini, Paul V.; Pamadi, Bandu N.

    2012-01-01

    The development of methodologies, techniques, and tools for analysis and simulation of stage separation dynamics is critically needed for successful design and operation of multistage reusable launch vehicles. As a part of this activity, the Constraint Force Equation (CFE) methodology was developed and implemented in the Program to Optimize Simulated Trajectories II (POST2). The objective of this paper is to demonstrate the capability of POST2/CFE to simulate a complete end-to-end mission. The vehicle configuration selected was the Two-Stage-To-Orbit (TSTO) Langley Glide Back Booster (LGBB) bimese configuration, an in-house concept consisting of a reusable booster and an orbiter having identical outer mold lines. The proximity and isolated aerodynamic databases used for the simulation were assembled using wind-tunnel test data for this vehicle. POST2/CFE simulation results are presented for the entire mission, from lift-off, through stage separation, orbiter ascent to orbit, and booster glide back to the launch site. Additionally, POST2/CFE stage separation simulation results are compared with results from industry standard commercial software used for solving dynamics problems involving multiple bodies connected by joints.

  12. Business Intelligence Modeling in Launch Operations

    Science.gov (United States)

    Bardina, Jorge E.; Thirumalainambi, Rajkumar; Davis, Rodney D.

    2005-01-01

    This technology project is to advance an integrated Planning and Management Simulation Model for evaluation of risks, costs, and reliability of launch systems from Earth to Orbit for Space Exploration. The approach builds on research done in the NASA ARC/KSC developed Virtual Test Bed (VTB) to integrate architectural, operations process, and mission simulations for the purpose of evaluating enterprise level strategies to reduce cost, improve systems operability, and reduce mission risks. The objectives are to understand the interdependency of architecture and process on recurring launch cost of operations, provide management a tool for assessing systems safety and dependability versus cost, and leverage lessons learned and empirical models from Shuttle and International Space Station to validate models applied to Exploration. The systems-of-systems concept is built to balance the conflicting objectives of safety, reliability, and process strategy in order to achieve long term sustainability. A planning and analysis test bed is needed for evaluation of enterprise level options and strategies for transit and launch systems as well as surface and orbital systems. This environment can also support agency simulation .based acquisition process objectives. The technology development approach is based on the collaborative effort set forth in the VTB's integrating operations. process models, systems and environment models, and cost models as a comprehensive disciplined enterprise analysis environment. Significant emphasis is being placed on adapting root cause from existing Shuttle operations to exploration. Technical challenges include cost model validation, integration of parametric models with discrete event process and systems simulations. and large-scale simulation integration. The enterprise architecture is required for coherent integration of systems models. It will also require a plan for evolution over the life of the program. The proposed technology will produce

  13. Business intelligence modeling in launch operations

    Science.gov (United States)

    Bardina, Jorge E.; Thirumalainambi, Rajkumar; Davis, Rodney D.

    2005-05-01

    The future of business intelligence in space exploration will focus on the intelligent system-of-systems real-time enterprise. In present business intelligence, a number of technologies that are most relevant to space exploration are experiencing the greatest change. Emerging patterns of set of processes rather than organizational units leading to end-to-end automation is becoming a major objective of enterprise information technology. The cost element is a leading factor of future exploration systems. This technology project is to advance an integrated Planning and Management Simulation Model for evaluation of risks, costs, and reliability of launch systems from Earth to Orbit for Space Exploration. The approach builds on research done in the NASA ARC/KSC developed Virtual Test Bed (VTB) to integrate architectural, operations process, and mission simulations for the purpose of evaluating enterprise level strategies to reduce cost, improve systems operability, and reduce mission risks. The objectives are to understand the interdependency of architecture and process on recurring launch cost of operations, provide management a tool for assessing systems safety and dependability versus cost, and leverage lessons learned and empirical models from Shuttle and International Space Station to validate models applied to Exploration. The systems-of-systems concept is built to balance the conflicting objectives of safety, reliability, and process strategy in order to achieve long term sustainability. A planning and analysis test bed is needed for evaluation of enterprise level options and strategies for transit and launch systems as well as surface and orbital systems. This environment can also support agency simulation based acquisition process objectives. The technology development approach is based on the collaborative effort set forth in the VTB's integrating operations, process models, systems and environment models, and cost models as a comprehensive disciplined

  14. Au/TiO2 Reusable Photocatalysts for Dye Degradation

    Directory of Open Access Journals (Sweden)

    Silija Padikkaparambil

    2013-01-01

    Full Text Available Nanogold doped TiO2 catalysts are synthesized, and their application in the photodegradation of dye pollutants is studied. The materials are characterized using different analytical techniques such as X-ray diffraction, transmission electron microscopy, UV-visible diffuse reflectance spectroscopy, and X-ray photoelectron spectroscopy. The results revealed the strong interaction between the metallic gold nanoparticles and the anatase TiO2 support. Au doped systems showed very good photoactivity in the degradation of dye pollutants under UV irradiation as well as in sunlight. A simple mechanism is proposed for explaining the excellent photoactivity of the systems. The reusability studies of the photocatalysts exhibited more than 98% degradation of the dye even after 10 repeated cycles.

  15. Linear quadratic servo control of a reusable rocket engine

    Science.gov (United States)

    Musgrave, Jeffrey L.

    1991-01-01

    The paper deals with the development of a design method for a servo component in the frequency domain using singular values and its application to a reusable rocket engine. A general methodology used to design a class of linear multivariable controllers for intelligent control systems is presented. Focus is placed on performance and robustness characteristics, and an estimator design performed in the framework of the Kalman-filter formalism with emphasis on using a sensor set different from the commanded values is discussed. It is noted that loop transfer recovery modifies the nominal plant noise intensities in order to obtain the desired degree of robustness to uncertainty reflected at the plant input. Simulation results demonstrating the performance of the linear design on a nonlinear engine model over all power levels during mainstage operation are discussed.

  16. A Reusable Software Architecture for Small Satellite AOCS Systems

    DEFF Research Database (Denmark)

    Alminde, Lars; Bendtsen, Jan Dimon; Laursen, Karl Kaas

    2006-01-01

    with both hardware and on-board software. Some of the key issues addressed by the framework are automatic translation of mathematical specifications of hybrid systems into executable software entities, management of execution of coupled models in a parallel distributed environment, as well as interaction......This paper concerns the software architecture called Sophy, which is an abbreviation for Simulation, Observation, and Planning in HYbrid systems. We present a framework that allows execution of hybrid dynamical systems in an on-line distributed computing environment, which includes interaction...... with external components, hardware and/or software, through generic interfaces. Sophy is primarily intended as a tool for development of model based reusable software for the control and autonomous functions of satellites and/or satellite clusters....

  17. Modeling Reusable and Interoperable Faceted Browsing Systems with Category Theory.

    Science.gov (United States)

    Harris, Daniel R

    2015-08-01

    Faceted browsing has become ubiquitous with modern digital libraries and online search engines, yet the process is still difficult to abstractly model in a manner that supports the development of interoperable and reusable interfaces. We propose category theory as a theoretical foundation for faceted browsing and demonstrate how the interactive process can be mathematically abstracted. Existing efforts in facet modeling are based upon set theory, formal concept analysis, and lightweight ontologies, but in many regards, they are implementations of faceted browsing rather than a specification of the basic, underlying structures and interactions. We will demonstrate that category theory allows us to specify faceted objects and study the relationships and interactions within a faceted browsing system. Implementations can then be constructed through a category-theoretic lens using these models, allowing abstract comparison and communication that naturally support interoperability and reuse.

  18. Foundations of reusable and interoperable facet models using category theory.

    Science.gov (United States)

    Harris, Daniel R

    2016-10-01

    Faceted browsing has become ubiquitous with modern digital libraries and online search engines, yet the process is still difficult to abstractly model in a manner that supports the development of interoperable and reusable interfaces. We propose category theory as a theoretical foundation for faceted browsing and demonstrate how the interactive process can be mathematically abstracted. Existing efforts in facet modeling are based upon set theory, formal concept analysis, and light-weight ontologies, but in many regards, they are implementations of faceted browsing rather than a specification of the basic, underlying structures and interactions. We will demonstrate that category theory allows us to specify faceted objects and study the relationships and interactions within a faceted browsing system. Resulting implementations can then be constructed through a category-theoretic lens using these models, allowing abstract comparison and communication that naturally support interoperability and reuse.

  19. Software Metrics to Estimate Software Quality using Software Component Reusability

    Directory of Open Access Journals (Sweden)

    Prakriti Trivedi

    2012-03-01

    Full Text Available Today most of the applications developed using some existing libraries, codes, open sources etc. As a code is accessed in a program, it is represented as the software component. Such as in java beans and in .net ActiveX controls are the software components. These components are ready to use programming code or controls that excel the code development. A component based software system defines the concept of software reusability. While using these components the main question arise is whether to use such components is beneficial or not. In this proposed work we are trying to present the answer for the same question. In this work we are presenting a set of software matrix that will check the interconnection between the software component and the application. How strong this relation defines the software quality after using this software component. The overall metrics will return the final result in terms of the boundless of the component with application.

  20. Reusable, flyback liquid rocket booster for the Space Shuttle

    Science.gov (United States)

    Benton, Mark G.

    1989-08-01

    This paper outlines a preliminary design for an unmanned, reusable, flyback liquid rocket booster (LRB) as an evolutionary follow-on to the Shuttle solid rocket booster (SRB). Previous Shuttle liquid-propellant booster concepts are reviewed in order to gain insight into these designs. The operating costs, environmental impacts, and abort options of the SRB are discussed. The LRB flight profile and advantages of LRB use are discussed. The preliminary design for the LRB is outlined in detail using calculations and drawings. This design maximizes the use of existing hardware and proven technology to minimize cost and development time. The LRB design is presented as a more capable, more environmentally acceptable, and safer Shuttle booster.

  1. 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.

  2. Improving learning of anatomy with reusable learning objects

    Directory of Open Access Journals (Sweden)

    P Rad

    2015-12-01

    Full Text Available Introduction: The use of modern educational technologies is useful for learning, durability, sociability, and upgrading professionalism. The aim of this study was evaluating the effect of reusable learning objects on improving learning of anatomy. Methods: This was a quasi-experimental study. Fourteen (reusable learning objects RLO from different parts of anatomy of human body including thorax, abdomen, and pelvis were prepared for medical student in Yasuj University of Medical Sciences in 2009. The length of the time for RLO was between 11-22 min. Because their capacities were low, so they were easy to use with cell phone or MP4. These materials were available to the students before the classes. The mean scores of students in anatomy of human body group were compared to the medical students who were not used this method and entered the university in 2008. A questionnaire was designed by the researcher to evaluate the effect of RLO and on, content, interest and motivation, participation, preparation and attitude. Result: The mean scores of anatomy of human body of medical student who were entered the university in 2009 have been increased compare to the students in 2008, but this difference was not significant. Based on the questionnaire data, it was shown that the RLO had a positive effect on improving learning anatomy of human body (75.5% and the effective relationship (60.6%. The students were interested in using RLO (74.6%, some students (54.2% believed that this method should be replaced by lecture. Conclusion: The use of RLO could promote interests and effective communication among the students and led to increasing self-learning motivation.

  3. 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.

  4. 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

  5. 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

  6. Human Performance Modeling and Simulation for Launch Team Applications

    Science.gov (United States)

    Peaden, Cary J.; Payne, Stephen J.; Hoblitzell, Richard M., Jr.; Chandler, Faith T.; LaVine, Nils D.; Bagnall, Timothy M.

    2006-01-01

    This paper describes ongoing research into modeling and simulation of humans for launch team analysis, training, and evaluation. The initial research is sponsored by the National Aeronautics and Space Administration's (NASA)'s Office of Safety and Mission Assurance (OSMA) and NASA's Exploration Program and is focused on current and future launch team operations at Kennedy Space Center (KSC). The paper begins with a description of existing KSC launch team environments and procedures. It then describes the goals of new Simulation and Analysis of Launch Teams (SALT) research. The majority of this paper describes products from the SALT team's initial proof-of-concept effort. These products include a nominal case task analysis and a discrete event model and simulation of launch team performance during the final phase of a shuttle countdown; and a first proof-of-concept training demonstration of launch team communications in which the computer plays most roles, and the trainee plays a role of the trainee's choice. This paper then describes possible next steps for the research team and provides conclusions. This research is expected to have significant value to NASA's Exploration Program.

  7. Structural Weight Estimation for Launch Vehicles

    Science.gov (United States)

    Cerro, Jeff; Martinovic, Zoran; Su, Philip; Eldred, Lloyd

    2002-01-01

    This paper describes some of the work in progress to develop automated structural weight estimation procedures within the Vehicle Analysis Branch (VAB) of the NASA Langley Research Center. One task of the VAB is to perform system studies at the conceptual and early preliminary design stages on launch vehicles and in-space transportation systems. Some examples of these studies for Earth to Orbit (ETO) systems are the Future Space Transportation System [1], Orbit On Demand Vehicle [2], Venture Star [3], and the Personnel Rescue Vehicle[4]. Structural weight calculation for launch vehicle studies can exist on several levels of fidelity. Typically historically based weight equations are used in a vehicle sizing program. Many of the studies in the vehicle analysis branch have been enhanced in terms of structural weight fraction prediction by utilizing some level of off-line structural analysis to incorporate material property, load intensity, and configuration effects which may not be captured by the historical weight equations. Modification of Mass Estimating Relationships (MER's) to assess design and technology impacts on vehicle performance are necessary to prioritize design and technology development decisions. Modern CAD/CAE software, ever increasing computational power and platform independent computer programming languages such as JAVA provide new means to create greater depth of analysis tools which can be included into the conceptual design phase of launch vehicle development. Commercial framework computing environments provide easy to program techniques which coordinate and implement the flow of data in a distributed heterogeneous computing environment. It is the intent of this paper to present a process in development at NASA LaRC for enhanced structural weight estimation using this state of the art computational power.

  8. Future Prospects for Hypersonic Flight Test For University Students

    OpenAIRE

    2005-01-01

    The transport to space of satellites and experiments with conventional expandable rockets is a very expensive and time demanding business and therefore almost prohibitive for Universities and High-School or Colleges laboratories. In this lecture an unconventional, low-cost reusable concept-system based on "electromagnetic railgun " is presented and discussed. The aims is to provide in the midterm with a system capable of launch in LEO small satellites of maximum 5 kg weight not by using conv...

  9. 股指期权推出对股票市场和股指期货市场波动性影响:以KOSPI200股指期权为例%The effect on volatility of stock market and stock index futures market after launching stock index options: A case of KOSPI200 index options

    Institute of Scientific and Technical Information of China (English)

    熊熊; 张宇; 张维; 张永杰

    2011-01-01

    Stock index option is the derivative products based on stock index, for security market it has the functions of price discovery, flourish stock market, enhance market stability and liquidity, promote capital formation, en8ure healthy security market. In this paper, we chose Korean derivatives market as example,analyzed the impact of the launch of KOSPI200 index options. we used GARCH (1,1) model and TARCH (1,1) model analyze the changes in volatility of KOSPI200 index and KOSPI200 index futures. We found that the launch of KOSPI200 index options aggravate the volatility of KOSPI200 index and KOSP1200 index futures significantly, and aggravate the asymmetric volatility of KOSPI200 index. The conclusion is important reference of China to whether introduce stock index option and the Risk Prevention after the introduce of stock index options.%股指期权是以股票指数为标的期权类衍生产品,对于证券市场来说期权具有价格发现、活跃股票市场、增强市场的流动性与稳定性、促进资本形成、确保资本市场良性运行等功能,以韩国KOSPI200指数和KOSPI200指数期货为研究对象,使用GARCH(1,1)模型、TARCH(1,1)模型对韩国KOSPI200股指期权推出后KOSPI200指数和KOSPI200指数期货的波动性进行了研究,研究结果表明:KOSPI200指数期权推出对于KOSPI200指数和KOSPI200指数期货的波动性和非对称波动性都有显著的影响,KOSPI200指数推出后KOSPI200指数和KOSPI200指数期货的波动增大,同时股指期权推出后现货市场的不对称性加大,而股指期货市场的不对称性减小.结论对于新兴市场经济国家股指期权产品的设计和中国股指期权推出后的风险防范有着重要的参考价值.

  10. Launch of the "MICE Procurement" website for your future events

    CERN Multimedia

    The MICE Office team

    2014-01-01

    The number of MICE (Meeting, Incentive, Conference and Event) requests is on the increase and our hotel offer is constantly being developed.   The MICE Office has decided to create a dedicated website in order to offer the best possible service to its users. This site is accessible from the FP webpage (MICE Procurement) using your NICE login. It gives you access to the list of the establishments which have a contract with CERN, grouped by geographic area/star rating, and all related information. The establishments listed on this website can accommodate your local events, organised by CERN or in partnership with an institution. They were selected following a market survey and as a result of a price enquiry in accordance with CERN's Purchasing Rules. We offer a number of standard packages, but we will try to respond to any specific requirements. On the same site you can also access a longer list of hotels (also accessible via the GS website) for which prices and conditions have been nego...

  11. Heavy Lift Launch Capability with a New Hydrocarbon Engine

    Science.gov (United States)

    Threet, Grady E., Jr.; Holt, James B.; Philips, Alan D.; Garcia, Jessica A.

    2011-01-01

    The Advanced Concepts Office at NASA's George C. Marshall Space Flight Center was tasked to define the thrust requirement of a new liquid oxygen rich staged combustion cycle hydrocarbon engine that could be utilized in a launch vehicle to meet NASA s future heavy lift needs. Launch vehicle concepts were sized using this engine for different heavy lift payload classes. Engine out capabilities for one of the heavy lift configurations were also analyzed for increased reliability that may be desired for high value payloads or crewed missions. The applicability for this engine in vehicle concepts to meet military and commercial class payloads comparable to current ELV capability was also evaluated.

  12. The CERN & Society programme launches its newsletter

    CERN Multimedia

    Matteo Castoldi

    2016-01-01

    The newsletter will be issued quarterly. Sign up to remain informed about the latest initiatives of the CERN & Society programme!    The CERN & Society programme encompasses projects in the areas of education and outreach, innovation and knowledge exchange, and culture and creativity that spread the CERN spirit of scientific curiosity for the inspiration and benefit of society. The programme is funded primarily by the CERN & Society Foundation, a charitable foundation established by CERN and supported by individuals, trusts, organisations and commercial companies. The projects are inspired or enabled by CERN but lie outside of the Laboratory’s specific research mandate. We especially want to help young talent from around the world to flourish in the future. The programme is now launching its newsletter, which will be issued quarterly. Everybody who wants to be informed about CERN & Society’s activities, stay up-to-date with its latest in...

