WorldWideScience

Sample records for toetavad aero airlinesi

  1. Aasta keeleteoks tunnistati "Lapse keelelist arengut toetavad mängud" / Mari Klein

    Index Scriptorium Estoniae

    Klein, Mari, 1979-

    2014-01-01

    Emakeelepäeval toimus Kuressaares Saaremaa Ühisgümnaasiumis 2013. aasta parima keeleteo konkursi lõpuüritus, kus tunnustati võitjaid. Peaauhinna võitsid Tallinna Ülikooli eesti keele professor Reili Argus ja Rocca al Mare Kooli eelkooliõpetaja Cattre Hein veebimänguga "Lapse keelelist arengut toetavad mängud"

  2. Equipment for Aero-Optical Flow Imaging

    National Research Council Canada - National Science Library

    Catrakis, Haris

    2004-01-01

    The AFOSR/DURIP Grant has provided the funds to develop a new Aero-Optics Laboratory at UC Irvine, in order to do basic research on aero-optical laser beam propagation through high-speed turbulent flows...

  3. AeroMACS system characterization and demonstrations

    Science.gov (United States)

    Kerczewski, R. J.; Apaza, R. D.; Dimond, R. P.

    This The Aeronautical Mobile Airport Communications System (AeroMACS) is being developed to provide a new broadband wireless communications capability for safety critical communications in the airport surface domain, providing connectivity to aircraft and other ground vehicles as well as connections between other critical airport fixed assets. AeroMACS development has progressed from requirements definition through technology definition, prototype deployment and testing, and now into national and international standards development. The first prototype AeroMACS system has been deployed at the Cleveland Hopkins International Airport (CLE) and the adjacent NASA Glenn Research Center (GRC). During the past three years, extensive technical testing has taken place to characterize the performance of the AeroMACS prototype and provide technical support for the standards development process. The testing has characterized AeroMACS link and network performance over a variety of conditions for both fixed and mobile data transmission and has included basic system performance testing and fixed and mobile applications testing. This paper provides a summary of the AeroMACS performance testing and the status of standardization activities that the testing supports.

  4. Method of making an aero-derivative gas turbine engine

    Science.gov (United States)

    Wiebe, David J.

    2018-02-06

    A method of making an aero-derivative gas turbine engine (100) is provided. A combustor outer casing (68) is removed from an existing aero gas turbine engine (60). An annular combustor (84) is removed from the existing aero gas turbine engine. A first row of turbine vanes (38) is removed from the existing aero gas turbine engine. A can annular combustor assembly (122) is installed within the existing aero gas turbine engine. The can annular combustor assembly is configured to accelerate and orient combustion gasses directly onto a first row of turbine blades of the existing aero gas turbine engine. A can annular combustor assembly outer casing (108) is installed to produce the aero-derivative gas turbine engine (100). The can annular combustor assembly is installed within an axial span (85) of the existing aero gas turbine engine vacated by the annular combustor and the first row of turbine vanes.

  5. Aero-disaster in Port Harcourt, Nigeria: A case study

    African Journals Online (AJOL)

    Aero-disaster in Port Harcourt, Nigeria: A case study ... Aero-disaster in Nigeria is posing a serious problem to government, the public and relatives of victims, ..... which was recorded in one of our victim's relation, ... this communication.

  6. Surface modifications of aero-bearings

    International Nuclear Information System (INIS)

    Wang Yirong; Chen Jin; Nie Gao; Lu Haolin; Yang Qifa; Xu Qiu; Wang Peilu; Chen Yuanru; Liu Zhongyang

    1988-01-01

    Different ion beam techniques, i.e. ion beam mixing and ion implantation by either single or multi-element ions, were adopted to modify surface properties of aero-bearing samples that were made of GCr15 or Cr4Mo4V alloys, Results showed that corrosion behaviour and wear resistance of the samples treated with any of the techniques were improved significantly

  7. Common indoor and outdoor aero-allergens in South Africa

    African Journals Online (AJOL)

    Aero-allergens in South Africa that are also encountered around the world are listed in Table I. In addition to this wide range of common aero-allergens, South Africans are also exposed to a full range of food allergens, some of which, e.g. perlemoen (Haliotis midae) and other seafood allergens, are unique to this region.

  8. THE TREATMENT OF AERO-OTITIS MEDIA BY REDECOMPRESSION,

    Science.gov (United States)

    The precipitating event preceding the appearance of aero- otitis media is the development of a relative vacuum within the middle ear. The aim of...obtaining normal pressure relationships between the middle ear and the environment. In 27 of a group of 33 men with severe aero- otitis media , this

  9. Advanced technology for aero gas turbine components

    Energy Technology Data Exchange (ETDEWEB)

    1987-09-01

    The Symposium is aimed at highlighting the development of advanced components for new aero gas turbine propulsion systems in order to provide engineers and scientists with a forum to discuss recent progress in these technologies and to identify requirements for future research. Axial flow compressors, the operation of gas turbine engines in dust laden atmospheres, turbine engine design, blade cooling, unsteady gas flow through the stator and rotor of a turbomachine, gear systems for advanced turboprops, transonic blade design and the development of a plenum chamber burner system for an advanced VTOL engine are among the topics discussed.

  10. Aero and vibroacoustics of automotive turbochargers

    Energy Technology Data Exchange (ETDEWEB)

    Nguyen-Schaefer, Hung [Bosch Mahle Turbo Systems GmbH, Stuttgart (Germany)

    2013-02-01

    First book about the aeroacoustics of automotive turbochargers. Author of the book ''Rotordynamics of Automotive Turbochargers'', Springer, 2012. Written by an R and D expert in the turbocharger industry. Aero and Vibroacoustics of Automotive Turbochargers is a topic involving aspects from the working fields of thermodynamics of turbomachinery, aerodynamics, rotordynamics, and noise propagation computation. In this broadly interdisciplinary subject, thermodynamics of turbomachinery is used to design the turbocharger and to determine its operating conditions. Aerodynamics is needed to study the compressor flow dynamics and flow instabilities of rotating stall and surge, which can produce growling and whining-type noises. Rotordynamics is necessary to study rotor unbalance and self-excited oil-whirl instabilities, which lead to whistling and constant tone-type noises in rotating floating oil-film type bearings. For the special case of turbochargers using ball bearings, some high-order harmonic and wear noises also manifest in the rotor operating range. Lastly, noise propagation computation, based on Lighthill's analogy, is required to investigate airborne noises produced by turbochargers in passenger vehicles. The content of this book is intended for advanced undergraduates, graduates in mechanical engineering, research scientists and practicing engineers who want to better understand the interactions between these working fields and the resulting impact on the interesting topic of Aero and Vibroacoustics of Automotive Turbochargers.

  11. Aero-Assisted Pre-Stage for Ballistic and Aero-Assisted Launch Vehicles

    Science.gov (United States)

    Ustinov, Eugene A.

    2012-01-01

    A concept of an aero-assisted pre-stage is proposed, which enables launch of both ballistic and aero-assisted launch vehicles from conventional runways. The pre-stage can be implemented as a delta-wing with a suitable undercarriage, which is mated with the launch vehicle, so that their flight directions are coaligned. The ample wing area of the pre-stage combined with the thrust of the launch vehicle ensure prompt roll-out and take-off of the stack at airspeeds typical for a conventional jet airliner. The launch vehicle is separated from the pre-stage as soon as safe altitude is achieved, and the desired ascent trajectory is reached. Nominally, the pre-stage is non-powered. As an option, to save the propellant of the launch vehicle, the pre-stage may have its own short-burn propulsion system, whereas the propulsion system of the launch vehicle is activated at the separation point. A general non-dimensional analysis of performance of the pre-stage from roll-out to separation is carried out and applications to existing ballistic launch vehicle and hypothetical aero-assisted vehicles (spaceplanes) are considered.

  12. Aero and vibroacoustics of automotive turbochargers

    CERN Document Server

    Nguyen-Schäfer, Hung

    2013-01-01

    Aero and Vibroacoustics of Automotive Turbochargers is a topic involving aspects from the working fields of thermodynamics of turbomachinery, aerodynamics, rotordynamics, and noise propagation computation.   In this broadly interdisciplinary subject, thermodynamics of turbomachinery is used to design the turbocharger and to determine its operating conditions.  Aerodynamics is needed to study the compressor flow dynamics and flow instabilities of rotating stall and surge, which can produce growling and whining-type noises. Rotordynamics is necessary to study rotor unbalance and self-excited oil-whirl instabilities, which lead to whistling and constant tone-type noises in rotating floating oil-film type bearings. For the special case of turbochargers using ball bearings, some high-order harmonic and wear noises also manifest in the rotor operating range. Lastly, noise propagation computation, based on Lighthill’s analogy, is required to investigate airborne noises produced by turbochargers in passenger vehi...

  13. MEMS and mil/aero: technology push and market pull

    Science.gov (United States)

    Clifford, Thomas H.

    2001-04-01

    MEMS offers attractive solutions to high-density fluidics, inertial, optical, switching and other demanding military/aerospace (mil/aero) challenges. However, full acceptance must confront the realities of production-scale producibility, verifiability, testability, survivability, as well as long-term reliability. Data on these `..ilities' are crucial, and are central in funding and deployment decisions. Similarly, mil/aero users must highlight specific missions, environmental exposures, and procurement issues, as well as the quirks of its designers. These issues are particularly challenging in MEMS, because of the laws of physics and business economics, as well as the risks of deploying leading-edge technology into no-fail applications. This paper highlights mil/aero requirements, and suggests reliability/qualification protocols, to guide development effort and to reassure mil/aero users that MEMS labs are mindful of the necessary realities.

  14. Generic methods for aero-engine exhaust emission prediction

    NARCIS (Netherlands)

    Shakariyants, S.A.

    2008-01-01

    In the thesis, generic methods have been developed for aero-engine combustor performance, combustion chemistry, as well as airplane aerodynamics, airplane and engine performance. These methods specifically aim to support diverse emission prediction studies coupled with airplane and engine

  15. Aeronautical Mobile Airport Communications System (AeroMACS)

    Science.gov (United States)

    Budinger, James M.; Hall, Edward

    2011-01-01

    To help increase the capacity and efficiency of the nation s airports, a secure wideband wireless communications system is proposed for use on the airport surface. This paper provides an overview of the research and development process for the Aeronautical Mobile Airport Communications System (AeroMACS). AeroMACS is based on a specific commercial profile of the Institute of Electrical and Electronics Engineers (IEEE) 802.16 standard known as Wireless Worldwide Interoperability for Microwave Access or WiMAX (WiMax Forum). The paper includes background on the need for global interoperability in air/ground data communications, describes potential AeroMACS applications, addresses allocated frequency spectrum constraints, summarizes the international standardization process, and provides findings and recommendations from the world s first AeroMACS prototype implemented in Cleveland, Ohio, USA.

  16. Optics equations for aero-optical analysis

    Science.gov (United States)

    Sutton, George W.; Pond, John E.

    2011-05-01

    Aero-optical effects occur around moving air vehicles and impact passive imaging or active systems. The air flow around the vehicle is compressed, and often there is a turbulent shear and/or boundary layer both of which cause variations in the index of refraction. Examples of these are reconnaissance aircraft, the Stratospheric Observatory for Infrared Optics (SOFIA), and optically homing hypersonic interceptors. In other applications, a laser beam can be formed within the vehicle, and projected outward and focused on an object. These include the Airborne Laser Laboratory, Airborne Laser and the Airborne Tactical Laser. There are many compressible fluid mechanics computer programs that can predict the air density distribution of the surrounding flow field including density fluctuations in turbulent shear and/or boundary layers. It is necessary for the physical optics to be used to predict the properties of the ensuing image plane intensity distribution, whether passive or active. These include the time-averaged image blur circle and instantaneous realizations. (Ray tracing is a poor approximation that gives erroneous results for small aberrations.)

  17. Integrated Reconfigurable Aero and Propulsion Control for Improved Flight Safety of Commercial Aircraft, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — The main objective of this project is to develop and test a novel innovative Integrated Reconfigurable Aero (i) Adaptive control design for the case of aero-only...

  18. Aero-Optic Evaluation Center (AOEC), Large Energy National Shock (LENS) Tunnels I & II

    Data.gov (United States)

    Federal Laboratory Consortium — The AOEC facility provides world class capability for aero-thermo-chemical, aerooptics and aero-propulsion testing in the Mach number range from 2.5 to 15 using the...

  19. Experimental Technique of Titanium Fire in Aero-engine

    Directory of Open Access Journals (Sweden)

    MI Guangbao

    2016-06-01

    Full Text Available Titanium fire is the typical catastrophic fault in the aero-engine. Aiming at the urgent demand for experimental technique of titanium fire from advanced high thrust-weight ratio aero-engine, the combustion technology and theory of titanium alloy based on friction oxygen concentration method (FOC were systematically studied. The evaluation method of fireproof property and the friction ignition model were built, and the fireproof mechanism was illustrated. By generalizing recent progress in experimental technique of titanium fire from three levels, including evolutionary rule, mechanism and prevention and control technology, the ideas and directions of experimental technique associated with the application research of titanium fire in the future were proposed, namely overall evaluation of fireproof property close to air flow environment of the aero-engine, prediction model of fireproof property and experimental verification of fireproof technique under the air flow environment of aero-engine. It is necessary to establish the prevention system of titanium fire in aero-engine, which contributes to the realization of "full titanium" in compressor and to the increase of high thrust-weight ratio.

  20. Vibration modelling and verifications for whole aero-engine

    Science.gov (United States)

    Chen, G.

    2015-08-01

    In this study, a new rotor-ball-bearing-casing coupling dynamic model for a practical aero-engine is established. In the coupling system, the rotor and casing systems are modelled using the finite element method, support systems are modelled as lumped parameter models, nonlinear factors of ball bearings and faults are included, and four types of supports and connection models are defined to model the complex rotor-support-casing coupling system of the aero-engine. A new numerical integral method that combines the Newmark-β method and the improved Newmark-β method (Zhai method) is used to obtain the system responses. Finally, the new model is verified in three ways: (1) modal experiment based on rotor-ball bearing rig, (2) modal experiment based on rotor-ball-bearing-casing rig, and (3) fault simulations for a certain type of missile turbofan aero-engine vibration. The results show that the proposed model can not only simulate the natural vibration characteristics of the whole aero-engine but also effectively perform nonlinear dynamic simulations of a whole aero-engine with faults.

  1. SIERRA/Aero User Manual Version 4.44

    Energy Technology Data Exchange (ETDEWEB)

    Sierra Thermal/Fluid Team

    2017-04-01

    SIERRA/Aero is a compressible fluid dynamics program intended to solve a wide variety compressible fluid flows including transonic and hypersonic problems. This document describes the commands for assembling a fluid model for analysis with this module, henceforth referred to simply as Aero for brevity. Aero is an application developed using the SIERRA Toolkit (STK). The intent of STK is to provide a set of tools for handling common tasks that programmers encounter when developing a code for numerical simulation. For example, components of STK provide field allocation and management, and parallel input/output of field and mesh data. These services also allow the development of coupled mechanics analysis software for a massively parallel computing environment. In the definitions of the commands that follow, the term Real_Max denotes the largest floating point value that can be represented on a given computer. Int_Max is the largest such integer value.

  2. SIERRA/Aero User Manual Version 4.46.

    Energy Technology Data Exchange (ETDEWEB)

    Sierra Thermal/Fluid Team

    2017-09-01

    SIERRA/Aero is a compressible fluid dynamics program intended to solve a wide variety compressible fluid flows including transonic and hypersonic problems. This document describes the commands for assembling a fluid model for analysis with this module, henceforth referred to simply as Aero for brevity. Aero is an application developed using the SIERRA Toolkit (STK). The intent of STK is to provide a set of tools for handling common tasks that programmers encounter when developing a code for numerical simulation. For example, components of STK provide field allocation and management, and parallel input/output of field and mesh data. These services also allow the development of coupled mechanics analysis software for a massively parallel computing environment. In the definitions of the commands that follow, the term Real_Max denotes the largest floating point value that can be represented on a given computer. Int_Max is the largest such integer value.

  3. SIERRA/Aero Theory Manual Version 4.44

    Energy Technology Data Exchange (ETDEWEB)

    Sierra Thermal/Fluid Team

    2017-04-01

    SIERRA/Aero is a two and three dimensional, node-centered, edge-based finite volume code that approximates the compressible Navier-Stokes equations on unstructured meshes. It is applicable to inviscid and high Reynolds number laminar and turbulent flows. Currently, two classes of turbulence models are provided: Reynolds Averaged Navier-Stokes (RANS) and hybrid methods such as Detached Eddy Simulation (DES). Large Eddy Simulation (LES) models are currently under development. The gas may be modeled either as ideal, or as a non-equilibrium, chemically reacting mixture of ideal gases. This document describes the mathematical models contained in the code, as well as certain implementation details. First, the governing equations are presented, followed by a description of the spatial discretization. Next, the time discretization is described, and finally the boundary conditions. Throughout the document, SIERRA/ Aero is referred to simply as Aero for brevity.

  4. SIERRA/Aero Theory Manual Version 4.46.

    Energy Technology Data Exchange (ETDEWEB)

    Sierra Thermal/Fluid Team

    2017-09-01

    SIERRA/Aero is a two and three dimensional, node-centered, edge-based finite volume code that approximates the compressible Navier-Stokes equations on unstructured meshes. It is applicable to inviscid and high Reynolds number laminar and turbulent flows. Currently, two classes of turbulence models are provided: Reynolds Averaged Navier-Stokes (RANS) and hybrid methods such as Detached Eddy Simulation (DES). Large Eddy Simulation (LES) models are currently under development. The gas may be modeled either as ideal, or as a non-equilibrium, chemically reacting mixture of ideal gases. This document describes the mathematical models contained in the code, as well as certain implementation details. First, the governing equations are presented, followed by a description of the spatial discretization. Next, the time discretization is described, and finally the boundary conditions. Throughout the document, SIERRA/ Aero is referred to simply as Aero for brevity.

  5. Vehicle Health Management Communications Requirements for AeroMACS

    Science.gov (United States)

    Kerczewski, Robert J.; Clements, Donna J.; Apaza, Rafael D.

    2012-01-01

    As the development of standards for the aeronautical mobile airport communications system (AeroMACS) progresses, the process of identifying and quantifying appropriate uses for the system is progressing. In addition to defining important elements of AeroMACS standards, indentifying the systems uses impacts AeroMACS bandwidth requirements. Although an initial 59 MHz spectrum allocation for AeroMACS was established in 2007, the allocation may be inadequate; studies have indicated that 100 MHz or more of spectrum may be required to support airport surface communications. Hence additional spectrum allocations have been proposed. Vehicle health management (VHM) systems, which can produce large volumes of vehicle health data, were not considered in the original bandwidth requirements analyses, and are therefore of interest in supporting proposals for additional AeroMACS spectrum. VHM systems are an emerging development in air vehicle safety, and preliminary estimates of the amount of data that will be produced and transmitted off an aircraft, both in flight and on the ground, have been prepared based on estimates of data produced by on-board vehicle health sensors and initial concepts of data processing approaches. This allowed an initial estimate of VHM data transmission requirements for the airport surface. More recently, vehicle-level systems designed to process and analyze VHM data and draw conclusions on the current state of vehicle health have been undergoing testing and evaluation. These systems make use of vehicle system data that is mostly different from VHM data considered previously for airport surface transmission, and produce processed system outputs that will be also need to be archived, thus generating additional data load for AeroMACS. This paper provides an analysis of airport surface data transmission requirements resulting from the vehicle level reasoning systems, within the context of overall VHM data requirements.

  6. Kaks õpikut, mis toetavad edasiminejat / Lia Eller

    Index Scriptorium Estoniae

    Eller, Lia

    2002-01-01

    Rets. rmt. : Kallas, Roman. Kõik on korras! = эстонский язык : практический курс и грамматика. J. Sarapuu, 2001.Metsa, Antidea ; Jänese, Anne. Sulle, õpetaja! : eesti keele suhtlusõpik kesktasemele. - Tallinn : TEA Kirjastus, 2000.

  7. Rotarid toetavad noorte haridust / Rita Loel

    Index Scriptorium Estoniae

    Loel, Rita, 1966-2012

    2009-01-01

    USA Minnesota Rotchesteri Rotary klubi liige, Kuressaares sündinud Ingrid Vaga Neel, külastas ametikooli UPA õpilaskodu, Kuressaare Gümnaasiumit ja huvikeskust, et vaadata kuidas kahe maa Rotary klubide ühisprojekt on töösse läinud

  8. Maailma naised toetavad Kiikla lastekodu / Annika Poldre

    Index Scriptorium Estoniae

    Poldre, Annika

    2006-01-01

    Eestit külastasid rahvusvahelise naisteorganisatsiooni Soroptimist International president Lynn Dunning Suurbritanniast ja asepresident Kirsten Sveder Rootsist. Külaskäigu eesmärk oli tutvuda Eesti soroptimistide ettevõtmisega - Ida-Virumaale Kiiklasse rajatava noortekoduga. Lisa: Soroptimistide klubid

  9. Overview of NASA Power Technologies for Space and Aero Applications

    Science.gov (United States)

    Beach, Raymond F.

    2014-01-01

    To achieve the ambitious goals that NASA has outlined for the next decades considerable development of power technology will be necessary. This presentation outlines the development objectives for both the space and aero applications. It further looks at the various power technologies that support these objectives and examines drivers that will be a driving force for future development.

  10. Assessment of Aero-radiometric Data of Southern Anambra Basin ...

    African Journals Online (AJOL)

    High-resolution aero-radiometric data from three radio-elements (Uranium, Potassium and Thorium) were used and processed independently to investigate the Southern Anambra basin for the prospect of producing radiogenic heat. The rock types in the study area were outlined while processing the elements in each rock ...

  11. Integrated evaluation of the geology, aero gamma spectrometry and aero magnetometry of the Sul-Riograndense Shield, southernmost Brazil

    Energy Technology Data Exchange (ETDEWEB)

    Hartmann, Leo A.; Savian, Jairo F., E-mail: leo.hartmann@ufrgs.br [Universidade Federal do Rio Grande do Sul (UFRS), Porto Alegre, RS (Brazil). Instituto de Geociencias; Lopes, William R. [Servico Geologico do Brasil (CPRM), Porto Alegre, RS (Brazil). Gerencia de Geologia e Mineracao

    2016-03-15

    An integrated evaluation of geology, aero gamma spectrometry and aero magnetometry of the Sul-Riograndense Shield is permitted by the advanced stage of understanding of the geology and geochronology of the southern Brazilian Shield and a 2010 airborne geophysical survey. Gamma rays are registered from the rocks near the surface and thus describe the distribution of major units in the shield, such as the Pelotas batholith, the juvenile São Gabriel terrane, the granulite-amphibolite facies Taquarembo terrane and the numerous granite intrusions in the foreland. Major structures are also observed, e.g., the Dorsal de Cangucu shear. Magnetic signals register near surface crustal compositions (analytic signal) and total crust composition (total magnetic signal), so their variation as measured indicates either shallow or whole crustal structures. The Cacapava shear is outstanding on the images as is the magnetic low along the N-S central portion of the shield. These integrated observations lead to the deepening of the understanding of the largest and even detailed structures of the Sul-Riograndense Shield, some to be correlated to field geology in future studies. Most significant is the presence of different provinces and their limits depending on the method used for data acquisition - geology, aero gamma spectrometry or aero magnetometry. (author)

  12. Aero-Acoustic Modelling using Large Eddy Simulation

    International Nuclear Information System (INIS)

    Shen, W Z; Soerensen, J N

    2007-01-01

    The splitting technique for aero-acoustic computations is extended to simulate three-dimensional flow and acoustic waves from airfoils. The aero-acoustic model is coupled to a sub-grid-scale turbulence model for Large-Eddy Simulations. In the first test case, the model is applied to compute laminar flow past a NACA 0015 airfoil at a Reynolds number of 800, a Mach number of 0.2 and an angle of attack of 20 deg. The model is then applied to compute turbulent flow past a NACA 0015 airfoil at a Reynolds number of 100 000, a Mach number of 0.2 and an angle of attack of 20 deg. The predicted noise spectrum is compared to experimental data

  13. Sensor fault diagnosis of aero-engine based on divided flight status.

    Science.gov (United States)

    Zhao, Zhen; Zhang, Jun; Sun, Yigang; Liu, Zhexu

    2017-11-01

    Fault diagnosis and safety analysis of an aero-engine have attracted more and more attention in modern society, whose safety directly affects the flight safety of an aircraft. In this paper, the problem concerning sensor fault diagnosis is investigated for an aero-engine during the whole flight process. Considering that the aero-engine is always working in different status through the whole flight process, a flight status division-based sensor fault diagnosis method is presented to improve fault diagnosis precision for the aero-engine. First, aero-engine status is partitioned according to normal sensor data during the whole flight process through the clustering algorithm. Based on that, a diagnosis model is built for each status using the principal component analysis algorithm. Finally, the sensors are monitored using the built diagnosis models by identifying the aero-engine status. The simulation result illustrates the effectiveness of the proposed method.

  14. Sensor fault diagnosis of aero-engine based on divided flight status

    Science.gov (United States)

    Zhao, Zhen; Zhang, Jun; Sun, Yigang; Liu, Zhexu

    2017-11-01

    Fault diagnosis and safety analysis of an aero-engine have attracted more and more attention in modern society, whose safety directly affects the flight safety of an aircraft. In this paper, the problem concerning sensor fault diagnosis is investigated for an aero-engine during the whole flight process. Considering that the aero-engine is always working in different status through the whole flight process, a flight status division-based sensor fault diagnosis method is presented to improve fault diagnosis precision for the aero-engine. First, aero-engine status is partitioned according to normal sensor data during the whole flight process through the clustering algorithm. Based on that, a diagnosis model is built for each status using the principal component analysis algorithm. Finally, the sensors are monitored using the built diagnosis models by identifying the aero-engine status. The simulation result illustrates the effectiveness of the proposed method.

  15. 76 FR 77108 - Airworthiness Directives; International Aero Engines Turbofan Engines

    Science.gov (United States)

    2011-12-12

    ... Airworthiness Directives; International Aero Engines Turbofan Engines AGENCY: Federal Aviation Administration...-D5, V2530-A5, and V2533-A5 turbofan engines. This AD was prompted by three reports of high- pressure..., V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528- D5, V2530-A5, and V2533-A5 turbofan engines...

  16. Maintenance Decision Based on Data Fusion of Aero Engines

    Directory of Open Access Journals (Sweden)

    Huawei Wang

    2013-01-01

    Full Text Available Maintenance has gained a great importance as a support function for ensuring aero engine reliability and availability. Cost-effectiveness and risk control are two basic criteria for accurate maintenance. Given that aero engines have much condition monitoring data, this paper presents a new condition-based maintenance decision system that employs data fusion for improving accuracy of reliability evaluation. Bayesian linear model has been applied, so that the performance degradation evaluation of aero engines could be realized. A reliability evaluation model has been presented based on gamma process, which achieves the accurate evaluation by information fusion. In reliability evaluation model, the shape parameter is estimated by the performance degradation evaluation result, and the scale parameter is estimated by failure, inspection, and repair information. What is more, with such reliability evaluation as input variables and by using particle swarm optimization (PSO, a stochastic optimization of maintenance decision for aircraft engines has been presented, in which the effectiveness and the accuracy are demonstrated by a numerical example.

  17. 78 FR 22168 - Airworthiness Directives; International Aero Engines AG Turbofan Engines

    Science.gov (United States)

    2013-04-15

    ... Airworthiness Directives; International Aero Engines AG Turbofan Engines AGENCY: Federal Aviation Administration... International Aero Engines AG (IAE), V2525-D5 and V2528-D5 turbofan engines, with a certain No. 4 bearing... turbofan engines, serial numbers V20001 through V20285, with No. 4 bearing internal scavenge tube, part...

  18. 76 FR 60396 - Airworthiness Directives; Piaggio Aero Industries S.p.A. Airplanes

    Science.gov (United States)

    2011-09-29

    ...., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service... on other P.180 aeroplanes, and Piaggio Aero Industries (PAI) had issued Service Bulletin (SB) No. 80... information by examining the MCAI in the AD docket. Relevant Service Information Piaggio Aero Industries S.p.A...

  19. 77 FR 35888 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Airplanes

    Science.gov (United States)

    2012-06-15

    ...., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service.... Relevant Service Information PIAGGIO AERO INDUSTRIES S.p.A. has issued Service Bulletin No. 80- 0318, dated... Instructions of Piaggio Aero Industries S.p.A. Mandatory Service Bulletin No. 80-0318, revision 2, dated March...

  20. 78 FR 36691 - Airworthiness Directives; Piaggio Aero Industries S.p.A Airplanes

    Science.gov (United States)

    2013-06-19

    ...., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service... condition, Piaggio Aero Industries (PAI) issued Service Bulletin (SB) 80-0345 to provide instructions for... in the AD docket. Relevant Service Information Piaggio Aero Industries S.p.A. has issued Mandatory...

  1. 76 FR 27872 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model P-180 Airplanes

    Science.gov (United States)

    2011-05-13

    ... through Friday, except Federal holidays. For service information identified in this AD, contact Piaggio... accomplishment instructions of Piaggio Aero Industries Alert Service Bulletin ASB- 80-0324, step 5, this AD.... Relevant Service Information PIAGGIO AERO INDUSTRIES S.p.A has issued Service Bulletin (Mandatory) N.: 80...

  2. 78 FR 69600 - Airworthiness Directives; Piaggio Aero Industries S.p.A Airplanes

    Science.gov (United States)

    2013-11-20

    ... p.m., Monday through Friday, except Federal holidays. For service information identified in this.... To address this potential unsafe condition, Piaggio Aero Industries (PAI) issued Service [[Page 69601... Service Information Piaggio Aero Industries S.p.A. has issued Mandatory Service Bulletin No.: 80-0381, Rev...

  3. 76 FR 54403 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Science.gov (United States)

    2011-09-01

    ... Federal holidays. For service information identified in this proposed AD, contact Piaggio Aero Industries... Service Information Piaggio Aero Industries S.p.A. has issued Mandatory Service Bulletin No. 80-0304... Accomplishment Instructions of Piaggio Aero Industries S.p.A. Mandatory Service Bulletin No. 80-0304, dated July...

  4. Aero-acoustics noise assessment for Wind-Lens turbine

    International Nuclear Information System (INIS)

    Hashem, I.; Mohamed, M.H.; Hafiz, A.A.