  13. 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

  14. A Reusable Component for Communication and Data Synchronization in Mobile Distributed Interactive Applications

    Directory of Open Access Journals (Sweden)

    Abdul Malik Khan

    2010-10-01

    Full Text Available In Distributed Interactive Applications (DIA such as multiplayer games, where many participants are involved in a same game session and communicate through a network, they may have an inconsistent view of the virtual world because of the communication delays across the network. This issue becomes even more challenging when communicating through a cellular network while executing the DIA client on a mobile terminal. Consistency maintenance algorithms may be used to obtain a uniform view of the virtual world. These algorithms are very complex and hard to program and therefore, the implementation and the future evolution of the application logic code become difficult. To solve this problem, we propose an approach where the consistency concerns are handled separately by a distributed component called a Synchronization Medium, which is responsible for the communication management as well as the consistency maintenance. We present the detailed architecture of the Synchronization Medium and the generic interfaces it offers to DIAs. We evaluate our approach both qualitatively and quantitatively. We first demonstrate that the Synchronization Medium is a reusable component through the development of two game applications, a car racing game and a space war game. A performance evaluation then shows that the overhead introduced by the Synchronization Medium remains acceptable.

  15. Development of a Reusable, Rate-Sensitive Abdomen for the Hybrid III Family of Dummies.

    Science.gov (United States)

    Rouhana, S W; Elhagediab, A M; Walbridge, A; Hardy, W N; Schneider, L W

    2001-11-01

    The objective of this work was to develop a reusable, rate-sensitive dummy abdomen with abdominal injury assessment capability. The primary goal for the abdomen developed was to have good biofidelity in a variety of loading situations that might be encountered in an automotive collision. This paper presents a review of previous designs for crash dummy abdomens, a description of the development of the new abdomen, results of testing with the new abdomen and instrumentation, and suggestions for future work. The biomechanical response targets for the new abdomen were determined from tests of the mid abdomen done in a companion biomechanical study. The response of the abdominal insert is an aggregate response of the dummy's entire abdominal area and does not address differences in upper versus lower abdominal response, solid versus hollow organs, or organ position or mobility. While the abdomen developed has demonstrated good biofidelity in rigid bar, seat belt and airbag loading situations, some work remains to be done before it can be used in crash testing.

  16. A LEON2&3 Emulation Board Qualified for Space Programs Based on Reusable Building Blocks

    Science.gov (United States)

    Caleno, Mauro; Quere, Gregory; Chenu, Xavier

    2014-08-01

    ESA/ESTEC has granted Airbus Defense and Space a study for the development of a versatile LEON2 and LEON3 emulation board hosted on a COTS FPGA board.The LEON Emulation Board (LEB) is a component for System Simulators used as Software Validation Facilities and Operational Simulators. It is an alternative to the full software simulation of the LEON processor; additionally, because it embeds the actual VHDL of the LEON processor, it is fully representative and delivers a performance higher than the instruction-set software simulators.The LEB enables simulating in software the functions of Systems on Chip not already embedded in the LEB. It is available in 3 configurations for the LEON2 FT and the LEON3. Moreover, as it is built around a set of reusable simulation building blocks (VHDL + software driver), it can easily be reassembled to emulate more accurately different Systems on Chips (SoC).This paper presents the key functions of the LEB, its performance, applications and potential future developments.

  17. The Role of Reusable Learning Objects in Occupational Therapy Entry-Level Education

    Directory of Open Access Journals (Sweden)

    Bryan M. Gee

    2014-10-01

    Full Text Available Out of early research, Cisco Systems (1999 have built an impressive foundation that advocates for reusable learning objects (RLOs. As the need for online methods for delivering both formal and informal educational content has increased, the prospect of greater influence through carefully constructed RLOs has grown. RLOs are any digital resource that can be used and reused to enhance online learning. RLOs typically are small, discrete, self-contained digital objects that may be sequenced, combined, and used within a variety of instructional activities. RLOs have been implemented in nursing, pharmacy, and physician assistant programs. However, there is a lack of literature regarding RLOs in occupational therapy education. An attitudinal survey was administered to occupational therapy students after they had used an RLO focused on goal writing. Student preferences toward RLO content, instructional design, and eLearning were generally positive. Nearly three-quarters of the students who responded to the survey indicated that the RLO presented was beneficial. All respondents noted that they would use the RLO for future occupational therapy courses. It is argued that incorporating RLOs offers a cost-effective, efficient learning tool, and also adds credibility to the given curriculum program as being innovative with instructing occupational-therapy related concepts.

  18. Investigation of Reusable Crucibles on Uranium Casting by Injection Method

    Energy Technology Data Exchange (ETDEWEB)

    Song, Hoon; Kim, Jong-Hwan; Ko, Young-Mo; Woo, Yoon-Myung; Kim, Ki-Hwan; Lee, Chan-Bock [Korea Atomic Energy Research Institute, Daejeon (Korea, Republic of)

    2014-10-15

    Slurry applied coatings must be recoated after every batch. Thermal plasma-sprayed coatings of refractory materials can be applied to develop a re-usable crucible coating for metallic fuel. Plasma-sprayed coating can provide a crucible with a denser, more durable, coating layer, compared with the more friable coating layer formed by slurry-coating. Plasma-sprayed coatings are consolidated by mechanical interlocking of the molten particles impacting on the substrate and are dense from the heat applied by the plasma. Although the protective layer is more difficult in a dense coating than in a porous coating, the increased coating density is advantageous because it should not require frequent recoating or U-Zr melt penetration. In this study, we used a Vacuum Plasma Spray (VPS) method, which is suitable to prevent oxidization and has a number of advantages such as low defect density and excellent adhesion of the coating layer, to investigate permanent coatings for re-usable crucibles for melting and casting of metallic fuel. After coatings, interaction studies between molten U-Zr alloys and the plasma sprayed coatings were also carried out. We summarized the results of the coating methods. All coated samples maintained good coating integrity in a U-Zr melt, but most of the coating method samples did not maintain integrity in the U-Zr-RE melt because of the cracks or microcracks of the coating layer, presumably formed from the thermal expansion difference. Only the TaC(100)-Y{sub 2}O{sub 3}(100) DL VPS coated rod survived the 2 cycles dipping test of U-Zr-RE melt. This is likely caused by good adhesion of the TaC coating onto the niobium rod and the chemical inertness of Y{sub 2}O{sub 3} coating material in the U-Zr-RE melt. Based on the results from the interactions with U-10Zr and U-10Zr-5RE melt, TaC(100)-Y{sub 2}O{sub 3}(100) plasma-sprayed coating methods have been applied to real graphite crucibles.

  19. The Future of Futures

    DEFF Research Database (Denmark)

    Frankel, Christian; Ossandón, José

    2013-01-01

    Review of Elena Esposito: The Future of Futures. The Time of Money in Financing and Society Cheltenham. Edward Elgar, 2011.......Review of Elena Esposito: The Future of Futures. The Time of Money in Financing and Society Cheltenham. Edward Elgar, 2011....

  20. Developing a Toolset Supporting the Construction of Reusable Components for Embedded Control Systems

    DEFF Research Database (Denmark)

    Guan, Wei; Sierszecki, Krzysztof; Angelov, Christo K.

    2010-01-01

    Reusing software components for embedded control applications enhances product quality and reduces time to market when appropriate (formal) methodologies and supporting toolsets are available. That is why industrial companies are interested in developing trusted, in-house reusable components for ...

  1. Constructing Relationship Between Software Metrics and Code Reusability in Object Oriented Design

    Directory of Open Access Journals (Sweden)

    Manoj H.M

    2016-02-01

    Full Text Available The role of the design pattern in the form of software metric and internal code architecture for object-oriented design plays a critical role in software engineering regarding production cost efficiency. This paper discusses code reusability that is a frequently exercised cost saving methodology in IT production. After reviewing existing literature towards a study on software metrics, we found that very few studies are witnessed to incline towards code reusability. Hence, we developed a simple analytical model that establishes a relationship between the design components of standard software metric and code reusability using case studies of three software projects (Customer Relationship Management project, Supply Chain Management project, and Enterprise Relationship Management project. We also testify our proposal using stochastic based Markov model to find that proposed system can extract significant information of maximized values of code reusability with increasing level of uncertainties of software project methodologies.

  2. A Reusable, Oxidizer-Cooled, Hybrid Aerospike Rocket Motor for Flight Test Project

    Data.gov (United States)

    National Aeronautics and Space Administration — The proposed innovation is to use the refrigerant capabilities of nitrous oxide (N2O) to provide the cooling required for reusable operation of an aerospike nozzle...

  3. Interconnection blocks: a method for providing reusable, rapid, multiple, aligned and planar microfluidic interconnections

    DEFF Research Database (Denmark)

    Sabourin, David; Snakenborg, Detlef; Dufva, Hans Martin

    2009-01-01

    In this paper a method is presented for creating 'interconnection blocks' that are re-usable and provide multiple, aligned and planar microfluidic interconnections. Interconnection blocks made from polydimethylsiloxane allow rapid testing of microfluidic chips and unobstructed microfluidic...

  4. REUSABILITY OF BOND ELUT CERTIFY COLUMNS FOR THE EXTRACTION OF DRUGS FROM PLASMA

    NARCIS (Netherlands)

    CHEN, XH; FRANKE, JP; WIJSBEEK, J; DEZEEUW, RA

    1993-01-01

    The reusability of Bond Elut Certify columns for the extraction of toxicologically relevant drugs from plasma has been evaluated. Pentobarbital, hexobarbital, mepivacaine, trimipramine and clonazepam were selected as test drugs to represent various classes of drugs. The columns were regenerated

  5. Response of Launch Pad Structures to Random Acoustic Excitation

    Directory of Open Access Journals (Sweden)

    Ravi N. Margasahayam

    1994-01-01

    Full Text Available The design of launch pad structures, particularly those having a large area-to-mass ratio, is governed by launch-induced acoustics, a relatively short transient with random pressure amplitudes having a non-Gaussian distribution. The factors influencing the acoustic excitation and resulting structural responses are numerous and cannot be predicted precisely. Two solutions (probabilistic and deterministic for the random vibration problem are presented in this article from the standpoint of their applicability to predict the response of ground structures exposed to rocket noise. Deficiencies of the probabilistic method, especially to predict response in the low-frequency range of launch transients (below 20 Hz, prompted the development of the deterministic analysis. The relationship between the two solutions is clarified for future implementation in a finite element method (FEM code.

  6. 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

  7. Nano copper ferrite: A reusable catalyst for the synthesis of , -unsaturated ketones

    Indian Academy of Sciences (India)

    Y L N Murthy; B S Diwakar; B Govindh; K Nagalakshmi; I V Kasi Viswanath; Rajendra Singh

    2012-05-01

    Copper ferrite nano material as reusable heterogeneous initiator in the synthesis of , -unsaturated ketones and allylation to acid chlorides are presented. The reaction of allylichalides with various acid chlorides is achieved in the presence of copper ferrite nano powders at room temperature in tetrahydrofuran (THF). The present method is first of its kind in the synthesis of title compounds without any additive/co-catalyst. The nano catalyst is easily recovered and its reusability is recorded.

  8. MLP based Reusability Assessment Automation Model for Java based Software Systems

    Directory of Open Access Journals (Sweden)

    Surbhi Maggo

    2014-08-01

    Full Text Available Reuse refers to a common principle of using existing resources repeatedly, that is pervasively applicable everywhere. In software engineering reuse refers to the development of software systems using already available artifacts or assets partially or completely, with or without modifications. Software reuse not only promises significant improvements in productivity and quality but also provides for the development of more reliable, cost effective, dependable and less buggy (considering that prior use and testing have removed errors software with reduced time and effort. In this paper we present an efficient and reliable automation model for reusability evaluation of procedure based object oriented software for predicting the reusability levels of the components as low, medium or high. The presented model follows a reusability metric framework that targets the requisite reusability attributes including maintainability (using the Maintainability Index for functional analysis of the components. Further Multilayer perceptron (using back propagation based neural network is applied for the establishment of significant relationships among these attributes for reusability prediction. The proposed approach provides support for reusability evaluation at functional level rather than at structural level. The automation support for this approach is provided in the form of a tool named JRA2M2 (Java based Reusability Assessment Automation Model using Multilayer Perceptron (MLP, implemented in Java. The performance of JRA2M2 is recorded using parameters like accuracy, classification error, precision and recall. The results generated using JRA2M2 indicate that the proposed automation tool can be effectively used as a reliable and efficient solution for automated evaluation of reusability.

  9. Constructing Relationship Between Software Metrics and Code Reusability in Object Oriented Design

    OpenAIRE

    Manoj H.M; Dr. Nandakumar A.N

    2016-01-01

    The role of the design pattern in the form of software metric and internal code architecture for object-oriented design plays a critical role in software engineering regarding production cost efficiency. This paper discusses code reusability that is a frequently exercised cost saving methodology in IT production. After reviewing existing literature towards a study on software metrics, we found that very few studies are witnessed to incline towards code reusability. Hence, we developed a simpl...

  10. Terminological Importation for Adapting Reusable Knowledge Representation Components in the KSM Environment

    OpenAIRE

    Sierra, José Luis; Molina, Martin

    1998-01-01

    This paper describes the adaptation approach of reusable knowledge representation components used in the KSM environment for the formulation and operationalisation of structured knowledge models. Reusable knowledge representation components in KSM are called primitives of representation. A primitive of representation provides: (1) a knowledge representation formalism (2) a set of tasks that use this knowledge together with several problem-solving methods to carry out these tasks (3) a knowled...

  11. How to encourage educators to create and share reusable eLearning materials

    OpenAIRE

    2004-01-01

    A reusable learning object (RLO) is a web-based multimedia digital resource based on a single learning objective, comprising a stand-alone collection of presentation, activity, assessment and links (Leeder et al, 2002, 2003), the advantage of which allow instructional designers to build small instructional components that can be re-used a number of times in different learning context (Wiley 2001). Reusable e-learning materials (REM) are known as the e-learning resources generated in the form ...

  12. The Effect of Software Reusability on Information Theory Based Software Metrics

    Science.gov (United States)

    1990-01-01

    disagree on how abstract the code needs to be before it may be reused. Kernighan [KERNI84] presents reuse at the program level utilizing the UNIX pipe... Kernighan , Brian W., "The UNIX System and Software Reusability," IEEE Transactions on Software Engineering, Vol. SE-10, No. 5, September 1984, pp. 513-518...KERNI84] Kernighan , Brian W., "The UNIX System and Software Reusability," IEEE Transactions on Software Engineering, Vol. SE-10, No. 5, September 1984, pp

  13. RAGE Architecture for Reusable Serious Gaming Technology Components

    Directory of Open Access Journals (Sweden)

    Wim van der Vegt

    2016-01-01

    Full Text Available For seizing the potential of serious games, the RAGE project—funded by the Horizon-2020 Programme of the European Commission—will make available an interoperable set of advanced technology components (software assets that support game studios at serious game development. This paper describes the overall software architecture and design conditions that are needed for the easy integration and reuse of such software assets in existing game platforms. Based on the component-based software engineering paradigm the RAGE architecture takes into account the portability of assets to different operating systems, different programming languages, and different game engines. It avoids dependencies on external software frameworks and minimises code that may hinder integration with game engine code. Furthermore it relies on a limited set of standard software patterns and well-established coding practices. The RAGE architecture has been successfully validated by implementing and testing basic software assets in four major programming languages (C#, C++, Java, and TypeScript/JavaScript, resp.. Demonstrator implementation of asset integration with an existing game engine was created and validated. The presented RAGE architecture paves the way for large scale development and application of cross-engine reusable software assets for enhancing the quality and diversity of serious gaming.

  14. Reusable Social Networking Capabilities for an Earth Science Collaboratory

    Science.gov (United States)

    Lynnes, C.; Da Silva, D.; Leptoukh, G. G.; Ramachandran, R.

    2011-12-01

    A vast untapped resource of data, tools, information and knowledge lies within the Earth science community. This is due to the fact that it is difficult to share the full spectrum of these entities, particularly their full context. As a result, most knowledge exchange is through person-to-person contact at meetings, email and journal articles, each of which can support only a limited level of detail. We propose the creation of an Earth Science Collaboratory (ESC): a framework that would enable sharing of data, tools, workflows, results and the contextual knowledge about these information entities. The Drupal platform is well positioned to provide the key social networking capabilities to the ESC. As a proof of concept of a rich collaboration mechanism, we have developed a Drupal-based mechanism for graphically annotating and commenting on results images from analysis workflows in the online Giovanni analysis system for remote sensing data. The annotations can be tagged and shared with others in the community. These capabilities are further supplemented by a Research Notebook capability reused from another online analysis system named Talkoot. The goal is a reusable set of modules that can integrate with variety of other applications either within Drupal web frameworks or at a machine level.

  15. Reusable, adhesiveless and arrayed in-plane microfluidic interconnects

    Science.gov (United States)

    Lo, R.; Meng, E.

    2011-05-01

    A reusable, arrayed interconnect capable of providing multiple simultaneous connections to and from a microfluidic device in an in-plane manner without the use of adhesives is presented. This method uses a 'pin-and-socket' design in which an SU-8 anchor houses multiple polydimethysiloxane septa (the socket) that each receive a syringe needle (the pin). A needle array containing multiple commercially available 33G (203 µm outer diameter) needles (up to eight) spaced either 2.54 or 1 mm (center-to-center) pierces the septa to access the microfluidic device interior. Finite element modeling and photoelastic stress experiments were used to determine the stress distribution during needle insertion; these results guided the SU-8 septa housing and septa design. The impact of needle diameter, needle tip style, insertion rate and number of needles on pre-puncture, post-puncture and removal forces was characterized. Pressurized connections to SU-8 channel systems withstood up to 62 kPa of pressurized water and maintained 25 kPa of pressurized water for over 24 h. The successful integration and functionality of the interconnect design with surface micromachined Parylene C microchannels was verified using Rhodamine B dye. Dual septa systems to access a single microchannel were demonstrated. Arrayed interconnects were compatible with integrated microfluidic systems featuring electrochemical sensors and actuators.