    2017-01-01

    This paper introduces an aero-acoustic computational study that investigates the noise caused by one of the most promising wind energy conversion concepts, namely the 'Wind-Lens' technology. The hybrid method - where the flow field and acoustic field are solved separately, was deemed to be an appropriate tool to compute this study. The need to investigate this phenomenon increased gradually, since the feasibility of utilizing Wind-Lens turbine within densely populated cities and urban areas depends largely on their noise generation. Ffowcs Williams-Hawkings (FW-H) equation and its integral solution are used to predict the noise radiating to the farfield. CFD Simulations of transient three-dimensional flow field using (URANS) unsteady Reynolds-averaged Navier-Stokes equations are computed to acquire the acoustic sources location and sound intensity. Then, the noise propagates from the before-mentioned sources to pre-defined virtual microphones positioned in different locations. ANSYS-FLUENT is used to calculate the flow field on and around such turbines which is required for the FW-H code. Some effective parameters are investigated such as Wind-Lens shape, brim height and tip speed ratio. Comparison of the noise emitted from the bare wind turbine and different types of Wind-Lens turbine reveals that, the Wind-Lens generates higher noise intensity. - Highlights: • Aero-acoustic noise generated by wind turbines are one of the major challenges. • Noise from wind turbine equipped with a brimmed diffuser is investigated. • A computational aero-acoustic study using the hybrid method is introduced. • Effective parameters are studied such Wind-Lens shape, brim height and speed ratio. • The optimal shape has a moderate power coefficient and the less noise generation.

  5. Future NASA Power Technologies for Space and Aero Propulsion Applications

    Science.gov (United States)

    Soeder, James F.

    2015-01-01

    To achieve the ambitious goals that NASA has outlined for the next decades considerable development of power technology will be necessary. This presentation outlines the development objectives for both space and aero applications. It further looks at the various power technologies that support these objectives and examines drivers that will be a driving force for future development. Finally, the presentation examines what type of non-traditional learning areas should be emphasized in student curriculum so that the engineering needs of the third decade of the 21st Century are met.

  6. Aero-acoustic noise of wind turbines. Noise prediction models

    Energy Technology Data Exchange (ETDEWEB)

    Maribo Pedersen, B. [ed.

    1997-12-31

    Semi-empirical and CAA (Computational AeroAcoustics) noise prediction techniques are the subject of this expert meeting. The meeting presents and discusses models and methods. The meeting may provide answers to the following questions: What Noise sources are the most important? How are the sources best modeled? What needs to be done to do better predictions? Does it boil down to correct prediction of the unsteady aerodynamics around the rotor? Or is the difficult part to convert the aerodynamics into acoustics? (LN)

  7. Optimization of Aero Engine Acceleration Control in Combat State Based on Genetic Algorithms

    Science.gov (United States)

    Li, Jie; Fan, Ding; Sreeram, Victor

    2012-03-01

    In order to drastically exploit the potential of the aero engine and improve acceleration performance in the combat state, an on-line optimized controller based on genetic algorithms is designed for an aero engine. For testing the validity of the presented control method, detailed joint simulation tests of the designed controller and the aero engine model are performed in the whole flight envelope. Simulation test results show that the presented control algorithm has characteristics of rapid convergence speed, high efficiency and can fully exploit the acceleration performance potential of the aero engine. Compared with the former controller, the designed on-line optimized controller (DOOC) can improve the security of the acceleration process and greatly enhance the aero engine thrust in the whole range of the flight envelope, the thrust increases an average of 8.1% in the randomly selected working states. The plane which adopts DOOC can acquire better fighting advantage in the combat state.

  8. Computation and analysis of backward ray-tracing in aero-optics flow fields.

    Science.gov (United States)

    Xu, Liang; Xue, Deting; Lv, Xiaoyi

    2018-01-08

    A backward ray-tracing method is proposed for aero-optics simulation. Different from forward tracing, the backward tracing direction is from the internal sensor to the distant target. Along this direction, the tracing in turn goes through the internal gas region, the aero-optics flow field, and the freestream. The coordinate value, the density, and the refractive index are calculated at each tracing step. A stopping criterion is developed to ensure the tracing stops at the outer edge of the aero-optics flow field. As a demonstration, the analysis is carried out for a typical blunt nosed vehicle. The backward tracing method and stopping criterion greatly simplify the ray-tracing computations in the aero-optics flow field, and they can be extended to our active laser illumination aero-optics study because of the reciprocity principle.

  9. Interference Analysis Status and Plans for Aeronautical Mobile Airport Communications System (AeroMACS)

    Science.gov (United States)

    Kerczewski, Robert J.; Wilson, Jeffrey D.

    2010-01-01

    Interference issues related to the operation of an aeronautical mobile airport communications system (AeroMACS) in the C-Band (specifically 5091-5150 MHz) is being investigated. The issue of primary interest is co-channel interference from AeroMACS into mobile-satellite system (MSS) feeder uplinks. The effort is focusing on establishing practical limits on AeroMACS transmissions from airports so that the threshold of interference into MSS is not exceeded. The analyses are being performed with the software package Visualyse Professional, developed by Transfinite Systems Limited. Results with omni-directional antennas and plans to extend the models to represent AeroMACS more accurately will be presented. These models should enable realistic analyses of emerging AeroMACS designs to be developed from NASA Test Bed, RTCA 223, and European results.

  10. Optimization of Heat Exchangers for Intercooled Recuperated Aero Engines

    Directory of Open Access Journals (Sweden)

    Dimitrios Misirlis

    2017-03-01

    Full Text Available In the framework of the European research project LEMCOTEC, a section was devoted to the further optimization of the recuperation system of the Intercooled Recuperated Aero engine (IRA engine concept, of MTU Aero Engines AG. This concept is based on an advanced thermodynamic cycle combining both intercooling and recuperation. The present work is focused only on the recuperation process. This is carried out through a system of heat exchangers mounted inside the hot-gas exhaust nozzle, providing fuel economy and reduced pollutant emissions. The optimization of the recuperation system was performed using computational fluid dynamics (CFD computations, experimental measurements and thermodynamic cycle analysis for a wide range of engine operating conditions. A customized numerical tool was developed based on an advanced porosity model approach. The heat exchangers were modeled as porous media of predefined heat transfer and pressure loss behaviour and could also incorporate major and critical heat exchanger design decisions in the CFD computations. The optimization resulted in two completely new innovative heat exchanger concepts, named as CORN (COnical Recuperative Nozzle and STARTREC (STraight AnnulaR Thermal RECuperator, which provided significant benefits in terms of fuel consumption, pollutants emission and weight reduction compared to more conventional heat exchanger designs, thus proving that further optimization potential for this technology exists.

  11. AeroVironment technician checks a Helios solar cell panel

    Science.gov (United States)

    2000-01-01

    A technician at AeroVironment's Design Development Center in Simi Valley, California, checks a panel of silicon solar cells for conductivity and voltage. The bi-facial cells, fabricated by SunPower, Inc., of Sunnyvale, California, are among 64,000 solar cells which have been installed on the Helios Prototype solar-powered aircraft to provide power to its 14 electric motors and operating systems. Developed by AeroVironment under NASA's Environmental Research Aircraft and Sensor Technology (ERAST) project, the Helios Prototype is the forerunner of a planned fleet of slow-flying, long duration, high-altitude aircraft which can perform atmospheric science missions and serve as telecommunications relay platforms in the stratosphere. Target goals set by NASA for the giant 246-foot span flying wing include reaching and sustaining subsonic horizontal flight at 100,000 feet altitude in 2001, and sustained continuous flight for at least four days and nights above 50,000 feet altitude with the aid of a regenerative fuel cell-based energy storage system now under development in 2003.

  12. Spectral Behavior of Weakly Compressible Aero-Optical Distortions

    Science.gov (United States)

    Mathews, Edwin; Wang, Kan; Wang, Meng; Jumper, Eric

    2016-11-01

    In classical theories of optical distortions by atmospheric turbulence, an appropriate and key assumption is that index-of-refraction variations are dominated by fluctuations in temperature and the effects of turbulent pressure fluctuations are negligible. This assumption is, however, not generally valid for aero-optical distortions caused by turbulent flow over an optical aperture, where both temperature and pressures fluctuations may contribute significantly to the index-of-refraction fluctuations. A general expression for weak fluctuations in refractive index is derived using the ideal gas law and Gladstone-Dale relation and applied to describe the spectral behavior of aero-optical distortions. Large-eddy simulations of weakly compressible, temporally evolving shear layers are then used to verify the theoretical results. Computational results support theoretical findings and confirm that if the log slope of the 1-D density spectrum in the inertial range is -mρ , the optical phase distortion spectral slope is given by - (mρ + 1) . The value of mρ is then shown to be dependent on the ratio of shear-layer free-stream densities and bounded by the spectral slopes of temperature and pressure fluctuations. Supported by HEL-JTO through AFOSR Grant FA9550-13-1-0001 and Blue Waters Graduate Fellowship Program.

  13. Predicting Cavitation on Marine and Hydrokinetic Turbine Blades with AeroDyn V15.04

    Energy Technology Data Exchange (ETDEWEB)

    Murray, Robynne [National Renewable Energy Laboratory (NREL), Golden, CO (United States)

    2017-09-14

    Cavitation is an important consideration in the design of marine and hydrokinetic (MHK) turbines. The National Renewable Energy Laboratory's AeroDyn performance code was originally developed for horizontal-axis wind turbines and did not have the capability to predict cavitation inception. Therefore, AeroDyn has been updated to include the ability to predict cavitation on MHK turbines based on user-specified vapor pressure and submerged depth. This report outlines a verification of the AeroDyn V15.04 performance code for MHK turbines through a comparison to publicly available performance data.

  14. Cancer chemotherapy of the upper aero digestive tract

    International Nuclear Information System (INIS)

    Vedrine, L.; Chargari, C.; Le Moulec, S.; Fayolle, M.; Ceccaldi, B.; Bauduceau, O.

    2008-01-01

    Tumours of the upper aero digestive tract represent the sixth most frequent kind of cancer in France and throughout the world. If the localised forms may be controlled in the long run in two thirds of cases by surgery or radiotherapy, only one third of locally advanced forms are accessible to a cure after association from radiotherapy and chemotherapy. Besides, with a median of survival less than six months, metastatic tumours present a catastrophic spontaneous prognosis among patients with a medical ground that is often heavily deteriorated by prolonged exposure to alcohol and tobacco. Thus, there is a necessity to implement adapted therapeutic strategies to each patient and based on satisfactory proof levels of effectiveness. Optimisation of existing chemotherapy protocols and development of new therapies, in particular of targeted therapies, remain an important objective in the hope to improve results of treatments in locally advanced and metastatic cancers of the oral cavity. (authors)

  15. Marketingový mix volejbalového klubu Aero Odolena Voda

    OpenAIRE

    Hons, Michal

    2013-01-01

    Title: Volleyball club Aero Odolena Voda marketing mix analysis Targets: To perform an overall evaluation of the current Aero Odolena Voda marketing mix, using SWOT analysis bring strenghts and weaknesses to light. Based on this analysis suggest possible modification that would lead to a better marketing mix. Methods: Using qualitative methods such as interview, alongside with quantitative methods such as questioning, SWOT analysis and using secundary dates. Results: The specific modification...

  16. A SERIES OF UNCOMMON FOREIGN BODIES PRESENTING IN THE AERO-DIGESTIVE TRACT

    Directory of Open Access Journals (Sweden)

    Jitendra Singh

    2016-02-01

    Full Text Available Foreign body impacted in the aero-digestive tract is one of the earliest reported problems. Coins, buttons, marbles, crayons, parts of toys etc. are the most commonly ingested foreign bodies in children. Fish, meat and chicken bones, dentures, nails etc.the most common foreign bodies ingested by adultsWe report a series of unusual foreign body ingestion in aero-digestive tract and their management by endoscopic retrieval.

  17. The DAN-AERO MW experiments. Final report

    Energy Technology Data Exchange (ETDEWEB)

    Aagaard Madsen, H.; Bak, C.; Schmidt Paulsen, U.; Gaunaa, M. (Risoe DTU, Roskilde (Denmark)); Fuglsang, P. (LM Glasfiber, Kolding (Denmark)); Romblad, J.; Olesen, N.A. (Vestas Wind Systems, Ringkoebing (Denmark)); Enevoldsen, P.; Laursen, J. (Siemens Wind Power, Ballerup (Denmark)); Jensen, Leo (DONG Energy, Fredericia (Denmark))

    2010-09-15

    This report describes the DAN-AERO MW experiments carried out within a collaborative, three years research project between Risoe DTU and the industrial partners LM Glasfiber, Siemens Wind Power, Vestas Wind Systems A/S and the utility company DONG Energy. The main objective of the project was to establish an experimental data base which can provide new insight into a number of fundamental aerodynamic and aero-acoustic issues, important for the design and operation of MW size turbines. The most important issue is the difference between airfoil characteristics measured under 2D, steady conditions in a wind tunnel and the unsteady 3D flow conditions on a rotor. The different transition characteristics might explain some of the differences between the 2D and 3D airfoil data and the experiments have been set up to provide data on this subject. The overall experimental approach has been to carry out a number of coordinated, innovative measurements on full scale MW size rotors as well as on airfoils for MW size turbines in wind tunnels. Shear and turbulence inflow characteristics were measured on a Siemens 3.6 MW turbine with a five hole pitot tube. Pressure and turbulent inflow characteristics were measured on a 2MW NM80 turbine with an 80 m rotor. One of the LM38.8 m blades on the rotor was replaced with a new LM38.8 m blade where instruments for surface pressure measurements at four radial sections were build into the blade during the blade production process. Additionally, the outmost section on the blade was further instrumented with around 50 microphones for high frequency surface pressure measurements. The surface pressure measurements have been correlated with inflow measurements from four five hole pitot tubes and two sensors for measuring the high frequency (50 Hz to10 kHz) contents of the inflow turbulence. In parallel, 2D wind tunnel measurements on common airfoils for wind turbine applications have been conducted in three different wind tunnels at Delft

  18. Experimental investigation on aero-optics of supersonic turbulent boundary layers.

    Science.gov (United States)

    Ding, Haolin; Yi, Shihe; Zhu, Yangzhu; He, Lin

    2017-09-20

    Nanoparticle-based planar laser scattering was used to measure the density distribution of the supersonic (Ma=3.0) turbulent boundary layer and the optical path difference (OPD), which is quite crucial for aero-optics study. Results were obtained using ray tracing. The influences of different layers in the boundary layer, turbulence scales, and light incident angle on aero-optics were examined, and the underlying flow physics were analyzed. The inner layer plays a dominant role, followed by the outer layer. One hundred OPD rms of the outer layer at different times satisfy the normal distribution better than that of the inner layer. Aero-optics induced by the outer layer is sensitive to the filter scale. When induced by the inner layer, it is not sensitive to the filter scale. The vortices with scales less than the Kolmogorov scale (=46.0  μm) have little influence on the aero-optics and could be ignored; the validity of the smallest optically active scale (=88.1  μm) proposed by Mani is verified, and vortices with scales less than that are ignored, resulting in a 1.62% decay of aero-optics; the filter with a width of 16-grid spacing (=182.4  μm) decreases OPD rms by 7.04%. With the increase of the angle between the wall-normal direction and the light-incident direction, the aero-optics becomes more serious, and the difference between the distribution of the OPD rms and the normal distribution increases. The difficulty of aero-optics correction is increased. Light tilted toward downstream experiences more distortions than when tilted toward upstream at the same angle relative to the wall-normal direction.

  19. Aero-methods and engineering research and development

    Energy Technology Data Exchange (ETDEWEB)

    Peterson, R K

    1979-01-01

    There is presently a sharp, ongoing increase in the volume of work being conducted throughout the country associated with the development of natural gas fields as well as the resulting accelerated development of major gas trunklines. Aero-methods have presently found wide application in the engineering and planning of equipment for such projects. Success has been obtained by the increased quantity and quality of the available engineering information: The ''Giprospetsgaz'' Institute is using aerial photography as the basis for selecting pipeline routes and to more accurately determine the equipment requirements along proposed trunklines such as for compressors, gas transfer stations, electrical power substations, worker settlements, water and transport infrastructure and communications. These requirements are the most important factors in reducing capital operating expenditures. The greatest savings, in economic terms, can be achieved by avoiding sparsely settled or uninhabited areas as much as possible. Similiarly, aerial photography coupled with computer application aids in the solution of engineering problems. Third-generation computers are recommended for this process.

  20. Spatial-temporal-covariance-based modeling, analysis, and simulation of aero-optics wavefront aberrations.

    Science.gov (United States)

    Vogel, Curtis R; Tyler, Glenn A; Wittich, Donald J

    2014-07-01

    We introduce a framework for modeling, analysis, and simulation of aero-optics wavefront aberrations that is based on spatial-temporal covariance matrices extracted from wavefront sensor measurements. Within this framework, we present a quasi-homogeneous structure function to analyze nonhomogeneous, mildly anisotropic spatial random processes, and we use this structure function to show that phase aberrations arising in aero-optics are, for an important range of operating parameters, locally Kolmogorov. This strongly suggests that the d5/3 power law for adaptive optics (AO) deformable mirror fitting error, where d denotes actuator separation, holds for certain important aero-optics scenarios. This framework also allows us to compute bounds on AO servo lag error and predictive control error. In addition, it provides us with the means to accurately simulate AO systems for the mitigation of aero-effects, and it may provide insight into underlying physical processes associated with turbulent flow. The techniques introduced here are demonstrated using data obtained from the Airborne Aero-Optics Laboratory.

  1. Fault Diagnosis of Demountable Disk-Drum Aero-Engine Rotor Using Customized Multiwavelet Method

    Directory of Open Access Journals (Sweden)

    Jinglong Chen

    2015-10-01

    Full Text Available The demountable disk-drum aero-engine rotor is an important piece of equipment that greatly impacts the safe operation of aircraft. However, assembly looseness or crack fault has led to several unscheduled breakdowns and serious accidents. Thus, condition monitoring and fault diagnosis technique are required for identifying abnormal conditions. Customized ensemble multiwavelet method for aero-engine rotor condition identification, using measured vibration data, is developed in this paper. First, customized multiwavelet basis function with strong adaptivity is constructed via symmetric multiwavelet lifting scheme. Then vibration signal is processed by customized ensemble multiwavelet transform. Next, normalized information entropy of multiwavelet decomposition coefficients is computed to directly reflect and evaluate the condition. The proposed approach is first applied to fault detection of an experimental aero-engine rotor. Finally, the proposed approach is used in an engineering application, where it successfully identified the crack fault of a demountable disk-drum aero-engine rotor. The results show that the proposed method possesses excellent performance in fault detection of aero-engine rotor. Moreover, the robustness of the multiwavelet method against noise is also tested and verified by simulation and field experiments.

  2. 75 FR 67639 - Airworthiness Directives; Piaggio Aero Industries S.p.A Model PIAGGIO P-180 Airplanes

    Science.gov (United States)

    2010-11-03

    ... Friday, except Federal holidays. For service information identified in this proposed AD, contact Piaggio... Piaggio Aero Industries have issued service information (referred to after this as ``the MCAI''), to... Information Piaggio Aero Industries S.p.A. has issued Service Bulletin (Mandatory) N.: SB 80-0275, Rev. N. 0...

  3. Numerical Investigation on Windback Seals Used in Aero Engines

    Directory of Open Access Journals (Sweden)

    Michael Flouros

    2018-01-01

    Full Text Available Seals are considered one of the most important flow elements in turbomachinery applications. The most traditional and widely known seal is the labyrinth seal but in recent years other types like the brush or carbon seals were introduced since they considerably reduce the sealing air consumption. When seals are used for sealing of aero engine bearing chambers they are subjected to high “bombardment” through oil particles which are present in the bearing chamber. These particles mainly result from the bearings as a consequence of the high rotational speeds. Particularly when carbon or brush seals are used, problems with carbon formation (coking may arise when oil gets trapped in the very tight gap of these seals. In order to prevent oil migration into the turbomachinery, particularly when the pressure difference over a seal is small or even negligible, significant improvement can be achieved through the introduction of so called windback seals. This seal has a row of static helical teeth (thread and below this thread a scalloped or smooth shaft section is rotating. Depending on the application, a windback seal can be used alone or as a combination with another seal (carbon, brush or labyrinth seal. A CFD analysis carried out with ANSYS CFX version 11 is presented in this paper with the aim to investigate this seal type. The simulations were performed by assuming a two-phase flow of air and oil in the bearing compartment. Design parameters like seal clearance, thread size, scallop width, were investigated at different operating conditions.

  4. SFC Optimization for Aero Engine Based on Hybrid GA-SQP Method

    Science.gov (United States)

    Li, Jie; Fan, Ding; Sreeram, Victor

    2013-12-01

    This study focuses on on-line specific fuel consumption (SFC) optimization of aero engines. For solving this optimization problem, a nonlinear pneumatic and thermodynamics model of the aero engine is built and a hybrid optimization technique which is formed by combining the genetic algorithm (GA) and the sequential quadratic programming (SQP) is presented. The ability of standard GA and standard SQP in solving this type of problem is investigated. It has been found that, although the SQP is fast, very little SFC reductions can be obtained. The GA is able to solve the problem well but a lot of computational time is needed. The presented hybrid GA-SQP gives a good SFC optimization effect and saves 76.6% computational time when compared to the standard GA. It has been shown that the hybrid GA-SQP is a more effective and higher real-time method for SFC on-line optimization of the aero engine.

  5. High-Temperature Adhesives for Thermally Stable Aero-Assist Technologies

    Science.gov (United States)

    Eberts, Kenneth; Ou, Runqing

    2013-01-01

    Aero-assist technologies are used to control the velocity of exploration vehicles (EVs) when entering Earth or other planetary atmospheres. Since entry of EVs in planetary atmospheres results in significant heating, thermally stable aero-assist technologies are required to avoid the high heating rates while maintaining low mass. Polymer adhesives are used in aero-assist structures because of the need for high flexibility and good bonding between layers of polymer films or fabrics. However, current polymer adhesives cannot withstand temperatures above 400 C. This innovation utilizes nanotechnology capabilities to address this need, leading to the development of high-temperature adhesives that exhibit high thermal conductivity in addition to increased thermal decomposition temperature. Enhanced thermal conductivity will help to dissipate heat quickly and effectively to avoid temperature rising to harmful levels. This, together with increased thermal decomposition temperature, will enable the adhesives to sustain transient high-temperature conditions.

  6. Problems of Aero-optics and Adaptive Optical Systems: Analytical Review

    Directory of Open Access Journals (Sweden)

    Yu. I. Shanin

    2017-01-01

    Full Text Available The analytical review gives the basic concepts of the aero-optics problem arising from the radiation propagation in the region of the boundary layers of a laser installation carrier aircraft. Estimates the radiation wave front distortions at its propagation in the near and far field. Presents main calculation approaches and methods to solve the gas-dynamic and optical problems in propagating laser radiation. Conducts a detailed analysis of the flows and their generating optical aberrations introduced by the aircraft turret (a projection platform of the on-board laser. Considers the effect of various factors (shock wave, difference in wall and flow temperatures on the flow pattern and the optical aberrations. Provides research data on the aero-optics obtained in the flying laboratory directly while in flight. Briefly considers the experimental research methods, diagnostic equipment, and synthesis of results while studying the aero-optics problem. Discusses some methods for mitigating the aerodynamic effects on the light propagation under flight conditions. Presents data about the passive, active, and hybrid effects on the flow in the boundary layers in order to reduce aberrations through improving the flow aerodynamics.The paper considers operation of adaptive optical systems under conditions of aero-optical distortions. Presents the study results concerning the reduction of the aero-optics effect on the characteristics of radiation in far field. Gives some research results regarding the effect on the efficiency of the adaptive system of a laser beam jitter and a time delay in the feedback signal transmission, which occur under application conditions. Provides data on adaptive correction of aero-optical wave fronts of radiation. Considers some application aspects in control systems of the on-board adaptive optics of adaptive filtration as a way to improve the efficiency of adaptive optical systems. The project in mind is to use obtained results

  7. Aero-MINE (Motionless INtegrated Energy) for Distributed Scalable Wind Power.

    Energy Technology Data Exchange (ETDEWEB)

    Houchens, Brent C. [Lawrence Livermore National Lab. (LLNL), Livermore, CA (United States); Blaylock, Myra L. [Lawrence Livermore National Lab. (LLNL), Livermore, CA (United States)

    2017-06-01

    The proposed Aero-MINE technology will extract energy from wind without any exterior moving parts. Aero-MINEs can be integrated into buildings or function stand-alone, and are scalable. This gives them advantages similar to solar panels, but with the added benefit of operation in cloudy or dark conditions. Furthermore, compared to solar panels, Aero-MINEs can be manufactured at lower cost and with less environmental impact. Power generation is isolated internally by the pneumatic transmission of air and the outlet air-jet nozzles amplify the effectiveness. Multiple units can be connected to one centrally located electric generator. Aero-MINEs are ideal for the built-environment, with numerous possible configurations ranging from architectural integration to modular bolt-on products. Traditional wind turbines suffer from many fundamental challenges. The fast-moving blades produce significant aero-acoustic noise, visual disturbances, light-induced flickering and impose wildlife mortality risks. The conversion of massive mechanical torque to electricity is a challenge for gears, generators and power conversion electronics. In addition, the installation, operation and maintenance of wind turbines is required at significant height. Furthermore, wind farms are often in remote locations far from dense regions of electricity customers. These technical and logistical challenges add significantly to the cost of the electricity produced by utility-scale wind farms. In contrast, distributed wind energy eliminates many of the logistical challenges. However, solutions such as micro-turbines produce relatively small amounts of energy due to the reduction in swept area and still suffer from the motion-related disadvantages of utility-scale turbines. Aero-MINEs combine the best features of distributed generation, while eliminating the disadvantages.

  8. Concept of the aero-train and its aerodynamic stability nature

    OpenAIRE

    Kohama, Yasuaki P.; Watanabe, Hideo; Kikuchi, Satoshi; Ota, Fukuo; Ito, Takatoshi; 小濱 泰昭; 渡部 英夫; 菊池 聡; 太田 福雄; 伊藤 高敏

    2000-01-01

    Taking into account the serious greenhouse effect of the earth, drastic proposal which prevents the carbon dioxide emission from transportation system must be done. In Japan, over 20 percent of the carbon dioxide are emitted from transportation. Aero-train is the new zero-emission high speed vehicle, which is being proposed. Wing in ground effect is introduced to obtain highest lift to drag ratio and highest payload ratio. In order to compare the performance of the aero-train at 500 km/h, wit...

  9. Identified state-space prediction model for aero-optical wavefronts

    Science.gov (United States)

    Faghihi, Azin; Tesch, Jonathan; Gibson, Steve

    2013-07-01

    A state-space disturbance model and associated prediction filter for aero-optical wavefronts are described. The model is computed by system identification from a sequence of wavefronts measured in an airborne laboratory. Estimates of the statistics and flow velocity of the wavefront data are shown and can be computed from the matrices in the state-space model without returning to the original data. Numerical results compare velocity values and power spectra computed from the identified state-space model with those computed from the aero-optical data.

  10. System Aero-Accelator for the purification of biodegradable effluents; Sistema aero-accelator para la depuracion de efluentes biodegradables (I)

    Energy Technology Data Exchange (ETDEWEB)

    Bosque Hernandez, J. L. del; Martin Sanchez, J. L. [Universidad de Salamanca (Spain)

    2000-07-01

    The contamination of the waters is one of the factors that contributes to the deterioration of our environment and since it is a very limited one its treatment descontaminant it is one of the politic's main objectives and environmental administration at all the levels, being spread to the total purification of the generated residual effluents. To reach this objective, big technological efforts are required that allow next to the creation of new processes, the adaptation of the processes existent depuratives, increasing the effectiveness of the same ones. One of the techniques of purification of possible recovery is the Compact System of active mires Aero-Accelator. Presently work is designed and it builds a plant pilot with Aero-Accelator geometry to study its behavior in the treatment of effluents of urban type with different loads pollutants. (Author) 16 refs.

  11. General catalogue of products and services - geology. AERO data base; 2. ed; Catalogo geral de produtos e servicos - geologia. Base de dados AERO

    Energy Technology Data Exchange (ETDEWEB)

    NONE

    1996-12-31

    The catalogue in the second edition aims at presenting to the user a general idea on the aerogeophysical projects of Brazil database (AERO) which belongs to SIGA (Brazilian geological information system). The 151 documents (projects) are listed as follows: 52 projects performed by CPRM/DNPM - Departamento Nacional de Producao Mineral; 33 projects performed by CNEN - Commissao Nacional de Energia Nuclear and NUCLEBRAS; 7 projects executed by State government and private companies; and 59 projects executed for PETROBRAS 159 figs., 5 tabs.

  12. General catalogue of products and services - geology. AERO data base; 2. ed; Catalogo geral de produtos e servicos - geologia. Base de dados AERO

    Energy Technology Data Exchange (ETDEWEB)

    NONE

    1995-12-31

    The catalogue in the second edition aims at presenting to the user a general idea on the aerogeophysical projects of Brazil database (AERO) which belongs to SIGA (Brazilian geological information system). The 151 documents (projects) are listed as follows: 52 projects performed by CPRM/DNPM - Departamento Nacional de Producao Mineral; 33 projects performed by CNEN - Commissao Nacional de Energia Nuclear and NUCLEBRAS; 7 projects executed by State government and private companies; and 59 projects executed for PETROBRAS 159 figs., 5 tabs.

  13. The Application of Advanced Technique of Fan Frame Unit on High Bypass Ratio Aero Engine

    Directory of Open Access Journals (Sweden)

    Hou Peng

    2017-01-01

    Full Text Available High bypass ratio aero-engine was widely used on military and civil aviation domain, as the power of larger aircraft. Fan frame unit was the main bearing frame of high bypass ratio aero-engine, which composed of strut, HUB MID BOX and external bypass parts. Resin/composite was used on external bypass parts(acoustic liner, containment ring, fan outlet guide vane and fan case skin fillets, which not only reduced the weight and manufacturing cost, but also improved the noise absorption, containment and anti-fatigue ability of engine. The design of composite was becoming a key technique for high bypass ratio aero-engine. In special test of the core engine, nitrogen cooling system was designed to cool the cavity of spool. The nitrogen pipeline passed through the inner cavity of fan frame, then inserted into NO. 3 bearing seal, so nitrogen gas was sent into the cavity of core engine spool. On high bypass ratio aero-engine, the external bypass and fan frame inner cavity were the design platform for advanced technique, such as composite and pipeline system, and also provided guarantee for reliable operation of engine.

  14. Performance of small-scale aero-derivative industrial gas turbines derived from helicopter engines

    Directory of Open Access Journals (Sweden)

    Barinyima Nkoi

    2013-12-01

    Full Text Available This paper considers comparative assessment of simple and advanced cycle small-scale aero-derivative industrial gas turbines derived from helicopter engines. More particularly, investigation was made of technical performance of the small-scale aero-derivative engine cycles based on existing and projected cycles for applications in industrial power generation, combined heat and power concept, rotating equipment driving, and/or allied processes. The investigation was done by carrying out preliminary design and performance simulation of a simple cycle (baseline two-spool small-scale aero-derivative turboshaft engine model, and some advanced counterpart aero-derivative configurations. The advanced configurations consist of recuperated and intercooled/recuperated engine cycles of same nominal power rating of 1.567 MW. The baseline model was derived from the conversion of an existing helicopter engine model. In doing so, design point and off-design point performances of the engine models were established. In comparing their performances, it was observed that to a large extent, the advanced engine cycles showed superior performance in terms of thermal efficiency, and specific fuel consumption. In numerical terms, thermal efficiencies of recuperated engine cycle, and intercooled/recuperated engine cycles, over the simple cycle at DP increased by 13.5%, and 14.5% respectively, whereas specific fuel consumption of these cycles over simple cycle at DP decreased by 12.5%, and 13% respectively. This research relied on open access public literature for data.

  15. FJ44 Turbofan Engine Test at NASA Glenn Research Center's Aero-Acoustic Propulsion Laboratory

    Science.gov (United States)

    Lauer, Joel T.; McAllister, Joseph; Loew, Raymond A.; Sutliff, Daniel L.; Harley, Thomas C.

    2009-01-01

    A Williams International FJ44-3A 3000-lb thrust class turbofan engine was tested in the NASA Glenn Research Center s Aero-Acoustic Propulsion Laboratory. This report presents the test set-up and documents the test conditions. Farfield directivity, in-duct unsteady pressures, duct mode data, and phased-array data were taken and are reported separately.

  16. 78 FR 1776 - Airworthiness Directives; International Aero Engines AG Turbofan Engines

    Science.gov (United States)

    2013-01-09

    ... Engines AG Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed... Aero Engines AG (IAE), V2525-D5 and V2528-D5 turbofan engines, with a certain number (No.) 4 bearing... proposed AD. Discussion We received a report of a fire warning on an IAE V2525 turbofan engine shortly...

  17. Aero-Hydro-Elastic Simulation Platform for Wave Energy Systems and floating Wind Turbines

    DEFF Research Database (Denmark)

    Kallesøe, Bjarne Skovmose

    This report present results from the PSO project 2008-1-10092 entitled Aero-Hydro-Elastic Simulation Platform for Wave Energy Systems and floating Wind Turbines that deals with measurements, modelling and simulations of the world’s first combined wave and wind energy platform. The floating energy...

  18. AERO: A Decision Support Tool for Wind Erosion Assessment in Rangelands and Croplands

    Science.gov (United States)

    Galloza, M.; Webb, N.; Herrick, J.

    2015-12-01

    Wind erosion is a key driver of global land degradation, with on- and off-site impacts on agricultural production, air quality, ecosystem services and climate. Measuring rates of wind erosion and dust emission across land use and land cover types is important for quantifying the impacts and identifying and testing practical management options. This process can be assisted by the application of predictive models, which can be a powerful tool for land management agencies. The Aeolian EROsion (AERO) model, a wind erosion and dust emission model interface provides access by non-expert land managers to a sophisticated wind erosion decision-support tool. AERO incorporates land surface processes and sediment transport equations from existing wind erosion models and was designed for application with available national long-term monitoring datasets (e.g. USDI BLM Assessment, Inventory and Monitoring, USDA NRCS Natural Resources Inventory) and monitoring protocols. Ongoing AERO model calibration and validation are supported by geographically diverse data on wind erosion rates and land surface conditions collected by the new National Wind Erosion Research Network. Here we present the new AERO interface, describe parameterization of the underpinning wind erosion model, and provide a summary of the model applications across agricultural lands and rangelands in the United States.

  19. Dependence of AeroMACS Interference on Airport Radiation Pattern Characteristics

    Science.gov (United States)

    Wilson, Jeffrey D.

    2012-01-01

    AeroMACS (Aeronautical Mobile Airport Communications System), which is based upon the IEEE 802.16e mobile wireless standard, is expected to be implemented in the 5091 to 5150 MHz frequency band. As this band is also occupied by Mobile Satellite Service (MSS) feeder uplinks, AeroMACS must be designed to avoid interference with this incumbent service. The aspects of AeroMACS operation that present potential interference are under analysis in order to enable the definition of standards that assure that such interference will be avoided. In this study, the cumulative interference power distribution at low earth orbit from AeroMACS transmitters at the 497 major airports in the contiguous United States was simulated with the Visualyse Professional software. The dependence of the interference power on the number of antenna beams per airport, gain patterns, and beam direction orientations was simulated. As a function of these parameters, the simulation results are presented in terms of the limitations on transmitter power required to maintain the cumulative interference power under the established threshold.

  20. Blades Forced Vibration Under Aero-Elastic Excitation Modeled by Van der Pol

    Czech Academy of Sciences Publication Activity Database

    Půst, Ladislav; Pešek, Luděk

    2017-01-01

    Roč. 27, č. 11 (2017), č. článku 1750166. ISSN 0218-1274 R&D Projects: GA ČR GA16-04546S Institutional support: RVO:61388998 Keywords : ade vibration * aero-elastic force * self-excitation * van der Pol Subject RIV: BI - Acoustics OBOR OECD: Applied mechanics Impact factor: 1.329, year: 2016

  1. Improving Aerospace Engineering Students' Achievements by an Open Aero Control Experiment Apparatus

    Science.gov (United States)

    Zeng, QingHua; Zhang, WeiHua; Huang, ZheZhi; Dong, RongHua

    2014-01-01

    This paper describes the development of an aero control experiment apparatus (ACEA) for use in aerospace control practical courses. The ACEA incorporates a systematic multihierarchy learning and teaching method, and was designed to improve aerospace engineering students' understanding of unmanned aerial vehicle (UAV) control systems. It offers a…

  2. Understanding Aero-Fractures using optics and acoustics

    Science.gov (United States)

    Turkaya, Semih; Toussaint, Renaud; Kvalheim Eriksen, Fredrik; Zecevic, Megan; Daniel, Guillaume; Grude Flekkøy, Eirik; Jørgen Måløy, Knut

    2016-04-01

    exponent p value around 0.5. An analytical model of overpressure diffusion predicting p = 0.5 and two other free parameters of the Omori Law (prefactor and origin time) is developed. The spatial density of the seismic events, and the time of end of formation of the channels can also be predicted using this developed model. Using direct simulations of acoustic emissions due to the air vibration in opening fractal cavities, the evolution in the power spectrum is investigated. 1. Turkaya S, Toussaint R, Eriksen FK, Zecevic M, Daniel G, Flekkøy EG, Måløy KJ. "Bridging aero-fracture evolution with the characteristics of the acoustic emissions in a porous medium." Front. Phys.3:70. 2015 doi: 10.3389/fphy.2015.00070

  3. Raudteelaste ametiühingud toetavad TALO streikijaid / Matis Song

    Index Scriptorium Estoniae

    Song, Matis, 1978-

    2003-01-01

    Eesti raudteelaste ja vedurijuhtide toetusstreigist 4. detsembril 2003. Kommentaarid Eesti Raudteelaste Ametiühingu esimehelt Jolan Shevtsovilt ja Eesti Vedurimeeste Ametiühingu juhilt Heino Rüütlilt

  4. Smart Rotor Modeling: Aero-Servo-Elastic Modeling of a Smart Rotor with Adaptive Trailing Edge Flaps

    DEFF Research Database (Denmark)

    Bergami, Leonardo

    the trailing edge flap deflection to actively reduce the fatigue loads on the structure. The performance of the smart rotor configuration and its control algorithms are finally quantified by aero-servo-elastic simulations of the smart rotor turbine operating in a standard turbulent wind field.......This book presents the formulation of an aero-servo-elastic model for a wind turbine rotor equipped with Adaptive Trailing Edge Flaps (ATEF), a smart rotor configuration. As the name suggests, an aero-servo-elastic model consists of three main components: an aerodynamic model, a structural model......, and a control model. The book first presents an engineering type of aerodynamic model that accounts for the dynamic effects of flap deflection. The aerodynamic model is implemented in a Blade Element Momentum framework, and coupled with a multi-body structural model in the aero-servoelastic simulation code HAWC...

  5. Fusing Simulation Results From Multifidelity Aero-servo-elastic Simulators - Application To Extreme Loads On Wind Turbine

    DEFF Research Database (Denmark)

    Abdallah, Imad; Sudret, Bruno; Lataniotis, Christos

    2015-01-01

    Fusing predictions from multiple simulators in the early stages of the conceptual design of a wind turbine results in reduction in model uncertainty and risk mitigation. Aero-servo-elastic is a term that refers to the coupling of wind inflow, aerodynamics, structural dynamics and controls. Fusing...... the response data from multiple aero-servo-elastic simulators could provide better predictive ability than using any single simulator. The co-Kriging approach to fuse information from multifidelity aero-servo-elastic simulators is presented. We illustrate the co-Kriging approach to fuse the extreme flapwise...... bending moment at the blade root of a large wind turbine as a function of wind speed, turbulence and shear exponent in the presence of model uncertainty and non-stationary noise in the output. The extreme responses are obtained by two widely accepted numerical aero-servo-elastic simulators, FAST...

  6. Response types and general stability conditions of linear aero-elastic system with two degrees-of-freedom

    Czech Academy of Sciences Publication Activity Database

    Náprstek, Jiří; Pospíšil, Stanislav

    2012-01-01

    Roč. 111, č. 1 (2012), s. 1-13 ISSN 0167-6105 R&D Projects: GA ČR(CZ) GA103/09/0094; GA AV ČR(CZ) IAA200710902 Institutional support: RVO:68378297 Keywords : aero-elastic system * self-excited vibration * instability * aero-elastic derivatives Subject RIV: JN - Civil Engineering Impact factor: 1.342, year: 2012

  7. Global Mobile Satellite Service Interference Analysis for the AeroMACS

    Science.gov (United States)

    Wilson, Jeffrey D.; Apaza, Rafael D.; Hall, Ward; Phillips, Brent

    2013-01-01

    The AeroMACS (Aeronautical Mobile Airport Communications System), which is based on the IEEE 802.16-2009 mobile wireless standard, is envisioned as the wireless network which will cover all areas of airport surfaces for next generation air transportation. It is expected to be implemented in the 5091-5150 MHz frequency band which is also occupied by mobile satellite service uplinks. Thus the AeroMACS must be designed to avoid interference with this incumbent service. Simulations using Visualyse software were performed utilizing a global database of 6207 airports. Variations in base station and subscriber antenna distribution and gain pattern were examined. Based on these simulations, recommendations for global airport base station and subscriber antenna power transmission limitations are provided.

  8. Multimedia in physics education: teaching videos about aero and fluid dynamics

    International Nuclear Information System (INIS)

    Wagner, Andreas; Altherr, Stefan; Eckert, Bodo; Jodl, Hans Joerg

    2007-01-01

    In a series of letters, we present teaching videos on topics which are difficult to understand for students, or which are difficult to realize experimentally in school, if at all. These videos can be used for quantitative analysis or visualization of phenomena. Here we present videos on aero and fluid dynamics which deal with the Navier-Stokes equation, the continuity equation and Karman's vortex street. (letters and comments)

  9. Qualification of Indigenously Developed Special Coatings for Aero-Engine Components

    OpenAIRE

    V. Sambasiva Rao; T. Rangaraju; V. Unnikrishnan

    1999-01-01

    The demand for higher performance and reliability of aero-engiaes necessitates its components to worksatisfactorily under severe operating conditions. The durability of various components in these environmentis often enhanced by applying suitable coatings. The development of new materials/processing methods andalso various coatings to protect the components have been driven by the ever-increasing severity of theaero-engine internal environment. While the selection of a coating is dictated by ...

  10. 76 FR 82202 - Airworthiness Directives; International Aero Engines AG Turbofan Engines

    Science.gov (United States)

    2011-12-30

    ... Engines AG Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed... International Aero Engines AG (IAE) V2500-A1, V2525-D5 and V2528-D5 turbofan engines, and certain serial numbers (S/Ns) of IAE V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, and V2533-A5 turbofan...

  11. Results of a WINGDES2/AERO2S Flap Optimization for the TCA

    Science.gov (United States)

    Yaros, Steven F.

    1999-01-01

    The codes WINGDES2 and AERO2S were easy to obtain, and technical help was readily available. The codes have a long, well-documented history of successful optimizations of various aircraft configurations. The codes were easy to use, although specification of input data was time-consuming. The Run times were short, allowing the many runs necessary for the Suction Parameter matrix to be accomplished within a day or two. The results of the optimization appear to be reasonable.

  12. Aero-elastic stability of airfoil flow using 2-D CFD

    Energy Technology Data Exchange (ETDEWEB)

    Johansen, J [Risoe National Lab., Roskilde (Denmark)

    1999-03-01

    A three degrees-of-freedom structural dynamics model has been coupled to a two-dimensional incompressible CFD code. The numerical investigation considers aero-elastic stability for two different airfoils; the NACA0012 and the LM 2 18 % airfoils. Stable and unstable configurations and limit cycle oscillations are predicted in accordance with literature for the first airfoil. An attempt to predict stall induced edge-wise vibrations on a wind turbine airfoil fails using this two-dimensional approach. (au)

  13. Role of offending out-door aero-allergen and CD14 C(-159)T ...

    African Journals Online (AJOL)

    Child- hood-onset and adult-onset of asthma showed significant difference in allergen sensitivity as well as genetic background with respect to CD14 polymorphism. Keywords: Asthma, aero-allergen, skin prick test, total IgE, CD14 gene polymorphism. DOI: https://dx.doi.org/10.4314/ahs.v17i4.18. Cite as: Dutta S, Mondal P, ...

  14. General catalogue of products and services - geology. AERO data base. 2. ed.

    International Nuclear Information System (INIS)

    1995-01-01

    The catalogue in the second edition aims at presenting to the user a general idea on the aerogeophysical projects of Brazil database (AERO) which belongs to SIGA (Brazilian geological information system). The 151 documents (projects) are listed as follows: 52 projects performed by CPRM/DNPM - Departamento Nacional de Producao Mineral; 33 projects performed by CNEN - Commissao Nacional de Energia Nuclear and NUCLEBRAS; 7 projects executed by State government and private companies; and 59 projects executed for PETROBRAS

  15. Practice in multi-disciplinary computing. Transonic aero-structural dynamics of semi-monocoque wing

    International Nuclear Information System (INIS)

    Onishi, Ryoichi; Guo, Zhihong; Kimura, Toshiya; Iwamiya, Toshiyuki

    2000-01-01

    Japan Atomic Energy Research Institute is currently involved in expanding the application areas of its distributed parallel computing facility. One of the most anticipated areas of applications is multi-disciplinary interaction problem. This paper introduces the status quo of the system for fluid-structural interaction analysis on the institute's parallel computers by exploring multi-disciplinary engineering methodology. Current application is focused on a transonic aero-elastic analysis of a three dimensional wing. The distinctive features of the system are: (1) Simultaneous executions of fluid and structural codes by exploiting distributed-and-parallel processing technologies. (2) Construction of a computational fluid (aero)-structural dynamics model which combines flow-field grid with a wing structure composed of the external surface and the internal reinforcements. The purpose of this paper is to summarize the basic concepts, analytical methods, and their implementations along with the computed aero-structural properties of a swept-back wing at March, 7 flow condition. (author)

  16. Numerical study of aero-excitation of steam-turbine rotor blade self-oscillations

    Science.gov (United States)

    Galaev, S. A.; Makhnov, V. Yu.; Ris, V. V.; Smirnov, E. M.

    2018-05-01

    Blade aero-excitation increment is evaluated by numerical solution of the full 3D unsteady Reynolds-averaged Navier-Stokes equations governing wet steam flow in a powerful steam-turbine last stage. The equilibrium wet steam model was adopted. Blade surfaces oscillations are defined by eigen-modes of a row of blades bounded by a shroud. Grid dependency study was performed with a reduced model being a set of blades multiple an eigen-mode nodal diameter. All other computations were carried out for the entire blade row. Two cases are considered, with an original-blade row and with a row of modified (reinforced) blades. Influence of eigen-mode nodal diameter and blade reinforcing on aero-excitation increment is analyzed. It has been established, in particular, that maximum value of the aero-excitation increment for the reinforced-blade row is two times less as compared with the original-blade row. Generally, results of the study point definitely to less probability of occurrence of blade self-oscillations in case of the reinforced blade-row.

  17. Performance of a Supercritical CO2 Bottoming Cycle for Aero Applications

    Directory of Open Access Journals (Sweden)

    Florian Jacob

    2017-03-01

    Full Text Available By 2050, the evolutionary approach to aero engine research may no longer provide meaningful returns on investment, whereas more radical approaches to improving thermal efficiency and reducing emissions might still prove cost effective. One such radical concept is the addition of a secondary power cycle that utilizes the otherwise largely wasted residual heat in the core engine’s exhaust gases. This could provide additional shaft power. Supercritical carbon dioxide closed-circuit power cycles are currently being investigated primarily for stationary power applications, but their high power density and efficiency, even for modest peak cycle temperatures, makes them credible bottoming cycle options for aero engine applications. Through individual geometric design and performance studies for each of the bottoming cycle’s major components, it was determined that a simple combined cycle aero engine could offer a 1.9% mission fuel burn benefit over a state-of-the-art geared turbofan for the year 2050. However, the even greater potential of more complex systems demands further investigation. For example, adding inter-turbine reheat (ITR to the combined cycle is predicted to significantly improve the fuel burn benefit.

  18. Mapped Chebyshev Pseudo-Spectral Method for Dynamic Aero-Elastic Problem of Limit Cycle Oscillation

    Science.gov (United States)

    Im, Dong Kyun; Kim, Hyun Soon; Choi, Seongim

    2018-05-01

    A mapped Chebyshev pseudo-spectral method is developed as one of the Fourier-spectral approaches and solves nonlinear PDE systems for unsteady flows and dynamic aero-elastic problem in a given time interval, where the flows or elastic motions can be periodic, nonperiodic, or periodic with an unknown frequency. The method uses the Chebyshev polynomials of the first kind for the basis function and redistributes the standard Chebyshev-Gauss-Lobatto collocation points more evenly by a conformal mapping function for improved numerical stability. Contributions of the method are several. It can be an order of magnitude more efficient than the conventional finite difference-based, time-accurate computation, depending on the complexity of solutions and the number of collocation points. The method reformulates the dynamic aero-elastic problem in spectral form for coupled analysis of aerodynamics and structures, which can be effective for design optimization of unsteady and dynamic problems. A limit cycle oscillation (LCO) is chosen for the validation and a new method to determine the LCO frequency is introduced based on the minimization of a second derivative of the aero-elastic formulation. Two examples of the limit cycle oscillation are tested: nonlinear, one degree-of-freedom mass-spring-damper system and two degrees-of-freedom oscillating airfoil under pitch and plunge motions. Results show good agreements with those of the conventional time-accurate simulations and wind tunnel experiments.

  19. Crystal spectroscopy of silicon aero-gel end-caps driven by a dynamic hohlraum on Z

    International Nuclear Information System (INIS)

    Nash, T.J.; Sanford, T.W.L.; Mock, R.C.; Leeper, R.J.; Chandler, G.A.; Bailey, J.E.; McKenney, J.L.; Mehlhorn, T.A.; Seaman, J.F.; McGurn, J.; Schroen, D.; Russell, C.; Lake, P.E.; Jobe, D.O.; Gilliland, T.; Nielsen, D.S.; Lucas, J.; Moore, T.; Torres, J.A.; MacFarlane, J.J.; Apruzese, J.P.; Chrien, R.; Idzorek, G.; Peterson, D.L.; Watt, R.

    2005-01-01

    We present results from crystal spectroscopic analysis of silicon aero-gel foams heated by dynamic hohlraums on Z. The dynamic hohlraum on Z creates a radiation source with a 230-eV average temperature over a 2.4-mm diameter. In these experiments silicon aero-gel foams with 10-mg/cm3 densities and 1.7-mm lengths were placed on both ends of the dynamic hohlraum. Several crystal spectrometers were placed both above and below the z-pinch to diagnose the temperature of the silicon aero-gel foam using the K-shell lines of silicon. The crystal spectrometers were (1) temporally integrated and spatially resolved, (2) temporally resolved and spatially integrated, and (3) both temporally and spatially resolved. The results indicate that the dynamic hohlraum heats the silicon aero-gel to approximately 150-eV at peak power. As the dynamic hohlraum source cools after peak power the silicon aero-gel continues to heat and jets axially at an average velocity of approximately 50-cm/μs. The spectroscopy has also shown that the reason for the up/down asymmetry in radiated power on Z is that tungsten enters the line-of-sight on the bottom of the machine much more than on the top

  20. 75 FR 10694 - Airworthiness Directives; AeroSpace Technologies of Australia Pty Ltd Models N22B, N22S, and N24A...

    Science.gov (United States)

    2010-03-09

    ... Airworthiness Directives; AeroSpace Technologies of Australia Pty Ltd Models N22B, N22S, and N24A Airplanes... authority for Australia, has issued AD GAF-N22-52, Amendment 1, dated January 2010 (referred to after this... examining the MCAI in the AD docket. Relevant Service Information AeroSpace Technologies of Australia...

  1. Machining the Integral Impeller and Blisk of Aero-Engines: A Review of Surface Finishing and Strengthening Technologies

    Science.gov (United States)

    Fu, Youzhi; Gao, Hang; Wang, Xuanping; Guo, Dongming

    2017-05-01

    The integral impeller and blisk of an aero-engine are high performance parts with complex structure and made of difficult-to-cut materials. The blade surfaces of the integral impeller and blisk are functional surfaces for power transmission, and their surface integrity has significant effects on the aerodynamic efficiency and service life of an aero-engine. Thus, it is indispensable to finish and strengthen the blades before use. This paper presents a comprehensive literature review of studies on finishing and strengthening technologies for the impeller and blisk of aero-engines. The review includes independent and integrated finishing and strengthening technologies and discusses advanced rotational abrasive flow machining with back-pressure used for finishing the integral impeller and blisk. A brief assessment of future research problems and directions is also presented.

  2. Development and Validation of a New Blade Element Momentum Skewed-Wake Model within AeroDyn: Preprint

    Energy Technology Data Exchange (ETDEWEB)

    Ning, S. A.; Hayman, G.; Damiani, R.; Jonkman, J.

    2014-12-01

    Blade element momentum methods, though conceptually simple, are highly useful for analyzing wind turbines aerodynamics and are widely used in many design and analysis applications. A new version of AeroDyn is being developed to take advantage of new robust solution methodologies, conform to a new modularization framework for National Renewable Energy Laboratory's FAST, utilize advanced skewed-wake analysis methods, fix limitations with previous implementations, and to enable modeling of highly flexible and nonstraight blades. This paper reviews blade element momentum theory and several of the options available for analyzing skewed inflow. AeroDyn implementation details are described for the benefit of users and developers. These new options are compared to solutions from the previous version of AeroDyn and to experimental data. Finally, recommendations are given on how one might select from the various available solution approaches.

  3. Aero-medical evacuation from the second Israel-Lebanon war: a descriptive study.

    Science.gov (United States)

    Schwartz, Dagan; Resheff, Avram; Geftler, Alex; Weiss, Aviram; Birenbaum, Erez; Lavon, Ophir

    2009-05-01

    The second Lebanon war started as a limited operation and progressed to a large-scale campaign. Most of the fighting took place in mountainous villages and small towns inhabited with civilians. The Israeli Defense Forces (IDF) Airborne rescue and evacuation unit is charged with air evacuation of soldiers and civilians in times of peace, limited conflict, and war. We describe this unit's activities in the second Lebanon war, analyzing injury, treatment, and evacuation characteristics Data were collected from flight medical reports, debriefings of aero-medical team members (usually immediately upon return from mission), ground units medical reports and debriefings, and hospital records. 725 IDF soldiers were injured and 117 killed either in Lebanon or near the Israeli-Lebanese border during the war. A total of 338 (46%) were evacuated in 95 airlifts (averaging 4.5 evacuees per airlift) from the fighting zones or the border. Air evacuation used dedicated helicopters with advanced care capacities, and most victims were evacuated straight from the battlefield, as the fighting was ensuing. Many wounded first received advanced medical care upon the arrival of the aero-medical teams. In military operations within civilian populated areas with threats to ground transport, air evacuation can sometimes be the only readily available option. Providing timely ground advanced medical care proved difficult in many instances. Thus, for many, the rescue helicopter was the first point of access to such care. Aero-medical aircrafts and personnel faced threats from gunfire and missiles, causing both delays in evacuation and a high average number of evacuees per airlift. This article proposes ways of coping with situations in which similar rescue and evacuation problems are likely.

  4. The spectral analysis of an aero-engine assembly incorporating a squeeze-film damper

    Science.gov (United States)

    Holmes, R.; Dede, M. M.

    1989-01-01

    Aero-engine structures have very low inherent damping and so artificial damping is often introduced by pumping oil into annular gaps between the casings and the outer races of some or all of the rolling-element bearings supporting the rotors. The thin oil films so formed are called squeeze film dampers and they can be beneficial in reducing rotor vibration due to unbalance and keeping to reasonable limits the forces transmitted to the engine casing. However, squeeze-film dampers are notoriously non-linear and as a result can introduce into the assembly such phenomena as subharmonic oscillations, jumps and combination frequencies. The purpose of the research is to investigate such phenomena both theoretically and experimentally on a test facility reproducing the essential features of a medium-size aero engine. The forerunner of this work was published. It was concerned with the examination of a squeeze-film damper in series with housing flexibility when supporting a rotor. The structure represented to a limited extent the essentials of the projected Rolls Royce RB401 engine. That research demonstrated the ability to calculate the oil-film forces arising from the squeeze film from known motions of the bearing components and showed that the dynamics of a shaft fitted with a squeeze film bearing can be predicted reasonably accurately. An aero-engine will normally have at least two shafts and so in addition to the excitation forces which are synchronous with the rotation of one shaft, there will also be forces at other frequencies from other shafts operating on the squeeze-film damper. Theoretical and experimental work to consider severe loading of squeeze-film dampers and to include these additional effects are examined.

  5. Recent trends in superalloys research for critical aero-engine components

    Energy Technology Data Exchange (ETDEWEB)

    Remy, Luc [Mine ParisTech, CNRS UMR 7633, 91 - Evry (France). Centre des Materiaux; Guedou, Jean-Yves [Snecma Safran Group, Moissy-Cramayel (France). Materials and Processes Dept.

    2010-07-01

    This paper is a brief survey of common research activity on superalloys for aero-engines between Snecma and Mines ParisTech Centre des Materiaux during recent years. First in disks applications, the development of new powder metallurgy superalloys is shown. Then grain boundary engineering is investigated in a wrought superalloy. Secondly, design oriented research on single crystals blades is shown: a damage model for low cycle fatigue is used for life prediction when cracks initiated at casting pores. The methodology developed for assessing coating life is illustrated for thermal barrier coating deposited on AMI single crystal superalloy. (orig.)

  6. Statistical learning methods for aero-optic wavefront prediction and adaptive-optic latency compensation

    Science.gov (United States)

    Burns, W. Robert

    Since the early 1970's research in airborne laser systems has been the subject of continued interest. Airborne laser applications depend on being able to propagate a near diffraction-limited laser beam from an airborne platform. Turbulent air flowing over the aircraft produces density fluctuations through which the beam must propagate. Because the index of refraction of the air is directly related to the density, the turbulent flow imposes aberrations on the beam passing through it. This problem is referred to as Aero-Optics. Aero-Optics is recognized as a major technical issue that needs to be solved before airborne optical systems can become routinely fielded. This dissertation research specifically addresses an approach to mitigating the deleterious effects imposed on an airborne optical system by aero-optics. A promising technology is adaptive optics: a feedback control method that measures optical aberrations and imprints the conjugate aberrations onto an outgoing beam. The challenge is that it is a computationally-difficult problem, since aero-optic disturbances are on the order of kilohertz for practical applications. High control loop frequencies and high disturbance frequencies mean that adaptive-optic systems are sensitive to latency in sensors, mirrors, amplifiers, and computation. These latencies build up to result in a dramatic reduction in the system's effective bandwidth. This work presents two variations of an algorithm that uses model reduction and data-driven predictors to estimate the evolution of measured wavefronts over a short temporal horizon and thus compensate for feedback latency. The efficacy of the two methods are compared in this research, and evaluated against similar algorithms that have been previously developed. The best version achieved over 75% disturbance rejection in simulation in the most optically active flow region in the wake of a turret, considerably outperforming conventional approaches. The algorithm is shown to be

  7. AeroPropulsoServoElasticity: Dynamic Modeling of the Variable Cycle Propulsion System

    Science.gov (United States)

    Kopasakis, George

    2012-01-01

    This presentation was made at the 2012 Fundamental Aeronautics Program Technical Conference and it covers research work for the Dynamic Modeling of the Variable cycle Propulsion System that was done under the Supersonics Project, in the area of AeroPropulsoServoElasticity. The presentation covers the objective for the propulsion system dynamic modeling work, followed by the work that has been done so far to model the variable Cycle Engine, modeling of the inlet, the nozzle, the modeling that has been done to model the affects of flow distortion, and finally presenting some concluding remarks and future plans.

  8. Applications of aero-acoustic analysis to wind turbine noise control

    International Nuclear Information System (INIS)

    Lowson, M.V.

    1992-01-01

    Wind turbine noise generation mechanisms are essentially equivalent to the aero-acoustic mechanisms of other rotors, which have been studied in depth for many years. Basic sources for the wind turbine noise radiation process are defined, and their significance assessed. From the analysis, areas of potential improvement in wind turbine noise prediction are defined. Suggestions are made for approaches to wind turbine noise control which separate the noise problems at cut-in from those at rated power. Some of these offer the possibility of noise reduction without unfavourable effects on performance. (author)

  9. Applications of aero-acoustic analysis to wind turbine noise control

    International Nuclear Information System (INIS)

    Lowson, M.

    1993-01-01

    Wind turbine noise generation mechanisms are essentially equivalent to the aero-acoustic mechanisms of other rotors, which have been studied in depth for many years. Basic sources for the wind turbine noise radiation process are defined, and their significance assessed. From the analysis, areas of potential improvement in wind turbine noise prediction are defined. Suggestions are made for approaches to wind turbine noise control which separate the noise problems at cut-in from those at rated power. Some of these offer the possibility of noise reduction without unfavourable effects on performance. (author)

  10. Aero-servo-viscoelasticity theory: Lifting surfaces, plates, velocity transients, flutter, and instability

    Science.gov (United States)

    Merrett, Craig G.