  16. Simple and reusable picoinjector for liquid delivery via nanofluidics approach

    KAUST Repository

    Li, Shunbo

    2014-03-25

    Precise control of sample volume is one of the most important functions in lab-on-a-chip (LOC) systems, especially for chemical and biological reactions. The common approach used for liquid delivery involves the employment of capillaries and microstructures for generating a droplet which has a volume in the nanoliter or picoliter range. Here, we report a novel approach for constructing a picoinjector which is based on well-controlled electroosmotic (EO) flow to electrokinetically drive sample solutions. This picoinjector comprises an array of interconnected nanochannels for liquid delivery. Such technique for liquid delivery has the advantages of well-controlled sample volume and reusable nanofluidic chip, and it was reported for the first time. In the study of the pumping process for this picoinjector, the EO flow rate was determined by the intensity of the fluorescent probe. The influence of ion concentration in electrolyte solutions over the EO flow rate was also investigated and discussed. The application of this EO-driven picoinjector for chemical reactions was demonstrated by the reaction between Fluo-4 and calcium chloride with the reaction cycle controlled by the applied square waves of different duty cycles. The precision of our device can reach down to picoliter per second, which is much smaller than that of most existing technologies. This new approach, thus, opens further possibilities of adopting nanofluidics for well-controlled chemical reactions with particular applications in nanoparticle synthesis, bimolecular synthesis, drug delivery, and diagnostic testing.

  17. Universal and reusable virus deactivation system for respiratory protection

    Science.gov (United States)

    Quan, Fu-Shi; Rubino, Ilaria; Lee, Su-Hwa; Koch, Brendan; Choi, Hyo-Jick

    2017-01-01

    Aerosolized pathogens are a leading cause of respiratory infection and transmission. Currently used protective measures pose potential risk of primary/secondary infection and transmission. Here, we report the development of a universal, reusable virus deactivation system by functionalization of the main fibrous filtration unit of surgical mask with sodium chloride salt. The salt coating on the fiber surface dissolves upon exposure to virus aerosols and recrystallizes during drying, destroying the pathogens. When tested with tightly sealed sides, salt-coated filters showed remarkably higher filtration efficiency than conventional mask filtration layer, and 100% survival rate was observed in mice infected with virus penetrated through salt-coated filters. Viruses captured on salt-coated filters exhibited rapid infectivity loss compared to gradual decrease on bare filters. Salt-coated filters proved highly effective in deactivating influenza viruses regardless of subtypes and following storage in harsh environmental conditions. Our results can be applied in obtaining a broad-spectrum, airborne pathogen prevention device in preparation for epidemic and pandemic of respiratory diseases.

  18. Mobile Authoring of Open Educational Resources as Reusable Learning Objects

    Directory of Open Access Journals (Sweden)

    Dr Kinshuk

    2013-06-01

    Full Text Available E-learning technologies have allowed authoring and playback of standardized reusable learning objects (RLO for several years. Effective mobile learning requires similar functionality at both design time and runtime. Mobile devices can play RLO using applications like SMILE, mobile access to a learning management system (LMS, or other systems which deploy content to mobile learners (Castillo & Ayala, 2008; Chu, Hwang, & Tseng, 2010; Hsu & Chen, 2010; Nakabayashi, 2009; Zualkernan, Nikkhah, & Al-Sabah, 2009. However, implementations which author content in a mobile context do not typically permit reuse across multiple contexts due to a lack of standardization. Standards based (IMS and SCORM authoring implementations exist for non-mobile platforms (Gonzalez-Barbone & Anido-Rifon, 2008; Griffiths, Beauvoir, Liber, & Barrett-Baxendale, 2009; Téllez, 2010; Yang, Chiu, Tsai, & Wu, 2004. However, this paradigm precludes capturing learning where and when it occurs. Consequently, RLO authored for e-learning lack learner generated content, especially with timely, relevant, and location aware examples.

  19. A microfabricated gecko-inspired controllable and reusable dry adhesive

    Science.gov (United States)

    Chary, Sathya; Tamelier, John; Turner, Kimberly

    2013-02-01

    Geckos utilize a robust reversible adhesive to repeatedly attach and detach from a variety of vertical and inverted surfaces, using structurally anisotropic micro- and nano-scale fibrillar structures. These fibers, when suitably articulated, are able to control the real area of contact and thereby generate high-to-low van der Waals forces. Key characteristics of the natural system include highly anisotropic adhesion and shear forces for controllable attachment, a high adhesion to initial preload force ratio (μ‧) of 8-16, lack of inter-fiber self-adhesion, and operation over more than 30 000 cycles without loss of adhesion performance. A highly reusable synthetic adhesive has been developed using tilted polydimethylsiloxane (PDMS) half-cylinder micron-scale fibers, retaining up to 77% of the initial value over 10 000 repeated test cycles against a flat glass puck. In comparison with other gecko-inspired adhesives tested over 10 000 cycles or more thus far, this paper reports the highest value of μ‧, along with a large shear force of ˜78 kPa, approaching the 88-226 kPa range of gecko toes. The anisotropic adhesion forces are close to theoretical estimates from the Kendall peel model, quantitatively showing how lateral shearing articulation in a manner similar to the gecko may be used to obtain adhesion anisotropy with synthetic fibers using a combination of tilt angle and anisotropic fiber geometry.

  20. Note: reliable and reusable ultrahigh vacuum optical viewports.

    Science.gov (United States)

    Arora, P; Sen Gupta, A

    2012-04-01

    We report a simple technique for the realization of ultrahigh vacuum optical viewports. The technique relies on using specially designed thin copper knife-edges and using a thin layer of Vacseal(®) on tip of the knife-edges between the optical flat and the ConFlat(®) (CF) flange. The design of the windows is such that it gives uniform pressure on the flat without breaking it. The assembled window is a complete unit, which can be mounted directly onto a CF flange of the vacuum chamber. It can be removed and reused without breaking the window seal. The design is reliable as more than a dozen such windows have survived several bake out and cooling cycles and have been leak tested up to 10(-11) Torr l/s level with a commercial Helium leak detector. The advantages of this technique are ease of assembly and leak proof sealing that survives multiple temperature cycling making the windows reliable and reusable.

  1. Nonlinear Control of a Reusable Rocket Engine for Life Extension

    Science.gov (United States)

    Lorenzo, Carl F.; Holmes, Michael S.; Ray, Asok

    1998-01-01

    This paper presents the conceptual development of a life-extending control system where the objective is to achieve high performance and structural durability of the plant. A life-extending controller is designed for a reusable rocket engine via damage mitigation in both the fuel (H2) and oxidizer (O2) turbines while achieving high performance for transient responses of the combustion chamber pressure and the O2/H2 mixture ratio. The design procedure makes use of a combination of linear and nonlinear controller synthesis techniques and also allows adaptation of the life-extending controller module to augment a conventional performance controller of the rocket engine. The nonlinear aspect of the design is achieved using non-linear parameter optimization of a prescribed control structure. Fatigue damage in fuel and oxidizer turbine blades is primarily caused by stress cycling during start-up, shutdown, and transient operations of a rocket engine. Fatigue damage in the turbine blades is one of the most serious causes for engine failure.

  2. Orbiting Depot and Reusable Lander for Lunar Transportation

    Science.gov (United States)

    Petro, Andrew

    2009-01-01

    A document describes a conceptual transportation system that would support exploratory visits by humans to locations dispersed across the surface of the Moon and provide transport of humans and cargo to sustain one or more permanent Lunar outpost. The system architecture reflects requirements to (1) minimize the amount of vehicle hardware that must be expended while maintaining high performance margins and (2) take advantage of emerging capabilities to produce propellants on the Moon while also enabling efficient operation using propellants transported from Earth. The system would include reusable single- stage lander spacecraft and a depot in a low orbit around the Moon. Each lander would have descent, landing, and ascent capabilities. A crew-taxi version of the lander would carry a pressurized crew module; a cargo version could carry a variety of cargo containers. The depot would serve as a facility for storage and for refueling with propellants delivered from Earth or propellants produced on the Moon. The depot could receive propellants and cargo sent from Earth on a variety of spacecraft. The depot could provide power and orbit maintenance for crew vehicles from Earth and could serve as a safe haven for lunar crews pending transport back to Earth.

  3. Converting Basic D3 Charts into Reusable Style Templates.

    Science.gov (United States)

    Harper, Jonathan; Agrawala, Maneesh

    2017-02-07

    We present a technique for converting a basic D3 chart into a reusable style template. Then, given a new data source we can apply the style template to generate a chart that depicts the new data, but in the style of the template. To construct the style template we first deconstruct the input D3 chart to recover its underlying structure: the data, the marks and the mappings that describe how the marks encode the data. We then rank the perceptual effectiveness of the deconstructed mappings. To apply the resulting style template to a new data source we first obtain importance ranks for each new data field. We then adjust the template mappings to depict the source data by matching the most important data fields to the most perceptually effective mappings. We show how the style templates can be applied to source data in the form of either a data table or another D3 chart. While our implementation focuses on generating templates for basic chart types (e.g. variants of bar charts, line charts, dot plots, scatterplots, etc.), these are the most commonly used chart types today. Users can easily find such basic D3 charts on the Web, turn them into templates, and immediately see how their own data would look in the visual style (e.g. colors, shapes, fonts, etc.) of the templates. We demonstrate the effectiveness of our approach by applying a diverse set of style templates to a variety of source datasets.

  4. 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...

  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. 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...

  7. Advanced Aero-Propulsive Mid-Lift-to-Drag Ratio Entry Vehicle for Future Exploration Missions

    Science.gov (United States)

    Campbell, C. H.; Stosaric, R. R; Cerimele, C. J.; Wong, K. A.; Valle, G. D.; Garcia, J. A.; Melton, J. E.; Munk, M. M.; Blades, E.; Kuruvila, G.; hide

    2012-01-01

    NASA is currently looking well into the future toward realizing Exploration mission possibilities to destinations including the Earth-Moon Lagrange points, Near-Earth Asteroids (NEAs) and the Moon. These are stepping stones to our ultimate destination Mars. New ideas will be required to conquer the significant challenges that await us, some just conceptions and others beginning to be realized. Bringing these ideas to fruition and enabling further expansion into space will require varying degrees of change, from engineering and integration approaches used in spacecraft design and operations, to high-level architectural capabilities bounded only by the limits of our ideas. The most profound change will be realized by paradigm change, thus enabling our ultimate goals to be achieved. Inherent to achieving these goals, higher entry, descent, and landing (EDL) performance has been identified as a high priority. Increased EDL performance will be enabled by highly-capable thermal protection systems (TPS), the ability to deliver larger and heavier payloads, increased surface access, and tighter landing footprints to accommodate multiple asset, single-site staging. In addition, realizing reduced cost access to space will demand more efficient approaches and reusable launch vehicle systems. Current operational spacecraft and launch vehicles do not incorporate the technologies required for these far-reaching missions and goals, nor what is needed to achieve the desired launch vehicle cost savings. To facilitate these missions and provide for safe and more reliable capabilities, NASA and its partners will need to make ideas reality by gaining knowledge through the design, development, manufacturing, implementation and flight testing of robotic and human spacecraft. To accomplish these goals, an approach is recommended for integrated development and implementation of three paradigm-shifting capabilities into an advanced entry vehicle system with additional application to launch

  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. 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

  12. 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.

  13. United States commitment to heavy lift launch vehicles

    Science.gov (United States)

    Gabris, Edward A.

    Observers of the United States' space program will note progress toward the development of a new launch system capable of supporting the nation's future space missions. The process of defining mission requirements, developing technically and politically acceptable solutions, making policy decisions, and developing budget support in a democratic society is protracted, but eventually yields decisions that represent the public interest. The consensus developing within the United States on a new launch capability including heavy-lift is embodied in the Joint NASA/DoD National Launch System. This launch vehicle concept has emerged after more than five years of studies by NASA, the DoD and every major industrial aerospace contractor in the U.S. In July 1991, Vice President Quayle, in his capacity as Chairman of the National Space Council stated the Nation's commitment to support of the NLS. This paper reviews progress to date, and the involvement of the four major constituencies; the Executive Branch operating through the National Space Council, the Legislative Branch, the various elements of the DoD, and NASA. The evolution of launch system "requirements", along with the form, content and rationale for the various decisions that have been made will be described and discussed.

  14. Intelligent launch and range operations virtual testbed (ILRO-VTB)

    Science.gov (United States)

    Bardina, Jorge; Rajkumar, Thirumalainambi

    2003-09-01

    Intelligent Launch and Range Operations Virtual Test Bed (ILRO-VTB) is a real-time web-based command and control, communication, and intelligent simulation environment of ground-vehicle, launch and range operation activities. ILRO-VTB consists of a variety of simulation models combined with commercial and indigenous software developments (NASA Ames). It creates a hybrid software/hardware environment suitable for testing various integrated control system components of launch and range. The dynamic interactions of the integrated simulated control systems are not well understood. Insight into such systems can only be achieved through simulation/emulation. For that reason, NASA has established a VTB where we can learn the actual control and dynamics of designs for future space programs, including testing and performance evaluation. The current implementation of the VTB simulates the operations of a sub-orbital vehicle of mission, control, ground-vehicle engineering, launch and range operations. The present development of the test bed simulates the operations of Space Shuttle Vehicle (SSV) at NASA Kennedy Space Center. The test bed supports a wide variety of shuttle missions with ancillary modeling capabilities like weather forecasting, lightning tracker, toxic gas dispersion model, debris dispersion model, telemetry, trajectory modeling, ground operations, payload models and etc. To achieve the simulations, all models are linked using Common Object Request Broker Architecture (CORBA). The test bed provides opportunities for government, universities, researchers and industries to do a real time of shuttle launch in cyber space.

  15. 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).

  16. Launch and Landing Effects Ground Operations (LLEGO) Model

    Science.gov (United States)

    2008-01-01

    LLEGO is a model for understanding recurring launch and landing operations costs at Kennedy Space Center for human space flight. Launch and landing operations are often referred to as ground processing, or ground operations. Currently, this function is specific to the ground operations for the Space Shuttle Space Transportation System within the Space Shuttle Program. The Constellation system to follow the Space Shuttle consists of the crewed Orion spacecraft atop an Ares I launch vehicle and the uncrewed Ares V cargo launch vehicle. The Constellation flight and ground systems build upon many elements of the existing Shuttle flight and ground hardware, as well as upon existing organizations and processes. In turn, the LLEGO model builds upon past ground operations research, modeling, data, and experience in estimating for future programs. Rather than to simply provide estimates, the LLEGO model s main purpose is to improve expenses by relating complex relationships among functions (ground operations contractor, subcontractors, civil service technical, center management, operations, etc.) to tangible drivers. Drivers include flight system complexity and reliability, as well as operations and supply chain management processes and technology. Together these factors define the operability and potential improvements for any future system, from the most direct to the least direct expenses.

  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. NASA's Space Launch System Program Update

    Science.gov (United States)

    May, Todd; Lyles, Garry

    2015-01-01

    and hardware build and testing, scale model acoustic and base heating tests. Construction of the Interim Cryogenic Propulsion Stage (ICPS) began. Advanced development provided a look into the future of SLS. Shell buckling knockdown factor testing refined decades-old design margins that added thousands of pounds to rocket payloads. Adaptive manufacturing and structured light scanning development promised to cut the cost and time associated with manufacturing and testing. This paper will provide an overview of the progress made over the past year and provide a glimpse of 2015 milestones and beyond on the way to the first launch in 2018.

  19. 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...

  20. 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.

  1. 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

  2. Differences in alarm events between disposable and reusable electrocardiography lead wires.

    Science.gov (United States)

    Albert, Nancy M; Murray, Terri; Bena, James F; Slifcak, Ellen; Roach, Joel D; Spence, Jackie; Burkle, Alicia

    2015-01-01

    Disposable electrocardiographic lead wires (ECG-LWs) may not be as durable as reusable ones. To examine differences in alarm events between disposable and reusable ECG-LWs. Two cardiac telemetry units were randomized to reusable ECG-LWs, and 2 units alternated between disposable and reusable ECG-LWs for 4 months. A remote monitoring team, blinded to ECG-LW type, assessed frequency and type of alarm events by using total counts and rates per 100 patient days. Event rates were compared by using generalized linear mixed-effect models for differences and noninferiority between wire types. In 1611 patients and 9385.5 patient days of ECG monitoring, patient characteristics were similar between groups. Rates of alarms for no telemetry, leads fail, or leads off were lower in disposable ECG-LWs (adjusted relative risk [95% CI], 0.71 [0.53-0.96]; noninferiority P monitoring (artifact) alarms were significantly noninferior (adjusted relative risk [95% CI]: 0.88, [0.62-1.24], P = .02; superiority P = .44). No between-group differences existed in false or true crisis alarms. Disposable ECG-LWs were noninferior to reusable ECG-LWs for all false-alarm events (N [rate per 100 patient days], disposable 2029 [79.1] vs reusable 6673 [97.9]; adjusted relative risk [95% CI]: 0.81 [0.63-1.06], P = .002; superiority P = .12.) Disposable ECG-LWs with patented push-button design had superior performance in reducing alarms created by no telemetry, leads fail, or leads off and significant noninferiority in all false-alarm rates compared with reusable ECG-LWs. Fewer ECG alarms may save nurses time, decrease alarm fatigue, and improve patient safety. ©2015 American Association of Critical-Care Nurses.

  3. Impacts of Launch Vehicle Fairing Size on Human Exploration Architectures

    Science.gov (United States)

    Jefferies, Sharon; Collins, Tim; Dwyer Cianciolo, Alicia; Polsgrove, Tara

    2017-01-01

    Human missions to Mars, particularly to the Martian surface, are grand endeavors that place extensive demands on ground infrastructure, launch capabilities, and mission systems. The interplay of capabilities and limitations among these areas can have significant impacts on the costs and ability to conduct Mars missions and campaigns. From a mission and campaign perspective, decisions that affect element designs, including those based on launch vehicle and ground considerations, can create effects that ripple through all phases of the mission and have significant impact on the overall campaign. These effects result in impacts to element designs and performance, launch and surface manifesting, and mission operations. In current Evolvable Mars Campaign concepts, the NASA Space Launch System (SLS) is the primary launch vehicle for delivering crew and payloads to cis-lunar space. SLS is currently developing an 8.4m diameter cargo fairing, with a planned upgrade to a 10m diameter fairing in the future. Fairing diameter is a driving factor that impacts many aspects of system design, vehicle performance, and operational concepts. It creates a ripple effect that influences all aspects of a Mars mission, including: element designs, grounds operations, launch vehicle design, payload packaging on the lander, launch vehicle adapter design to meet structural launch requirements, control and thermal protection during entry and descent at Mars, landing stability, and surface operations. Analyses have been performed in each of these areas to assess and, where possible, quantify the impacts of fairing diameter selection on all aspects of a Mars mission. Several potential impacts of launch fairing diameter selection are identified in each of these areas, along with changes to system designs that result. Solutions for addressing these impacts generally result in increased systems mass and propellant needs, which can further exacerbate packaging and flight challenges. This paper

  4. 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...