    Modern flight vehicles are fabricated from composite materials resulting in flexible structures that behave differently from the more traditional elastic metal structures. Composite materials offer a number of advantages compared to metals, such as improved strength to mass ratio, and intentional material property anisotropy. Flexible aircraft structures date from the Wright brothers' first aircraft with fabric covered wooden frames. The flexibility of the structure was used to warp the lifting surface for flight control, a concept that has reappeared as aircraft morphing. These early structures occasionally exhibited undesirable characteristics during flight such as interactions between the empennage and the aft fuselage, or control problems with the elevators. The research to discover the cause and correction of these undesirable characteristics formed the first foray into the field of aeroelasticity. Aeroelasticity is the intersection and interaction between aerodynamics, elasticity, and inertia or dynamics. Aeroelasticity is well suited for metal aircraft, but requires expansion to improve its applicability to composite vehicles. The first is a change from elasticity to viscoelasticity to more accurately capture the solid mechanics of the composite material. The second change is to include control systems. While the inclusion of control systems in aeroelasticity lead to aero-servo-elasticity, more control possibilities exist for a viscoelastic composite material. As an example, during the lay-up of carbon-epoxy plies, piezoelectric control patches are inserted between different plies to give a variety of control options. The expanded field is called aero-servo-viscoelasticity. The phenomena of interest in aero-servo-viscoelasticity are best classified according to the type of structure considered, either a lifting surface or a panel, and the type of dynamic stability present. For both types of structures, the governing equations are integral

  11. Comparison of caffeine disposition following administration by oral solution (energy drink) and inspired powder (AeroShot) in human subjects.

    Science.gov (United States)

    Laizure, S Casey; Meibohm, Bernd; Nelson, Kembral; Chen, Feng; Hu, Zhe-Yi; Parker, Robert B

    2017-12-01

    To determine the disposition and effects of caffeine after administration using a new dosage form (AeroShot) that delivers caffeine by inspiration of a fine powder into the oral cavity and compare it to an equivalent dose of an oral solution (energy drink) as the reference standard. Healthy human subjects (n = 17) inspired a 100 mg caffeine dose using the AeroShot device or consumed an energy drink on separate study days. Heart rate, blood pressure and subject assessments of effects were measured over an 8-h period. Plasma concentrations of caffeine and its major metabolites were determined by liquid chromatography-mass spectrometry. Pharmacokinetic, cardiovascular and perceived stimulant effects were compared between AeroShot and energy drink phases using a paired t test and standard bioequivalency analysis. Caffeine disposition was similar after caffeine administration by the AeroShot device and energy drink: peak plasma concentration 1790 and 1939 ng ml -1 , and area under the concentration-time curve (AUC) 15 579 and 17 569 ng ml -1 × h, respectively, but they were not bioequivalent: AeroShot AUC of 80.3% (confidence interval 71.2-104.7%) and peak plasma concentration of 86.3% (confidence interval 62.8-102.8%) compared to the energy drink. Female subjects did have a significantly larger AUC compared to males after consumption of the energy drink. The heart rate and blood pressure were not significantly affected by the 100 mg caffeine dose, and there were no consistently perceived stimulant effects by the subjects using visual analogue scales. Inspiration of caffeine as a fine powder using the AeroShot device produces a similar caffeine profile and effects compared to administration of an oral solution (energy drink). © 2017 The British Pharmacological Society.

  12. The Chaotic Prediction for Aero-Engine Performance Parameters Based on Nonlinear PLS Regression

    Directory of Open Access Journals (Sweden)

    Chunxiao Zhang

    2012-01-01

    Full Text Available The prediction of the aero-engine performance parameters is very important for aero-engine condition monitoring and fault diagnosis. In this paper, the chaotic phase space of engine exhaust temperature (EGT time series which come from actual air-borne ACARS data is reconstructed through selecting some suitable nearby points. The partial least square (PLS based on the cubic spline function or the kernel function transformation is adopted to obtain chaotic predictive function of EGT series. The experiment results indicate that the proposed PLS chaotic prediction algorithm based on biweight kernel function transformation has significant advantage in overcoming multicollinearity of the independent variables and solve the stability of regression model. Our predictive NMSE is 16.5 percent less than that of the traditional linear least squares (OLS method and 10.38 percent less than that of the linear PLS approach. At the same time, the forecast error is less than that of nonlinear PLS algorithm through bootstrap test screening.

  13. Research and Development of Some Advanced High Temperature Titanium Alloys for Aero-engine

    Directory of Open Access Journals (Sweden)

    CAI Jian-ming

    2016-08-01

    Full Text Available Some advanced high temperature titanium alloys are usually selected to be manufactured into blade, disc, case, blisk and bling under high temperature environment in compressor and turbine system of a new generation high thrust-mass ratio aero-engine. The latest research progress of 600℃ high temperature titanium alloy, fireproof titanium alloy, TiAl alloy, continuous SiC fiber reinforced titanium matrix composite and their application technology in recent years in China were reviewed in this paper. The key technologies need to be broken through in design, processing and application of new material and component are put forward, including industrial ingot composition of high purified and homogeneous control technology, preparation technology of the large size bar and special forgings, machining technology of blisk and bling parts, material property evaluation and application design technique. The future with the continuous application of advanced high temperature titanium alloys, will be a strong impetus to the development of China's aero-engine technology.

  14. The Design and Semi-Physical Simulation Test of Fault-Tolerant Controller for Aero Engine

    Science.gov (United States)

    Liu, Yuan; Zhang, Xin; Zhang, Tianhong

    2017-11-01

    A new fault-tolerant control method for aero engine is proposed, which can accurately diagnose the sensor fault by Kalman filter banks and reconstruct the signal by real-time on-board adaptive model combing with a simplified real-time model and an improved Kalman filter. In order to verify the feasibility of the method proposed, a semi-physical simulation experiment has been carried out. Besides the real I/O interfaces, controller hardware and the virtual plant model, semi-physical simulation system also contains real fuel system. Compared with the hardware-in-the-loop (HIL) simulation, semi-physical simulation system has a higher degree of confidence. In order to meet the needs of semi-physical simulation, a rapid prototyping controller with fault-tolerant control ability based on NI CompactRIO platform is designed and verified on the semi-physical simulation test platform. The result shows that the controller can realize the aero engine control safely and reliably with little influence on controller performance in the event of fault on sensor.

  15. Takagi-Sugeno fuzzy model identification for turbofan aero-engines with guaranteed stability

    Directory of Open Access Journals (Sweden)

    Ruichao LI

    2018-06-01

    Full Text Available This paper is concerned with identifying a Takagi-Sugeno (TS fuzzy model for turbofan aero-engines working under the maximum power status (non-afterburning. To establish the fuzzy system, theoretical contributions are made as follows. First, by fixing antecedent parameters, the estimation of consequent parameters in state-space representations is formulated as minimizing a quadratic cost function. Second, to avoid obtaining unstable identified models, a new theorem is proposed to transform the prior-knowledge of stability into constraints. Then based on the aforementioned work, the identification problem is synthesized as a constrained quadratic optimization. By solving the constrained optimization, a TS fuzzy system is identified with guaranteed stability. Finally, the proposed method is applied to the turbofan aero-engine using simulation data generated from an aerothermodynamics component-level model. Results show the identified fuzzy model achieves a high fitting accuracy while stabilities of the overall fuzzy system and all its local models are also guaranteed. Keywords: Constrained optimization, Fuzzy system, Stability, System identification, Turbofan engine

  16. Aero-Propulsion Technology (APT) Task V Low Noise ADP Engine Definition Study

    Science.gov (United States)

    Holcombe, V.

    2003-01-01

    A study was conducted to identify and evaluate noise reduction technologies for advanced ducted prop propulsion systems that would allow increased capacity operation and result in an economically competitive commercial transport. The study investigated the aero/acoustic/structural advancements in fan and nacelle technology required to match or exceed the fuel burned and economic benefits of a constrained diameter large Advanced Ducted Propeller (ADP) compared to an unconstrained ADP propulsion system with a noise goal of 5 to 10 EPNDB reduction relative to FAR 36 Stage 3 at each of the three measuring stations namely, takeoff (cutback), approach and sideline. A second generation ADP was selected to operate within the maximum nacelle diameter constrain of 160 deg to allow installation under the wing. The impact of fan and nacelle technologies of the second generation ADP on fuel burn and direct operating costs for a typical 3000 nm mission was evaluated through use of a large, twin engine commercial airplane simulation model. The major emphasis of this study focused on fan blade aero/acoustic and structural technology evaluations and advanced nacelle designs. Results of this study have identified the testing required to verify the interactive performance of these components, along with noise characteristics, by wind tunnel testing utilizing and advanced interaction rig.

  17. Aftereffect of radiotherapy of upper aero-digestive tracts in odontological care

    International Nuclear Information System (INIS)

    Schiochet, Luc

    2010-01-01

    In its first part, this thesis proposes a detailed presentation of the upper aero-digestive tract cancer. The author defines the cancerous process, describes anatomic aspects, and discusses epidemiological aspects (occurrence, mortality, survival, and epidemiological data in different countries). In the second part, the author discusses the role of radiotherapy and of dental surgery in taking a cancerous patient into care (general principles of radiotherapy, therapeutic options and choices, association of radiotherapy, chemotherapy and surgery). Principles of radiotherapy are then more precisely addressed: physical principles (X rays, gamma rays, electrons, neutrons, and protons), radioactivity doses, radiotherapy effect, main equipment, radiotherapy techniques (conformational or intensity-modulated radiotherapy, computed tomography, Cyberknife, external radiotherapy, brachytherapy). The third part addresses early oral-facial complications induced by radiotherapy: factors favouring these complications, nervous effects, effects on the blood system and on the skin, hyposialia and xerostomia, radio-induced mucositis of upper aero-digestive tracts. The next part addresses late effects: late cutaneous after-effects, late radio-mucositis, limitation of mouth opening, tooth decays, osteoradionecrosis. The last part addresses the role of the dental surgeon in taking into care a patient whose head and neck have been irradiated: role before irradiation, during irradiation, and after irradiation [fr

  18. Fuselage boundary-layer refraction of fan tones radiated from an installed turbofan aero-engine.

    Science.gov (United States)

    Gaffney, James; McAlpine, Alan; Kingan, Michael J

    2017-03-01

    A distributed source model to predict fan tone noise levels of an installed turbofan aero-engine is extended to include the refraction effects caused by the fuselage boundary layer. The model is a simple representation of an installed turbofan, where fan tones are represented in terms of spinning modes radiated from a semi-infinite circular duct, and the aircraft's fuselage is represented by an infinitely long, rigid cylinder. The distributed source is a disk, formed by integrating infinitesimal volume sources located on the intake duct termination. The cylinder is located adjacent to the disk. There is uniform axial flow, aligned with the axis of the cylinder, everywhere except close to the cylinder where there is a constant thickness boundary layer. The aim is to predict the near-field acoustic pressure, and in particular, to predict the pressure on the cylindrical fuselage which is relevant to assess cabin noise. Thus no far-field approximations are included in the modelling. The effect of the boundary layer is quantified by calculating the area-averaged mean square pressure over the cylinder's surface with and without the boundary layer included in the prediction model. The sound propagation through the boundary layer is calculated by solving the Pridmore-Brown equation. Results from the theoretical method show that the boundary layer has a significant effect on the predicted sound pressure levels on the cylindrical fuselage, owing to sound radiation of fan tones from an installed turbofan aero-engine.

  19. A Co-modeling Method Based on Component Features for Mechatronic Devices in Aero-engines

    Science.gov (United States)

    Wang, Bin; Zhao, Haocen; Ye, Zhifeng

    2017-08-01

    Data-fused and user-friendly design of aero-engine accessories is required because of their structural complexity and stringent reliability. This paper gives an overview of a typical aero-engine control system and the development process of key mechatronic devices used. Several essential aspects of modeling and simulation in the process are investigated. Considering the limitations of a single theoretic model, feature-based co-modeling methodology is suggested to satisfy the design requirements and compensate for diversity of component sub-models for these devices. As an example, a stepper motor controlled Fuel Metering Unit (FMU) is modeled in view of the component physical features using two different software tools. An interface is suggested to integrate the single discipline models into the synthesized one. Performance simulation of this device using the co-model and parameter optimization for its key components are discussed. Comparison between delivery testing and the simulation shows that the co-model for the FMU has a high accuracy and the absolute superiority over a single model. Together with its compatible interface with the engine mathematical model, the feature-based co-modeling methodology is proven to be an effective technical measure in the development process of the device.

  20. Study on aero-dynamic characteristics of the sloop rig (continued); Sloop ring no kuriki tokusei no ichikaiseki (zoku)

    Energy Technology Data Exchange (ETDEWEB)

    Shinkai, A.; Iyoda, H. [Kyushu University, Fukuoka (Japan). Faculty of Engineering

    1997-09-04

    A numerical simulation method was formerly provided for analyzing aero-dynamic characteristics of sloop rig by the vortex distribution method. For this method, aero-dynamic characteristics of the sloop rib were formulated by treating air flow around sail as a two-dimensional problem and by assuming sail as a membrane. The sloop rig is a yacht for more than two persons, which is the most popular form of rig. A main sail and a jib sheet are fixed on a mast. In this study, the method developed based on the panel method was introduced for analyzing the effects of jib sheet which can control the jib trim angle. Generality of the present aero-dynamic characteristics was enhanced, and problems of the analysis method were extracted through the numerical simulation of a yacht with sloop rig. Influence of the position of fairleader on the aero-dynamic characteristics was qualitatively grasped by considering the effects of jib sheet and by trimming the elevation into ideal one. 6 refs., 11 figs.

  1. 75 FR 22512 - Airworthiness Directives; Piaggio Aero Industries S.p.A. Model PIAGGIO P-180 Airplanes

    Science.gov (United States)

    2010-04-29

    ... Airworthiness Directives; Piaggio Aero Industries S.p.A. Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation... presence of potential ignition sources such as electrical equipment and connectors. As a consequence, this..., agree with their substance. But we might have found it necessary to use different words from those in...

  2. A study on optimal control of the aero-propulsion system acceleration process under the supersonic state

    Directory of Open Access Journals (Sweden)

    Fengyong Sun

    2017-04-01

    Full Text Available In order to solve the aero-propulsion system acceleration optimal problem, the necessity of inlet control is discussed, and a fully new aero-propulsion system acceleration process control design including the inlet, engine, and nozzle is proposed in this paper. In the proposed propulsion system control scheme, the inlet, engine, and nozzle are simultaneously adjusted through the FSQP method. In order to implement the control scheme design, an aero-propulsion system component-level model is built to simulate the inlet working performance and the matching problems between the inlet and engine. Meanwhile, a stabilizing inlet control scheme is designed to solve the inlet control problems. In optimal control of the aero-propulsion system acceleration process, the inlet is an emphasized control unit in the optimal acceleration control system. Two inlet control patterns are discussed in the simulation. The simulation results prove that by taking the inlet ramp angle as an active control variable instead of being modulated passively, acceleration performance could be obviously enhanced. Acceleration objectives could be obtained with a faster acceleration time by 5%.

  3. 76 FR 7694 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Science.gov (United States)

    2011-02-11

    ... Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes AGENCY: Federal Aviation... Piaggio service bulletin number specified in the Alternative Methods of Compliance (AMOCs) section is..., except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received...

  4. 76 FR 4056 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Science.gov (United States)

    2011-01-24

    ..., is considered the State of Design for PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P- 180 airplanes. A... ensuring that the drain lines of the environmental unit condenser are not clogged. Since AD 2007-24-15... condition described previously is likely to exist or develop in other products of the same type design. AD...

  5. Aerosols at the poles: an AeroCom Phase II multi-model evaluation

    Directory of Open Access Journals (Sweden)

    M. Sand

    2017-10-01

    Full Text Available Atmospheric aerosols from anthropogenic and natural sources reach the polar regions through long-range transport and affect the local radiation balance. Such transport is, however, poorly constrained in present-day global climate models, and few multi-model evaluations of polar anthropogenic aerosol radiative forcing exist. Here we compare the aerosol optical depth (AOD at 550 nm from simulations with 16 global aerosol models from the AeroCom Phase II model intercomparison project with available observations at both poles. We show that the annual mean multi-model median is representative of the observations in Arctic, but that the intermodel spread is large. We also document the geographical distribution and seasonal cycle of the AOD for the individual aerosol species: black carbon (BC from fossil fuel and biomass burning, sulfate, organic aerosols (OAs, dust, and sea-salt. For a subset of models that represent nitrate and secondary organic aerosols (SOAs, we document the role of these aerosols at high latitudes.The seasonal dependence of natural and anthropogenic aerosols differs with natural aerosols peaking in winter (sea-salt and spring (dust, whereas AOD from anthropogenic aerosols peaks in late spring and summer. The models produce a median annual mean AOD of 0.07 in the Arctic (defined here as north of 60° N. The models also predict a noteworthy aerosol transport to the Antarctic (south of 70° S with a resulting AOD varying between 0.01 and 0.02. The models have estimated the shortwave anthropogenic radiative forcing contributions to the direct aerosol effect (DAE associated with BC and OA from fossil fuel and biofuel (FF, sulfate, SOAs, nitrate, and biomass burning from BC and OA emissions combined. The Arctic modelled annual mean DAE is slightly negative (−0.12 W m−2, dominated by a positive BC FF DAE in spring and a negative sulfate DAE in summer. The Antarctic DAE is governed by BC FF. We perform sensitivity

  6. Switching LPV Control with Double-Layer LPV Model for Aero-Engines

    Science.gov (United States)

    Tang, Lili; Huang, Jinquan; Pan, Muxuan

    2017-11-01

    To cover the whole range of operating conditions of aero-engine, a double-layer LPV model is built so as to take into account of the variability due to the flight altitude, Mach number and the rotational speed. With this framework, the problem of designing LPV state-feedback robust controller that guarantees desired bounds on both H_∞ and H_2 performances is considered. Besides this, to reduce the conservativeness caused by a single LPV controller of the whole flight envelope and the common Lyapunov function method, a new method is proposed to design a family of LPV switching controllers. The switching LPV controllers can ensure that the closed-loop system remains stable in the sense of Lyapunov under arbitrary switching logic. Meanwhile, the switching LPV controllers can ensure the parameters change smoothly. The validity and performance of the theoretical results are demonstrated through a numerical example.

  7. Methodologies for predicting the part-load performance of aero-derivative gas turbines

    DEFF Research Database (Denmark)

    Haglind, Fredrik; Elmegaard, Brian

    2009-01-01

    Prediction of the part-load performance of gas turbines is advantageous in various applications. Sometimes reasonable part-load performance is sufficient, while in other cases complete agreement with the performance of an existing machine is desirable. This paper is aimed at providing some guidance...... on methodologies for predicting part-load performance of aero-derivative gas turbines. Two different design models – one simple and one more complex – are created. Subsequently, for each of these models, the part-load performance is predicted using component maps and turbine constants, respectively. Comparisons...... with manufacturer data are made. With respect to the design models, the simple model, featuring a compressor, combustor and turbines, results in equally good performance prediction in terms of thermal efficiency and exhaust temperature as does a more complex model. As for part-load predictions, the results suggest...

  8. Propulsion System Dynamic Modeling of the NASA Supersonic Concept Vehicle for AeroPropulsoServoElasticity

    Science.gov (United States)

    Kopasakis, George; Connolly, Joseph W.; Seiel, Jonathan

    2016-01-01

    A summary of the propulsion system modeling under NASA's High Speed Project (HSP) AeroPropulsoServoElasticity (APSE) task is provided with a focus on the propulsion system for the low-boom supersonic configuration developed by Lockheed Martin and referred to as the N+2 configuration. This summary includes details on the effort to date to develop computational models for the various propulsion system components. The objective of this paper is to summarize the model development effort in this task, while providing more detail in the modeling areas that have not been previously published. The purpose of the propulsion system modeling and the overall APSE effort is to develop an integrated dynamic vehicle model to conduct appropriate unsteady analysis of supersonic vehicle performance. This integrated APSE system model concept includes the propulsion system model, and the vehicle structural aerodynamics model. The development to date of such a preliminary integrated model will also be summarized in this report

  9. Reliability Estimation of Aero-engine Based on Mixed Weibull Distribution Model

    Science.gov (United States)

    Yuan, Zhongda; Deng, Junxiang; Wang, Dawei

    2018-02-01

    Aero-engine is a complex mechanical electronic system, based on analysis of reliability of mechanical electronic system, Weibull distribution model has an irreplaceable role. Till now, only two-parameter Weibull distribution model and three-parameter Weibull distribution are widely used. Due to diversity of engine failure modes, there is a big error with single Weibull distribution model. By contrast, a variety of engine failure modes can be taken into account with mixed Weibull distribution model, so it is a good statistical analysis model. Except the concept of dynamic weight coefficient, in order to make reliability estimation result more accurately, three-parameter correlation coefficient optimization method is applied to enhance Weibull distribution model, thus precision of mixed distribution reliability model is improved greatly. All of these are advantageous to popularize Weibull distribution model in engineering applications.

  10. OC3—Benchmark Exercise of Aero-elastic Offshore Wind Turbine Codes

    Science.gov (United States)

    Passon, P.; Kühn, M.; Butterfield, S.; Jonkman, J.; Camp, T.; Larsen, T. J.

    2007-07-01

    This paper introduces the work content and status of the first international investigation and verification of aero-elastic codes for offshore wind turbines as performed by the "Offshore Code Comparison Collaboration"(OC3) within the "IEA Wind Annex XXIII - Subtask 2". An overview is given on the state-of-the-art of the concerned offshore wind turbine simulation codes. Exemplary results of benchmark simulations from the first phase of the project are presented and discussed while subsequent phases are introduced. Furthermore, the paper discusses areas where differences between the codes have been identified and the sources of those differences, such as the differing theories implemented into the individual codes. Finally, further research and code development needs are presented based on the latest findings from the current state of the project.

  11. A Modular Aero-Propulsion System Simulation of a Large Commercial Aircraft Engine

    Science.gov (United States)

    DeCastro, Jonathan A.; Litt, Jonathan S.; Frederick, Dean K.

    2008-01-01

    A simulation of a commercial engine has been developed in a graphical environment to meet the increasing need across the controls and health management community for a common research and development platform. This paper describes the Commercial Modular Aero Propulsion System Simulation (C-MAPSS), which is representative of a 90,000-lb thrust class two spool, high bypass ratio commercial turbofan engine. A control law resembling the state-of-the-art on board modern aircraft engines is included, consisting of a fan-speed control loop supplemented by relevant engine limit protection regulator loops. The objective of this paper is to provide a top-down overview of the complete engine simulation package.

  12. Presentations from the Aeroelastic Workshop - latest results from AeroOpt

    Energy Technology Data Exchange (ETDEWEB)

    Hartvig Hansen, M. (ed.)

    2011-10-15

    This report contains the slides of the presentations at the Aeroelastic Workshop held at Risoe-DTU for the wind energy industry in Denmark on October 27, 2011. The scientific part of the agenda at this workshop was 1) Detailed and reduced models of dynamic mooring system (Anders M. Hansen). 2) Bend-twist coupling investigation in HAWC2 (Taeseong Kim). 3) Q3UIC - A new aerodynamic airfoil tool including rotational effects (Nestor R. Garcia). 4) Influence of up-scaling on loads, control and aerodynamic modeling (Helge Aa. Madsen). 5) Aerodynamic damping of lateral tower vibrations (Bjarne S. Kallesoee). 6) Open- and closed-loop aeroservoelastic analysis with HAWCStab2 (Morten H. Hansen). 7) Design and test of a thick, flatback, high-lift multielement airfoil (Frederik Zahle). The presented results are mainly obtained in the EUDP project ''Aeroelastic Optimization of MW Wind Turbines (AeroOpt)''. (Author)

  13. The Role of Free-Stream Turbulence on High Pressure Turbine Aero-Thermal Stage Interaction

    Science.gov (United States)

    Kopriva, James Earl

    Turbulence plays an important role on the aero-thermal performance of modern aircraft engine High Pressure Turbines (HPT). The role of the vane wake and passage turbulence on the downstream blade flow field is an important consideration for both performance and durability. Obtaining measurements to fully characterize the flow field can be challenging and costly in an experimental facility. Advances in computational Fluid Dynamic (CFD) modeling and High Performance Computing (HPC) are providing opportunity to close these measurement gaps. In order for CFD to be adopted, methods need to be both accurate and efficient. Meshing approaches must also be able to resolve complex HPT geometry while maintaining quality adequate for scale-resolved simulations. Therefore, the accuracy of executing scale-resolved simulations with a second-order code on a mesh of prisms and tetrahedrals in Fluent is considered. Before execution of the HPT computational study, a building block approach is taken to gain quantified predictive performance in the modeling approach as well as understanding limitations in lower computational cost modeling approaches. The predictive capability for Reynolds Averaged Navier Stokes (RANS), Hybrid Large Eddy Simulation (LES), and wall-resolved LES turbulence modeling approaches are first assessed for a cylinder in cross-flow at a Reynolds number of 2580. The flow condition and simple geometry facilitate a quick turn-around for modeling assessment before moving the HPT vane study at high Reynolds and Mach number conditions. Modeling approaches are then assessed relative to the experimental measurements of Arts and Rouvroit (1992) on a pitch-line HPT uncooled vane at high Mach and Reynolds numbers conditions with low (0-6%) free-stream turbulence. The current unstructured second-order LES approach agrees with experimental data and is found to be within the equivalent experimental uncertainty when compared to the structured high-ordered solver FDL3DI. The

  14. EFFECT OF AERO-/ANAEROBIOSIS ON DECARBOXYLASE ACTIVITY OF SELECTED LACTIC ACID BACTERIA

    Directory of Open Access Journals (Sweden)

    Stanislav Kráčmar

    2010-05-01

    Full Text Available Biogenic amines are undesirable compounds produced in foods mainly through bacterial decarboxylase activity. The aim of this study was to investigate some environmental conditions (particularly aero/anaerobiosis, sodium chloride concentration (0–2% w/w, and amount of lactose (0–1% w/w on the activity of tyrosine decarboxylase enzymes of selected six technological important Lactococcus lactis strains. The levels of parameters tested were chosen according to real situation in fermented dairy products technology (especially cheese-making. Tyramine was determined by the ion-exchange chromatography with post-column ninhydrine derivatization and spectrophotometric detection. Tyrosine decarboxylation occurred during the active growth phase. Under the model conditions used, oxygen availability had influence on tyramine production, anaerobiosis seemed to favour the enzyme activity because all L. lactis strains produced higher tyramine amount. doi:10.5219/43

  15. An AeroCom Assessment of Black Carbon in Arctic Snow and Sea Ice

    Science.gov (United States)

    Jiao, C.; Flanner, M. G.; Balkanski, Y.; Bauer, S. E.; Bellouin, N.; Bernsten, T. K.; Bian, H.; Carslaw, K. S.; Chin, M.; DeLuca, N.; hide

    2014-01-01

    Though many global aerosols models prognose surface deposition, only a few models have been used to directly simulate the radiative effect from black carbon (BC) deposition to snow and sea ice. Here, we apply aerosol deposition fields from 25 models contributing to two phases of the Aerosol Comparisons between Observations and Models (AeroCom) project to simulate and evaluate within-snow BC concentrations and radiative effect in the Arctic. We accomplish this by driving the offline land and sea ice components of the Community Earth System Model with different deposition fields and meteorological conditions from 2004 to 2009, during which an extensive field campaign of BC measurements in Arctic snow occurred. We find that models generally underestimate BC concentrations in snow in northern Russia and Norway, while overestimating BC amounts elsewhere in the Arctic. Although simulated BC distributions in snow are poorly correlated with measurements, mean values are reasonable. The multi-model mean (range) bias in BC concentrations, sampled over the same grid cells, snow depths, and months of measurements, are -4.4 (-13.2 to +10.7) ng/g for an earlier phase of AeroCom models (phase I), and +4.1 (-13.0 to +21.4) ng/g for a more recent phase of AeroCom models (phase II), compared to the observational mean of 19.2 ng/g. Factors determining model BC concentrations in Arctic snow include Arctic BC emissions, transport of extra-Arctic aerosols, precipitation, deposition efficiency of aerosols within the Arctic, and meltwater removal of particles in snow. Sensitivity studies show that the model-measurement evaluation is only weakly affected by meltwater scavenging efficiency because most measurements were conducted in non-melting snow. The Arctic (60-90degN) atmospheric residence time for BC in phase II models ranges from 3.7 to 23.2 days, implying large inter-model variation in local BC deposition efficiency. Combined with the fact that most Arctic BC deposition originates

  16. An AeroCom assessment of black carbon in Arctic snow and sea ice

    Energy Technology Data Exchange (ETDEWEB)

    Jiao, C.; Flanner, M. G.; Balkanski, Y.; Bauer, S. E.; Bellouin, N.; Berntsen, T. K.; Bian, H.; Carslaw, K. S.; Chin, M.; De Luca, N.; Diehl, T.; Ghan, S. J.; Iversen, T.; Kirkevåg, A.; Koch, D.; Liu, X.; Mann, G. W.; Penner, J. E.; Pitari, G.; Schulz, M.; Seland, Ø.; Skeie, R. B.; Steenrod, S. D.; Stier, P.; Takemura, T.; Tsigaridis, K.; van Noije, T.; Yun, Y.; Zhang, K.

    2014-01-01

    Though many global aerosols models prognose surface deposition, only a few models have been used to directly simulate the radiative effect from black carbon (BC) deposition to snow and sea ice. In this paper, we apply aerosol deposition fields from 25 models contributing to two phases of the Aerosol Comparisons between Observations and Models (AeroCom) project to simulate and evaluate within-snow BC concentrations and radiative effect in the Arctic. We accomplish this by driving the offline land and sea ice components of the Community Earth System Model with different deposition fields and meteorological conditions from 2004 to 2009, during which an extensive field campaign of BC measurements in Arctic snow occurred. We find that models generally underestimate BC concentrations in snow in northern Russia and Norway, while overestimating BC amounts elsewhere in the Arctic. Although simulated BC distributions in snow are poorly correlated with measurements, mean values are reasonable. The multi-model mean (range) bias in BC concentrations, sampled over the same grid cells, snow depths, and months of measurements, are -4.4 (-13.2 to +10.7) ng g-1 for an earlier phase of AeroCom models (phase I), and +4.1 (-13.0 to +21.4) ng g-1 for a more recent phase of AeroCom models (phase II), compared to the observational mean of 19.2 ng g-1. Factors determining model BC concentrations in Arctic snow include Arctic BC emissions, transport of extra-Arctic aerosols, precipitation, deposition efficiency of aerosols within the Arctic, and meltwater removal of particles in snow. Sensitivity studies show that the model–measurement evaluation is only weakly affected by meltwater scavenging efficiency because most measurements were conducted in non-melting snow. The Arctic (60–90° N) atmospheric residence time for BC in phase II models ranges from 3.7 to 23.2 days, implying large inter-model variation in local BC deposition efficiency. Combined with

  17. Investigation on flow oscillation modes and aero-acoustics generation mechanism in cavity

    Science.gov (United States)

    Yang, Dang-Guo; Lu, Bo; Cai, Jin-Sheng; Wu, Jun-Qiang; Qu, Kun; Liu, Jun

    2018-05-01

    Unsteady flow and multi-scale vortex transformation inside a cavity of L/D = 6 (ratio of length to depth) at Ma = 0.9 and 1.5 were studied using the numerical simulation method of modified delayed detached eddy simulation (DDES) in this paper. Aero-acoustic characteristics for the cavity at same flow conditions were obtained by the numerical method and 0.6 m by 0.6 m transonic and supersonic wind-tunnel experiments. The analysis on the computational and experimental results indicates that some vortex generates from flow separation in shear-layer over the cavity, and the vortex moves from forward to downward of the cavity at some velocity, and impingement of the vortex and the rear-wall of the cavity occurs. Some sound waves spread abroad to the cavity fore-wall, which induces some new vortex generation, and the vortex sheds, moves and impinges on the cavity rear-wall. New sound waves occur. The research results indicate that sound wave feedback created by the impingement of the shedding-vortices and rear cavity face leads to flow oscillations and noise generation inside the cavity. Analysis on aero-acoustic characteristics inside the cavity is feasible. The simulated self-sustained flow-oscillation modes and peak sound pressure on typical frequencies inside the cavity agree well with Rossiter’s and Heller’s predicated results. Moreover, the peak sound pressure occurs in the first and second flow-oscillation modes and most of sound energy focuses on the low-frequency region. Compared with subsonic speed (Ma = 0.9), aerodynamic noise is more intense at Ma = 1.5, which is induced by compression wave or shock wave in near region of fore and rear cavity face.

  18. Advanced Engineering Methods for Assessing Welding Distortion in Aero-Engine Assemblies

    International Nuclear Information System (INIS)

    Jackson, Kathryn; Darlington, Roger

    2011-01-01

    Welding remains an attractive fabrication method for aero-engine assemblies, offering high production rates and reduced total cost, particularly for large complex assemblies. However, distortion generated during the welding process continues to provide a major challenge in terms of the control of geometric tolerances and residual stress. The welding distortion is influenced by the sequence and position of joints, the clamping configuration and the design of the assembly. For large complex assemblies the range of these options may be large. Hence the use of numerical simulation at an early stage of the product development process is valuable to enable a wide range of these factors to be explored with the aim of minimising welding distortions before production commences, and thereby reducing the product development time. In this paper, a new technique for simulation of welding distortions based on a shrinkage analysis is evaluated for an aero-engine assembly. The shrinkage simulations were built and solved using the ESI Group software Weld Planner. The rapid simulation speed enabled a wide range of welding plans to be explored, leading to recommendations for the fabrication process. The sensitivity of the model to mesh size and material properties is reported. The results of the shrinkage analysis were found to be similar to those of a transient analysis generated using ESI Group software SysWeld. The solution times were found to be significantly lower for the shrinkage analysis than the transient analysis. Hence it has been demonstrated that shrinkage analysis is a valuable tool for exploring the fabrication process of a welded assembly at an early stage of the product development process.

  19. C-Band Airport Surface Communications System Standards Development. Phase II Final Report. Volume 2: Test Bed Performance Evaluation and Final AeroMACS Recommendations

    Science.gov (United States)

    Hall, Edward; Magner, James

    2011-01-01

    This report is provided as part of ITT s NASA Glenn Research Center Aerospace Communication Systems Technical Support (ACSTS) contract NNC05CA85C, Task 7: New ATM Requirements-Future Communications, C-Band and L-Band Communications Standard Development and was based on direction provided by FAA project-level agreements for New ATM Requirements-Future Communications. Task 7 included two subtasks. Subtask 7-1 addressed C-band (5091- to 5150-MHz) airport surface data communications standards development, systems engineering, test bed and prototype development, and tests and demonstrations to establish operational capability for the Aeronautical Mobile Airport Communications System (AeroMACS). Subtask 7-2 focused on systems engineering and development support of the L-band digital aeronautical communications system (L-DACS). Subtask 7-1 consisted of two phases. Phase I included development of AeroMACS concepts of use, requirements, architecture, and initial high-level safety risk assessment. Phase II builds on Phase I results and is presented in two volumes. Volume I is devoted to concepts of use, system requirements, and architecture, including AeroMACS design considerations. Volume II (this document) describes an AeroMACS prototype evaluation and presents final AeroMACS recommendations. This report also describes airport categorization and channelization methodologies. The purposes of the airport categorization task were (1) to facilitate initial AeroMACS architecture designs and enable budgetary projections by creating a set of airport categories based on common airport characteristics and design objectives, and (2) to offer high-level guidance to potential AeroMACS technology and policy development sponsors and service providers. A channelization plan methodology was developed because a common global methodology is needed to assure seamless interoperability among diverse AeroMACS services potentially supplied by multiple service providers.

  20. C-Band Airport Surface Communications System Standards Development. Phase II Final Report. Volume 1: Concepts of Use, Initial System Requirements, Architecture, and AeroMACS Design Considerations

    Science.gov (United States)

    Hall, Edward; Isaacs, James; Henriksen, Steve; Zelkin, Natalie

    2011-01-01

    This report is provided as part of ITT s NASA Glenn Research Center Aerospace Communication Systems Technical Support (ACSTS) contract NNC05CA85C, Task 7: New ATM Requirements-Future Communications, C-Band and L-Band Communications Standard Development and was based on direction provided by FAA project-level agreements for New ATM Requirements-Future Communications. Task 7 included two subtasks. Subtask 7-1 addressed C-band (5091- to 5150-MHz) airport surface data communications standards development, systems engineering, test bed and prototype development, and tests and demonstrations to establish operational capability for the Aeronautical Mobile Airport Communications System (AeroMACS). Subtask 7-2 focused on systems engineering and development support of the L-band digital aeronautical communications system (L-DACS). Subtask 7-1 consisted of two phases. Phase I included development of AeroMACS concepts of use, requirements, architecture, and initial high-level safety risk assessment. Phase II builds on Phase I results and is presented in two volumes. Volume I (this document) is devoted to concepts of use, system requirements, and architecture, including AeroMACS design considerations. Volume II describes an AeroMACS prototype evaluation and presents final AeroMACS recommendations. This report also describes airport categorization and channelization methodologies. The purposes of the airport categorization task were (1) to facilitate initial AeroMACS architecture designs and enable budgetary projections by creating a set of airport categories based on common airport characteristics and design objectives, and (2) to offer high-level guidance to potential AeroMACS technology and policy development sponsors and service providers. A channelization plan methodology was developed because a common global methodology is needed to assure seamless interoperability among diverse AeroMACS services potentially supplied by multiple service providers.

  1. Reconstruction of the aero-mixture channels of the pulverized coal plant of the 100MW power plant unit

    Directory of Open Access Journals (Sweden)

    Ivanovic Vladan B.

    2011-01-01

    Full Text Available After the last revitalization of thermal power block of 100 MW in TPP “Kostolac A”, made in the year 2004, during the operation of the plant, pulverized coal deposition often occurred in horizontal sections of the aero-mixture channels. Deposition phenomenon manifested itself in places ahead of spherical compensators in the direction of flow of pulverized coal to the burners, due to unfavorable configuration of these channels. Coal dust deposited in the channels dried and spontaneously combusted, causing numerous damage to channels and its isolation as well as the frequent stoppage of the operation for necessary interventions. The paper presents the original solution of reconstruction of aero-mixture channels which prevented deposition of coal dust and its eventual ignition. In this way the reliability of the mill plant is maximized and higher availability of boiler and block as a whole is achieved.

  2. Aero-structural optimization of wind turbine blades using a reduced set of design load cases including turbulence

    DEFF Research Database (Denmark)

    Sessarego, Matias; Shen, Wen Zhong

    2018-01-01

    Modern wind turbine aero-structural blade design codes generally use a smaller fraction of the full design load base (DLB) or neglect turbulent inflow as defined by the International Electrotechnical Commission standards. The current article describes an automated blade design optimization method...... based on surrogate modeling that includes a very large number of design load cases (DLCs) including turbulence. In the present work, 325 DLCs representative of the full DLB are selected based on the message-passing-interface (MPI) limitations in Matlab. Other methods are currently being investigated, e.......g. a Python MPI implementation, to overcome the limitations in Matlab MPI and ultimately achieve a full DLB optimization framework. The reduced DLB and the annual energy production are computed using the state-of-the-art aero-servo-elastic tool HAWC2. Furthermore, some of the interior dimensions of the blade...

  3. Improvement on Main/backup Controller Switching Device of the Nozzle Throat Area Control System for a Turbofan Aero Engine

    Science.gov (United States)

    Li, Jie; Duan, Minghu; Yan, Maode; Li, Gang; Li, Xiaohui

    2014-06-01

    A full authority digital electronic controller (FADEC) equipped with a full authority hydro-mechanical backup controller (FAHMBC) is adopted as the nozzle throat area control system (NTACS) of a turbofan aero engine. In order to ensure the switching reliability of the main/backup controller, the nozzle throat area control switching valve was improved from three-way convex desktop slide valve to six-way convex desktop slide valve. Simulation results show that, if malfunctions of FAEDC occur and abnormal signals are outputted from FADEC, NTACS will be seriously influenced by the main/backup controller switching in several working states, while NTACS will not be influenced by using the improved nozzle throat area control switching valve, thus the controller switching process will become safer and smoother and the working reliability of this turbofan aero engine is improved by the controller switching device improvement.

  4. CONSIDERATIONS ON ANATOMY AND PHYSIOLOGY OF LYMPH VESSELS OF UPPER AERO DIGESTIVE ORGANS AND CERVICAL SATELLITE LYMPH NODE GROUP.

    Science.gov (United States)

    Ciupilan, Corina; Stan, C I

    2016-01-01

    The almost constant local regional development of the cancers of upper aero digestive organs requires the same special attention to cervical lymph node metastases, as well as to the primary neoplastic burning point. The surgical therapy alone or associated has a mutilating, damaging character, resulting in loss of an organ and function, most of the times with social implications, involving physical distortions with aesthetic consequences, which make the reintegration of the individual into society questionable. The problem of cervical lymph node metastases is vast and complex, reason why we approached several anatomical and physiological aspects of lymph vessels of the aero digestive organs. Among the available elements during treatment, the headquarters of the tumour, its histologic degree, and its infiltrative nature, each of them significantly influences the possibility of developing metastases.

  5. Emergency airway management in critically injured patients: a survey of U.S. aero-medical transport programs.

    Science.gov (United States)

    James, Dorsha N; Voskresensky, Igor V; Jack, Meg; Cotton, Bryan A

    2009-06-01

    Pre-hospital airway management represents the intervention most likely to impact outcomes in critically injured patients. As such, airway management issues dominate quality improvement (QI) reviews of aero-medical programs. The purpose of this study was to evaluate current practice patterns of airway management in trauma among U.S. aero-medical service (AMS) programs. The Association of Air Medical Services (AAMS) Resource Guide from 2005 to 2006 was utilized to identify the e-mail addresses of all directors of U.S. aero-medical transport programs. Program directors from 182 U.S. aero-medical programs were asked to participate in an anonymous, web-based survey of emergency airway management protocols and practices. Non-responders to the initial request were contacted a second time by e-mail. 89 programs responded. 98.9% have rapid sequence intubation (RSI) protocols. 90% use succinylcholine, 70% use long-acting neuromuscular blockers (NMB) within their RSI protocol. 77% have protocols for mandatory in-flight sedation but only 13% have similar protocols for maintenance paralytics. 60% administer long-acting NMB immediately after RSI, 13% after confirmation of neurological activity. Given clinical scenarios, however, 97% administer long-acting NMB to patients with scene and in-flight Glasgow Coma Scale (GCS) of 3, even for brief transport times. The majority of AMS programs have well defined RSI and in-flight sedation protocols, while protocols for in-flight NMB are uncommon. Despite this, nearly all programs administer long-acting NMB following RSI, irrespective of GCS or flight time. Given the impact of in-flight NMB on initial assessment, early intervention, and injury severity scoring, a critical appraisal of current AMS airway management practices appears warranted.

  6. Turbofan Volume Dynamics Model for Investigations of Aero-Propulso-Servo-Elastic Effects in a Supersonic Commercial Transport

    Science.gov (United States)

    Connolly, Joseph W.; Kopasakis, George; Lemon, Kimberly A.

    2010-01-01

    A turbofan simulation has been developed for use in aero-propulso-servo-elastic coupling studies, on supersonic vehicles. A one-dimensional lumped volume approach is used whereby each component (fan, high-pressure compressor, combustor, etc.) is represented as a single volume using characteristic performance maps and conservation equations for continuity, momentum and energy. The simulation is developed in the MATLAB/SIMULINK (The MathWorks, Inc.) environment in order to facilitate controls development, and ease of integration with a future aero-servo-elastic vehicle model being developed at NASA Langley. The complete simulation demonstrated steady state results that closely match a proposed engine suitable for a supersonic business jet at the cruise condition. Preliminary investigation of the transient simulation revealed expected trends for fuel flow disturbances as well as upstream pressure disturbances. A framework for system identification enables development of linear models for controller design. Utilizing this framework, a transfer function modeling an upstream pressure disturbance s impacts on the engine speed is developed as an illustrative case of the system identification. This work will eventually enable an overall vehicle aero-propulso-servo-elastic model

  7. Integrated approach for stress based lifing of aero gas turbine blades

    Science.gov (United States)

    Abu, Abdullahi Obonyegba

    In order to analyse the turbine blade life, the damage due to the combined thermal and mechanical loads should be adequately accounted for. This is more challenging when detailed component geometry is limited. Therefore, a compromise between the level of geometric detail and the complexity of the lifing method to be implemented would be necessary. This research focuses on how the life assessment of aero engine turbine blades can be done, considering the balance between available design inputs and adequate level of fidelity. Accordingly, the thesis contributes to developing a generic turbine blade lifing method that is based on the engine thermodynamic cycle; as well as integrating critical design/technological factors and operational parameters that influence the aero engine blade life. To this end, thermo-mechanical fatigue was identified as the critical damage phenomenon driving the life of the turbine blade.. The developed approach integrates software tools and numerical models created using the minimum design information typically available at the early design stages. Using finite element analysis of an idealised blade geometry, the approach captures relevant impacts of thermal gradients and thermal stresses that contribute to the thermo-mechanical fatigue damage on the gas turbine blade. The blade life is evaluated using the Neu/Sehitoglu thermo-mechanical fatigue model that considers damage accumulation due to fatigue, oxidation, and creep. The leading edge is examined as a critical part of the blade to estimate the damage severity for different design factors and operational parameters. The outputs of the research can be used to better understand how the environment and the operating conditions of the aircraft affect the blade life consumption and therefore what is the impact on the maintenance cost and the availability of the propulsion system. This research also finds that the environmental (oxidation) effect drives the blade life and the blade coolant

  8. Review of modern low emissions combustion technologies for aero gas turbine engines

    Science.gov (United States)

    Liu, Yize; Sun, Xiaoxiao; Sethi, Vishal; Nalianda, Devaiah; Li, Yi-Guang; Wang, Lu

    2017-10-01

    Pollutant emissions from aircraft in the vicinity of airports and at altitude are of great public concern due to their impact on environment and human health. The legislations aimed at limiting aircraft emissions have become more stringent over the past few decades. This has resulted in an urgent need to develop low emissions combustors in order to meet legislative requirements and reduce the impact of civil aviation on the environment. This article provides a comprehensive review of low emissions combustion technologies for modern aero gas turbines. The review considers current high Technologies Readiness Level (TRL) technologies including Rich-Burn Quick-quench Lean-burn (RQL), Double Annular Combustor (DAC), Twin Annular Premixing Swirler combustors (TAPS), Lean Direct Injection (LDI). It further reviews some of the advanced technologies at lower TRL. These include NASA multi-point LDI, Lean Premixed Prevaporised (LPP), Axially Staged Combustors (ASC) and Variable Geometry Combustors (VGC). The focus of the review is placed on working principles, a review of the key technologies (includes the key technology features, methods of realising the technology, associated technology advantages and design challenges, progress in development), technology application and emissions mitigation potential. The article concludes the technology review by providing a technology evaluation matrix based on a number of combustion performance criteria including altitude relight auto-ignition flashback, combustion stability, combustion efficiency, pressure loss, size and weight, liner life and exit temperature distribution.

  9. Propulsion System Dynamic Modeling for the NASA Supersonic Concept Vehicle: AeroPropulsoServoElasticity

    Science.gov (United States)

    Kopasakis, George; Connolly, Joseph; Seidel, Jonathan

    2014-01-01

    A summary of the propulsion system modeling under NASA's High Speed Project (HSP) AeroPropulsoServoElasticity (APSE) task is provided with a focus on the propulsion system for the low-boom supersonic configuration developed by Lockheed Martin and referred to as the N+2 configuration. This summary includes details on the effort to date to develop computational models for the various propulsion system components. The objective of this paper is to summarize the model development effort in this task, while providing more detail in the modeling areas that have not been previously published. The purpose of the propulsion system modeling and the overall APSE effort is to develop an integrated dynamic vehicle model to conduct appropriate unsteady analysis of supersonic vehicle performance. This integrated APSE system model concept includes the propulsion system model, and the vehicle structural-aerodynamics model. The development to date of such a preliminary integrated model will also be summarized in this report.propulsion system dynamics, the structural dynamics, and aerodynamics.

  10. A novel full scale experimental characterization of wind turbine aero-acoustic noise sources - preliminary results

    DEFF Research Database (Denmark)

    Aagaard Madsen, Helge; Bertagnolio, Franck; Fischer, Andreas

    2016-01-01

    of the blade and the noise on the ground in a distance of about one rotor diameter. In total six surface microphones were used to measure the SP at the leading edge (LE) and trailing edge (TE) of the blade. In parallel noise was measured by eight microphones placed on plates on the ground around the turbine......The paper describes a novel full scale experiment on a 500 kW wind turbine with the main objective to characterize the aero-acoustic noise sources. The idea behind the instrumentation is to study the link and correlation between the surface pressure (SP) fluctuations in the boundary layer...... in equidistant angles on a circle with a radius of about one rotor diameter. The data were analyzed in segments of 2.2 s which is the time for one rotor revolution. The spectra for the TE microphones on the suction side of the blade show a characteristic roll-off pattern around a frequency of 600-700 Hz...

  11. New design of a compact aero-robotic drilling end effector: An experimental analysis

    Directory of Open Access Journals (Sweden)

    Shi Zhenyun

    2016-08-01

    Full Text Available This paper presents the development of a normal adjustment cell (NAC in aero-robotic drilling to improve the quality of vertical drilling, by using an intelligent double-eccentric disk normal adjustment mechanism (2-EDNA, a spherical plain bearing and a floating compress module with sensors. After the surface normal vector is calculated based on the laser sensors’ feedback, the 2-EDNA concept is conceived specifically to address the deviation of the spindle from the surface normal at the drilling point. Following the angle calculation, depending on the actual initial position, two precise eccentric disks (PEDs with an identical eccentric radius are used to rotate with the appropriate angles using two high-resolution DC servomotors. The two PEDs will carry the spindle to coincide with the surface normal, keeping the vertex of the drill bit still to avoid repeated adjustment and position compensation. A series of experiments was conducted on an aeronautical drilling robot platform with a precise NAC. The effect of normal adjustment on bore diameter, drilling force, burr size, drilling heat, and tool wear was analyzed. The results validate that using the NAC in robotic drilling results in greatly improved vertical drilling quality and is attainable in terms of intelligence and accuracy.

  12. Dynamic behavior of aero-engine rotor with fusing design suffering blade off

    Directory of Open Access Journals (Sweden)

    Cun WANG

    2017-06-01

    Full Text Available Fan blade off (FBO from a running turbofan rotor will introduce sudden unbalance into the dynamical system, which will lead to the rub-impact, the asymmetry of rotor and a series of interesting dynamic behavior. The paper first presents a theoretical study on the response excited by sudden unbalance. The results reveal that the reaction force of the bearing located near the fan could always reach a very high value which may lead to the crush of ball, journal sticking, high stress on the other components and some other failures to endanger the safety of engine in FBO event. Therefore, the dynamic influence of a safety design named “fusing” is investigated by mechanism analysis. Meantime, an explicit FBO model is established to simulate the FBO event, and evaluate the effectiveness and potential dynamic influence of fusing design. The results show that the fusing design could reduce the vibration amplitude of rotor, the reaction force on most bearings and loads on mounts, but the sudden change of support stiffness induced by fusing could produce an impact effect which will couple with the influence of sudden unbalance. Therefore, the implementation of the design should be considered carefully with optimized parameters in actual aero-engine.

  13. Unusual structure in forsterite glass synthesized by an aero-acoustic levitation technique

    International Nuclear Information System (INIS)

    Kohara, Shinji; Suzuya, Kentaro; Takeuchi, Ken

    2005-01-01

    Forsterite Mg 2 SiO 4 exhibits an orthorhombic structure consisted of two kinds of MgO 6 octahedra. One of them forms edge-sharing ribbons along the [001] direction which are linked by the other kind of edge-sharing MgO 6 octahedra, resulting in a three-dimensional framework. Given only 33.3 mol% of SiO 2 in the material, the SiO 4 tetrahedra are isolated within the framework, sharing the O-O bonds with the common edges of the MgO 6 octahedra. If forsterite can be vitrified, an interesting question concerning the glass structure arises because there is insufficient glass forming SiO 2 to establish the corner-sharing SiO 4 tetrahedral net-work needed in conventional silicate glasses. A bulk Mg 2 SiO 4 glass was synthesized using an aero-acoustic levitation technique and to visualize the short-to intermediate-range structure by a combined high-energy synchrotron x-ray and neutron diffraction and reverse Monte Carlo computer simulation. We found that the role of network former is largely taken on by corner-and edge-sharing ionic magnesium species that adopt 4-, 5- and 6-coordination with oxygen. (author)

  14. Uncertainty of measurement for large product verification: evaluation of large aero gas turbine engine datums

    International Nuclear Information System (INIS)

    Muelaner, J E; Wang, Z; Keogh, P S; Brownell, J; Fisher, D

    2016-01-01

    Understanding the uncertainty of dimensional measurements for large products such as aircraft, spacecraft and wind turbines is fundamental to improving efficiency in these products. Much work has been done to ascertain the uncertainty associated with the main types of instruments used, based on laser tracking and photogrammetry, and the propagation of this uncertainty through networked measurements. Unfortunately this is not sufficient to understand the combined uncertainty of industrial measurements, which include secondary tooling and datum structures used to locate the coordinate frame. This paper presents for the first time a complete evaluation of the uncertainty of large scale industrial measurement processes. Generic analysis and design rules are proven through uncertainty evaluation and optimization for the measurement of a large aero gas turbine engine. This shows how the instrument uncertainty can be considered to be negligible. Before optimization the dominant source of uncertainty was the tooling design, after optimization the dominant source was thermal expansion of the engine; meaning that no further improvement can be made without measurement in a temperature controlled environment. These results will have a significant impact on the ability of aircraft and wind turbines to improve efficiency and therefore reduce carbon emissions, as well as the improved reliability of these products. (paper)

  15. Towards an Aero-Propulso-Servo-Elasticity Analysis of a Commercial Supersonic Transport

    Science.gov (United States)

    Connolly, Joseph W.; Kopasakis, George; Chwalowski, Pawel; Sanetrik, Mark D.; Carlson, Jan-Renee; Silva, Walt A.; McNamara, Jack

    2016-01-01

    This paper covers the development of an aero-propulso-servo-elastic (APSE) model using computational fluid dynamics (CFD) and linear structural deformations. The APSE model provides the integration of the following two previously developed nonlinear dynamic simulations: a variable cycle turbofan engine and an elastic supersonic commercial transport vehicle. The primary focus of this study is to provide a means to include relevant dynamics of a turbomachinery propulsion system into the aeroelastic studies conducted during a vehicle design, which have historically neglected propulsion effects. A high fidelity CFD tool is used here for the integration platform. The elastic vehicle neglecting the propulsion system serves as a comparison of traditional approaches to the APSE results. An overview of the methodology is presented for integrating the propulsion system and elastic vehicle. Static aeroelastic analysis comparisons between the traditional and developed APSE models for a wing tip detection indicate that the propulsion system impact on the vehicle elastic response could increase the detection by approximately ten percent.

  16. Aero-hydro-elastic simulation platform for wave energy systems and floating wind turbines

    Energy Technology Data Exchange (ETDEWEB)

    Kallesoee, B.S.

    2011-01-15

    This report present results from the PSO project 2008-1-10092 entitled Aero-Hydro-Elastic Simulation Platform for Wave Energy Systems and floating Wind Turbines that deals with measurements, modelling and simulations of the world's first combined wave and wind energy platform. The floating energy conversion platform, Poseidon, is owned and operated by Floating Power Plant A/S. The platform has been operating for two test periods; one period where it was operating as a wave energy conversion platform only and one period where the three turbines was mounted and the platform operated as a combined wind and wave energy platform. The PSO project has equipped the platform with comprehensive measurements equipment for measuring platform motion, wave and wind conditions and turbine loads. Data from the first test period has been used for determine if the turbine could be mounted on the platform. Preliminary analysis of data from the second test period indicates that the platform is suitable as wind turbine foundation and that the turbines reduce the platform motion. (Author)

  17. AEROS: a real-time emergency response system for atmospheric releases of toxic material

    International Nuclear Information System (INIS)

    Nasstrom, J.S.; Greenly, G.D.

    1986-01-01

    The Atmospheric Release Advisory Capability (ARAC) at the Lawrence Livermore National Laboratory has developed a sophisticated computer-based real-time emergency response system for radiotoxic releases into the atmosphere. The ARAC Emergency Response Operating System (AEROS) has a centralized computer facility linked to remote site computers, meteorological towers, and meteorological data sources. The system supports certain fixed sites, but has the ability to respond to accidents at arbitrary locations. Product quality and response time are optimized by using complex three-dimensional dispersion models; extensive on-line data bases; automated data processing; and an efficient user interface, employing graphical computer displays and computer-displayed forms. Upon notification, the system automatically initiates a response to an emergency and proceeds through preliminary calculations, automatically processing accident information, meteorological data, and model parameters. The model calculations incorporate mass-consistent three-dimensional wind fields, terrain effects, and particle-in-cell diffusion. Model products are color images of dose or deposition contours overlaid on a base map

  18. Aero Engine Component Fault Diagnosis Using Multi-Hidden-Layer Extreme Learning Machine with Optimized Structure

    Directory of Open Access Journals (Sweden)

    Shan Pang

    2016-01-01

    Full Text Available A new aero gas turbine engine gas path component fault diagnosis method based on multi-hidden-layer extreme learning machine with optimized structure (OM-ELM was proposed. OM-ELM employs quantum-behaved particle swarm optimization to automatically obtain the optimal network structure according to both the root mean square error on training data set and the norm of output weights. The proposed method is applied to handwritten recognition data set and a gas turbine engine diagnostic application and is compared with basic ELM, multi-hidden-layer ELM, and two state-of-the-art deep learning algorithms: deep belief network and the stacked denoising autoencoder. Results show that, with optimized network structure, OM-ELM obtains better test accuracy in both applications and is more robust to sensor noise. Meanwhile it controls the model complexity and needs far less hidden nodes than multi-hidden-layer ELM, thus saving computer memory and making it more efficient to implement. All these advantages make our method an effective and reliable tool for engine component fault diagnosis tool.

  19. Cooperating to Compete in the Global Air Cargo Industry: The Case of the DHL Express and Lufthansa Cargo A.G. Joint Venture Airline ‘AeroLogic’

    Directory of Open Access Journals (Sweden)

    Glenn Baxter

    2018-03-01

    Full Text Available This paper presents a case study of the DHL Express and Lufthansa Cargo strategic joint venture cargo airline ‘AeroLogic’, the global air cargo industry’s largest operative joint venture between an airline and a leading international express and logistics provider. The study used a qualitative research approach. The data gathered for the study was examined by document analysis. The strategic analysis of the AeroLogic joint venture was based on the use of Porter’s Five Forces framework. The study found that the AeroLogic joint venture airline has provided synergistic benefits to both partners and has allowed the partners to access new markets and to participate in the evolution of the air cargo industry. The new venture has also enabled both joint venture partners to enhance their competitive position in the global air cargo industry through strengthened service offerings and has provided the partners with increased cargo capacities, a larger route network, and greater frequencies within their own route networks. The study also found that the AeroLogic business model is unique in the air cargo industry. A limitation of the study was that AeroLogic’s annual revenue or freight traffic data was not available. It was, therefore, not possible to analyse the business performance of the joint venture.

  20. Feasibility investigation of coupling a desalination prototype functioning by Aero-Evapo-Condensation with solar units

    International Nuclear Information System (INIS)

    Bourouni, K.; Bouden, C.; Chaibi, M.

    2003-01-01

    The rural regions of south Mediterranean countries suffer from problems of drinking water supply. However, the majority of these regions have important resources of brackish salt water. Thus, brackish water desalination on a small scale presents a potential solution to this problem. For this reason, a number of small desalination prototypes are being developed worldwide. Bourouni et al. have developed a water desalination unit functioning by the Aero-Evapo-Condensation-Process (AECP) in order to satisfy this kind of water demand. One of the advantages of this prototype is that it allows the use of low temperature energy such as geothermal and solar energies abundant in these countries. An initial experiment was carried on an AECP prototype coupled to a geothermal spring in the south of Tunisia. The results relative to the technical and economic performances of the unit have shown that this kind of coupling is promising. On the other hand, the brackish water springs in these countries are often non-geothermal. In this case, the use of solar energy can be considered. Thus, we develop, in the present article, a feasibility investigation on the coupling of the AECP prototype with solar units. In fact, we analyse, in the first part of this article, the possibilities of this coupling in a manner that the functioning mode of the solar units will be compatible with that of the AECP prototype. To attempt this objective, two kinds of solar installation scenarios are considered and modelled to obtain their energetic contribution. Hence, the elaborated models are coupled to the one developed by Bourouni et al. for the AECP prototype to determine the technical and economic performances of the whole installation. In the last part of this article, a solar unit dimensioning is performed in order to minimise the total cost of the distilled water. (author)

  1. Dynamic modeling and vibration characteristics analysis of the aero-engine dual-rotor system with Fan blade out

    Science.gov (United States)

    Yu, Pingchao; Zhang, Dayi; Ma, Yanhong; Hong, Jie

    2018-06-01

    Fan Blade Out (FBO) from a running rotor of the turbofan engine will not only introduce the sudden unbalance and inertia asymmetry into the rotor, but also apply large impact load and induce rotor-to-stator rubbing on the rotor, which makes the mass, gyroscopic and stiffness matrixes of the dynamic equation become time-varying and highly nonlinear, consequently leads to the system's complicated vibration. The dynamic analysis of the aero-engine rotor system is one essential requirement of the authorities and is vital to the aero-engine's safety. The paper aims at studying the dynamic responses of the complicated dual-rotor systems at instantaneous and windmilling statuses when FBO event occurs. The physical process and mechanical characteristics of the FBO event are described qualitatively, based on which the dynamic modeling for an aero-engine dual-rotor system is carried out considering several excitations caused by FBO. Meanwhile the transient response during the instantaneous status and steady-state response at the windmilling status are obtained. The results reveal that the sudden unbalance can induce impact load to the rotor, and lead to the sharp increase of the vibration amplitude and reaction force. The rub-impact will apply constraint effects on the rotor and restrict the transient vibration amplitude, while the inertia asymmetry has little influence on the transient response. When the rotor with huge unbalance operates at windmilling status, the rub-impact turns to be the main factor determining the rotor's dynamic behavior, and several potential motion states, such as instable dry whip, intermittent rubbing and synchronous full annular rubbing would happen on certain conditions.