  5. Application of statistical distribution theory to launch-on-time for space construction logistic support

    Science.gov (United States)

    Morgenthaler, George W.

    1989-01-01

    The ability to launch-on-time and to send payloads into space has progressed dramatically since the days of the earliest missile and space programs. Causes for delay during launch, i.e., unplanned 'holds', are attributable to several sources: weather, range activities, vehicle conditions, human performance, etc. Recent developments in space program, particularly the need for highly reliable logistic support of space construction and the subsequent planned operation of space stations, large unmanned space structures, lunar and Mars bases, and the necessity of providing 'guaranteed' commercial launches have placed increased emphasis on understanding and mastering every aspect of launch vehicle operations. The Center of Space Construction has acquired historical launch vehicle data and is applying these data to the analysis of space launch vehicle logistic support of space construction. This analysis will include development of a better understanding of launch-on-time capability and simulation of required support systems for vehicle assembly and launch which are necessary to support national space program construction schedules. In this paper, the author presents actual launch data on unscheduled 'hold' distributions of various launch vehicles. The data have been supplied by industrial associate companies of the Center for Space Construction. The paper seeks to determine suitable probability models which describe these historical data and that can be used for several purposes such as: inputs to broader simulations of launch vehicle logistic space construction support processes and the determination of which launch operations sources cause the majority of the unscheduled 'holds', and hence to suggest changes which might improve launch-on-time. In particular, the paper investigates the ability of a compound distribution probability model to fit actual data, versus alternative models, and recommends the most productive avenues for future statistical work.

  6. Application of statistical distribution theory to launch-on-time for space construction logistic support

    Science.gov (United States)

    Morgenthaler, George W.

    1989-01-01

    The ability to launch-on-time and to send payloads into space has progressed dramatically since the days of the earliest missile and space programs. Causes for delay during launch, i.e., unplanned 'holds', are attributable to several sources: weather, range activities, vehicle conditions, human performance, etc. Recent developments in space program, particularly the need for highly reliable logistic support of space construction and the subsequent planned operation of space stations, large unmanned space structures, lunar and Mars bases, and the necessity of providing 'guaranteed' commercial launches have placed increased emphasis on understanding and mastering every aspect of launch vehicle operations. The Center of Space Construction has acquired historical launch vehicle data and is applying these data to the analysis of space launch vehicle logistic support of space construction. This analysis will include development of a better understanding of launch-on-time capability and simulation of required support systems for vehicle assembly and launch which are necessary to support national space program construction schedules. In this paper, the author presents actual launch data on unscheduled 'hold' distributions of various launch vehicles. The data have been supplied by industrial associate companies of the Center for Space Construction. The paper seeks to determine suitable probability models which describe these historical data and that can be used for several purposes such as: inputs to broader simulations of launch vehicle logistic space construction support processes and the determination of which launch operations sources cause the majority of the unscheduled 'holds', and hence to suggest changes which might improve launch-on-time. In particular, the paper investigates the ability of a compound distribution probability model to fit actual data, versus alternative models, and recommends the most productive avenues for future statistical work.

  7. Heavy Lift Launch Capability with a New Hydrocarbon Engine (NHE)

    Science.gov (United States)

    Threet, Grady E., Jr.; Holt, James B.; Philips, Alan D.; Garcia, Jessica A.

    2011-01-01

    The Advanced Concepts Office (ACO) at NASA Marshall Space Flight Center has analyzed over 2000 Ares V and other heavy lift concepts in the last 3 years. These concepts were analyzed for Lunar Exploration Missions, heavy lift capability to Low Earth Orbit (LEO) as well as exploratory missions to other near earth objects in our solar system. With the pending retirement of the Shuttle fleet, our nation will be without a civil heavy lift launch capability, so the future development of a new heavy lift capability is imperative for the exploration and large science missions our Agency has been tasked to deliver. The majority of the heavy lift concepts analyzed by ACO during the last 3 years have been based on liquid oxygen / liquid hydrogen (LOX/LH2) core stage and solids booster stage propulsion technologies (Ares V / Shuttle Derived and their variants). These concepts were driven by the decisions made from the results of the Exploration Systems Architecture Study (ESAS), which in turn, led to the Ares V launch vehicle that has been baselined in the Constellation Program. Now that the decision has been made at the Agency level to cancel Constellation, other propulsion options such as liquid hydrocarbon fuels are back in the exploration trade space. NASA is still planning exploration missions with the eventual destination of Mars and a new heavy lift launch vehicle is still required and will serve as the centerpiece of our nation s next exploration architecture s infrastructure. With an extensive launch vehicle database already developed on LOX/LH2 based heavy lift launch vehicles, ACO initiated a study to look at using a new high thrust (> 1.0 Mlb vacuum thrust) hydrocarbon engine as the primary main stage propulsion in such a launch vehicle.

  8. Comparative life cycle assessment of disposable and reusable laryngeal mask airways.

    Science.gov (United States)

    Eckelman, Matthew; Mosher, Margo; Gonzalez, Andres; Sherman, Jodi

    2012-05-01

    Growing awareness of the negative impacts from the practice of health care on the environment and public health calls for the routine inclusion of life cycle criteria into the decision-making process of device selection. Here we present a life cycle assessment of 2 laryngeal mask airways (LMAs), a one-time-use disposable Unique™ LMA and a 40-time-use reusable Classic™ LMA. In life cycle assessment, the basis of comparison is called the "functional unit." For this report, the functional unit of the disposable and reusable LMAs was taken to be maintenance of airway patency by 40 disposable LMAs or 40 uses of 1 reusable LMA. This was a cradle-to-grave study that included inputs and outputs for the manufacture, transport, use, and waste phases of the LMAs. The environmental impacts of the 2 LMAs were estimated using SimaPro life cycle assessment software and the Building for Environmental and Economic Sustainability impact assessment method. Sensitivity and simple life cycle cost analyses were conducted to aid in interpretation of the results. The reusable LMA was found to have a more favorable environmental profile than the disposable LMA as used at Yale New Haven Hospital. The most important sources of impacts for the disposable LMA were the production of polymers, packaging, and waste management, whereas for the reusable LMA, washing and sterilization dominated for most impact categories. The differences in environmental impacts between these devices strongly favor reusable devices. These benefits must be weighed against concerns regarding transmission of infection. Health care facilities can decrease their environmental impacts by using reusable LMAs, to a lesser extent by selecting disposable LMA models that are not made of certain plastics, and by ordering in bulk from local distributors. Certain practices would further reduce the environmental impacts of reusable LMAs, such as increasing the number of devices autoclaved in a single cycle to 10 (-25% GHG

  9. A Evaluation of Software Re-Usability Using Software Metrics through Fuzzy Logic

    Directory of Open Access Journals (Sweden)

    Manoj Kumar Singh

    2014-06-01

    Full Text Available flexibility and quality through reusability, replace-ability, efficient reusability and scalability are some additional benefits of Component based software development .Component Based Software Engineering (CBSE is a paradigm that aims at constructing and designing systems using a pre-defined set of software components explicitly created for reuse. According to Clements, CBSE embodies the “the „buy, don‟t build‟ philosophy”. The idea of reusing software components has been present in software engineering for several decades. Although the software industry developed massively in recent decades, component reuse is still facing numerous challenges and lacking adoption by practitioners. One of the impediments preventing efficient and effective reuse is the difficulty to determine which artifacts are best suited to solve a particular problem in a given context and how easy it will be to reuse them there. So far, no clear framework is describing the reusability of software and structuring appropriate metrics that can be found in literature. Nevertheless, a good understanding of reusability as well as adequate and easy to use metrics for quantification of reusability are necessary to simplify and accelerate the adoption of component reuse in software development. Keywords—

  10. A Machine Learning based Efficient Software Reusability Prediction Model for Java Based Object Oriented Software

    Directory of Open Access Journals (Sweden)

    Surbhi Maggo

    2014-01-01

    Full Text Available Software reuse refers to the development of new software systems with the likelihood of completely or partially using existing components or resources with or without modification. Reusability is the measure of the ease with which previously acquired concepts and objects can be used in new contexts. It is a promising strategy for improvements in software quality, productivity and maintainability as it provides for cost effective, reliable (with the consideration that prior testing and use has eliminated bugs and accelerated (reduced time to market development of the software products. In this paper we present an efficient automation model for the identification and evaluation of reusable software components to measure the reusability levels (high, medium or low of procedure oriented Java based (object oriented software systems. The presented model uses a metric framework for the functional analysis of the Object oriented software components that target essential attributes of reusability analysis also taking into consideration Maintainability Index to account for partial reuse. Further machine learning algorithm LMNN is explored to establish relationships between the functional attributes. The model works at functional level rather than at structural level. The system is implemented as a tool in Java and the performance of the automation tool developed is recorded using criteria like precision, recall, accuracy and error rate. The results gathered indicate that the model can be effectively used as an efficient, accurate, fast and economic model for the identification of procedure based reusable components from the existing inventory of software resources.

  11. Real-time diagnostics for a reusable rocket engine

    Science.gov (United States)

    Guo, T. H.; Merrill, W.; Duyar, A.

    1992-01-01

    A hierarchical, decentralized diagnostic system is proposed for the Real-Time Diagnostic System component of the Intelligent Control System (ICS) for reusable rocket engines. The proposed diagnostic system has three layers of information processing: condition monitoring, fault mode detection, and expert system diagnostics. The condition monitoring layer is the first level of signal processing. Here, important features of the sensor data are extracted. These processed data are then used by the higher level fault mode detection layer to do preliminary diagnosis on potential faults at the component level. Because of the closely coupled nature of the rocket engine propulsion system components, it is expected that a given engine condition may trigger more than one fault mode detector. Expert knowledge is needed to resolve the conflicting reports from the various failure mode detectors. This is the function of the diagnostic expert layer. Here, the heuristic nature of this decision process makes it desirable to use an expert system approach. Implementation of the real-time diagnostic system described above requires a wide spectrum of information processing capability. Generally, in the condition monitoring layer, fast data processing is often needed for feature extraction and signal conditioning. This is usually followed by some detection logic to determine the selected faults on the component level. Three different techniques are used to attack different fault detection problems in the NASA LeRC ICS testbed simulation. The first technique employed is the neural network application for real-time sensor validation which includes failure detection, isolation, and accommodation. The second approach demonstrated is the model-based fault diagnosis system using on-line parameter identification. Besides these model based diagnostic schemes, there are still many failure modes which need to be diagnosed by the heuristic expert knowledge. The heuristic expert knowledge is

  12. Reusable, Extensible High-Level Data-Distribution Concept

    Science.gov (United States)

    James, Mark; Zima, Hans; Diaconescua, Roxana

    2007-01-01

    A framework for high-level specification of data distributions in data-parallel application programs has been conceived. [As used here, distributions signifies means to express locality (more specifically, locations of specified pieces of data) in a computing system composed of many processor and memory components connected by a network.] Inasmuch as distributions exert a great effect on the performances of application programs, it is important that a distribution strategy be flexible, so that distributions can be adapted to the requirements of those programs. At the same time, for the sake of productivity in programming and execution, it is desirable that users be shielded from such error-prone, tedious details as those of communication and synchronization. As desired, the present framework enables a user to refine a distribution type and adjust it to optimize the performance of an application program and conceals, from the user, the low-level details of communication and synchronization. The framework provides for a reusable, extensible, data-distribution design, denoted the design pattern, that is independent of a concrete implementation. The design pattern abstracts over coding patterns that have been found to be commonly encountered in both manually and automatically generated distributed parallel programs. The following description of the present framework is necessarily oversimplified to fit within the space available for this article. Distributions are among the elements of a conceptual data-distribution machinery, some of the other elements being denoted domains, index sets, and data collections (see figure). Associated with each domain is one index set and one distribution. A distribution class interface (where "class" is used in the object-oriented-programming sense) includes operations that enable specification of the mapping of an index to a unit of locality. Thus, "Map(Index)" specifies a unit, while "LocalLayout(Index)" specifies the local address

  13. Modular and Reusable Power System Design for the BRRISON Balloon Telescope

    Science.gov (United States)

    Truesdale, Nicholas A.

    High altitude balloons are emerging as low-cost alternatives to orbital satellites in the field of telescopic observation. The near-space environment of balloons allows optics to perform near their diffraction limit. In practice, this implies that a telescope similar to the Hubble Space Telescope could be flown for a cost of tens of millions as opposed to billions. While highly feasible, the design of a balloon telescope to rival Hubble is limited by funding. Until a prototype is proven and more support for balloon science is gained, projects remain limited in both hardware costs and man hours. Thus, to effectively create and support balloon payloads, engineering designs must be efficient, modular, and if possible reusable. This thesis focuses specifically on a modular power system design for the BRRISON comet-observing balloon telescope. Time- and cost-saving techniques are developed that can be used for future missions. A modular design process is achieved through the development of individual circuit elements that span a wide range of capabilities. Circuits for power conversion, switching and sensing are designed to be combined in any configuration. These include DC-DC regulators, MOSFET drivers for switching, isolated switches, current sensors and voltage sensing ADCs. Emphasis is also given to commercially available hardware. Pre-fabricated DC-DC converters and an Arduino microcontroller simplify the design process and offer proven, cost-effective performance. The design of the BRRISON power system is developed from these low-level circuits elements. A board for main power distribution supports the majority of flight electronics, and is extensible to additional hardware in future applications. An ATX computer power supply is developed, allowing the use of a commercial ATX motherboard as the flight computer. The addition of new capabilities is explored in the form of a heater control board. Finally, the power system as a whole is described, and its overall

  14. 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...

  15. 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.

  16. 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.

  17. Wireless Data Acquisition System for Launch Vehicles

    Directory of Open Access Journals (Sweden)

    Sabooj Ray

    2013-03-01

    Full Text Available Present launch vehicle integration architecture for avionics uses wired link to transfer data between various sub-systems. Depending on system criticality and complexity, MIL1553 and RS485 are the common protocols that are adopted. These buses have their inherent complexity and failure issues due to harness defects or under adverse flight environments. To mitigate this problem, a prototype wireless, data acquisition system for telemetry applications has been developed and demonstrated. The wireless system simplifies the integration, while reducing weight and costs. Commercial applications of wireless systems are widespread. Few systems have recently been developed for complex and critical environments. Efforts have been underway to make such architectures operational in promising application scenarios. This paper discusses the system concept for adapting a wireless system to the existing bus topology. The protocol involved and the internal implementation of the different modules are described. The test results are presented; some of the issues faced are discussed and the; future course of action is identified.Defence Science Journal, 2013, 63(2, pp.186-191, DOI:http://dx.doi.org/10.14429/dsj.63.4262

  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. Dust-Tolerant Reusable Connection Mechanisms for Lunar Environments Project

    Data.gov (United States)

    National Aeronautics and Space Administration — Dust, especially lunar dust, has been identified as a significant and present challenge in future exploration missions. In addition to posing contamination and...

  20. Dust-Tolerant, Reusable Connection Mechanism for Lunar Environments Project

    Data.gov (United States)

    National Aeronautics and Space Administration — Lunar dust has been identified as a significant and present challenge in future exploration missions. Significant development is called for in the area of devices...

  1. 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...

  2. Rapid Contingency Simulation Modeling of the NASA Crew Launch Vehicle

    Science.gov (United States)

    Betts, Kevin M.; Rutherford, R. Chad; McDuffie, James; Johnson, Matthew D.

    2007-01-01

    The NASA Crew Launch Vehicle is a two-stage orbital launcher designed to meet NASA's current as well as future needs for human space flight. In order to free the designers to explore more possibilities during the design phase, a need exists for the ability to quickly perform simulation on both the baseline vehicle as well as the vehicle after proposed changes due to mission planning, vehicle configuration and avionics changes, proposed new guidance and control algorithms, and any other contingencies the designers may wish to consider. Further, after the vehicle is designed and built, the need will remain for such analysis in the event of future mission planning. An easily reconfigurable, modular, nonlinear six-degree-of-freedom simulation matching NASA Marshall's in-house high-fidelity simulator is created with the ability to quickly perform simulation and analysis of the Crew Launch Vehicle throughout the entire launch profile. Simulation results are presented and discussed, and an example comparison fly-off between two candidate controllers is presented.

  3. 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

  4. 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.

  5. 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,

  6. 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.

  7. An Evolvable Approach to Launch Vehicles for Exploration

    Science.gov (United States)

    Cheuvront, David L.; Nguyen, Tri X.

    2005-01-01

    This paper presents ideas that may be used individually or in combination to mitigate high costs for separate developments of new crew and heavy-lift cargo launch vehicles, while providing the foundation for a highly reliable and evolvable approach to exploration. Consideration is given to reclassification of cargo for launch purposes into high value versus low value categories, rather than the presently-defined crew versus cargo categories. Objectives for the reclassification are to reduce the gap between payload mass requirements for crew and cargo payloads to better allow closure on a single moderately-sized common core vehicle to reduce development cost, achieve an economical balance between launch frequency and payload mass, and to improve total mission reliability and safety, as compared a light-weight crew vehicle and heavy cargo lift approach. Concepts to reduce design and flight qualification costs for a common core vehicle with derivatives are presented. Appropriate types and mass of cargo for each class of vehicle are identified. Utilization of existing infrastructure and flight hardware is considered to reduce costs and build on proven capabilities. The approach enables low-risk incorporation of international and commercial launch of relatively low-cost, easily replaceable assets as a means to evolve toward longer-duration and more distant missions. Benefits are identified for ground idrastructure, personnel, training, logistics, spares, and system evolution. Technology needs are compared with needs for other aspects of exploration. Technology development phasing, demonstration, and reliability growth opportunities are considered. Flexibility to adapt to future technologies such as advanced in-space propulsion is contrasted with an approach of sizing the cargo launch vehicle based on today's in-space propellants.