  2. Small wind turbine performance evaluation using field test data and a coupled aero-electro-mechanical model

    Science.gov (United States)

    Wallace, Brian D.

    A series of field tests and theoretical analyses were performed on various wind turbine rotor designs at two Penn State residential-scale wind-electric facilities. This work involved the prediction and experimental measurement of the electrical and aerodynamic performance of three wind turbines; a 3 kW rated Whisper 175, 2.4 kW rated Skystream 3.7, and the Penn State designed Carolus wind turbine. Both the Skystream and Whisper 175 wind turbines are OEM blades which were originally installed at the facilities. The Carolus rotor is a carbon-fiber composite 2-bladed machine, designed and assembled at Penn State, with the intent of replacing the Whisper 175 rotor at the off-grid system. Rotor aerodynamic performance is modeled using WT_Perf, a National Renewable Energy Laboratory developed Blade Element Momentum theory based performance prediction code. Steady-state power curves are predicted by coupling experimentally determined electrical characteristics with the aerodynamic performance of the rotor simulated with WT_Perf. A dynamometer test stand is used to establish the electromechanical efficiencies of the wind-electric system generator. Through the coupling of WT_Perf and dynamometer test results, an aero-electro-mechanical analysis procedure is developed and provides accurate predictions of wind system performance. The analysis of three different wind turbines gives a comprehensive assessment of the capability of the field test facilities and the accuracy of aero-electro-mechanical analysis procedures. Results from this study show that the Carolus and Whisper 175 rotors are running at higher tip-speed ratios than are optimum for power production. The aero-electro-mechanical analysis predicted the high operating tip-speed ratios of the rotors and was accurate at predicting output power for the systems. It is shown that the wind turbines operate at high tip-speeds because of a miss-match between the aerodynamic drive torque and the operating torque of the wind

  3. PREFACE: The 2nd International Conference on Geological, Geographical, Aerospace and Earth Sciences 2014 (AeroEarth 2014)

    Science.gov (United States)

    Lumban Gaol, Ford; Soewito, Benfano

    2015-01-01

    The 2nd International Conference on Geological, Geographical, Aerospace and Earth Sciences 2014 (AeroEarth 2014), was held at Discovery Kartika Plaza Hotel, Kuta, Bali, Indonesia during 11 - 12 October 2014. The AeroEarth 2014 conference aims to bring together researchers and engineers from around the world. Through research and development, earth scientists have the power to preserve the planet's different resource domains by providing expert opinion and information about the forces which make life possible on Earth. Earth provides resources and the exact conditions to make life possible. However, with the advent of technology and industrialization, the Earth's resources are being pushed to the brink of depletion. Non-sustainable industrial practices are not only endangering the supply of the Earth's natural resources, but are also putting burden on life itself by bringing about pollution and climate change. A major role of earth science scholars is to examine the delicate balance between the Earth's resources and the growing demands of industrialization. Through research and development, earth scientists have the power to preserve the planet's different resource domains by providing expert opinion and information about the forces which make life possible on Earth. We would like to express our sincere gratitude to all in the Technical Program Committee who have reviewed the papers and developed a very interesting Conference Program as well as the invited and plenary speakers. This year, we received 98 papers and after rigorous review, 17 papers were accepted. The participants come from eight countries. There are four Parallel Sessions and two invited Speakers. It is an honour to present this volume of IOP Conference Series: Earth and Environmental Science (EES) and we deeply thank the authors for their enthusiastic and high-grade contributions. Finally, we would like to thank the conference chairmen, the members of the steering committee, the organizing committee

  4. Smart rotor modeling aero-servo-elastic modeling of a smart rotor with adaptive trailing edge flaps

    CERN Document Server

    Bergami, Leonardo

    2014-01-01

    A smart rotor is a wind turbine rotor that, through a combination of sensors, control units and actuators actively reduces the variation of the aerodynamic loads it has to withstand. Smart rotors feature?promising load alleviation potential and might provide the technological breakthrough required by the next generation of large wind turbine rotors.The book presents the aero-servo-elastic model of a smart rotor with Adaptive Trailing Edge Flaps for active load alleviation and provides an insight on the rotor aerodynamic, structural and control modeling. A novel model for the unsteady aerodynam

  5. One Generation of New Material, One Generation of New Type Engine:Development Trend of Aero-engine and Its Requirements for Materials

    Directory of Open Access Journals (Sweden)

    LIU Da-xiang

    2017-10-01

    Full Text Available Based on the brief review of accelerated developing status of aircraft power technology in the world, the present status and developing trend of key materials technology for aero-engine were analyzed. In accordance with the idea of "one generation of new material, one generation of new type engine", development requirements for the materials technology of the system and main parts of aero-engine were proposed. Suggestions for improving development and application level of the materials technology in China were presented from aspects of quality stability and technical maturity, investigation and verification for engineering, materials system and data, composite materials, airworthiness certificate,etc.

  6. Modeling C-Band Co-Channel Interference From AeroMACS Omni-Directional Antennas to Mobile Satellite Service Feeder Uplinks

    Science.gov (United States)

    Wilson, Jeffrey D.

    2011-01-01

    A new C-band (5091 to 5150 MHz) airport communications system designated as Aeronautical Mobile Airport Communications System (AeroMACS) is being planned under the Federal Aviation Administration s NextGen program. An interference analysis software program, Visualyse Professional (Transfinite Systems Ltd), is being utilized to provide guidelines on limitations for AeroMACS transmitters to avoid interference with other systems. A scenario consisting of a single omni-directional transmitting antenna at each of the major contiguous United States airports is modeled and the steps required to build the model are reported. The results are shown to agree very well with a previous study.

  7. The AERO system: a 3D-like approach for recording gene expression patterns in the whole mouse embryo.

    Directory of Open Access Journals (Sweden)

    Hirohito Shimizu

    Full Text Available We have recently constructed a web-based database of gene expression in the mouse whole embryo, EMBRYS (http://embrys.jp/embrys/html/MainMenu.html. To allow examination of gene expression patterns to the fullest extent possible, this database provides both photo images and annotation data. However, since embryos develop via an intricate process of morphogenesis, it would be of great value to track embryonic gene expression from a three dimensional perspective. In fact, several methods have been developed to achieve this goal, but highly laborious procedures and specific operational skills are generally required. We utilized a novel microscopic technique that enables the easy capture of rotational, 3D-like images of the whole embryo. In this method, a rotary head equipped with two mirrors that are designed to obtain an image tilted at 45 degrees to the microscope stage captures serial images at 2-degree intervals. By a simple operation, 180 images are automatically collected. These 2D images obtained at multiple angles are then used to reconstruct 3D-like images, termed AERO images. By means of this system, over 800 AERO images of 191 gene expression patterns were captured. These images can be easily rotated on the computer screen using the EMBRYS database so that researchers can view an entire embryo by a virtual viewing on a computer screen in an unbiased or non-predetermined manner. The advantages afforded by this approach make it especially useful for generating data viewed in public databases.

  8. Polypyrrole/silver coaxial nanowire aero-sponges for temperature-independent stress sensing and stress-triggered Joule heating.

    Science.gov (United States)

    He, Weina; Li, Guangyong; Zhang, Shangquan; Wei, Yong; Wang, Jin; Li, Qingwen; Zhang, Xuetong

    2015-04-28

    To obtain ideal sensing materials with nearly zero temperature coefficient resistance (TCR) for self-temperature-compensated pressure sensors, we proposed an Incipient Network Conformal Growth (INCG) technology to prepare hybrid and elastic porous materials: the nanoparticles (NPs) are first dispersed in solvent to form an incipient network, another component is then introduced to coat the incipient network conformally via wet chemical route. The conformal coatings not only endow NPs with high stability but also offer them additional structural elasticity, meeting requirements for future generations of portable, compressive and flexible devices. The resultant polypyrrole/silver coaxial nanowire hybrid aero-sponges prepared via INCG technology have been processed into a piezoresistive sensor with highly sensing stability (low TCR 0.86 × 10(-3)/°C), sensitivity (0.33 kPa(-1)), short response time (1 ms), minimum detectable pressure (4.93 Pa) after suffering repeated stimuli, temperature change and electric heating. Moreover, a stress-triggered Joule heater can be also fabricated mainly by the PPy-Ag NW hybrid aero-sponges with nearly zero temperature coefficient.

  9. Emerging and established global life-style risk factors for cancer of the upper aero-digestive tract.

    Science.gov (United States)

    Gupta, Bhawna; Johnson, Newell W

    2014-01-01

    Upper aero-digestive tract cancer is a multidimensional problem, international trends showing complex rises and falls in incidence and mortality across the globe, with variation across different cultural and socio-economic groups. This paper seeks some explanations and identifies some research and policy needs. The literature illustrates the multifactorial nature of carcinogenesis. At the cellular level, it is viewed as a multistep process involving multiple mutations and selection for cells with progressively increasing capacity for proliferation, survival, invasion, and metastasis. Established and emerging risk factors, in addition to changes in incidence and prevalence of cancers of the upper aero-digestive tract, were identified. Exposure to tobacco and alcohol, as well as diets inadequate in fresh fruits and vegetables, remain the major risk factors, with persistent infection by particular so-called "high risk" genotypes of human papillomavirus increasingly recognised as also playing an important role in a subset of cases, particularly for the oropharynx. Chronic trauma to oral mucosa from poor restorations and prostheses, in addition to poor oral hygiene with a consequent heavy microbial load in the mouth, are also emerging as significant risk factors. Understanding and quantifying the impact of individual risk factors for these cancers is vital for health decision-making, planning and prevention. National policies and programmes should be designed and implemented to control exposure to environmental risks, by legislation if necessary, and to raise awareness so that people are provided with the information and support they need to adopt healthy lifestyles.

  10. Effective L/D: A Theoretical Approach to the Measurement of Aero-Structural Efficiency in Aircraft Design

    Science.gov (United States)

    Guynn, Mark D.

    2015-01-01

    There are many trade-offs in aircraft design that ultimately impact the overall performance and characteristics of the final design. One well recognized and well understood trade-off is that of wing weight and aerodynamic efficiency. Higher aerodynamic efficiency can be obtained by increasing wing span, usually at the expense of higher wing weight. The proper balance of these two competing factors depends on the objectives of the design. For example, aerodynamic efficiency is preeminent for sailplanes and long slender wings result. Although the wing weight-drag trade is universally recognized, aerodynamic efficiency and structural efficiency are not usually considered in combination. This paper discusses the concept of "aero-structural efficiency," which combines weight and drag characteristics. A metric to quantify aero-structural efficiency, termed effective L/D, is then derived and tested with various scenarios. Effective L/D is found to be a practical and robust means to simultaneously characterize aerodynamic and structural efficiency in the context of aircraft design. The primary value of the effective L/D metric is as a means to better communicate the combined system level impacts of drag and structural weight.

  11. Surface integrity of GH4169 affected by cantilever finish grinding and the application in aero-engine blades

    Directory of Open Access Journals (Sweden)

    Li Xun

    2015-10-01

    Full Text Available GH4169 is the main material for aero-engine blades and integrated blisks. Because GH4169 has a poor milling performance, the profile precision and surface integrity of blades and integrated blisks are difficult to be met by utilizing the conventional milling process, which directly influence the global performance and reliability of aero-engines. Through grinding experiments on parameters and surface integrity optimization, the helical cantilever grinding process utilizing a 300# CBN RB wheel is presented and applied in finish machining of GH4169 blades. The profile errors of the blade surface are within ±0.01 mm, the roughness is less than 0.4 μm, the residual compressive stresses and the hardening rate are appropriate, there are no phenomena of burr and smearing with the grinding chips, and the leading/trailing edge can be smoothly connected with the suction/pressure surface. All the experimental results indicate that this grinding process is greatly suitable for the profile finish machining of GH4169 blades.

  12. Nonlinear Dynamic Modeling of a Supersonic Commercial Transport Turbo-Machinery Propulsion System for Aero-Propulso-Servo-Elasticity Research

    Science.gov (United States)

    Connolly, Joe; Carlson, Jan-Renee; Kopasakis, George; Woolwine, Kyle

    2015-01-01

    This paper covers the development of an integrated nonlinear dynamic model for a variable cycle turbofan engine, supersonic inlet, and convergent-divergent nozzle that can be integrated with an aeroelastic vehicle model to create an overall Aero-Propulso-Servo-Elastic (APSE) modeling tool. The primary focus of this study is to provide a means to capture relevant thrust dynamics of a full supersonic propulsion system by using relatively simple quasi-one dimensional computational fluid dynamics (CFD) methods that will allow for accurate control algorithm development and capture the key aspects of the thrust to feed into an APSE model. Previously, propulsion system component models have been developed and are used for this study of the fully integrated propulsion system. An overview of the methodology is presented for the modeling of each propulsion component, with a focus on its associated coupling for the overall model. To conduct APSE studies the described dynamic propulsion system model is integrated into a high fidelity CFD model of the full vehicle capable of conducting aero-elastic studies. Dynamic thrust analysis for the quasi-one dimensional dynamic propulsion system model is presented along with an initial three dimensional flow field model of the engine integrated into a supersonic commercial transport.

  13. N3S-AERO: a multidimensional model for numerical simulation of all wet cooling tower systems

    International Nuclear Information System (INIS)

    Razafindrakoto, E.; Hofmann, F.

    1997-01-01

    3D model is more required to optimize the design of new cooling tower by way of parameters studies, to improve the performance of the existing ones from changes in fill zone or water distribution. Therefore, the Directions des Etudes et Recherches with collaboration of the Direction de l'Equipement of EDF, has developed a specific version of the finite element CFD code N3S, denoted N3S-AERO, for the simulation of natural or mechanical draught wet cooling towers. It solves mass, momentum, heat and humidity averaged Navier-Stokes equations including buoyancy terms with variable density for air flow in the whole domain mass, heat equations for water flow in exchange zones. With standard results of N3S as air velocity and scalar fields, N3S-AERO gives in return water temperature fields mean values of variables at inlet or outlet of each exchange zone and thermal performance of the tower. 2D axisymmetrical and 3D industrial cases have soon been done. Major flow phenomena are well predicted and averaged cold water values are in good agreement with ID-TEFERI code or measurements

  14. Rare earth oxide aero- and xerogels. Tuning porosity and catalytic properties

    Energy Technology Data Exchange (ETDEWEB)

    Neumann, Bjoern

    2013-11-15

    , katalytisch vielversprechende Seltenerdoxide im Hinblick auf Porositaet und Zusammensetzung so zu veraendern, dass sie fuer Oxidationsreaktionen und die oxidative Kupplung von Methan gute Ergebnisse aufweisen. Dabei lag einerseits ein grosser Schwerpunkt auf Sol-gel-chemischen Methoden und hier besonders auf der sog. ''Epoxide Addition Method''. Neben Aero- und Xerogelen der reinen Seltenerdoxide wurden auch Hybridsysteme aus den Seltenerdoxiden und Aluminiumoxid praepariert, umfangreich charakterisiert und katalytisch getestet. Des Weiteren wurden duenne Xerogel Filme und makroporoese Monolithe, letztere mittels einer direkten Schaeumungsmethode, hergestellt. Die Ergebnisse der Arbeit belegen das grosse Potential v.a. der Sol-Gel-Chemie, poroese Materialien mit variabler und kontrollierbarer Porositaet und Zusammensetzung fuer die heterogene Katalyse verfuegbar zu machen und dabei leistungsfaehigere Katalysatoren zu erhalten.

  15. Investigation of global particulate nitrate from the AeroCom phase III experiment

    Directory of Open Access Journals (Sweden)

    H. Bian

    2017-11-01

    Full Text Available An assessment of global particulate nitrate and ammonium aerosol based on simulations from nine models participating in the Aerosol Comparisons between Observations and Models (AeroCom phase III study is presented. A budget analysis was conducted to understand the typical magnitude, distribution, and diversity of the aerosols and their precursors among the models. To gain confidence regarding model performance, the model results were evaluated with various observations globally, including ground station measurements over North America, Europe, and east Asia for tracer concentrations and dry and wet depositions, as well as with aircraft measurements in the Northern Hemisphere mid-to-high latitudes for tracer vertical distributions. Given the unique chemical and physical features of the nitrate occurrence, we further investigated the similarity and differentiation among the models by examining (1 the pH-dependent NH3 wet deposition; (2 the nitrate formation via heterogeneous chemistry on the surface of dust and sea salt particles or thermodynamic equilibrium calculation including dust and sea salt ions; and (3 the nitrate coarse-mode fraction (i.e., coarse/total. It is found that HNO3, which is simulated explicitly based on full O3-HOx-NOx-aerosol chemistry by all models, differs by up to a factor of 9 among the models in its global tropospheric burden. This partially contributes to a large difference in NO3−, whose atmospheric burden differs by up to a factor of 13. The atmospheric burdens of NH3 and NH4+ differ by 17 and 4, respectively. Analyses at the process level show that the large diversity in atmospheric burdens of NO3−, NH3, and NH4+ is also related to deposition processes. Wet deposition seems to be the dominant process in determining the diversity in NH3 and NH4+ lifetimes. It is critical to correctly account for contributions of heterogeneous chemical production of nitrate on dust and sea salt, because this process

  16. APPLICATION OF ROUGH SET THEORY TO MAINTENANCE LEVEL DECISION-MAKING FOR AERO-ENGINE MODULES BASED ON INCREMENTAL KNOWLEDGE LEARNING

    Institute of Scientific and Technical Information of China (English)

    陆晓华; 左洪福; 蔡景

    2013-01-01

    The maintenance of an aero-engine usually includes three levels ,and the maintenance cost and period greatly differ depending on the different maintenance levels .To plan a reasonable maintenance budget program , airlines would like to predict the maintenance level of aero-engine before repairing in terms of performance parame-ters ,which can provide more economic benefits .The maintenance level decision rules are mined using the histori-cal maintenance data of a civil aero-engine based on the rough set theory ,and a variety of possible models of upda-ting rules produced by newly increased maintenance cases added to the historical maintenance case database are in-vestigated by the means of incremental machine learning .The continuously updated rules can provide reasonable guidance suggestions for engineers and decision support for planning a maintenance budget program before repai-ring .The results of an example show that the decision rules become more typical and robust ,and they are more accurate to predict the maintenance level of an aero-engine module as the maintenance data increase ,which illus-trates the feasibility of the represented method .

  17. On the aero-elastic design of the DTU 10MW wind turbine blade for the LIFES50+ wind tunnel scale model

    DEFF Research Database (Denmark)

    Bayati, I.; Belloli, M.; Bernini, L.

    2016-01-01

    and for different angles of attack. The aero-elastic design algorithm was set to define the optimal spanwise thickness over chord ratio (t/c), the chord length and the twist to match the first flapwise scaled natural frequency. An aluminium mould for the carbon fibre was CNC manufactured based on B-Splines CAD...

  18. Host model uncertainties in aerosol radiative forcing estimates: results from the AeroCom Prescribed intercomparison study

    Directory of Open Access Journals (Sweden)

    P. Stier

    2013-03-01

    Full Text Available Simulated multi-model "diversity" in aerosol direct radiative forcing estimates is often perceived as a measure of aerosol uncertainty. However, current models used for aerosol radiative forcing calculations vary considerably in model components relevant for forcing calculations and the associated "host-model uncertainties" are generally convoluted with the actual aerosol uncertainty. In this AeroCom Prescribed intercomparison study we systematically isolate and quantify host model uncertainties on aerosol forcing experiments through prescription of identical aerosol radiative properties in twelve participating models. Even with prescribed aerosol radiative properties, simulated clear-sky and all-sky aerosol radiative forcings show significant diversity. For a purely scattering case with globally constant optical depth of 0.2, the global-mean all-sky top-of-atmosphere radiative forcing is −4.47 Wm−2 and the inter-model standard deviation is 0.55 Wm−2, corresponding to a relative standard deviation of 12%. For a case with partially absorbing aerosol with an aerosol optical depth of 0.2 and single scattering albedo of 0.8, the forcing changes to 1.04 Wm−2, and the standard deviation increases to 1.01 W−2, corresponding to a significant relative standard deviation of 97%. However, the top-of-atmosphere forcing variability owing to absorption (subtracting the scattering case from the case with scattering and absorption is low, with absolute (relative standard deviations of 0.45 Wm−2 (8% clear-sky and 0.62 Wm−2 (11% all-sky. Scaling the forcing standard deviation for a purely scattering case to match the sulfate radiative forcing in the AeroCom Direct Effect experiment demonstrates that host model uncertainties could explain about 36% of the overall sulfate forcing diversity of 0.11 Wm−2 in the AeroCom Direct Radiative Effect experiment. Host model errors in aerosol radiative forcing are largest in regions of uncertain host model

  19. 3D quantitative interpretation of archaeo-magnetic data: Adaptation of aero-magnetic interpretation techniques for archaeological purposes

    Science.gov (United States)

    Cheyney, S.; Hill, I. A.; Linford, N.; Fishwick, S.; Leech, C.

    2011-12-01

    High-resolution total-field magnetic data can be collected rapidly and relatively cheaply over large archaeological sites due to recent advances in data collection. However, interpretation of these datasets still generally comprises a sequence of data correction and filtering operations prior to a 2D visual interpretation based on pattern recognition. In contrast, current developments in aero-magnetic interpretation have led to several tools for identifying location, shape and depth information of anomalous sources. These methods often fail when directly applied to archaeo-magnetic data, due to the particular noise content typical in very near-surface surveys. Here techniques are explored that allow these aero-magnetic interpretation tools to be applied to archaeological problems, without the need for extensive, often biased user input. It is shown that full 3D quantitative interpretation of the subsurface is possible from just the magnetic data alone. Inversion of magnetic data is increasingly being applied to aero-magnetic surveys to produce 3D models of the subsurface magnetisation. Typically, an objective function is minimised in order to create a smooth distribution of magnetisation away from a reference model (or halfspace if no a-priori information is available). Often, although a good fit to the observed values may be obtained, the final model will be non-unique and biased by the reference model. Testing of synthetic data shows that when archaeo-magnetic datasets are inverted without applying a-priori information, large discrepancies between the true and modelled depths can occur. Where no a-priori information is available, information regarding the horizontal location of sources can be obtained from derivative-based methods such as the absolute horizontal gradient, tilt-angle and theta-map. Using pseudogravity data with these techniques, overcomes the problem of noise amplification that has previously hampered archaeological uses of these techniques. Depth

  20. Aero-Propulsive Model Design from a Commercial Aircraft in Climb and Cruise Regime using Performance Data =

    Science.gov (United States)

    Tudor, Magdalena

    IATA has estimated, in 2012, at about 2% of global carbon dioxide emissions, the environmental impact of the air transport, as a consequence caused by the rapidly growing of global movement demand of people and goods, and which was effectively taken into account in the development of the aviation industry. The historic achievements of scientific and technical progress in the field of commercial aviation were contributed to this estimate, and even today the research continues to make progress to help to reduce the emissions of greenhouse gases. Advances in commercial aircraft, and its engine design technology had the aim to improve flight performance. These improvements have enhanced the global flight planning of these types of aircrafts. Almost all of these advances rely on generated performance data as reference sources, the most of which are classified as "confidential" by the aircraft manufacturers. There are very few aero-propulsive models conceived for the climb regime in the literature, but none of them was designed without access to an engine database, and/or to performance data in climb and in cruise regimes with direct applicability for flight optimization. In this thesis, aero-propulsive models methodologies are proposed for climb and cruise regimes, using system identification and validation methods, through which airplane performance can be computed and stored in the most compact and easily accessible format for this kind of performance data. The acquiring of performance data in this format makes it possible to optimize flight profiles, used by on-board Flight Management Systems. The aero-propulsive models developed here were investigated on two aircrafts belonging to commercial class, and both of them had offered very good accuracy. One of their advantages is that they can be adapted to any other aircraft of the same class, even if there is no access to their corresponding engine flight data. In addition, these models could save airlines a considerable

  1. HAWC2 and BeamDyn: Comparison Between Beam Structural Models for Aero-Servo-Elastic Frameworks: Preprint

    Energy Technology Data Exchange (ETDEWEB)

    Pavese, Christian; Kim, Taeseong; Wang, Qi; Jonkman, Jason; Sprague, Michael A.

    2016-08-01

    This work presents a comparison of two beam codes for aero-servo-elastic frameworks: a new structural model for the aeroelastic code HAWC2 and a new nonlinear beam model, BeamDyn, for the aeroelastic modularization framework FAST v8. The main goal is to establish the suitability of the two approaches to model the structural behaviour of modern wind turbine blades in operation. Through a series of benchmarking structural cases of increasing complexity, the capability of the two codes to simulate highly nonlinear effects is investigated and analyzed. Results show that even though the geometrically exact beam theory can better model effects such as very large deflections, rotations, and structural couplings, an approach based on a multi-body formulation assembled through linear elements is capable of computing accurate solutions for typical nonlinear beam theory benchmarking cases.

  2. Initial comments on the aero geophysical information present at the B and C areas of the Itatira (Brazil) project

    International Nuclear Information System (INIS)

    Castro, Neivaldo Araujo de; Castelo Branco, Raimundo Mariano Gomes

    1999-01-01

    The aero geophysical project called Itatira,, accomplished by LASA Engenharia e Prospeccoes S.A., Between September and November/1977 through contract with NUCLEBRAS, corresponds to one of the first project of this gender accomplished in national territory. In this project were flight more than 80 000 km of linear lines, which covered approximately 38 000 km 2 on the precambrian terrains of the Ceara State, NE Brazil. For several reasons, the total area of the project was subdivided in three sub-areas (A, B and C), each one covered by a different airship (LAS, 1977). This paper presents the geophysical information and preliminary interpretations of the areas B and C that were obtained through the integrated use of the soft wares AUTOCAD r. 14, OASIS MONTAJ r.4.2 and ERMAPPER r.5.5. (author)

  3. Re-irradiation associated to cetuximab and paclitaxel in the recurrences in irradiated field of upper aero-digestive ducts tumors resistant to platina salts; Re-irradiation associee au cetuximab et au paclitaxel dans les recidives en territoire irradie des tumeurs des voies aero-digestives superieures resistantes aux sels de platine

    Energy Technology Data Exchange (ETDEWEB)

    Martin, L.M. [Centre Guillaume-Le-Conquerant, 76 - Le Havre (France); Moran, A.R.; Pavlovitch, J.M. [Clinique du Petit-Colmoulin, 76 - Harfleur (France); El Amarti, R. [Hopital Monod, 76 - Montivilliers (France); Damour, M. [CMC Ormeaux-Vauban, 76 - Le Havre (France)

    2007-11-15

    The objective of this study is to present the preliminary results of the toxicity and efficiency evaluation of the association 're-irradiation-cetuximab-paclitaxel' in the recurrences of upper aero-digestive ducts tumors in irradiated field resistant to platinum salts. (N.C.)

  4. Electron-beam-welded segmental heat pipes of AlMgSi 1 for the thermal model of the satellite Aeros-A

    Energy Technology Data Exchange (ETDEWEB)

    Hoell, H.; Lasar, H.

    1974-07-01

    For the purposes of tests with the thermal model of the German aeronomy satellite Aeros-A, a heat pipe system of optimized weight was developed in order to transport thermal energy from the solar cells of the cylindrical satellite to the conical bottom. Because of stringent requirements on the fabrication process, electron beam welding is used for bonding. The welding process is described and preliminary test results are given. (LEW)

  5. THE APPLICATION OF REMOTE SENSING AND AERO-GEOPHYSICS DATA FUSION ON METALLOGENIC PROGNOSIS IN QIMANTAGE OF EAST KUNLUN MONTAIN AREA

    OpenAIRE

    Jia, W.; Zhang, H.; Lin, J.; Zhao, H.

    2013-01-01

    Based on west of Qimantage of East Kunlun mountain area, takes advantage of ASTER data, according to the altered mineral spectral characteristics, remote sensing alteration information is extracted. Incorporation the anomaly extraction results with high-precision aero geophysical data processing results, a multiple resource information fusion model is proposed. The fusion model of two totally different type of data which is a special attention in geospatial academia now, which can im...

  6. Simulating Global AeroMACS Airport Ground Station Antenna Power Transmission Limits to Avoid Interference With Mobile Satellite Service Feeder Uplinks

    Science.gov (United States)

    Wilson, Jeffrey D.

    2013-01-01

    The Aeronautical Mobile Airport Communications System (AeroMACS), which is based upon the IEEE 802.16e mobile wireless standard, is expected to be implemented in the 5091 to 5150 MHz frequency band. As this band is also occupied by Mobile Satellite Service feeder uplinks, AeroMACS must be designed to avoid interference with this incumbent service. The aspects of AeroMACS operation that present potential interference are under analysis in order to enable the definition of standards that assure that such interference will be avoided. In this study, the cumulative interference power distribution at low Earth orbit from transmitters at global airports was simulated with the Visualyse Professional software. The dependence of the interference power on antenna distribution, gain patterns, duty cycle, and antenna tilt was simulated. As a function of these parameters, the simulation results are presented in terms of the limitations on transmitter power from global airports required to maintain the cumulative interference power under the established threshold.

  7. Aero-thermal optimization of film cooling flow parameters on the suction surface of a high pressure turbine blade

    Science.gov (United States)

    El Ayoubi, Carole; Hassan, Ibrahim; Ghaly, Wahid

    2012-11-01

    This paper aims to optimize film coolant flow parameters on the suction surface of a high-pressure gas turbine blade in order to obtain an optimum compromise between a superior cooling performance and a minimum aerodynamic penalty. An optimization algorithm coupled with three-dimensional Reynolds-averaged Navier Stokes analysis is used to determine the optimum film cooling configuration. The VKI blade with two staggered rows of axially oriented, conically flared, film cooling holes on its suction surface is considered. Two design variables are selected; the coolant to mainstream temperature ratio and total pressure ratio. The optimization objective consists of maximizing the spatially averaged film cooling effectiveness and minimizing the aerodynamic penalty produced by film cooling. The effect of varying the coolant flow parameters on the film cooling effectiveness and the aerodynamic loss is analyzed using an optimization method and three dimensional steady CFD simulations. The optimization process consists of a genetic algorithm and a response surface approximation of the artificial neural network type to provide low-fidelity predictions of the objective function. The CFD simulations are performed using the commercial software CFX. The numerical predictions of the aero-thermal performance is validated against a well-established experimental database.