  8. Design for Safety - The Ares Launch Vehicles Paradigm Change

    Science.gov (United States)

    Safie, Fayssal M.; Maggio, Gaspare

    2010-01-01

    The lessons learned from the S&MA early involvement in the Ares I launch vehicle design phases proved that performing an in-line function jointly with engineering is critical for S&MA to have an effective role in supporting the system, element, and component design. These lessons learned were used to effectively support the Ares V conceptual design phase and planning for post conceptual design phases. The Top level Conceptual LOM assessment for Ares V performed by the S&MA community jointly with the engineering Advanced Concept Office (ACO) was influential in the final selection of the Ares V system configuration. Post conceptual phase, extensive reliability effort should be planned to support future Heavy Lift Launch Vehicles (HLLV) design. In-depth reliability analysis involving the design, manufacturing, and system engineering communities is critical to understand design and process uncertainties and system integrated failures.

  9. 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...

  10. 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...

  11. 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...

  12. 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...

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

    Science.gov (United States)

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

    2012-12-01

    an email-based review of expert end-users and earth science researchers to eliciting how pre-launch activities and research is being conducted in thematic group's organizations. Our focus through the SMAP Applications Program will be to (1) improve the missions understanding of the SMAP user community requirements, (2) document and communicate the perceived challenges and advantages to the mission scientists, and (3) facilitate the movement of science into policy and decision making arenas. We will analyze the data of this review to understand the perceived benefits to pre-launch efforts, user engagement and define areas were the connection between science development and user engagement can continue to improve and further benefit future mission pre launch efforts. The research will facilitate collaborative opportunities between agencies, broadening the fields of science where soil moisture observation data can be applied.

  14. Aerodynamic Control-Augmentation Devices For Saturn-Class Launch Vehicles With Aft Centers Of Gravity

    Science.gov (United States)

    Barret, Chris

    1995-01-01

    Report describes study of aerodynamic flight-control-augmentation devices proposed for use in increasing payload capabilities of future launch vehicles by allowing more aft centers of gravity. Proposed all-movable devices not only provide increased control authority during ascent trajectory, but also reduce engine gimballing requirements and enhance crew safety. Report proposes various aerodynamic control surfaces mounted fore and aft on Saturn-class launch vehicle.

  15. The Space Shuttle Decision: NASA's Search for a Reusable Space Vehicle

    Science.gov (United States)

    Heppenheimer, T. A.

    1999-01-01

    This significant new study of the decision to build the Space Shuttle explains the Shuttle's origins and early development. In addition to internal NASA discussions, this work details the debates in the late 1960s and early 1970s among policymakers in Congress, the Air Force, and the Office of Management and Budget over the roles and technical designs of the Shuttle. Examining the interplay of these organizations with sometimes conflicting goals, the author not only explains how the world's premier space launch vehicle came into being, but also how politics can interact with science, technology, national security, and economics in national government. The weighty policy decision to build the Shuttle represents the first component of the broader story: future NASA volumes will cover the Shuttle's development and operational histories.

  16. The Use of Reusable Learning Objects to Enhance the Delivery of Veterinary Education: A Literature Review

    Science.gov (United States)

    Chapman-Waterhouse, Emily; Silva-Fletcher, Ayona; Whittlestone, Kim

    2017-01-01

    The increased demand from learners in higher education to access resources flexibly has resulted in considerable development in the use of Reusable Learning Objects (RLO) via a blended learning format across the sector. This critical review sets out to identify what is currently known about RLO and how those concepts can be applied to…

  17. Research on the Development Approach for Reusable Model in Parallel Discrete Event Simulation

    Directory of Open Access Journals (Sweden)

    Jianbo Li

    2015-01-01

    Full Text Available Model reuse is an essential means to meet the demand of model development in complex simulation. An effective approach to realize the model reusability is to establish standard model specification including interface specification and representation specification. By standardizing model’s external interfaces, Reusable Component Model Framework (RCMF achieves the model reusability acting as an interface specification. However, the RCMF model is presently developed just through manual programing. Besides implementing model’s business logic, modeler should also ensure the model strictly following the reusable framework, which is very distracting. And there lacks model description information for instructing model reuse or integration. To address these issues, we first explored an XML-based model description file which completed RCMF as the model representation and then proposed a RCMF model development tool—SuKit. Model description file describes a RCMF model and can be used for regenerating a model and instructing model integration. SuKit can generate a skeleton RCMF model together with a model-customized description file with the configured information. Modeler then just needs to concentrate on the model processing logic. The case study indicates that SuKit has good capability of developing RCMF models and the well-formed description file can be used for model reuse and integration.

  18. Silica Sulfuric Acid: An Eco-Friendly and Reusable Catalyst for Synthesis of Benzimidazole Derivatives

    OpenAIRE

    Bahareh Sadeghi; Mahboobeh Ghasemi Nejad

    2013-01-01

    Silica sulfuric acid (SiO2-OSO3H) as an eco-friendly, readily available, and reusable catalyst is applied to benzimidazole derivatives synthesis under reflux in ethanol. The procedure is very simple and the products are isolated with an easy workup in good-to-excellent yields.

  19. Silica Sulfuric Acid: An Eco-Friendly and Reusable Catalyst for Synthesis of Benzimidazole Derivatives

    Directory of Open Access Journals (Sweden)

    Bahareh Sadeghi

    2013-01-01

    Full Text Available Silica sulfuric acid (SiO2-OSO3H as an eco-friendly, readily available, and reusable catalyst is applied to benzimidazole derivatives synthesis under reflux in ethanol. The procedure is very simple and the products are isolated with an easy workup in good-to-excellent yields.

  20. Experiences Gained Using a Set of SCORM Compliant Reusable Learning Objects for Teaching Programming

    Science.gov (United States)

    Costelloe, Eileen; Sherry, Elizabeth; Magee, Patricia

    2009-01-01

    A collaboration between three higher education institutions in Ireland and two European partners has resulted in the design and development of reusable learning objects for undergraduate programming students that would assist in their learning. This international project conducted extensive research of over 600 students' examination scripts in…

  1. Facility arrangements and the environmental performance of disposable and reusable cups

    NARCIS (Netherlands)

    Potting, José; Harst-Wintraecken, van der Eugenie

    2015-01-01

    Purpose: This paper integrates two complementary life cycle assessment (LCA) studies with the aim to advice facility managers on the sustainable use of cups, either disposable or reusable. Study 1 compares three disposable cups, i.e., made from fossil-based polystyrene (PS), biobased and composta

  2. REUSABILITY OF BOND ELUT CERTIFY COLUMNS FOR THE EXTRACTION OF DRUGS FROM PLASMA

    NARCIS (Netherlands)

    CHEN, XH; FRANKE, JP; WIJSBEEK, J; DEZEEUW, RA

    1993-01-01

    The reusability of Bond Elut Certify columns for the extraction of toxicologically relevant drugs from plasma has been evaluated. Pentobarbital, hexobarbital, mepivacaine, trimipramine and clonazepam were selected as test drugs to represent various classes of drugs. The columns were regenerated imme

  3. Orion Launch Abort System Jettison Motor Performance During Exploration Flight Test 1

    Science.gov (United States)

    McCauley, Rachel J.; Davidson, John B.; Winski, Richard G.

    2015-01-01

    This paper presents an overview of the flight test objectives and performance of the Orion Launch Abort System during Exploration Flight Test-1. Exploration Flight Test-1, the first flight test of the Orion spacecraft, was managed and led by the Orion prime contractor, Lockheed Martin, and launched atop a United Launch Alliance Delta IV Heavy rocket. This flight test was a two-orbit, high-apogee, high-energy entry, low-inclination test mission used to validate and test systems critical to crew safety. This test included the first flight test of the Launch Abort System performing Orion nominal flight mission critical objectives. Although the Orion Program has tested a number of the critical systems of the Orion spacecraft on the ground, the launch environment cannot be replicated completely on Earth. Data from this flight will be used to verify the function of the jettison motor to separate the Launch Abort System from the crew module so it can continue on with the mission. Selected Launch Abort System flight test data is presented and discussed in the paper. Through flight test data, Launch Abort System performance trends have been derived that will prove valuable to future flights as well as the manned space program.

  4. European spatial planning: past, present, future

    NARCIS (Netherlands)

    Faludi, A.K.F.

    2009-01-01

    Three stages have been identified in the development of the EU: the launch era; the doldrums era and the renaissance/boom era. Presently though, the EU is in a crisis. These stages serve as a framework for discussing the past, present and future for European spatial planning. Thus, during the launch

  5. 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.

  6. 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.

  7. 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.

  8. An air launched, highly responsive military transatmospheric vehicle (TAV), based on existing aerospace systems

    Science.gov (United States)

    Hampsten, Kenneth R.

    1996-03-01

    A novel vehicle design is presented that minimizes Research Development Test and Evaluation (RDT&E) cost. The proposed TAV can satisfy a broad range of military mission applications for the 21st century. TAV deployment is provided by a Rockwell B-1B bomber. Pre-launch orientation of the vehicle is centerline, underneath the B-1B forward weapon bays. Launch occurs at 30,000 ft, Mach 0.90, and at a flight path angle of 15-20 degrees. The TAV is a Two-Stage-To-Orbit (TSTO) vehicle utilizing Liquid Oxygen (LOX) and RP-1 (kerosene) propellants. The reusable upper stage, or TAV, incorporates a 130 cubic foot payload bay for mission specific equipment. The booster can either be expended, or potentially recovered for reuse. TAV reentry relies on a biconic aeroshell for the hypersonic flight phase and a parafoil for the subsonic, terminal recovery phase. Nominal mission performance is between 1,150-1,800 lbs of payload into a 100 nmi circular orbit.

  9. Space Launch System Upper Stage Technology Assessment

    Science.gov (United States)

    Holladay, Jon; Hampton, Bryan; Monk, Timothy

    2014-01-01

    The Space Launch System (SLS) is envisioned as a heavy-lift vehicle that will provide the foundation for future beyond low-Earth orbit (LEO) exploration missions. Previous studies have been performed to determine the optimal configuration for the SLS and the applicability of commercial off-the-shelf in-space stages for Earth departure. Currently NASA is analyzing the concept of a Dual Use Upper Stage (DUUS) that will provide LEO insertion and Earth departure burns. This paper will explore candidate in-space stages based on the DUUS design for a wide range of beyond LEO missions. Mission payloads will range from small robotic systems up to human systems with deep space habitats and landers. Mission destinations will include cislunar space, Mars, Jupiter, and Saturn. Given these wide-ranging mission objectives, a vehicle-sizing tool has been developed to determine the size of an Earth departure stage based on the mission objectives. The tool calculates masses for all the major subsystems of the vehicle including propellant loads, avionics, power, engines, main propulsion system components, tanks, pressurization system and gases, primary structural elements, and secondary structural elements. The tool uses an iterative sizing algorithm to determine the resulting mass of the stage. Any input into one of the subsystem sizing routines or the mission parameters can be treated as a parametric sweep or as a distribution for use in Monte Carlo analysis. Taking these factors together allows for multi-variable, coupled analysis runs. To increase confidence in the tool, the results have been verified against two point-of-departure designs of the DUUS. The tool has also been verified against Apollo moon mission elements and other manned space systems. This paper will focus on trading key propulsion technologies including chemical, Nuclear Thermal Propulsion (NTP), and Solar Electric Propulsion (SEP). All of the key performance inputs and relationships will be presented and

  10. Reusable science tools for analog exploration missions: xGDS Web Tools, VERVE, and Gigapan Voyage

    Science.gov (United States)

    Lee, Susan Y.; Lees, David; Cohen, Tamar; Allan, Mark; Deans, Matthew; Morse, Theodore; Park, Eric; Smith, Trey

    2013-10-01

    The Exploration Ground Data Systems (xGDS) project led by the Intelligent Robotics Group (IRG) at NASA Ames Research Center creates software tools to support multiple NASA-led planetary analog field experiments. The two primary tools that fall under the xGDS umbrella are the xGDS Web Tools (xGDS-WT) and Visual Environment for Remote Virtual Exploration (VERVE). IRG has also developed a hardware and software system that is closely integrated with our xGDS tools and is used in multiple field experiments called Gigapan Voyage. xGDS-WT, VERVE, and Gigapan Voyage are examples of IRG projects that improve the ratio of science return versus development effort by creating generic and reusable tools that leverage existing technologies in both hardware and software. xGDS Web Tools provides software for gathering and organizing mission data for science and engineering operations, including tools for planning traverses, monitoring autonomous or piloted vehicles, visualization, documentation, analysis, and search. VERVE provides high performance three dimensional (3D) user interfaces used by scientists, robot operators, and mission planners to visualize robot data in real time. Gigapan Voyage is a gigapixel image capturing and processing tool that improves situational awareness and scientific exploration in human and robotic analog missions. All of these technologies emphasize software reuse and leverage open source and/or commercial-off-the-shelf tools to greatly improve the utility and reduce the development and operational cost of future similar technologies. Over the past several years these technologies have been used in many NASA-led robotic field campaigns including the Desert Research and Technology Studies (DRATS), the Pavilion Lake Research Project (PLRP), the K10 Robotic Follow-Up tests, and most recently we have become involved in the NASA Extreme Environment Mission Operations (NEEMO) field experiments. A major objective of these joint robot and crew experiments is

  11. NASA Space Technology Draft Roadmap Area 13: Ground and Launch Systems Processing

    Science.gov (United States)

    Clements, Greg

    2011-01-01

    This slide presentation reviews the technology development roadmap for the area of ground and launch systems processing. The scope of this technology area includes: (1) Assembly, integration, and processing of the launch vehicle, spacecraft, and payload hardware (2) Supply chain management (3) Transportation of hardware to the launch site (4) Transportation to and operations at the launch pad (5) Launch processing infrastructure and its ability to support future operations (6) Range, personnel, and facility safety capabilities (7) Launch and landing weather (8) Environmental impact mitigations for ground and launch operations (9) Launch control center operations and infrastructure (10) Mission integration and planning (11) Mission training for both ground and flight crew personnel (12) Mission control center operations and infrastructure (13) Telemetry and command processing and archiving (14) Recovery operations for flight crews, flight hardware, and returned samples. This technology roadmap also identifies ground, launch and mission technologies that will: (1) Dramatically transform future space operations, with significant improvement in life-cycle costs (2) Improve the quality of life on earth, while exploring in co-existence with the environment (3) Increase reliability and mission availability using low/zero maintenance materials and systems, comprehensive capabilities to ascertain and forecast system health/configuration, data integration, and the use of advanced/expert software systems (4) Enhance methods to assess safety and mission risk posture, which would allow for timely and better decision making. Several key technologies are identified, with a couple of slides devoted to one of these technologies (i.e., corrosion detection and prevention). Development of these technologies can enhance life on earth and have a major impact on how we can access space, eventually making routine commercial space access and improve building and manufacturing, and weather

  12. STS-112 Commander Ashby in white room before launch

    Science.gov (United States)

    2002-01-01

    KENNEDY SPACE CENTER, FLA. - -- In the White Room at Launch Pad 39B, STS-112 Commander Jeffrey Ashby receives assistance with his spacesuit before boarding Space Shuttle Atlantis. Liftoff is schedued for 3:46 p.m. EDT. Along with a crew of six, Atlantis will carry the S1 Integrated Truss Structure and the Crew and Equipment Translation Aid (CETA) Cart A to the International Space Station (ISS). The CETA is the first of two human-powered carts that will ride along the ISS railway, providing mobile work platforms for future spacewalking astronauts. On the 11-day mission, three spacewalks are planned to attach the S1 truss.

  13. 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...

  14. 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.

  15. 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).

  16. 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...

  17. 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...

  18. 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

  19. 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.

  20. 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.

  1. 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.

  2. 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).

  3. 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.

  4. 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.

  5. 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.

  6. Modular Growth NTR Space Transportation System for Future NASA Human Lunar, NEA and Mars Exploration Missions

    Science.gov (United States)

    Borowski, Stanley K.; McCurdy, David R.; Packard, Thomas W.

    2012-01-01

    reusable Mars architecture, Copernicus' saddle truss / drop tank assembly is replaced by an in-line tank and "star truss" assembly with paired modular drop tanks to further increase the vehicle's propellant capacity. Shorter "1-way" transit time fast-conjunction Mars missions are another possibility using this vehicle configuration but, as with reusability, increased launch mass is required. "Scaled down" versions of Copernicus (sized to a SLS lift capability of approx.70 t - 100 t) can be developed initially allowing reusable lunar cargo delivery and crewed landing missions, easy NEA missions (e.g., 2000 SG344 also in 2028) or an expendable mission to Apophis. Mission scenario descriptions, key vehicle features and operational characteristics are provided along with a brief discussion of NASA's current activities and its "pre-decisional" plans for future NTR development.

  7. 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.

  8. 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...

  9. 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.

  10. 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.

  11. 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

  12. Mars Mobile Lander Systems for 2005 and 2007 Launch Opportunities

    Science.gov (United States)

    Sabahi, D.; Graf, J. E.

    2000-01-01

    A series of Mars missions are proposed for the August 2005 launch opportunity on a medium class Evolved Expendable Launch Vehicle (EELV) with a injected mass capability of 2600 to 2750 kg. Known as the Ranger class, the primary objective of these Mars mission concepts are: (1) Deliver a mobile platform to Mars surface with large payload capability of 150 to 450 kg (depending on launch opportunity of 2005 or 2007); (2) Develop a robust, safe, and reliable workhorse entry, descent, and landing (EDL) capability for landed mass exceeding 750 kg; (3) Provide feed forward capability for the 2007 opportunity and beyond; and (4) Provide an option for a long life telecom relay orbiter. A number of future Mars mission concepts desire landers with large payload capability. Among these concepts are Mars sample return (MSR) which requires 300 to 450 kg landed payload capability to accommodate sampling, sample transfer equipment and a Mars ascent vehicle (MAV). In addition to MSR, large in situ payloads of 150 kg provide a significant step up from the Mars Pathfinder (MPF) and Mars Polar Lander (MPL) class payloads of 20 to 30 kg. This capability enables numerous and physically large science instruments as well as human exploration development payloads. The payload may consist of drills, scoops, rock corers, imagers, spectrometers, and in situ propellant production experiment, and dust and environmental monitoring.