  8. Aerosol Vacuum-Assisted Plasma Ionization (Aero-VaPI) Coupled to Ion Mobility-Mass Spectrometry

    Science.gov (United States)

    Blair, Sandra L.; Ng, Nga L.; Zambrzycki, Stephen C.; Li, Anyin; Fernández, Facundo M.

    2018-02-01

    In this communication, we report on the real-time analysis of organic aerosol particles by Vacuum-assisted Plasma Ionization-Mass Spectrometry (Aero-VaPI-MS) using a home-built VaPI ion source coupled to a Synapt G2-S HDMS ion mobility-mass spectrometry (IM-MS) system. Standards of organic molecules of interest in prebiotic chemistry were used to generate aerosols. Monocaprin and decanoic acid aerosol particles were successfully detected in both the positive and negative ion modes, respectively. A complex aerosol mixture of different sizes of polymers of L-malic acid was also examined through ion mobility (IM) separations, resulting in the detection of polymers of up to eight monomeric units. This noncommercial plasma ion source is proposed as a low cost alternative to other plasma ionization platforms used for aerosol analysis, and a higher-performance alternative to more traditional aerosol mass spectrometers. VaPI provides robust online ionization of organics in aerosols without extensive ion activation, with the coupling to IM-MS providing higher peak capacity and excellent mass accuracy. [Figure not available: see fulltext.

  9. The effect of harmonized emissions on aerosol properties in global models – an AeroCom experiment

    Directory of Open Access Journals (Sweden)

    C. Textor

    2007-08-01

    Full Text Available The effects of unified aerosol sources on global aerosol fields simulated by different models are examined in this paper. We compare results from two AeroCom experiments, one with different (ExpA and one with unified emissions, injection heights, and particle sizes at the source (ExpB. Surprisingly, harmonization of aerosol sources has only a small impact on the simulated inter-model diversity of the global aerosol burden, and consequently global optical properties, as the results are largely controlled by model-specific transport, removal, chemistry (leading to the formation of secondary aerosols and parameterizations of aerosol microphysics (e.g., the split between deposition pathways and to a lesser extent by the spatial and temporal distributions of the (precursor emissions.

    The burdens of black carbon and especially sea salt become more coherent in ExpB only, because the large ExpA diversities for these two species were caused by a few outliers. The experiment also showed that despite prescribing emission fluxes and size distributions, ambiguities in the implementation in individual models can lead to substantial differences.

    These results indicate the need for a better understanding of aerosol life cycles at process level (including spatial dispersal and interaction with meteorological parameters in order to obtain more reliable results from global aerosol simulations. This is particularly important as such model results are used to assess the consequences of specific air pollution abatement strategies.

  10. A Mission Concept: Re-Entry Hopper-Aero-Space-Craft System on-Mars (REARM-Mars)

    Science.gov (United States)

    Davoodi, Faranak

    2013-01-01

    Future missions to Mars that would need a sophisticated lander, hopper, or rover could benefit from the REARM Architecture. The mission concept REARM Architecture is designed to provide unprecedented capabilities for future Mars exploration missions, including human exploration and possible sample-return missions, as a reusable lander, ascend/descend vehicle, refuelable hopper, multiple-location sample-return collector, laboratory, and a cargo system for assets and humans. These could all be possible by adding just a single customized Re-Entry-Hopper-Aero-Space-Craft System, called REARM-spacecraft, and a docking station at the Martian orbit, called REARM-dock. REARM could dramatically decrease the time and the expense required to launch new exploratory missions on Mars by making them less dependent on Earth and by reusing the assets already designed, built, and sent to Mars. REARM would introduce a new class of Mars exploration missions, which could explore much larger expanses of Mars in a much faster fashion and with much more sophisticated lab instruments. The proposed REARM architecture consists of the following subsystems: REARM-dock, REARM-spacecraft, sky-crane, secure-attached-compartment, sample-return container, agile rover, scalable orbital lab, and on-the-road robotic handymen.

  11. Effect of chevron nozzle penetration on aero-acoustic characteristics of jet at M = 0.8

    Science.gov (United States)

    Nikam, S. R.; Sharma, S. D.

    2017-12-01

    Aero-acoustic characteristics of a high-speed jet with chevron nozzles are experimentally investigated at a Mach number of 0.8. The main focus is to examine the effects of the extent of chevron penetration and its position in the mixing layer. Chevron nozzles with three different levels of penetration employed at three different longitudinal locations from the nozzle lip are tested, and the results are compared with those of a plain baseline nozzle. The chevrons are found to produce a lobed shear layer through the notched region, thereby increasing the surface area of the jet, particularly in the close vicinity of the nozzle, which increases the mixing and reduces the potential core length. This effect becomes more prominent with increasing penetration closer to the nozzle lip in the thinner mixing layer. Near field and far field noise measurements show distinctly different acoustic features due to chevrons. The chevrons are found to effectively shift the dominant noise source upstream closer to the nozzle. Present investigation proposes a simpler method for locating the dominant noise source from the peak of the centerline velocity decay rate. The overall noise levels registered along the jet edge immediately downstream of the chevrons are higher, but further downstream they are reduced in comparison with the plain baseline nozzle. Also, the chevrons beam the noise towards higher polar angles at higher frequencies. At shallow polar angles with respect to the jet axis in the far field, chevrons suppress the noise at low frequencies with increasing penetration, but for higher polar angles, while they continue to suppress the low frequency noise, at higher frequencies the trend is found to reverse. The noise measured in the near field close to the jet edge is composed of two components: acoustic and hydrodynamic. Of these two components, the chevrons are found to reduce the hydrodynamic component in comparison with the acoustic one.

  12. Effect of chevron nozzle penetration on aero-acoustic characteristics of jet at M = 0.8

    Energy Technology Data Exchange (ETDEWEB)

    Nikam, S R [K. J. Somaiya college of Engineering, Mumbai (India); Sharma, S D, E-mail: srnikam12@gmail.com [I.I.T. Bombay, Mumbai (India)

    2017-12-15

    Aero-acoustic characteristics of a high-speed jet with chevron nozzles are experimentally investigated at a Mach number of 0.8. The main focus is to examine the effects of the extent of chevron penetration and its position in the mixing layer. Chevron nozzles with three different levels of penetration employed at three different longitudinal locations from the nozzle lip are tested, and the results are compared with those of a plain baseline nozzle. The chevrons are found to produce a lobed shear layer through the notched region, thereby increasing the surface area of the jet, particularly in the close vicinity of the nozzle, which increases the mixing and reduces the potential core length. This effect becomes more prominent with increasing penetration closer to the nozzle lip in the thinner mixing layer. Near field and far field noise measurements show distinctly different acoustic features due to chevrons. The chevrons are found to effectively shift the dominant noise source upstream closer to the nozzle. Present investigation proposes a simpler method for locating the dominant noise source from the peak of the centerline velocity decay rate. The overall noise levels registered along the jet edge immediately downstream of the chevrons are higher, but further downstream they are reduced in comparison with the plain baseline nozzle. Also, the chevrons beam the noise towards higher polar angles at higher frequencies. At shallow polar angles with respect to the jet axis in the far field, chevrons suppress the noise at low frequencies with increasing penetration, but for higher polar angles, while they continue to suppress the low frequency noise, at higher frequencies the trend is found to reverse. The noise measured in the near field close to the jet edge is composed of two components: acoustic and hydrodynamic. Of these two components, the chevrons are found to reduce the hydrodynamic component in comparison with the acoustic one. (paper)

  13. Using Satellite Observations to Evaluate the AeroCOM Volcanic Emissions Inventory and the Dispersal of Volcanic SO2 Clouds in MERRA

    Science.gov (United States)

    Hughes, Eric J.; Krotkov, Nickolay; da Silva, Arlindo; Colarco, Peter

    2015-01-01

    Simulation of volcanic emissions in climate models requires information that describes the eruption of the emissions into the atmosphere. While the total amount of gases and aerosols released from a volcanic eruption can be readily estimated from satellite observations, information about the source parameters, like injection altitude, eruption time and duration, is often not directly known. The AeroCOM volcanic emissions inventory provides estimates of eruption source parameters and has been used to initialize volcanic emissions in reanalysis projects, like MERRA. The AeroCOM volcanic emission inventory provides an eruptions daily SO2 flux and plume top altitude, yet an eruption can be very short lived, lasting only a few hours, and emit clouds at multiple altitudes. Case studies comparing the satellite observed dispersal of volcanic SO2 clouds to simulations in MERRA have shown mixed results. Some cases show good agreement with observations Okmok (2008), while for other eruptions the observed initial SO2 mass is half of that in the simulations, Sierra Negra (2005). In other cases, the initial SO2 amount agrees with the observations but shows very different dispersal rates, Soufriere Hills (2006). In the aviation hazards community, deriving accurate source terms is crucial for monitoring and short-term forecasting (24-h) of volcanic clouds. Back trajectory methods have been developed which use satellite observations and transport models to estimate the injection altitude, eruption time, and eruption duration of observed volcanic clouds. These methods can provide eruption timing estimates on a 2-hour temporal resolution and estimate the altitude and depth of a volcanic cloud. To better understand the differences between MERRA simulations and volcanic SO2 observations, back trajectory methods are used to estimate the source term parameters for a few volcanic eruptions and compared to their corresponding entry in the AeroCOM volcanic emission inventory. The nature of

  14. Retrospective study of the evolution of nutritional, inflammatory and bacteriological profiles of patients suffering from inoperable aero-digestive duct tumour during sequential or concomitant chemo-radiotherapy

    International Nuclear Information System (INIS)

    Martin, L.; Brocard, C.; Coudray, C.; Pavlovitch, J.M.

    2010-01-01

    The authors report a retrospective study which aimed at analysing a cohort of consecutive patients in terms of clinic and biological aspects reflecting their nutritional and inflammatory status as well as the status of their buccal bacterial flora during a sequential or concomitant chemo-radiotherapy. The objective was to detect a possible difference between these both therapeutic modalities, and a possible relationship with toxicity. Several data have been collected for patients suffering from inoperable aero-digestive tract tumour: weight, body mass index, prealbumin, albumin, orosomucoid, C-reactive protein, PINI index, and buccal bacterial flora. The evolution of these nutritional biological criteria appears to depend on the treatment modality. Short communication

  15. Stability of two-degrees-of-freedom aero-elastic models with frequency and time variable parametric self-induced forces

    Czech Academy of Sciences Publication Activity Database

    Náprstek, Jiří; Pospíšil, Stanislav; Yau, J. D.

    2015-01-01

    Roč. 57, August (2015), s. 91-107 ISSN 0889-9746 R&D Projects: GA MŠk(CZ) LO1219; GA ČR(CZ) GC13-34405J Institutional support: RVO:68378297 Keywords : aero-elastic system * self-excited vibration * dynamic stability * Routh–Hurwitz conditions * flutter derivatives * divergence Subject RIV: JM - Building Engineering Impact factor: 1.709, year: 2015 http://dx.doi.org/10.1016/j.jfluidstructs.2015.05.010

  16. Mineralogy and characterization of deposited particles of the aero sediments collected in the vicinity of power plants and the open pit coal mine: Kolubara (Serbia).

    Science.gov (United States)

    Cvetković, Željko; Logar, Mihovil; Rosić, Aleksandra

    2013-05-01

    In this paper, particular attention was paid to the presence of aerosol solid particles, which occurred mainly as a result of exploitation and coal combustion in the thermal power plants of the Kolubara basin. Not all of the particles created by this type of anthropogenic pollution have an equal impact on human health, but it largely depends on their size and shape. The mineralogical composition and particle size distribution in the samples of aero sediments were defined. The samples were collected close to the power plant and open pit coal mine, in the winter and summer period during the year 2007. The sampling was performed by using precipitators placed in eight locations within the territory of the Lazarevac municipality. In order to characterize the sedimentary particles, several methods were applied: microscopy, SEM-EDX and X-ray powder diffraction. The concentration of aero sediments was also determined during the test period. Variety in the mineralogical composition and particle size depends on the position of the measuring sites, geology of the locations, the annual period of collecting as well as possible interactions. By applying the mentioned methods, the presence of inhalational and respiratory particles variously distributed in the winter and in the summer period was established. The most common minerals are quartz and feldspar. The presence of gypsum, clay minerals, calcite and dolomite as secondary minerals was determined, as well as the participation of organic and inorganic amorphic matter. The presence of quartz as a toxic mineral has a particular impact on human health.

  17. Real-time analysis of ambient organic aerosols using aerosol flowing atmospheric-pressure afterglow mass spectrometry (AeroFAPA-MS)

    Science.gov (United States)

    Brüggemann, Martin; Karu, Einar; Stelzer, Torsten; Hoffmann, Thorsten

    2015-04-01

    Organic aerosol accounts for a major fraction of atmospheric aerosols and has implications on the earth's climate and human health. However, due to the chemical complexity its measurement remains a major challenge for analytical instrumentation.1 Here, we present the development, characterization and application of a new soft ionization technique that allows mass spectrometric real-time detection of organic compounds in ambient aerosols. The aerosol flowing atmospheric-pressure afterglow (AeroFAPA) ion source utilizes a helium glow discharge plasma to produce excited helium species and primary reagent ions. Ionization of the analytes occurs in the afterglow region after thermal desorption and results mainly in intact molecular ions, facilitating the interpretation of the acquired mass spectra. In the past, similar approaches were used to detect pesticides, explosives or illicit drugs on a variety of surfaces.2,3 In contrast, the AeroFAPA source operates 'online' and allows the detection of organic compounds in aerosols without a prior precipitation or sampling step. To our knowledge, this is the first application of an atmospheric-pressure glow discharge ionization technique to ambient aerosol samples. We illustrate that changes in aerosol composition and concentration are detected on the time scale of seconds and in the ng-m-3 range. Additionally, the successful application of AeroFAPA-MS during a field study in a mixed forest region in Central Europe is presented. Several oxidation products of monoterpenes were clearly identified using the possibility to perform tandem MS experiments. The acquired data are in agreement with previous studies and demonstrate that AeroFAPA-MS is a suitable tool for organic aerosol analysis. Furthermore, these results reveal the potential of this technique to enable new insights into aerosol formation, growth and transformation in the atmosphere. References: 1) IPCC, 2013: Summary for Policymakers. In: Climate Change 2013: The

  18. Parallelization of the unstructured Navier-stoke solver LILAC for the aero-thermal analysis of a gas-cooled reactor

    International Nuclear Information System (INIS)

    Kim, J. T.; Kim, S. B.; Lee, W. J.

    2004-01-01

    Currently lilac code is under development to analyse thermo-hydraulics of the gas-cooled reactor(GCR) especially high-temperature GCR which is one of the gen IV nuclear reactors. The lilac code was originally developed for the analysis of thermo-hydraulics in a molten pool. And now it is modified to resolve the compressible gas flows in the GCR. The more complexities in the internal flow geometries of the GCR reactor and aero-thermal flows, the number of computational cells are increased and finally exceeds the current computing powers of the desktop computers. To overcome the problem and well resolve the interesting physics in the GCR it is conducted to parallels the lilac code by the decomposition of a computational domain or grid. Some benchmark problems are solved with the parallelized lilac code and its speed-up characteristics by the parallel computation is evaluated and described in the article

  19. Futurepath: The Story of Research and Technology at NASA Lewis Research Center. Structures for Flight Propulsion, ARC Sprayed Monotape, National Aero-Space Plane

    Science.gov (United States)

    1989-01-01

    The story of research and technology at NASA Lewis Research Center's Structures Division is presented. The job and designs of the Structures Division needed for flight propulsion is described including structural mechanics, structural dynamics, fatigue, and fracture. The video briefly explains why properties of metals used in structural mechanics need to be tested. Examples of tests and simulations used in structural dynamics (bodies in motion) are briefly described. Destructive and non-destructive fatigue/fracture analysis is also described. The arc sprayed monotape (a composite material) is explained, as are the programs in which monotape plays a roll. Finally, the National Aero-Space Plane (NASP or x-30) is introduced, including the material development and metal matrix as well as how NASP will reduce costs for NASA.

  20. Results from the ASPIRE study for breast reconstruction utilizing the AeroForm™ patient controlled carbon dioxide-inflated tissue expanders.

    Science.gov (United States)

    Connell, Tony F

    2015-09-01

    Therapeutic or prophylactic mastectomy is often indicated for women with breast cancer, or for those at a high risk of developing cancer due to familial history or genetic mutations. Favorable aesthetic and psychological results make prosthetic reconstruction of the breast with placement of tissue expanders followed by permanent implant a popular choice for women diagnosed with breast cancer. This study describes the results of the ASPIRE trial, the objective of which was to provide supportive data to demonstrate the performance and safety of the AeroForm™ System in a population with broader selection criteria than previous studies. Results of the earlier PACE clinical studies (PACE 1 and 2) demonstrated that the AeroForm™ System could be used safely and effectively to achieve the desired expansion necessary for successful breast reconstruction. In the current ASPIRE trial described in the paper, performance of the device was evaluated by successful tissue expansion and exchange to breast implant(s) unless precluded by a non-device related event. Safety data was evaluated based on reported adverse events. A prospective, single center, open-label study in which subjects who met the inclusion criteria and agreed to participate were enrolled and implanted with the AeroForm expander either at the time of mastectomy (immediate) or sometime after mastectomy (delayed). In the event of a bilateral procedure, the expander was implanted in each side. Subjects were followed until the explant of the tissue expander(s) and exchange for silicone or saline breast implant(s). Thirty-four expanders were placed in 21 subjects in the clinical trial; the average age of subjects was 49.7 ± 8.6 years with average BMI of 26.1 ± 4.7. Bilateral procedures accounted for 62% of the total and 88% of the reconstructions were completed with a latissimus dorsi flap (anterior approach) per the investigators standard procedure. Four (12%) of the cases (12%) were completed in two subjects

  1. New aero-gravity results from the Arctic: Linking the latest Cretaceous-early Cenozoic plate kinematics of the North Atlantic and Arctic Ocean

    DEFF Research Database (Denmark)

    Døssing, Arne; Hopper, J.R.; Olesen, Arne Vestergaard

    2013-01-01

    The tectonic history of the Arctic Ocean remains poorly resolved and highly controversial. Details regarding break up of the Lomonosov Ridge from the Barents-Kara shelf margins and the establishment of seafloor spreading in the Cenozoic Eurasia Basin are unresolved. Significantly, the plate...... tectonic evolution of the Mesozoic Amerasia Basin is essentially unknown. The Arctic Ocean north of Greenland is at a critical juncture that formed at the locus of a Mesozoic three-plate setting between the Lomonosov Ridge, Greenland, and North America. In addition, the area is close to the European plate...... plateau against an important fault zone north of Greenland. Our results provide new constraints for Cretaceous-Cenozoic plate reconstructions of the Arctic. Key Points Presentation of the largest aero-gravity survey acquired over the Arctic Ocean Plate tectonic link between Atlantic and Arctic spreading...

  2. AeroADL: applying the integration of the Suomi-NPP science algorithms with the Algorithm Development Library to the calibration and validation task

    Science.gov (United States)

    Houchin, J. S.

    2014-09-01

    A common problem for the off-line validation of the calibration algorithms and algorithm coefficients is being able to run science data through the exact same software used for on-line calibration of that data. The Joint Polar Satellite System (JPSS) program solved part of this problem by making the Algorithm Development Library (ADL) available, which allows the operational algorithm code to be compiled and run on a desktop Linux workstation using flat file input and output. However, this solved only part of the problem, as the toolkit and methods to initiate the processing of data through the algorithms were geared specifically toward the algorithm developer, not the calibration analyst. In algorithm development mode, a limited number of sets of test data are staged for the algorithm once, and then run through the algorithm over and over as the software is developed and debugged. In calibration analyst mode, we are continually running new data sets through the algorithm, which requires significant effort to stage each of those data sets for the algorithm without additional tools. AeroADL solves this second problem by providing a set of scripts that wrap the ADL tools, providing both efficient means to stage and process an input data set, to override static calibration coefficient look-up-tables (LUT) with experimental versions of those tables, and to manage a library containing multiple versions of each of the static LUT files in such a way that the correct set of LUTs required for each algorithm are automatically provided to the algorithm without analyst effort. Using AeroADL, The Aerospace Corporation's analyst team has demonstrated the ability to quickly and efficiently perform analysis tasks for both the VIIRS and OMPS sensors with minimal training on the software tools.

  3. Solar Tower Experiments for Radiometric Calibration and Validation of Infrared Imaging Assets and Analysis Tools for Entry Aero-Heating Measurements

    Science.gov (United States)

    Splinter, Scott C.; Daryabeigi, Kamran; Horvath, Thomas J.; Mercer, David C.; Ghanbari, Cheryl M.; Ross, Martin N.; Tietjen, Alan; Schwartz, Richard J.

    2008-01-01

    The NASA Engineering and Safety Center sponsored Hypersonic Thermodynamic Infrared Measurements assessment team has a task to perform radiometric calibration and validation of land-based and airborne infrared imaging assets and tools for remote thermographic imaging. The IR assets and tools will be used for thermographic imaging of the Space Shuttle Orbiter during entry aero-heating to provide flight boundary layer transition thermography data that could be utilized for calibration and validation of empirical and theoretical aero-heating tools. A series of tests at the Sandia National Laboratories National Solar Thermal Test Facility were designed for this task where reflected solar radiation from a field of heliostats was used to heat a 4 foot by 4 foot test panel consisting of LI 900 ceramic tiles located on top of the 200 foot tall Solar Tower. The test panel provided an Orbiter-like entry temperature for the purposes of radiometric calibration and validation. The Solar Tower provided an ideal test bed for this series of radiometric calibration and validation tests because it had the potential to rapidly heat the large test panel to spatially uniform and non-uniform elevated temperatures. Also, the unsheltered-open-air environment of the Solar Tower was conducive to obtaining unobstructed radiometric data by land-based and airborne IR imaging assets. Various thermocouples installed on the test panel and an infrared imager located in close proximity to the test panel were used to obtain surface temperature measurements for evaluation and calibration of the radiometric data from the infrared imaging assets. The overall test environment, test article, test approach, and typical test results are discussed.

  4. A-Train Aerosol Observations Preliminary Comparisons with AeroCom Models and Pathways to Observationally Based All-Sky Estimates

    Science.gov (United States)

    Redemann, J.; Livingston, J.; Shinozuka, Y.; Kacenelenbogen, M.; Russell, P.; LeBlanc, S.; Vaughan, M.; Ferrare, R.; Hostetler, C.; Rogers, R.; hide

    2014-01-01

    We have developed a technique for combining CALIOP aerosol backscatter, MODIS spectral AOD (aerosol optical depth), and OMI AAOD (absorption aerosol optical depth) retrievals for the purpose of estimating full spectral sets of aerosol radiative properties, and ultimately for calculating the 3-D distribution of direct aerosol radiative forcing. We present results using one year of data collected in 2007 and show comparisons of the aerosol radiative property estimates to collocated AERONET retrievals. Use of the recently released MODIS Collection 6 data for aerosol optical depths derived with the dark target and deep blue algorithms has extended the coverage of the multi-sensor estimates towards higher latitudes. We compare the spatio-temporal distribution of our multi-sensor aerosol retrievals and calculations of seasonal clear-sky aerosol radiative forcing based on the aerosol retrievals to values derived from four models that participated in the latest AeroCom model intercomparison initiative. We find significant inter-model differences, in particular for the aerosol single scattering albedo, which can be evaluated using the multi-sensor A-Train retrievals. We discuss the major challenges that exist in extending our clear-sky results to all-sky conditions. On the basis of comparisons to suborbital measurements, we present some of the limitations of the MODIS and CALIOP retrievals in the presence of adjacent or underlying clouds. Strategies for meeting these challenges are discussed.

  5. Forecasting olive crop yields based on long-term aero biological data series and bio climatic conditions for the southern Iberian Peninsula

    Energy Technology Data Exchange (ETDEWEB)

    Aguilera, F.; Ruiz-Valenzuela, L.

    2014-06-01

    In the present study, bio-meteorological models for predicting olive-crop production in the southern Iberian Peninsula were developed. These covered a 16-year period: 1994-2009. The forecasting models were constructed using the partial least-squares regression method, taking the annual olive yield as the dependent variable, and both aero biological and meteorological parameters as the independent variables. Two regression models were built for the prediction of crop production prior to the final harvest at two different times of the year: July and November. The percentage variance explained by the models was between 83% and 93%. Through these forecasting models, the main factors that influence olive-crop yield were identified. Pollen index and accumulated precipitation, especially as rain recorded during the pre-flowering months, were the most important parameters for providing an explanation of fluctuations in fruit production. The temperature recorded during the two months preceding budburst was another important variable, which showed positive effects on the final yield. The July model that provides accurate predictions of fruit production eight months prior to the final harvest is proposed as an optimal model to forecast fruit produced by olive trees in western Mediterranean areas. (Author)

  6. Direct Aerosol Radiative Forcing from Combined A-Train Observations - Preliminary Comparisons with AeroCom Models and Pathways to Observationally Based All-sky Estimates

    Science.gov (United States)

    Redemann, J.; Livingston, J. M.; Shinozuka, Y.; Kacenelenbogen, M. S.; Russell, P. B.; LeBlanc, S. E.; Vaughan, M.; Ferrare, R. A.; Hostetler, C. A.; Rogers, R. R.; Burton, S. P.; Torres, O.; Remer, L. A.; Stier, P.; Schutgens, N.

    2014-12-01

    We describe a technique for combining CALIOP aerosol backscatter, MODIS spectral AOD (aerosol optical depth), and OMI AAOD (absorption aerosol optical depth) retrievals for the purpose of estimating full spectral sets of aerosol radiative properties, and ultimately for calculating the 3-D distribution of direct aerosol radiative forcing. We present results using one year of data collected in 2007 and show comparisons of the aerosol radiative property estimates to collocated AERONET retrievals. Use of the recently released MODIS Collection 6 data for aerosol optical depths derived with the dark target and deep blue algorithms has extended the coverage of the multi-sensor estimates towards higher latitudes. Initial calculations of seasonal clear-sky aerosol radiative forcing based on our multi-sensor aerosol retrievals compare well with over-ocean and top of the atmosphere IPCC-2007 model-based results, and with more recent assessments in the "Climate Change Science Program Report: Atmospheric Aerosol Properties and Climate Impacts" (2009). For the first time, we present comparisons of our multi-sensor aerosol direct radiative forcing estimates to values derived from a subset of models that participated in the latest AeroCom initiative. We discuss the major challenges that exist in extending our clear-sky results to all-sky conditions. On the basis of comparisons to suborbital measurements, we present some of the limitations of the MODIS and CALIOP retrievals in the presence of adjacent or underlying clouds. Strategies for meeting these challenges are discussed.

  7. Modeling, Analysis, and Control of a Hypersonic Vehicle with Significant Aero-Thermo-Elastic-Propulsion Interactions: Elastic, Thermal and Mass Uncertainty

    Science.gov (United States)

    Khatri, Jaidev

    This thesis examines themodeling, analysis, and control system design issues for scramjet powered hypersonic vehicles. A nonlinear three degrees of freedom longitudinal model which includes aero-propulsion-elasticity effects was used for all analyses. This model is based upon classical compressible flow and Euler-Bernouli structural concepts. Higher fidelity computational fluid dynamics and finite element methods are needed for more precise intermediate and final evaluations. The methods presented within this thesis were shown to be useful for guiding initial control relevant design. The model was used to examine the vehicle's static and dynamic characteristics over the vehicle's trimmable region. The vehicle has significant longitudinal coupling between the fuel equivalency ratio (FER) and the flight path angle (FPA). For control system design, a two-input two-output plant (FER - elevator to speed-FPA) with 11 states (including 3 flexible modes) was used. Velocity, FPA, and pitch were assumed to be available for feedback. Aerodynamic heat modeling and design for the assumed TPS was incorporated to original Bolender's model to study the change in static and dynamic properties. De-centralized control stability, feasibility and limitations issues were dealt with the change in TPS elasticity, mass and physical dimension. The impact of elasticity due to TPS mass, TPS physical dimension as well as prolonged heating was also analyzed to understand performance limitations of de-centralized control designed for nominal model.

  8. AQUA-motion domain and metaphorization patterns in European Portuguese: AQUA-motion metaphor in AERO-motion and abstract domains

    Directory of Open Access Journals (Sweden)

    Hanna Jakubowicz Batoréo

    2016-03-01

    Full Text Available The AQUA-motion verbs – as studied by Majsak & Rahilina 2003 and 2007, Lander, Majsak & Rahilina [2005] 2008, 2012 and 2013, and Divjak & Lemmens 2007, and in European Portuguese (EP by Batoréo, 2007, 2008, 2009; Batoréo et al., 2007; Casadinho, 2007 – allow typically metaphorical uses, which we postulate can be organized in patterns. Our study shows that in European Portuguese there are two metaphorization patterns to be observed: (i AQUA-motion metaphor in AERO-motion domain and (ii AQUA-motion metaphor in abstract domain (e.g. abundance, arts, politics, etc.. In the first case, where the target domain of the metaphorization is the air, in EP we navigate through a crowd or we float in a waltz, whereas in the second, where it is abstract, we swim in money or in blood, and politicians navigate at sea or face floating currency in finances. In the present paper we survey the EP verbs of AQUA-motion metaphors in non-elicited data from electronically available language corpora (cf. Linguateca. In some cases comparisons are made with typologically diferent languages (as, e.g. Polish, cf. Prokofjeva’s 2007, Batoréo 2009.

  9. AERO2S - SUBSONIC AERODYNAMIC ANALYSIS OF WINGS WITH LEADING- AND TRAILING-EDGE FLAPS IN COMBINATION WITH CANARD OR HORIZONTAL TAIL SURFACES (IBM PC VERSION)

    Science.gov (United States)

    Carlson, H. W.