  13. Ways to Increase Launch Velocities of 2-Stage Gas Guns

    Science.gov (United States)

    Bogdanoff, David W.; Cambier, Jean-Luc; Arnold, James O. (Technical Monitor)

    1994-01-01

    The amount of space debris is rapidly increasing and the debris is distributed over a wide variety of orbits. Satellites, manned space vehicles and space stations will have to pay increasing attention to the dangers of impacts with space debris. Various armoring techniques (i.e., double or triple layer armor) will have to tested extensively to determine the most effective armor per unit weight. Intersecting near-earth orbits can lead to impact velocities up to 15 km/sec. Conventional two-stage light gas guns can launch intact, controlled-shape projectiles with a density of 1.2 gm/cc and length- to-diameter ratios of 0.5-1.0 at velocities up to 8-9 km/sec. Higher velocities (10-11 km/sec) can be obtained' for very light projectiles. The higher launch velocities tend to be very severe on the high pressure coupling and barrel of the gun and lead to short component lifetimes. Clearly, the ability to raise the launch velocity of a gun (for reasonably massive projectile shapes) from 8-9 km/sec to 11-13 km/sec (or higher), without reduction of component lifetimes, would have significant benefits. This would allow much better simulation of the higher velocity debris impacts as well as better simulation of high speed re-entry into planetary atmospheres. Several techniques for increasing the launcher muzzle velocity above 8-9 km/sec have been studied using CFD simulations and appear to offer the potential for significant gains. The first technique is to use multiple compressions, instead of a single compression, in the pump tube of the light gas gun. In a sense, this is a kind of pre-heating of the gas in the pump tube; other types of pre-heating have yielded disappointing results in the past. The dynamics of the multiple compression pump tube is very different, however, from the earlier techniques, where the pump tube was typically heated ohmically before the gun 2 cycle was started. In this paper, we present CFD calculations that show that significant increases in muzzle

  14. 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

  15. Materials in NASA's Space Launch System: The Stuff Dreams are Made of

    Science.gov (United States)

    May, Todd A.

    2012-01-01

    Mr. Todd May, Program Manager for NASA's Space Launch System, will showcase plans and progress the nation s new super-heavy-lift launch vehicle, which is on track for a first flight to launch an Orion Multi-Purpose Crew Vehicle around the Moon in 2017. Mr. May s keynote address will share NASA's vision for future human and scientific space exploration and how SLS will advance those plans. Using new, in-development, and existing assets from the Space Shuttle and other programs, SLS will provide safe, affordable, and sustainable space launch capabilities for exploration payloads starting at 70 metric tons (t) and evolving through 130 t for entirely new deep-space missions. Mr. May will also highlight the impact of material selection, development, and manufacturing as they contribute to reducing risk and cost while simultaneously supporting the nation s exploration goals.

  16. Heat Transfer Measurement and Modeling in Rigid High-Temperature Reusable Surface Insulation Tiles

    Science.gov (United States)

    Daryabeigi, Kamran; Knutson, Jeffrey R.; Cunnington, George R.

    2011-01-01

    Heat transfer in rigid reusable surface insulations was investigated. Steady-state thermal conductivity measurements in a vacuum were used to determine the combined contribution of radiation and solid conduction components of heat transfer. Thermal conductivity measurements at higher pressures were then used to estimate the effective insulation characteristic length for gas conduction modeling. The thermal conductivity of the insulation can then be estimated at any temperature and pressure in any gaseous media. The methodology was validated by comparing estimated thermal conductivities with published data on a rigid high-temperature silica reusable surface insulation tile. The methodology was also applied to the alumina enhanced thermal barrier tiles. Thermal contact resistance for thermal conductivity measurements on rigid tiles was also investigated. A technique was developed to effectively eliminate thermal contact resistance on the rigid tile s cold-side surface for the thermal conductivity measurements.

  17. Performance of Cost Assessment on Reusable Components for Software Development using Genetic Programming

    Directory of Open Access Journals (Sweden)

    T.Tejaswini

    2015-08-01

    Full Text Available Reusability is the quality of a piece of software, which enables it to be used again, be it partial, modified or complete. A wide range of modeling techniques have been proposed and applied for software quality predictions. Complexity and size metrics have been used to predict the number of defects in software components. Estimation of cost is important, during the process of software development. There are two main types of cost estimation approaches: algorithmic methods and non-algorithmic methods. In this work, using genetic programming which is a branch of evolutionary algorithms, a new algorithmic method is presented for software development cost estimation, using the implementation of this method; new formulas were obtained for software development cost estimation in which reusability of components is given priority. After evaluation of these formulas, the mean and standard deviation of the magnitude of relative error is better than related algorithmic methods such as COCOMO formulas.

  18. Preparation Of KF-Modified Kaolinite As Green And Reusable Catalyst For Microwave Assisted Biodiesel Conversion

    Science.gov (United States)

    Fatimah, I.; Andiena, R. Z.; Yudha, S. P.

    2017-02-01

    Preparation of KF-modified kaolinite catalyst for microwave-assisted biodiesel conversion has been investigated. Kaolinite modification was conducted by solid-solid reaction between naturally occurring kaolinite mineral and KF salt followed by heating at 200oC for 2h. Prepared catalyst was characterized by using XRD, BET surface area analyzer, and SEM-EDX analysis and for catalytic activity tests, biodiesel conversion of jatropha oil was simulated. The comparison between microwave utilization and conventional method of biodiesel conversion were studied, moreover study on the catalyst reusability was performed. The results show that prepared catalyst gives the better physicochemical character of kaolinite as heterogeneous catalysts application as shown by the higher conversion and also reusability. Furthermore, the use of microwave irradiation exhibits the more time effectiveness. In general, the greener biodiesel conversion using presented methods is promising technique to be developed.

  19. Polydopamine tethered enzyme/metal-organic framework composites with high stability and reusability

    Science.gov (United States)

    Wu, Xiaoling; Yang, Cheng; Ge, Jun; Liu, Zheng

    2015-11-01

    An enzyme/metal-organic framework (MOF) composite with both highly stable and easily reusable features was prepared via tethering enzyme/MOF nanocrystals with polydopamine (PDA). The micrometer-sized PDA tethered enzyme/MOF composite can be easily repeatedly used without obvious activity loss, promising for efficient enzymatic catalysis at low cost with long-term operational stability under harsh conditions.An enzyme/metal-organic framework (MOF) composite with both highly stable and easily reusable features was prepared via tethering enzyme/MOF nanocrystals with polydopamine (PDA). The micrometer-sized PDA tethered enzyme/MOF composite can be easily repeatedly used without obvious activity loss, promising for efficient enzymatic catalysis at low cost with long-term operational stability under harsh conditions. Electronic supplementary information (ESI) available: Synthesis of enzyme-MOF nanocrystals, SEM, TEM, CLSM characterization and measurements of enzymatic performances. See DOI: 10.1039/c5nr05190h

  20. Probabilistic Fracture Mechanics and Optimum Fracture Control Analytical Procedures for a Reusable Solid Rocket Motor Case

    Science.gov (United States)

    Hanagud, S.; Uppaluri, B.

    1977-01-01

    A methodology for the reliability analysis of a reusable solid rocket motor case is discussed. The analysis is based on probabilistic fracture mechanics and probability distribution for initial flaw sizes. The developed reliability analysis is used to select the structural design variables of the solid rocket motor case on the basis of minimum expected cost and specified reliability bounds during the projected design life of the case. Effects of failure prevention plans such as nondestructive inspection and the material erosion between missions are also considered in the developed procedure for selection of design variables. The reliability-based procedure can be modified to consider other similar structures of reusable space vehicle systems with different failure prevention plans.

  1. Reusable Electronics and Adaptable Communication as Implemented in the Odin Modular Robot

    DEFF Research Database (Denmark)

    Garcia, Ricardo Franco Mendoza; Lyder, Andreas; Christensen, David Johan

    2009-01-01

    This paper describes the electronics and communication system of Odin, a novel heterogeneous modular robot made of links and joints. The electronics is divided into two printed circuit boards: a General board with reusable components and a Specific board with non-reusable components. While...... electrical signals. The implementations of actuator and power links show that splitting the electronics into General and Specific boards allows rapid development of different types of modules, and an analysis of performance indicates that the communication system is simple, fast and flexible....... As the electronic design reuses approx. 50% of components between two different types of modules, we find it convenient for heterogeneous modular robots where production costs demand a small set of parts. In addition, as the features of the communication system are desirable in modular robots, we think...

  2. Heterogeneous Baylis-Hillman using a polystyrene-bound 4-(N-benzyl-N-methylamino)pyridine as reusable catalyst.

    Science.gov (United States)

    Corma, Avelino; García, Hermenegildo; Leyva, Antonio

    2003-11-21

    An insoluble Merrifield type resin having 4-aminopyridine units is a suitable and reusable heterogeneous catalyst for the Baylis-Hillman coupling of aromatic aldehydes and alpha,beta-unsaturated ketones.

  3. 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...

  4. 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.

  5. 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.

  6. 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.

  7. 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

  8. A Machine Learning based Efficient Software Reusability Prediction Model for Java Based Object Oriented Software

    OpenAIRE

    Surbhi Maggo; Chetna Gupta

    2014-01-01

    Software reuse refers to the development of new software systems with the likelihood of completely or partially using existing components or resources with or without modification. Reusability is the measure of the ease with which previously acquired concepts and objects can be used in new contexts. It is a promising strategy for improvements in software quality, productivity and maintainability as it provides for cost effective, reliable (with the consideration that prior testing and use has...

  9. Reusable Component Technology in the Development of Agile Supply Chain Management System

    Institute of Scientific and Technical Information of China (English)

    2002-01-01

    Agile Supply Chain Management (ASCM) is one of the ke y techniques, which support dynamic enterprise alliance and realize agile manufa cturing. But the optimal run of ASCS depends on a good-constructed Agile Supply Chain Management System (ASCMS), so that the materials flow, information flow a nd funding flow in the supply chain are used with high efficiency. The requireme nts of ASCMS are constantly changeable, which requires that ASCMS has dynamical reuse, integration and open interface. Reusable compo...

  10. Data as a service a framework for providing reusable enterprise data services

    CERN Document Server

    Sarkar, Pushpak

    2015-01-01

    Data as a Service shows how organizations can leverage "data as a service" by providing real-life case studies on the various and innovative architectures and related patterns. Comprehensive approach to introducing data as a service in any organization. A re-usable and flexible SOA based architecture framework. Roadmap to introduce 'big data as a service' for potential clients. Presents a thorough description of each component in the DaaS reference architecture so readers can implement solutions.

  11. Aerodynamic heat transfer to RSI tile surfaces and gap intersections. [Reusable Surface Insulation

    Science.gov (United States)

    Dunavant, J. C.; Throckmorton, D. A.

    1974-01-01

    Review of the results of aerothermal heating tests of a simulated reusable surface insulation (RSI) tile array, performed on the sidewall of a Mach-10 hypersonic tunnel. In particular, the heating characteristics of the tile array, such as they result from heating inside the tile-expansion-space providing gaps between individual tiles, are investigated. The results include the finding that heating on the upstream face of a tile is strongly affected by the interacting longitudinal gap flow.

  12. Design of control system rapid prototyping for suborbital reusable launch vehicle%亚轨道飞行器控制系统快速原型设计

    Institute of Scientific and Technical Information of China (English)

    毛瑞; 李新国; 泮斌峰

    2014-01-01

    In order to achieve the fast, cheap, efficient and other design requirements for flight vehicle control system, the design of suborbital spacecraft control system based on rapid control prototyping technology is proposed, and the design of hardware system, software system and real-time simulation is done in this paper. The system consists of the overall control computer, two real-time numerical simulation computers, VMIC, hardware interfaces, physical devices and other components. The six degrees of freedom mathematical model of SRLV re-entry process were built. The control distribution and classical control methods for attitude control is designed, too. RtFly platform is selected to the distributed rapid prototyping simulation. Simulation results show that the control parameter adjustment convenient, real-time system is good, rapid control prototyping technology can be effectively applied to aircraft control system design. The result of Simulation shows that the control parameters are easy to adjust and optimize, and the system has good real-time performance. Rapid control prototyping technology could be effectively applied to aircraft control system design.%为了实现对飞行器控制系统的快速、廉价、高效等设计需求,提出了一种基于快速控制原型技术的亚轨道飞行器控制系统设计方案,并完成系统的软硬件设计与实时仿真。该系统由总体控制计算机、两台实时数值仿真机、VMIC、硬件接口以及物理设备等组成,建立了亚轨道飞行器再入阶段六自由度运动模型,设计控制分配并采用经典控制方法进行姿态控制,通过RtFly平台进行分布式快速原型仿真。仿真结果表明,控制参数调节方便,系统实时性良好,快速控制原型技术可以有效应用于飞行器控制系统设计。

  13. 可重复使用运载器上升段运动分析%Ascend Motion Analysis of Reusable Launch Vehicle

    Institute of Scientific and Technical Information of China (English)

    闫晓东; 唐硕

    2005-01-01

    本文简要介绍了可重复使用运载器的特点和飞行过程,并针对串联两级可重复使用运载器,在建立其动力学数学模型的基础上,计算分析了其上升段的动力学运动过程,可为RLV的上升段弹道优化设计以及RLV方案研究提供有力的支持.

  14. Poorly processed reusable surface disinfection tissue dispensers may be a source of infection.

    Science.gov (United States)

    Kampf, Günter; Degenhardt, Stina; Lackner, Sibylle; Jesse, Katrin; von Baum, Heike; Ostermeyer, Christiane

    2014-01-21

    Reusable surface disinfectant tissue dispensers are used in hospitals in many countries because they allow immediate access to pre-soaked tissues for targeted surface decontamination. On the other hand disinfectant solutions with some active ingredients may get contaminated and cause outbreaks. We determined the frequency of contaminated surface disinfectant solutions in reusable dispensers and the ability of isolates to multiply in different formulations. Reusable tissue dispensers with different surface disinfectants were randomly collected from healthcare facilities. Solutions were investigated for bacterial contamination. The efficacy of two surface disinfectants was determined in suspension tests against two isolated species directly from a contaminated solution or after 5 passages without selection pressure in triplicate. Freshly prepared use solutions were contaminated to determine survival of isolates. 66 dispensers containing disinfectant solutions with surface-active ingredients were collected in 15 healthcare facilities. 28 dispensers from nine healthcare facilities were contaminated with approximately 107 cells per mL of Achromobacter species 3 (9 hospitals), Achromobacter xylosoxidans or Serratia marcescens (1 hospital each). In none of the hospitals dispenser processing had been adequately performed. Isolates regained susceptibility to the disinfectants after five passages without selection pressure but were still able to multiply in different formulations from different manufacturers at room temperature within 7 days. Neglecting adequate processing of surface disinfectant dispensers has contributed to frequent and heavy contamination of use-solutions based on surface active ingredients. Tissue dispenser processing should be taken seriously in clinical practice.

  15. Comparison of successful intubation with two different blades of laryngoscope: single-use and reusable.

    Directory of Open Access Journals (Sweden)

    Ali Shahriari

    2007-05-01

    Full Text Available BACKGROUND: Many types of single-use blades are manufactured with different designs and materials. There have been several reports of difficulties in obtaining a view of the glottis with single-use laryngoscopes. The purpose of this prospective study was to compare the quickness and the success rate of endotracheal intubations with two different laryngoscope blades: disposable laryngoscope blades and reusable laryngoscope blades. METHODS: The study included 200 patients aged 18 to 70 who were admitted to the operating room of the Ali Ebne Abitaleb Hospital in Zahedan. The patients were randomly divided in two groups. Disposable laryngoscope blades were used for the first group and reusable laryngoscope blades were used for the second group. The endotracheal intubation duration and the failure rate of the intubation were assessed in the two groups. RESULTS: No failures and prolongations of intubations were found in the reusable laryngoscope blades group compared with 21% incidence of prolonged intubations and 14% incidence of failed intubations in the prolonged intubations group which led to change of the laryngoscope by the anesthetists (P<0.05. CONCLUSIONS: The single-use laryngoscope blades appear to be efficient devices because they do not modify the ease of endotracheal intubation in most cases. Nonetheless, for difficult intubations it is advised to maintain conventional laryngoscopes in reserve.

  16. Re-emergence of papulonodular napkin dermatitis with use of reusable diapers: report of 5 cases.

    Science.gov (United States)

    Maruani, Annabel; Lorette, Gérard; Barbarot, Sébastien; Potier, Alexandra; Bessis, Didier; Hasselmann, Caroline; Mazereeuw-Hautier, Juliette

    2013-04-01

    The use of reusable diapers, often made of cotton and bamboo material, is becoming more widespread in France--with the "eco" fashion, as they are considered more natural, ecologic and economic. We report 5 cases of papulonodular lesions in convex skin areas associated with the use of these diapers in infants. One case was typical Sevestre and Jacquet erosive dermatitis. The 4 others presented skin-coloured umbilicated papules or nodules with slight or no erythema and could be considered early-stage Sevestre and Jacquet erosive dermatitis, granuloma gluteale (1 case) or pseudo-verrucous papules. These 3 diagnoses probably belong to the same disease spectrum, proposed as "irritant napkin papulonodules". Napkin lesions occurred subsequent to 1) in all cases, use of reusable diapers, which are probably less absorbent than disposable diapers; 2) in 2 cases, insufficient food, which was responsible for lack of weight gain and delayed healing; and 3) in 1 case, diarrhea, which worsened the moisture. We alert physicians to possible papulonodular napkin dermatitis in infants wearing reusable diapers.

  17. Using Selection Pressure as an Asset to Develop Reusable, Adaptable Software Systems

    Science.gov (United States)

    Berrick, S. W.; Lynnes, C.

    2007-12-01

    The Goddard Earth Sciences Data and Information Services Center (GES DISC) at NASA has over the years developed and honed a number of reusable architectural components for supporting large-scale data centers with a large customer base. These include a processing system (S4PM) and an archive system (S4PA) based upon a workflow engine called the Simple, Scalable, Script-based Science Processor (S4P); an online data visualization and analysis system (Giovanni); and the radically simple and fast data search tool, Mirador. These subsystems are currently reused internally in a variety of combinations to implement customized data management on behalf of instrument science teams and other science investigators. Some of these subsystems (S4P and S4PM) have also been reused by other data centers for operational science processing. Our experience has been that development and utilization of robust, interoperable, and reusable software systems can actually flourish in environments defined by heterogeneous commodity hardware systems, the emphasis on value-added customer service, and continual cost reduction pressures. The repeated internal reuse that is fostered by such an environment encourages and even forces changes to the software that make it more reusable and adaptable. Allowing and even encouraging such selective pressures to software development has been a key factor in the success of S4P and S4PM, which are now available to the open source community under the NASA Open Source Agreement.

  18. Reusable nanomaterial and plant biomass composites for the removal of Methylene Blue from water.

    Science.gov (United States)

    Jain, Nidhi; Basniwal, Rupesh Kumar; Suman; Srivastava, Ashwani Kumar; Jain, Vinod Kumar

    2010-06-01

    A novel composite has been prepared from nanomaterials and powdered orange peel. The composite is adhered to a plastic strip and may be employed for the removal of synthetic dyes from aqueous solutions, for example from dyehouse effluents. Using Methylene Blue (CI Basic Blue 9) as the reference dye, the characteristics of the adsorbent have been studied. The effect of pH, type of nanomaterial (e.g. carbon nanotubes, activated carbon nanotubes, or titanium dioxide nanoparticles), contact time, and reusability have each been investigated. The results show that the adsorption capacity of suspended orange peel powder, an orange peel strip, and an activated carbon nanotube/orange peel strip were 46%, 67% and 78%, respectively. The uptake of dye was greatly affected by the pH of the solution, maximum absorption being obtained at pH 10, and none at all at pH 2. The improved performance was probably the result of the increased area available for adsorption compared with orange peel powder alone. The system was found to be reusable for up to six cycles without appreciable loss of adsorption and desorption efficiency. The nanomaterial in the composite enhanced performance, not only by increasing adsorption efficiency but also by inhibiting biodegradation of the orange peel powder, thereby increasing the life of the strips. The system offers an economical, user-friendly, efficient and reusable adsorption treatment for the removal of dyes from wastewater.

  19. Sustaining Human Presence on Mars Using ISRU and a Reusable Lander

    Science.gov (United States)

    Arney, Dale C.; Jones, Christopher A.; Klovstad, Jordan J.; Komar, D.R.; Earle, Kevin; Moses, Robert; Shyface, Hilary R.

    2015-01-01

    This paper presents an analysis of the impact of ISRU (In-Site Resource Utilization), reusability, and automation on sustaining a human presence on Mars, requiring a transition from Earth dependence to Earth independence. The study analyzes the surface and transportation architectures and compared campaigns that revealed the importance of ISRU and reusability. A reusable Mars lander, Hercules, eliminates the need to deliver a new descent and ascent stage with each cargo and crew delivery to Mars, reducing the mass delivered from Earth. As part of an evolvable transportation architecture, this investment is key to enabling continuous human presence on Mars. The extensive use of ISRU reduces the logistics supply chain from Earth in order to support population growth at Mars. Reliable and autonomous systems, in conjunction with robotics, are required to enable ISRU architectures as systems must operate and maintain themselves while the crew is not present. A comparison of Mars campaigns is presented to show the impact of adding these investments and their ability to contribute to sustaining a human presence on Mars.

  20. 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

  1. 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.

  2. 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.

  3. 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.

  4. 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.

  5. 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.

  6. Typical High-Temperature Seal Structur of Reusable and Hypersonic Vehicles%飞行器典型热密封结构

    Institute of Scientific and Technical Information of China (English)

    李凡; 王树浩; 陈江涛; 赵光辉; 于焕光

    2013-01-01

    Reusable and hypersonic vehicles pose an extraordinary challenge for seal structures. Airframes and engines require lightweight, high-temperature seal structural that can withstand the extreme environment of hypersonic flight. This paper reviews relevant seal technology for typical vehicles (e. g. Space Shuttle, X-38 and X-51) and presents several seal technologies for future hypersonic vehicles, foucs on high-temperature seal structural of the space shuttle TPS, vehicle penetrations and control surfaces.%对航天飞机、X-38和X-51等飞行器的热密封结构进行了综合评述.分析了机身TPS、机身开口部位及控制面三个安装部位的热密封结构特点,综述了其热密封组件的研究历程和使用现状.

  7. 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

  8. 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

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

    Science.gov (United States)

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

    or satellite of interest, size of objects in conjunction and foremost, the closest approach distance. For solving the close approach problem the trajectories of launch vehicle and the payload upon injection have been generated at short intervals within the total launch window so as to account for the short duration of the conjunctions. SPADEPRO analysis has been carried out for Two Line Element (TLE) set of objects with different epoch dates leading to the actual day of launch so as to determine the sensitivity of blackout period with regards to epoch of space objects TLE sets. Authors have developed SPADEPRO analysis package described above, consisting of modules which provide the respective functions of (1) ephemeris generation and reconstruction of primary object (launch vehicle or its payload upon insertion), (2) determination of close approaches with resident space objects, (3) computation of the covariance of the primary and the secondary objects to represent the knowledge uncertainty (resident space objects) and (4) computation of the collision risk given the covariance. This has been successfully applied to PSLV-C3 launch in October 2001. References: (1) Felix R Hoots, Linda L Crawford &Ronald L Roehrich, An Analytic Method to Determine Future Close Approaches Between Satellites, Celestial Mechanics, Volume- 33 (1984), pp 143-158. (2) James Woodburn, Determination of Close Approaches for Earth-Fixed Launch Trajectories, AAS 98-134. (3) Gordon D Bredvik &James E Strub, Determination of Acceptable Launch Windows for Satellite Collision Avoidance, AAS 91-373. (4) Gary Bollenbacher &James D Guptill, Launch Collision Probability, NASA/TP-1999-208852.

  10. 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

  11. Using the iBook in medical education and healthcare settings--the iBook as a reusable learning object; a report of the author's experience using iBooks Author software.

    Science.gov (United States)

    Payne, Karl Fb; Goodson, Alexander Mc; Tahim, Arpan; Wharrad, Heather J; Fan, Kathleen

    2012-12-01

    The recently launched iBooks 2 from Apple has created a new genre of 'interactive multimedia eBook'. This article aims to dscribe the benefit of the iBook in a medical education and healthcare setting. We discuss the attributes of an iBook as compared with the requirements of the conventional web-based Reusable Learning Object. The structure and user interface within an iBook is highlighted, and the iBook-creating software iBooks Author is discussed in detail. A report of personal experience developing and distributing an iBook for junior trainees in oral and maxillofacial surgery is provided, with discussion of the limitations of this approach and the need for further evidence-based studies.

  12. 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.

  13. 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.

  14. 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).

  15. 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...

  16. 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,

  17. 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.

  18. 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...

  19. 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

  20. 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.

  1. 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/).

  2. 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…

  3. 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.

  4. 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.

  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. Vibration isolation for launch of a space station orbital replacement unit

    Science.gov (United States)

    Maly, Joseph R.; Pendleton, Scott C.; James, George H., III; Mimovich, Mark

    2004-07-01

    Delivery of Orbital Replacement Units (ORUs) to the International Space Station (ISS) and other on-orbit destinations is an important component of the space program. ORUs are integrated on orbit with space assets to maintain and upgrade functionality. For ORUs comprised of sensitive equipment, the dynamic launch environment drives design and testing requirements, and high frequency random vibrations are generally the cause for failure. Vibration isolation can mitigate the structure-borne vibration environment during launch, and hardware has been developed that can provide a reduced environment for current and future launch environments. Random vibration testing of one ORU to equivalent Space Shuttle launch levels revealed that its qualification and acceptance requirements were exceeded. An isolation system was designed to mitigate the structure-borne launch vibration environment. To protect this ORU, the random vibration levels at 50 Hz must be attenuated by a factor of two and those at higher frequencies even more. Design load factors for Shuttle launch are high, so a metallic load path is needed to maintain strength margins. Isolation system design was performed using a finite element model of the ORU on its carrier with representative disturbance inputs. Iterations on the model led to an optimized design based on flight-proven SoftRide MultiFlex isolators. Component testing has been performed on prototype isolators to validate analytical predictions.

  7. Spray-On Foam Insulations for Launch Vehicle Cryogenic Tanks

    Science.gov (United States)

    Fesmire, J. E.; Cofman, B. E.; Menghelli, B. J.; Heckle, K. W.

    2011-01-01

    different methods is provided. Recent advancements and applications of SOFI systems on future launch vehicles and spacecraft are also addressed.

  8. Design Considerations for a Launch Vehicle Development Flight Instrumentation System

    Science.gov (United States)

    Johnson, Martin L.; Crawford, Kevin

    2011-01-01

    When embarking into the design of a new launch vehicle, engineering models of expected vehicle performance are always generated. While many models are well established and understood, some models contain design features that are only marginally known. Unfortunately, these analytical models produce uncertainties in design margins. The best way to answer these analytical issues is with vehicle level testing. The National Aeronautics and Space Administration respond to these uncertainties by using a vehicle level system called the Development Flight Instrumentation, or DFI. This DFI system can be simple to implement, with only a few measurements, or it may be a sophisticated system with hundreds of measurement and video, without a recording capability. From experience with DFI systems, DFI never goes away. The system is renamed and allowed to continue, in most cases. Proper system design can aid the transition to future data requirements. This paper will discuss design features that need to be considered when developing a DFI system for a launch vehicle. It will briefly review the data acquisition units, sensors, multiplexers and recorders, telemetry components and harnessing. It will present a reasonable set of requirements which should be implemented in the beginning of the program in order to start the design. It will discuss a simplistic DFI architecture that could be the basis for the next NASA launch vehicle. This will be followed by a discussion of the "experiences gained" from a past DFI system implementation, such as the very successful Ares I-X test flight. Application of these design considerations may not work for every situation, but they may direct a path toward success or at least make one pause and ask the right questions.

  9. NASA's Space Launch System: An Enabling Capability for International Exploration

    Science.gov (United States)

    Creech, Stephen D.; May, Todd A.; Robinson, Kimberly F.

    2014-01-01

    As the program moves out of the formulation phase and into implementation, work is well underway on NASA's new Space Launch System, the world's most powerful launch vehicle, which will enable a new era of human exploration of deep space. As assembly and testing of the rocket is taking place at numerous sites around the United States, mission planners within NASA and at the agency's international partners continue to evaluate utilization opportunities for this ground-breaking capability. Developed 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. NASA is developing this new capability in an austere economic climate, a fact which has inspired the SLS team to find innovative solutions to the challenges of designing, developing, fielding, and operating the largest rocket in history, via a path that will deliver an initial 70 metric ton (t) capability in December 2017 and then continuing through an incremental evolutionary strategy to reach a full capability greater than 130 t. SLS will be enabling for the first missions of human exploration beyond low Earth in almost half a century, and from its first crewed flight will be able to carry humans farther into space than they have ever voyaged before. In planning for the future of exploration, the International Space Exploration Coordination Group, representing 12 of the world's space agencies, has created the Global Exploration Roadmap, which outlines paths toward a human landing on Mars, beginning with capability-demonstrating missions to the Moon or an asteroid. The Roadmap and corresponding NASA research outline the requirements for reference missions for these destinations. SLS will offer a robust way to transport international crews and the air, water, food, and equipment they would need for such missions.

  10. 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

  11. 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.

  12. Testing Strategies and Methodologies for the Max Launch Abort System

    Science.gov (United States)

    Schaible, Dawn M.; Yuchnovicz, Daniel E.

    2011-01-01

    The National Aeronautics and Space Administration (NASA) Engineering and Safety Center (NESC) was tasked to develop an alternate, tower-less launch abort system (LAS) as risk mitigation for the Orion Project. The successful pad abort flight demonstration test in July 2009 of the "Max" launch abort system (MLAS) provided data critical to the design of future LASs, while demonstrating the Agency s ability to rapidly design, build and fly full-scale hardware at minimal cost in a "virtual" work environment. Limited funding and an aggressive schedule presented a challenge for testing of the complex MLAS system. The successful pad abort flight demonstration test was attributed to the project s systems engineering and integration process, which included: a concise definition of, and an adherence to, flight test objectives; a solid operational concept; well defined performance requirements, and a test program tailored to reducing the highest flight test risks. The testing ranged from wind tunnel validation of computational fluid dynamic simulations to component ground tests of the highest risk subsystems. This paper provides an overview of the testing/risk management approach and methodologies used to understand and reduce the areas of highest risk - resulting in a successful flight demonstration test.

  13. 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.

  14. Modelling informally collected quantities of bulky waste and reusable items in Austria

    Energy Technology Data Exchange (ETDEWEB)

    Ramusch, R., E-mail: roland.ramusch@boku.ac.at; Pertl, A.; Scherhaufer, S.; Schmied, E.; Obersteiner, G.

    2015-10-15

    Highlights: • Informal collectors from Hungary collect bulky waste and reusable items in Austria. • Two methodologies were applied to estimate the informally collected quantities. • Both approaches lead to an estimation of roughly 100,000 t p.a. informally collected. • The formal Austrian system collects 72 kg/cap/yr of bulky waste, WEE & scrap metal. • Informal collection amounts to approx. 12 kg/cap/yr. - Abstract: Disparities in earnings between Western and Eastern European countries are the reason for a well-established informal sector actively involved in collection and transboundary shipment activities from Austria to Hungary. The preferred objects are reusable items and wastes within the categories bulky waste, WEEE and metals, intended to be sold on flea markets. Despite leading to a loss of recyclable resources for Austrian waste management, these informal activities may contribute to the extension of the lifetime of certain goods when they are reused in Hungary; nevertheless they are discussed rather controversially. The aim of this paper is to provide objective data on the quantities informally collected and transhipped. The unique activities of informal collectors required the development and implementation of a new set of methodologies. The concept of triangulation was used to verify results obtained by field visits, interviews and a traffic counting campaign. Both approaches lead to an estimation of approx. 100,000 t per year of reusable items informally collected in Austria. This means that in addition to the approx. 72 kg/cap/yr formally collected bulky waste, bulky waste wood, household scrap (excluding packaging) and WEEE, up to a further 12 kg/cap/yr might, in the case that informal collection is abandoned, end up as waste or in the second-hand sector.

  15. Non-Toxic Reaction Control System for the Reusable First Stage Vehicle

    Science.gov (United States)

    Keith, E. L.; Rothschild, W. J.

    1999-01-01

    This paper presents the Boeing Reusable Space Systems vision of a Reaction Control System (RCS) for the Reusable First Stage (RFS) being considered as a replacement for the Solid Rocket Booster for the Space Shuttle. The requirement is to achieve reliable vehicle control during the upper atmospheric portion of the RFS trajectory while enabling more efficient ground operations, unhindered by constraints caused by operating with highly toxic RCS propellants. Boeing's objective for this effort is to develop a safer, more efficient and environmentally friendly RCS design approach that is suitable for the RFS concept of operations, including a low cost, efficient turnaround cycle. The Boeing RCS concept utilizes ethanol and liquid oxygen in place of the highly toxic, suspected carcinogen, ozone-depleting mono-methyl-hydrazine and highly toxic nitrogen tetroxide. The Space Shuttle Upgrade program, under the leadership of the NASA Johnson Space Flight Center, is currently developing liquid oxygen and ethanol (ethyl alcohol) technology for use as non-toxic orbital maneuvering system (OMS) and RCS. The development of this liquid oxygen and ethanol technology for the Space Shuttle offers a significant leverage to select much of the same technology for the RFS program. There are significant design and development issues involved with bringing this liquid oxygen and ethanol technology to a state of maturity suitable for an operational RCS. The risks associated with a new LOX and Ethanol RCS are mitigated by maintaining kerosene and hydrogen peroxide RCS technology as an alternative. These issues, presented within this paper, include managing the oxygen supply and achieving reliable ignition in the short pulse mode of engine operation. Performance, reliability and operations requirements are presented along with a specific RCS design concept to satisfying these requirements. The work reported in this paper was performed under NASA Marshall Space Flight Center Contract Number

  16. Development of Constraint Force Equation Methodology for Application to Multi-Body Dynamics Including Launch Vehicle Stage Seperation

    Science.gov (United States)

    Pamadi, Bandu N.; Toniolo, Matthew D.; Tartabini, Paul V.; Roithmayr, Carlos M.; Albertson, Cindy W.; Karlgaard, Christopher D.

    2016-01-01

    The objective of this report is to develop and implement a physics based method for analysis and simulation of multi-body dynamics including launch vehicle stage separation. The constraint force equation (CFE) methodology discussed in this report provides such a framework for modeling constraint forces and moments acting at joints when the vehicles are still connected. Several stand-alone test cases involving various types of joints were developed to validate the CFE methodology. The results were compared with ADAMS(Registered Trademark) and Autolev, two different industry standard benchmark codes for multi-body dynamic analysis and simulations. However, these two codes are not designed for aerospace flight trajectory simulations. After this validation exercise, the CFE algorithm was implemented in Program to Optimize Simulated Trajectories II (POST2) to provide a capability to simulate end-to-end trajectories of launch vehicles including stage separation. The POST2/CFE methodology was applied to the STS-1 Space Shuttle solid rocket booster (SRB) separation and Hyper-X Research Vehicle (HXRV) separation from the Pegasus booster as a further test and validation for its application to launch vehicle stage separation problems. Finally, to demonstrate end-to-end simulation capability, POST2/CFE was applied to the ascent, orbit insertion, and booster return of a reusable two-stage-to-orbit (TSTO) vehicle concept. With these validation exercises, POST2/CFE software can be used for performing conceptual level end-to-end simulations, including launch vehicle stage separation, for problems similar to those discussed in this report.

  17. 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.

  18. Spacecraft Power Source Installation at Launch Complex

    Science.gov (United States)

    Lytal, Paul; Hoffman, Pamela

    2010-01-01

    For certain space missions, an assembly must be integrated onto the spacecraft as late as possible in the launch vehicle processing flow. 12This late integration can be driven for a variety of reasons including thermal or hazardous materials constraints. This paper discusses the process of integrating an assembly onto a spacecraft as late as one week prior to the opening of the launch window. Consideration is given to achieving sufficient access for hardware integration, methods of remotely securing hardware to the spacecraft, maintaining spacecraft cleanliness throughout the integration process, and electrically integrating the component to the spacecraft. Specific examples are taken from the remote mechanical, electrical, and fluid cooling system integration of the power source onto the Mars Science Laboratory (MSL) Rover at the Atlas V Vertical Integration Facility (VIF) at Cape Canaveral Air Force Station, Florida.

  19. Offshore Space Center (offshore launch site)

    Science.gov (United States)

    Harvey, D. G.

    1980-07-01

    Any activity requiring the development of the HLLV can benefit by operations from an offshore space center (OSC) since operating near the equator provides a twenty percent increase in payload in an ecliptic plan orbit. Some OSC concepts considered include a moored floating (semisubmersible) design, a stationary design supported by fixed piles, and a combination of these two. The facility supports: a 15,000 foot long, 300 foot wide runway, designed to accommodate a two staged winged launch vehicle, with a one million pound payload capacity to low earth orbit; an industrial area for HLLV maintenance; an airport terminal, control and operation center, and observation tower; liquid hydrogen and liquid oxygen production and storage, and fuel storage platforms; a power generation station, docks with an unloading area; two separate launch sites; and living accommodations for 10,000 people. Potential sites include the Paramount Seamount in the Pacific Ocean off the north coast of South America. Cost estimates are considered.

  20. STS-114: Discovery Launch Postponement Press Briefing

    Science.gov (United States)

    2005-01-01

    This press briefing addresses the problem that occurred prior to the launch of the STS-114. Dean Acosta, Deputy Assistant Administrator of Public Affairs, introduces the panel which consists of Dr. Michael Griffin, NASA Administrator, William Readdy, Associate Administrator for Space Operations, Wayne Hale, Space Shuttle Program Deputy Manager, Steve Poulas, Orbiter Project Manager, Mike Leinbach, NASA Launch Director, and Bill Parsons, Space Shuttle Program Manager. Wayne Hale expresses that a problem occurred with one of the low level sensors in the hydrogen tank and that the cause of the problem must be identified and rectified. Steve Poulos talks about establishing a troubleshooting plan as a part of the scrub effort and Mike Leinbach describes the process of draining the external tank. Wayne Hale answers questions about the sensors and if the Space Shuttle Discovery is safe to fly and Steve Poulos answers questions about the possible suspects for this problem.

  1. A low-cost reusable phantom for ultrasound-guided subclavian vein cannulation

    Directory of Open Access Journals (Sweden)

    Varun Cheruparambath

    2012-01-01

    Full Text Available Guidelines support the use of ultrasound (US-guided central venous cannulation in the intensive care unit. Traditional techniques based on anatomical landmarks are blind procedures and inexpert USG procedures may be hazardous. Commercially available phantoms for simulation and training are expensive. The technique of making a low-cost reusable gelatin phantom which simulates subclavian vein anatomy is described. Techniques to improve eye-hand skills with this phantom are described. This phantom is easy to make, inexpensive and easily renewable.

  2. Developing a Toolset Supporting the Construction of Reusable Components for Embedded Control Systems

    DEFF Research Database (Denmark)

    Guan, Wei; Sierszecki, Krzysztof; Angelov, Christo K.

    2010-01-01

    Reusing software components for embedded control applications enhances product quality and reduces time to market when appropriate (formal) methodologies and supporting toolsets are available. That is why industrial companies are interested in developing trusted, in-house reusable components....... That demand can be satisfied by a highly customized toolset providing an integrated development environment for rapid graphical component specification, component validation, automatic generation of artifacts and documentation. The paper presents a possible solution for creating a customized toolset based...... on open-source technology, in accordance with industrial requirements, as well as the approach used to engineer a toolset supporting component development for embedded control applications....

  3. Radiation exposure to the orbiting lunar station and lunar surface related to reusable nuclear shuttle operations

    Science.gov (United States)

    Hutchinson, P. I.

    1972-01-01

    The radiation environment created by the Reusable Nuclear Vehicle (RNS) in performing its normal mission functions while in the lunar vicinity and the impact of that environment on the Orbiting Lunar Station (OLS) and/or the lunar surface are examined. Lunar surface exposures from the operating reactor were evaluated for both the arrival and departure burns and while there is little probability that manned bases would lie along the paths in which measurable exposures would be recorded, the analyses do indicate the need to consider this possibility in planning such operations. Conclusions supported by the analyses and recommended operational constraints for the RNS are presented.

  4. A Software Pattern of the Genetic Algorithm -a Study on Reusable Object Model of Genetic Algorithm

    Institute of Scientific and Technical Information of China (English)

    2001-01-01

    The Genetic Algorithm (GA) has been a pop research field, butthere is little concern on GA in view of Software Engineering and this result in a serie s of problems. In this paper, we extract a GA's software pattern, draw a model d iagram of the reusable objects, analyze the advantages and disadvantages of the pattern, and give a sample code at the end. We are then able to improve the reus ability and expansibility of GA. The results make it easier to program a new GA code by using some existing successful operators, thereby reducing the difficult ies and workload of programming a GA's code, and facilitate the GA application.

  5. Damage-mitigating control of a reusable rocket engine for high performance and extended life

    Science.gov (United States)

    Ray, Asok; Dai, Xiaowen

    1995-01-01

    The goal of damage mitigating control in reusable rocket engines is to achieve high performance with increased durability of mechanical structures such that functional lives of the critical components are increased. The major benefit is an increase in structural durability with no significant loss of performance. This report investigates the feasibility of damage mitigating control of reusable rocket engines. Phenomenological models of creep and thermo-mechanical fatigue damage have been formulated in the state-variable setting such that these models can be combined with the plant model of a reusable rocket engine, such as the Space Shuttle Main Engine (SSME), for synthesizing an optimal control policy. Specifically, a creep damage model of the main thrust chamber wall is analytically derived based on the theories of sandwich beam and viscoplasticity. This model characterizes progressive bulging-out and incremental thinning of the coolant channel ligament leading to its eventual failure by tensile rupture. The objective is to generate a closed form solution of the wall thin-out phenomenon in real time where the ligament geometry is continuously updated to account for the resulting deformation. The results are in agreement with those obtained from the finite element analyses and experimental observation for both Oxygen Free High Conductivity (OFHC) copper and a copper-zerconium-silver alloy called NARloy-Z. Due to its computational efficiency, this damage model is suitable for on-line applications of life prediction and damage mitigating control, and also permits parametric studies for off-line synthesis of damage mitigating control systems. The results are presented to demonstrate the potential of life extension of reusable rocket engines via damage mitigating control. The control system has also been simulated on a testbed to observe how the damage at different critical points can be traded off without any significant loss of engine performance. The research work

  6. Numerical Simulation of a Thermal-Protection Element of a Promising Reusable Capsule-Type Lander

    Science.gov (United States)

    Prosuntsov, P. V.; Shulyakovskii, A. V.; Taraskin, N. Yu.

    2017-01-01

    An indestructible multilayer thermal-barrier coating is proposed for a promising reusable capsule-type lander. This coating is based on a porous carbon-ceramic material. The thermal state of the coating proposed was simulated mathematically for different types of its reinforcement and different values of the porosity and the heat-conductivity coefficient of the carbon-ceramic material. Results of a numerical simulation of the temperature state of an element of the multilayer thermal-barrier coating are presented. On the basis of these data, the thickness and the weight efficiency of the coating were estimated.

  7. Customized oligonucleotide microchips that convert multiple genetic information to simple patterns, are portable and reusable

    Science.gov (United States)

    Mirzabekov, Andrei; Guschin, Dmitry Y.; Chik, Valentine; Drobyshev, Aleksei; Fotin, Alexander; Yershov, Gennadiy; Lysov, Yuri

    2002-01-01

    This invention relates to using customized oligonucleotide microchips as biosensors for the detection and identification of nucleic acids specific for different genes, organisms and/or individuals in the environment, in food and in biological samples. The microchips are designed to convert multiple bits of genetic information into simpler patterns of signals that are interpreted as a unit. Because of an improved method of hybridizing oligonucleotides from samples to microchips, microchips are reusable and transportable. For field study, portable laser or bar code scanners are suitable.

  8. Nanosphere of Semicrystalline Polyaniline Powder: An Effective, Versatile, and Reusable Catalyst for Hantzsch Reaction

    Directory of Open Access Journals (Sweden)

    Ravi Bolagam

    2014-01-01

    Full Text Available Polyaniline salt containing 1-hydroxyethane-1,1-diphosphonic acid with nanosphere morphology in semicrystalline powder form was successfully synthesized by interfacial polymerization pathway and demonstrated as polymer based acid catalyzed in the synthesis of 1,4-dihydropyridines and polyhydroquinoline derivatives. This catalyst promotes the reaction under solvent free condition in excellent yield in 10 min with recyclability. The advantages of this methodology are the easy synthesis of polymer containing acid group catalyst in powder form having easily handlable, efficient, versatile, and reusable nature.

  9. Application of Markov chain theory to ASTP natural environment launch criteria at Kennedy Space Center

    Science.gov (United States)

    Graves, M. E.; Perlmutter, M.

    1974-01-01

    To aid the planning of the Apollo Soyuz Test Program (ASTP), certain natural environment statistical relationships are presented, based on Markov theory and empirical counts. The practical results are in terms of conditional probability of favorable and unfavorable launch conditions at Kennedy Space Center (KSC). They are based upon 15 years of recorded weather data which are analyzed under a set of natural environmental launch constraints. Three specific forecasting problems were treated: (1) the length of record of past weather which is useful to a prediction; (2) the effect of persistence in runs of favorable and unfavorable conditions; and (3) the forecasting of future weather in probabilistic terms.

  10. Thermographic testing used on the X-33 space launch vehicle program by BFGoodrich Aerospace

    Science.gov (United States)

    Burleigh, Douglas D.

    1999-03-01

    The X-33 program is a team effort sponsored by NASA under Cooperative Agreement NCC8-115, and led by the Lockheed Martin Corporation. Team member BFGoodrich Aerospace Aerostructures Group (formerly Rohr) is responsible for design, manufacture, and integration of the Thermal Protection System (TPS) of the X-33 launch vehicle. The X-33 is a half-scale, experimental prototype of a vehicle called RLV (Reusable Launch Vehicle) or VentureStarTM, an SSTO (single stage to orbit) vehicle, which is a proposed successor to the aging Space Shuttle. Thermographic testing has been employed by BFGoodrich Aerospace Aerostructures Group for a wide variety of uses in the testing of components of the X-33. Thermographic NDT (TNDT) has been used for inspecting large graphite- epoxy/aluminum honeycomb sandwich panels used on the Leeward Aeroshell structure of the X-33. And TNDT is being evaluated for use in inspecting carbon-carbon composite parts such as the nosecap and wing leading edge components. Pulsed Infrared Testing (PIRT), a special form of TNDT, is used for the routine inspection of sandwich panels made of brazed inconel honeycomb and facesheets. In the developmental and qualification testing of sub-elements of the X-33, thermography has been used to monitor (1) Arc Jet tests at NASA Ames Research Center in Mountain view, CA and NASA Johnson Space Center in Houston, TX, (2) High Temperature (wind) Tunnel Tests (HTT) at Nasa Langley Research Center in Langley, VA, and (3) Hot Gas Tests at NASA Marshall Space Flight Center in Huntsville, AL.

  11. Smart Coatings for Launch Site Corrosion Protection

    Science.gov (United States)

    Calle, Luz M.

    2014-01-01

    Smart, environmentally friendly paint system for early corrosion detection, mitigation, and healing that will enable supportability in KSC launch facilities and ground systems through their operational life cycles. KSC's Corrosion Technology Laboratory is developing a smart, self-healing coating that can detect and repair corrosion at an early stage. This coating is being developed using microcapsules specifically designed to deliver the contents of their core when corrosion starts.

  12. Towards Performance Prognostics of a Launch Valve

    Science.gov (United States)

    2014-10-02

    estimations for the next step. In particular, this work implements a simplified version of the Risk-Sensitive Particle Filter (RSPF) presented by Orchard ...et. al. ( Orchard , 2010). The RSPF maintains a subset of particles in the high- risk, low-likelihood realm to maintain coverage in these areas when...This is a step towards allowing the Launch Valve performance analysis to be handled automatically in real-time onboard ship and provide timely

  13. Ares Launch Vehicles Lean Practices Case Study

    Science.gov (United States)

    Doreswamy, Rajiv, N.; Self, Timothy A.

    2008-01-01

    This viewgraph presentation describes test strategies and lean philisophies and practices that are applied to Ares Launch Vehicles. The topics include: 1) Testing strategy; 2) Lean Practices in Ares I-X; 3) Lean Practices Applied to Ares I-X Schedule; 4) Lean Event Results; 5) Lean, Six Sigma, and Kaizen Practices in the Ares Projects Office; 6) Lean and Kaizen Success Stories; and 7) Ares Six Sigma Practices.

  14. White list management system was officially launched

    Institute of Scientific and Technical Information of China (English)

    2012-01-01

    March 28,in China International Exhibition Center the China National Textile and Apparel Council,held a seminar on the Japanese textile industry standards & white list management system,marking the two sides to build a white list management system was officially launched. It is understood that the white list management system developed self-regulatory standards for the Japanese textile industry,that textiles do

  15. Sinopec Launches Shanghai Asphalt Sales Company

    Institute of Scientific and Technical Information of China (English)

    2004-01-01

    @@ Sinopec Shanghai Asphalt Sales Company was launched in Shanghai on September 22, marking Sinopec as the largest asphalt supplier in China integrated in famous brand,production, sales and research, and distribution network.This is another important initiative for Sinopec's asphalt segment, after Sinopec won the bid for construction of F 1 racing course, to grasp the market opportunities, further improve the product quality and the level of after-sales services, and further make its asphalt business larger and stronger.

  16. Battelle estimate of launch service demand

    Science.gov (United States)

    Conlon, R. J.; Day, J. B.

    1987-01-01

    The annual non-NASA non-DOD demand for launches by non-Soviet services is estimated for the period 1986-2001 on the basis of currently available data. The assumptions and methods employed in generating the bottom-up Outside Users Payload Model, the data sources, and the use of equivalent Space Shuttle flights as a payload measure are explained in detail. The numerical results are presented in extensive tables and graphs and briefly characterized.

  17. NASA Space Launch System Operations Strategy

    Science.gov (United States)

    Singer, Joan A.; Cook, Jerry R.

    2012-01-01

    The National Aeronautics and Space Administration's (NASA) Space Launch System (SLS) Program, managed at the Marshall Space Flight Center, is charged with delivering a new capability for human and scientific exploration beyond Earth orbit. The SLS also will provide backup crew and cargo services to the International Space Station, where astronauts have been training for long-duration voyages to destinations such as asteroids and Mars. For context, the SLS will be larger than the Saturn V, providing 10 percent more thrust at liftoff in its initial 70 metric ton (t) configuration and 20 percent more in its evolved 130 t configuration. The SLS Program knows that affordability is the key to sustainability. This paper will provide an overview of its operations strategy, which includes initiatives to reduce both development and fixed costs by using existing hardware and infrastructure assets to meet a first launch by 2017 within the projected budget. It also has a long-range plan to keep the budget flat using competitively selected advanced technologies that offer appropriate return on investment. To arrive at the launch vehicle concept, the SLS Program conducted internal engineering and business studies that have been externally validated by industry and reviewed by independent assessment panels. A series of design reference missions has informed the SLS operations concept, including launching the Orion Multi-Purpose Crew Vehicle on an autonomous demonstration mission in a lunar flyby scenario in 2017, and the first flight of a crew on Orion for a lunar flyby in 2021. Additional concepts address the processing of very large payloads, using a series of modular fairings and adapters to flexibly configure the rocket for the mission. This paper will describe how the SLS, Orion, and 21st Century Ground Systems programs are working together to create streamlined, affordable operations for sustainable exploration.

  18. Textile materials trading center formally launched online

    Institute of Scientific and Technical Information of China (English)

    2012-01-01

    Textile materials trading center was formally launched online in Wuxi City,Jiangsu Province. This is the first third-party electronic trading platform for spot trading in China textile materials professional market. The project will strive to build the most influential textile materials trading center of East China,the whole country and even the whole world China textile materials trading center will be

  19. Dual-Fuel Propulsion in Single-Stage Advanced Manned Launch System Vehicle

    Science.gov (United States)

    Lepsch, Roger A., Jr.; Stanley, Douglas O.; Unal, Resit

    1995-01-01

    As part of the United States Advanced Manned Launch System study to determine a follow-on, or complement, to the Space Shuttle, a reusable single-stage-to-orbit concept utilizing dual-fuel rocket propulsion has been examined. Several dual-fuel propulsion concepts were investigated. These include: a separate-engine concept combining Russian RD-170 kerosene-fueled engines with space shuttle main engine-derivative engines: the kerosene- and hydrogen-fueled Russian RD-701 engine; and a dual-fuel, dual-expander engine. Analysis to determine vehicle weight and size characteristics was performed using conceptual-level design techniques. A response-surface methodology for multidisciplinary design was utilized to optimize the dual-fuel vehicles with respect to several important propulsion-system and vehicle design parameters, in order to achieve minimum empty weight. The tools and methods employed in the analysis process are also summarized. In comparison with a reference hydrogen- fueled single-stage vehicle, results showed that the dual-fuel vehicles were from 10 to 30% lower in empty weight for the same payload capability, with the dual-expander engine types showing the greatest potential.

  20. Risk Estimation Methodology for Launch Accidents.

    Energy Technology Data Exchange (ETDEWEB)

    Clayton, Daniel James; Lipinski, Ronald J.; Bechtel, Ryan D.

    2014-02-01

    As compact and light weight power sources with reliable, long lives, Radioisotope Power Systems (RPSs) have made space missions to explore the solar system possible. Due to the hazardous material that can be released during a launch accident, the potential health risk of an accident must be quantified, so that appropriate launch approval decisions can be made. One part of the risk estimation involves modeling the response of the RPS to potential accident environments. Due to the complexity of modeling the full RPS response deterministically on dynamic variables, the evaluation is performed in a stochastic manner with a Monte Carlo simulation. The potential consequences can be determined by modeling the transport of the hazardous material in the environment and in human biological pathways. The consequence analysis results are summed and weighted by appropriate likelihood values to give a collection of probabilistic results for the estimation of the potential health risk. This information is used to guide RPS designs, spacecraft designs, mission architecture, or launch procedures to potentially reduce the risk, as well as to inform decision makers of the potential health risks resulting from the use of RPSs for space missions.