    1994-01-01

    necessary only to add an identification record and the namelist data that are to be changed from the previous run. This code was originally developed in 1989 in FORTRAN V on a CDC 6000 computer system, and was later ported to an MS-DOS environment. Both versions are available from COSMIC. There are only a few differences between the PC version (LAR-14458) and CDC version (LAR-14178) of AERO2S distributed by COSMIC. The CDC version has one main source code file while the PC version has two files which are easier to edit and compile on a PC. The PC version does not require a FORTRAN compiler which supports NAMELIST because a special INPUT subroutine has been added. The CDC version includes two MODIFY decks which can be used to improve the code and prevent the possibility of some infrequently occurring errors while PC-version users will have to make these code changes manually. The PC version includes an executable which was generated with the Ryan McFarland/FORTRAN compiler and requires 253K RAM and an 80x87 math co-processor. Using this executable, the sample case requires about four hours to execute on an 8MHz AT-class microcomputer with a co-processor. The source code conforms to the FORTRAN 77 standard except that it uses variables longer than six characters. With two minor modifications, the PC version should be portable to any computer with a FORTRAN compiler and sufficient memory. The CDC version of AERO2S is available in CDC NOS Internal format on a 9-track 1600 BPI magnetic tape. The PC version is available on a set of two 5.25 inch 360K MS-DOS format diskettes. IBM AT is a registered trademark of International Business Machines. MS-DOS is a registered trademark of Microsoft Corporation. CDC is a registered trademark of Control Data Corporation. NOS is a trademark of Control Data Corporation.

  10. AERO2S - SUBSONIC AERODYNAMIC ANALYSIS OF WINGS WITH LEADING- AND TRAILING-EDGE FLAPS IN COMBINATION WITH CANARD OR HORIZONTAL TAIL SURFACES (CDC VERSION)

    Science.gov (United States)

    Darden, C. M.

    1994-01-01

    necessary only to add an identification record and the namelist data that are to be changed from the previous run. This code was originally developed in 1989 in FORTRAN V on a CDC 6000 computer system, and was later ported to an MS-DOS environment. Both versions are available from COSMIC. There are only a few differences between the PC version (LAR-14458) and CDC version (LAR-14178) of AERO2S distributed by COSMIC. The CDC version has one main source code file while the PC version has two files which are easier to edit and compile on a PC. The PC version does not require a FORTRAN compiler which supports NAMELIST because a special INPUT subroutine has been added. The CDC version includes two MODIFY decks which can be used to improve the code and prevent the possibility of some infrequently occurring errors while PC-version users will have to make these code changes manually. The PC version includes an executable which was generated with the Ryan McFarland/FORTRAN compiler and requires 253K RAM and an 80x87 math co-processor. Using this executable, the sample case requires about four hours to execute on an 8MHz AT-class microcomputer with a co-processor. The source code conforms to the FORTRAN 77 standard except that it uses variables longer than six characters. With two minor modifications, the PC version should be portable to any computer with a FORTRAN compiler and sufficient memory. The CDC version of AERO2S is available in CDC NOS Internal format on a 9-track 1600 BPI magnetic tape. The PC version is available on a set of two 5.25 inch 360K MS-DOS format diskettes. IBM AT is a registered trademark of International Business Machines. MS-DOS is a registered trademark of Microsoft Corporation. CDC is a registered trademark of Control Data Corporation. NOS is a trademark of Control Data Corporation.

  11. Late xerostomia after intensity-modulated conformational radiotherapy of upper aero-digestive tract cancers: study 2004-03 by the head and neck oncology and radiotherapy Group (Gortec)

    International Nuclear Information System (INIS)

    Toledano, I.; Lapeyre, M.; Graff, P.; Serre, C.; Bensadoun, R.J.; Bensadoun, R.J.; Ortholan, C.; Calais, G.; Alfonsi, M.; Giraud, P.; Racadot, S.

    2010-01-01

    The authors report a retrospective assessment of late xerostomia according to the RTOG (Radiation Therapy Oncology Group) classification of the European Organization for Research and Treatment of Cancer (EORTC) among patients treated by intensity-modulated conformational radiotherapy (IMRT) and suffering from upper aero-digestive tract carcinomas of different stages. Some of these patients have bee operated, and some have been treated by chemotherapy. It appears that the IMRT results in a reduction of late xerostomia, and even in an absence of salivary toxicity. Short communication

  12. Towards the improvements of simulating the chemical and optical properties of Chinese aerosols using an online coupled model – CUACE/Aero

    Directory of Open Access Journals (Sweden)

    Chun-Hong Zhou

    2012-07-01

    Full Text Available CUACE/Aero, the China Meteorological Administration (CMA Unified Atmospheric Chemistry Environment for aerosols, is a comprehensive numerical aerosol module incorporating emissions, gaseous chemistry and size-segregated multi-component aerosol algorithm. On-line coupled into a meso-scale weather forecast model (MM5, its performance and improvements for aerosol chemical and optical simulations have been evaluated using the observations data of aerosols/gases from the intensive observations and from the CMA Atmosphere Watch network, plus aerosol optical depth (AOD data from CMA Aerosol Remote Sensing network (CARSNET and from Moderate Resolution Imaging Spectroradiometer (MODIS. Targeting Beijing and North China region from July 13 to 31, 2008, when a heavy hazy weather system occurred, the model captured the general variations of PM10 with most of the data within a factor of 2 from the observations and a combined correlation coefficient (r of 0.38 (significance level=0.05. The correlation coefficients are better at rural than at urban sites, and better at daytime than at nighttime. Chemically, the correlation coefficients between the daily-averaged modelled and observed concentrations range from 0.34 for black carbon (BC to 0.09 for nitrates with sulphate, ammonium and organic carbon (OC in between. Like the PM10, the values of chemical species are higher for the daytime than those for the nighttime. On average, the sulphate, ammonium, nitrate and OC are underestimated by about 60, 70, 96.0 and 10.8%, respectively. Black carbon is overestimated by about 120%. A new size distribution for the primary particle emissions was constructed for most of the anthropogenic aerosols such as BC, OC, sulphate, nitrate and ammonium from the observed size distribution of atmospheric aerosols in Beijing. This not only improves the correlation between the modelled and observed AOD, but also reduces the overestimation of AOD simulated by the original model size

  13. Adaptative control of aero-acoustic instabilities. Application to propulsion systems; Controle adaptatif des instabilites aeroacoustiques. Application aux systemes de propulsion

    Energy Technology Data Exchange (ETDEWEB)

    Mettenleiter, M.

    2000-02-15

    This work treats active adaptive control of aero-acoustic instabilities. In particular, we are interested in an application to solid propellant rockets. The study is part of the research program ASSM coordinated by CNES and ONERA and the aim is to increase the performance of the P230 segmented solid propellant boosters of the Ariane 5 rocket. The work has been carried out in collaboration with other partners of this program. The main objective of this study is the development of control algorithms, able to diminish low frequency instabilities encountered in propulsion systems. First, the instability phenomenon is analyzed in a simplified experimental setup and similarity is shown with instabilities observed in real propulsion systems. This study enables us to conceive adaptive control strategies, which have been tested on three different levels: - In a simplified dynamical simulation; - During an experimental study; - Using full numerical simulations. The three levels of application made it possible to study the behaviour of the different control strategies. We could show that the actuator signal modifies the behaviour of the system on the acoustic level. But as there is a strong interaction between the pressure fluctuations and the hydrodynamic behaviour, the flow structure is also modified by active control. This behaviour corresponds to the simplified model of the phenomenon, which has been used to define the control algorithms. The control action 'at the noise source' makes it possible to distinguish this kind of algorithms from schemes based on the anti-noise principle. After this first part, where we showed the feasibility of control, we particularly considered algorithms which can act in an unknown environment. The information about the system behaviour. which is necessary for convergence of the controller is now obtained in parallel during control. An identification off-line, used at the beginning of the research, is no longer necessary. Self

  14. What Controls the Vertical Distribution of Aerosol? Relationships Between Process Sensitivity in HadGEM3-UKCA and Inter-Model Variation from AeroCom Phase II

    Science.gov (United States)

    Kipling, Zak; Stier, Philip; Johnson, Colin E.; Mann, Graham W.; Bellouin, Nicolas; Bauer, Susanne E.; Bergman, Tommi; Chin, Mian; Diehl, Thomas; Ghan, Steven J.; hide

    2016-01-01

    The vertical profile of aerosol is important for its radiative effects, but weakly constrained by observations on the global scale, and highly variable among different models. To investigate the controlling factors in one particular model, we investigate the effects of individual processes in HadGEM3-UKCA and compare the resulting diversity of aerosol vertical profiles with the inter-model diversity from the AeroCom Phase II control experiment. In this way we show that (in this model at least) the vertical profile is controlled by a relatively small number of processes, although these vary among aerosol components and particle sizes. We also show that sufficiently coarse variations in these processes can produce a similar diversity to that among different models in terms of the global-mean profile and, to a lesser extent, the zonal-mean vertical position. However, there are features of certain models' profiles that cannot be reproduced, suggesting the influence of further structural differences between models. In HadGEM3-UKCA, convective transport is found to be very important in controlling the vertical profile of all aerosol components by mass. In-cloud scavenging is very important for all except mineral dust. Growth by condensation is important for sulfate and carbonaceous aerosol (along with aqueous oxidation for the former and ageing by soluble material for the latter). The vertical extent of biomass-burning emissions into the free troposphere is also important for the profile of carbonaceous aerosol. Boundary-layer mixing plays a dominant role for sea salt and mineral dust, which are emitted only from the surface. Dry deposition and below-cloud scavenging are important for the profile of mineral dust only. In this model, the microphysical processes of nucleation, condensation and coagulation dominate the vertical profile of the smallest particles by number (e.g. total CN >3 nm), while the profiles of larger particles (e.g. CN>100 nm) are controlled by the

  15. Formation of YxNd1-xBa2Cu3O7-δ (0≤x≤0.9) superconductors from an undercooled melt via aero-acoustic levitation

    International Nuclear Information System (INIS)

    Gustafson, D.E.; Hofmeister, W.H.; Bayuzick, R.J.; Nagashio, K.; Kuribayashi, K.

    2003-01-01

    This paper presents the results of rapid solidification experiments performed on the copper oxide superconductors Y x Nd 1-x Ba 2 Cu 3 O 7-δ (0≤x≤0.9). Spherical rare earth (RE) 123 specimens were levitated in O 2 using aero-acoustic levitation (AAL), melted with a laser, undercooled, and solidified. The peritectic transformation temperature for the reaction RE 2 BaCuO 5 +liquid→REBa 2 Cu 3 O 7-δ corresponding to the maximum recalescence temperature during solidification was determined. RE123 was formed directly from the melt for Y-Nd binary alloy compositions with Nd concentration greater than 20% (Y concentration less than 80%). A minimum in the peritectic transformation temperature for the Nd/Y123 system corresponding to a composition Y 0.3 Nd 0.7 123 was determined at 66 deg. C below the peritectic of pure Nd123

  16. Analysis of the role of the gene coding the Amyloid-Precursor Protein Binding Protein 1 (APP-BP1) in the radio-sensitivity of epidermoid carcinomas of the upper aero-digestive tract infected by the human papillomavirus

    International Nuclear Information System (INIS)

    Guihard, S.; Altmeyer, A.; Ramolu, L.; Macabre, C.; Abecassis, J.; Noel, G.; Jung, A.C.

    2010-01-01

    As the human papillomavirus (HPV) is at the origin of 25% of upper aero-digestive tract cancers, and as these tumours present an increased radio-sensitivity compared to other tumours, probably due to a greater transcriptional activity of p53, the authors report the study on the influence of a decrease of the expression of the APP-BP1 in these tumours which could favour a radio-induced apoptosis. By using a reverse transcriptase polymerase chain reaction (RT-PCR), they assessed the APP-BP1 expression levels as well as expression levels of transcriptions coding onco-proteins known to be over-expressed in HPV+ tumours. They compared the radio-sensitivities of HPV+ and HPV- cells, the first one appearing to be greater than the second one. Short communication

  17. Experimental and Numerical Investigation of the Outer Ring Cooling Concept in a Hybrid and in an All-Steel Ball Bearing Used in Aero-Engines by the Introduction of a Helical Duct

    Directory of Open Access Journals (Sweden)

    Michael Flouros

    2018-02-01

    Full Text Available Rolling element bearings for aero engine applications have to withstand very challenging operating conditions because of the high thermal impact due to elevated rotational speeds and loads. The high rate of heat generation in the bearing has to be sustained by the materials, and in the absence of lubrication these will fail within seconds. For this reason, aero engine bearings have to be lubricated and cooled by a continuous oil stream. When the oil has reached the outer ring it has already been heated up, thus its capability to remove extra heat from the outer ring is considerably reduced. Increasing the mass flow of oil to the bearing is not a solution since excess oil quantity would cause high parasitic losses (churning in the bearing chamber and also increase the demands in the oil system for oil storage, scavenging, cooling, hardware weight, etc. A method has been developed for actively cooling the outer ring of the bearing. The idea behind the outer ring cooling concept was adopted from fins that are used for cooling electronic devices. A spiral groove engraved in the outer ring material of the bearing would function as a fin body with oil instead of air as the cooling medium. The method was first evaluated in an all steel ball bearing and the results were a 50% reduction in the lubricating oil flow with an additional reduction in heat generation by more than 25%. It was then applied on a Hybrid ball bearing of the same size and the former results were reconfirmed. Hybrid bearings are a combination of steel made parts, like the outer ring, the inner ring, and the cage and of ceramic rolling elements. This paper describes the work done to-date as a follow up of the work described in, and demonstrates the potential of the outer ring cooling for a bearing. Friction loss coefficient, Nusselt number, and efficiency correlations have been developed on the basis of the test results and have been compared to correlations from other authors

  18. Formation of Y{sub x}Nd{sub 1-x}Ba{sub 2}Cu{sub 3}O{sub 7-{delta}} (0{<=}x{<=}0.9) superconductors from an undercooled melt via aero-acoustic levitation

    Energy Technology Data Exchange (ETDEWEB)

    Gustafson, D.E.; Hofmeister, W.H.; Bayuzick, R.J.; Nagashio, K.; Kuribayashi, K

    2003-01-20

    This paper presents the results of rapid solidification experiments performed on the copper oxide superconductors Y{sub x}Nd{sub 1-x}Ba{sub 2}Cu{sub 3}O{sub 7-{delta}} (0{<=}x{<=}0.9). Spherical rare earth (RE) 123 specimens were levitated in O{sub 2} using aero-acoustic levitation (AAL), melted with a laser, undercooled, and solidified. The peritectic transformation temperature for the reaction RE{sub 2}BaCuO{sub 5}+liquid{yields}REBa{sub 2}Cu{sub 3}O{sub 7-{delta}} corresponding to the maximum recalescence temperature during solidification was determined. RE123 was formed directly from the melt for Y-Nd binary alloy compositions with Nd concentration greater than 20% (Y concentration less than 80%). A minimum in the peritectic transformation temperature for the Nd/Y123 system corresponding to a composition Y{sub 0.3}Nd{sub 0.7}123 was determined at 66 deg. C below the peritectic of pure Nd123.

  19. SFRO booklets - The radiotherapy of cancers: of anal canal (Anus), brain, mediastinum, pancreas, lung, prostate, rectum, breast, upper aero-digestive tract (ENT cancers), cervix, endometrium (cervical cancers), and bladder for a better understanding of radiotherapy, sarcoma radiotherapy - To better understand your treatment

    International Nuclear Information System (INIS)

    Leroy, Thomas; Mornex, Francoise; Peiffert, Didier; Thariat, Juliette; Faivre, Jean-Christophe; Huguet, Florence; Vendrely, Veronique; Barillot, Isabelle; Janoray, Guillaume; Bibault, Jean-Emmanuel; Antoni, Delphine; Crehange, Gilles; Meillan, Nicolas; Pichon, Baptiste; Biau, Julian; Pointreau, Yoann; Mirabel, Xavier; Leysalle, Axel; Claren, Audrey; Cartier, Lysian; Chand, Mari-Eve; Jacob, Julian; Renard-Oldrini, Sophie; Le Pechoux, Cecile; Ducassou, Anne; Moureau-Zabotto, Laurence; Lagrange, Jean Leon; Molina, Sarah

    2016-07-01

    This document gathers several booklets which, for different types of cancers, propose information regarding the anatomy and location of the cancer, its diagnosis, possible treatments, secondary effects during treatment, some practical advices, issues related to the post-treatment period, associations and other resources which can be useful for patient information, and a glossary of the main terms used for this cancer and its treatment. Cancer types are anal canal (Anus), brain, mediastinum, pancreas, lung, prostate, rectum, breast, upper aero-digestive tract (ENT cancers), cervix, endometrium (cervical cancers), and bladder cancers

  20. Aero-acoustic Computations of Wind Turbines

    DEFF Research Database (Denmark)

    Shen, Wen Zhong; Michelsen, Jess; Sørensen, Jens Nørkær

    2002-01-01

    A numerical algorithm for acoustic noise generation is extended to 3D flows. The approach involves two parts comprising a viscous incompressible flow part and an inviscid acoustic part. In order to simulate noise generated from a wind turbine, the incompressible and acoustic equations are written...

  1. SAM2_AERO_PRF_NAT

    Data.gov (United States)

    National Aeronautics and Space Administration — Stratospheric Aerosol Measurement II - Aerosol Profile - Native format which measures solar irradiance attenuated by aerosol particles in the Arctic & Antarctic...

  2. The aero- and hydromechanics of keel yachts

    CERN Document Server

    Slooff, J W

    2015-01-01

    How and why does sail boat performance depend on the configuration and trim of boat and sails? This book provides the yachtsman with answers in a relatively straightforward account of the physical mechanisms of sailing. It presents an accessible overview of the fluid dynamic aspects of sailing and sailing technology, addressing both aeromechanics and hydromechanics.  Readers are provided with the basic principles of physics and general mechanics that will assist their understanding of the fluid mechanics of sailing yachts. Rich appendices cover not only in-depth, mathematical-physical treatments and derivations for those wishing to explore further, but also helpful summaries of basic mathematical notions for those wishing to refresh their knowledge.  This work explores keel yachts, specifically single-masted mono-hulls with ‘fore-and-aft’, Bermuda-rigged sails. However, much of it is applicable to other types of sailing vessels such as multi-hulls, yachts with multiple masts, windsurf boards and the li...

  3. Aero particles characterization emitted by mobile sources

    International Nuclear Information System (INIS)

    Rojas V, A.; Romero G, E. T.; Lopez G, H.

    2009-01-01

    In our country, the mobile sources that conform most of the emissions at the atmosphere, are concentrated on the urban areas. For the present work, samples coming from the escapes of terrestrial transport were obtained, such as: passenger buses, load transport and particular vehicles of the Metropolitan area of the Toluca valley. The material was analyzed by means of scanning electron microscopy of low vacuum and X-ray diffraction. The objective was to characterize the emitted particles by mobile sources, morphological and chemically to know the structure, size and elements that compose them. (Author)

  4. Aero-Acoustic Computations of Wind Turbines

    DEFF Research Database (Denmark)

    Zhu, Wei Jun

    2008-01-01

    both for laminar and turbulent flows. Results have shown that sound generation is due to the unsteadiness of the flow field and the spectrum of sound has a strong relation with fluctuating forces on the solid body. Flow and acoustic simulation were also carried out for a wind turbine where general...

  5. Aero-acoustic Computations of Wind Turbines

    DEFF Research Database (Denmark)

    Shen, Wen Zhong; Michelsen, Jess; Sørensen, Jens Nørkær

    2002-01-01

    A numerical algorithm for acoustic noise generation is extended to 3D flows. The approach involves two parts comprising a viscous incompressible flow part and an inviscid acoustic part. In order to simulate noise generated from a wind turbine, the incompressible and acoustic equations are written...... in polar coordinates. The developed algorithm is combined with a so-called actuator-line technique in which the loading is distributed along lines representing the blade forces. Computations are carried out for the 500kW Nordtank wind turbine equipped with three LM19 blades. ©2001 The American Institute...

  6. The DAN-AERO MW Experiments

    DEFF Research Database (Denmark)

    Aagaard Madsen, Helge; Bak, Christian; Schmidt Paulsen, Uwe

    a number of coordinated, innovative measurements on full scale MW size rotors as well as on airfoils for MW size turbines in wind tunnels. Shear and turbulence inflow characteristics were measured on a Siemens 3.6 MW turbine with a five hole pitot tube. Pressure and turbulent inflow characteristics were...... on the blade was further instrumented with around 50 microphones for high frequency surface pressure measurements. The surface pressure measurements have been correlated with inflow measurements from four five hole pitot tubes and two sensors for measuring the high frequency (50 Hz to10 kHz) contents...

  7. Aero-Hydroacoustics for Ships. Volume 1

    Science.gov (United States)

    1984-06-01

    be seen by evaluating the tangential gradient (l/r) 9p(rlc)/ 3d as = ’/2 and noting that it1" vanishes there. Thus we see that the normal velocity...W.H. and T. Roestel, "Berechnung der Druck -vCrteilun- and Flugeiprofilen in gashaltiger Wasscrstr6mun :," ZAI4M, Vol. 54, pp. 571-588 (197O4) S 3 S...Griffin and Ramberg measured greater vortex strengths with a peak-to-peak cyl- inder displacement of O. 3d than with no motion. This increase in circulation

  8. Fluid Temperature of Aero Hydraulic Systems

    Directory of Open Access Journals (Sweden)

    I. S. Shumilov

    2016-01-01

    Full Text Available In modern supersonic aircrafts due to aerodynamic skin heating a temperature of hydraulics environment significantly exceeds that of permissible for fluids used. The same problem exists for subsonic passenger aircrafts, especially for Airbuses, which have hydraulics of high power where convective heat transfer with the environment is insufficient and there is no required temperature control of fluid. The most significant in terms of heat flow is the flow caused by the loss of power to the pump and when designing the hydraulic system (HS it is necessary to pay very serious attention to it. To use a constant capacity pump is absolutely unacceptable, since HS efficiency in this case is extremely low, and the most appropriate are variable-capacity pumps, cut-off pumps, dual-mode pumps. The HS fluid cooling system should provide high reliability, lightweight, simple design, and a specified heat transfer in all flight modes.A system cooling the fluid by the fuel of feeding lines of the aircraft engines is the most effective, and it is widely used in supersonic aircrafts, where power of cooling system is essential. Subsonic aircrafts widely use convective heat exchangers. In thermal design of the aircraft hydraulics, the focus is generally given to the maximum and minimum temperatures of the HS fluid, the choice of the type of heat exchanger (convective or flow-through, the place of its installation. In calculating the operating temperature of a hydraulic system and its cooling systems it is necessary to determine an increase of the working fluid temperature when throttling it. There are three possible formulas to calculate the fluid temperature in throttling, with the error of a calculated temperature drop from 30% to 4%.The article considers the HS stationary and noon-stationary operating conditions and their calculation, defines temperatures of fluid and methods to control its specified temperature. It also discusses various heat exchanger schemes, makes recommendations for regulation of heat flows, power reduction of cooling system, and choice of heat insulation elements of HS.

  9. Cleaner aero-engines taking off

    International Nuclear Information System (INIS)

    Lothigius, J.

    1991-01-01

    Airlines operating on domestic routes in Sweden have to pay taxes on their emissions of nitrogen oxides, hydrocarbons and carbon dioxide. These taxes have spurred improvements in engine design, but are unlikely to slow the growth in air traffic

  10. Aero-acoustic performance of Fractal Spoilers

    Science.gov (United States)

    Nedic, J.; Ganapathisubramani, B.; Vassilicos, C.; Boree, J.; Brizzi, L.; Spohn, A.

    2010-11-01

    One of the major environmental problems facing the aviation industry is that of aircraft noise. The work presented in this paper, done as part of the OPENAIR Project, looks at reducing spoiler noise through means of large-scale fractal porosity. It is hypothesised that the highly turbulent flow generated by these grids, which have multi-length-scales, would remove the re-circulation region and with it, the low frequency noise it generates. In its place, a higher frequency noise is introduced which is susceptible to atmospheric attenuation, and would be deemed less offensive to the human ear. A total of nine laboratory scaled spoilers were looked at, seven of which had a fractal design, one conventionally porous and one solid for reference. All of the spoilers were mounted on a flat plate and inclined at 30^o to the horizontal. Far-field, microphone array and PIV measurements were taken in an anechoic chamber to determine the acoustic performance and to study the flow coming through the spoilers. A significant reduction in sound pressure level is recorded and is found to be very sensitive to small changes in fractal grid parameters. Wake and drag force measurements indicated that the spoilers increase the drag whilst having minimal effect on the lift.

  11. Theoretical and experimental study of heat transfers and pressure drops along surfaces fitted with herring-bone fins: correlation between geometric and aero thermal parameters; Etudes theorique et experimentale du transfert de chaleur et des pertes de charge de surfaces munies d'ailettes disposees en chevron - correlation entre parametres geometriques et aerothermiques

    Energy Technology Data Exchange (ETDEWEB)

    Pelce, J; Malherbe, J; Pierre, B [Commissariat a l' Energie Atomique, Saclay (France). Centre d' Etudes Nucleaires

    1965-07-01

    Principal results are given of experimental research which has been carried out on the flow of a fluid along a surface fitted with herringbone fins. Aero-thermal tests have been effected on a large number of these surfaces whose geometrical parameters have been made to vary systematically. In particular, work on a large scale model has made it possible to analyse the mechanisms of heat transfer and of pressure drops. On this basis a theoretical study has led to the establishment of a correlation between the geometric configuration and the aero-thermal performances of these surfaces. Experimental results are in good agreement with the theoretical relationships. An expression has thus been derived applicable to this type of herring-boned surface in a wide zone. (authors) [French] L'ecoulement d'un fluide au voisinage d'une surface munie d'ailettes disposees en chevron a fait l'objet de recherches experimentales dont on a rappele les principaux resultats. Des essais aerothermiques ont ete effectues sur un grand nombre de ces surfaces dont a fait varier les parametres geometriques de facon systematique. En particulier, des etudes sur une maquette a grande echelle ont permis d'analyser les mecanismes de transfert de chaleur et de perte de charge. Sur ces bases, une etude theorique a conduit a des correlations entre la geometrie et les performances aerothermiques de ces surfaces. Les resultats experimentaux sont en bon accord avec les relations theoriques. On possede ainsi une formulation pour ce type de surface ailettee valable dans un domaine etendu. (auteurs)

  12. Za prezidentom v Jevrosojuz

    Index Scriptorium Estoniae

    2001-01-01

    Presidendi Euroopa Liitu astumist toetavad avaldused mõjutavad vanemat ja vaesemat elanikkonnakihti. Pealk. ajalehes Narvskaja Gazeta (2001/Nov/20): "Prezident Estonii privlekajet narod k Jevrosojuzu", lk. 2

  13. Kaadrid otsustavad kõik / Jarno Laur

    Index Scriptorium Estoniae

    Laur, Jarno, 1975-

    2002-01-01

    Noored Mõõdukad taotlesid neli aastat tagasi valimisliitude kaotamist Riigikogu valimistel ja toetavad praegugi Eesti poliitika selgemaks muutumist, kuid see peaks toimuma loomulikul teel, mitte sunniga

  14. Advanced materials and protective coatings in aero-engines application

    OpenAIRE

    M. Hetmańczyk; L. Swadźba; B. Mendala

    2007-01-01

    Purpose: The following article demonstrates the characteristics of the materials applied as parts of aircraft engine turbines and the stationary gas turbines. The principal technologies for manufacturing the heat resistant coatings and the erosion and corrosion resistant coatings were characterized. Sample applications for the aforementioned coatings are presented: on turbine blades, compressor blades and on parts of combustion chambers of aircraft engines.Design/methodology/approach: The nic...

  15. Combined Aero and Underhood Thermal Analysis for Heavy Duty Trucks

    Energy Technology Data Exchange (ETDEWEB)

    Vegendla, Prasad [Argonne National Lab. (ANL), Argonne, IL (United States); Sofu, Tanju [Argonne National Lab. (ANL), Argonne, IL (United States); Saha, Rohit [Cummins Inc., Columbus, IN (United States); Madurai Kumar, Mahesh [Cummins Inc., Columbus, IN (United States); Hwang, L. K [Cummins Inc., Columbus, IN (United States)

    2017-01-31

    Aerodynamic analysis of the medium-duty delivery truck was performed to achieve vehicle design optimization. Three dimensional CFD simulations were carried out for several improved designs, with a detailed external component analysis of wheel covers, side skirts, roof fairings, and rounded trailer corners. The overall averaged aerodynamics drag reduction through the design modifications were shown up to 22.3% through aerodynamic considerations alone, which is equivalent to 11.16% fuel savings. The main identified fuel efficiencies were based on second generation devices, including wheel covers, side skirts, roof fairings, and rounded trailer corners. The important findings of this work were; (i) the optimum curvature radius of the rounded trailer edges found to be 125 mm, with an arc length of 196.3 mm, (ii) aerodynamic drag reduction increases with dropping clearance of side skirts between wheels and ground, and (iii) aerodynamic drag reduction increases with an extension of front bumper towards the ground.

  16. Process Improvement Through Tool Integration in Aero-Mechanical Design

    Science.gov (United States)

    Briggs, Clark

    2010-01-01

    Emerging capabilities in commercial design tools promise to significantly improve the multi-disciplinary and inter-disciplinary design and analysis coverage for aerospace mechanical engineers. This paper explores the analysis process for two example problems of a wing and flap mechanical drive system and an aircraft landing gear door panel. The examples begin with the design solid models and include various analysis disciplines such as structural stress and aerodynamic loads. Analytical methods include CFD, multi-body dynamics with flexible bodies and structural analysis. Elements of analysis data management, data visualization and collaboration are also included.

  17. Micro-Optical Distributed Sensors for Aero Propulsion Applications

    Science.gov (United States)

    Arnold, S.; Otugen, V.

    2003-01-01

    The objective of this research is to develop micro-opto-mechanical system (MOMS)-based sensors for time- and space-resolved measurements of flow properties in aerodynamics applications. The measurement technique we propose uses optical resonances in dielectric micro-spheres that can be excited by radiation tunneling from optical fibers. It exploits the tunneling-induced and morphology-dependent shifts in the resonant frequencies. The shift in the resonant frequency is dependent on the size, shape, and index of refraction of the micro-sphere. A physical change in the environment surrounding a micro-bead can change one or more of these properties of the sphere thereby causing a shift in frequency of resonance. The change of the resonance frequency can be detected with high resolution by scanning a frequency-tunable laser that is coupled into the fiber and observing the transmission spectrum at the output of the fiber. It is expected that, in the future, the measurement concept will lead to a system of distributed micro-sensors providing spatial data resolved in time and space. The present project focuses on the development and demonstration of temperature sensors using the morphology-dependent optical resonances although in the latter part of the work, we will also develop a pressure sensor. During the period covered in this report, the optical and electronic equipment necessary for the experimental work was assembled and the experimental setup was designed for the single sensor temperature measurements. Software was developed for real-time tracking of the optical resonance shifts. Some preliminary experiments were also carried out to detect temperature using a single bead in a water bath.

  18. Denutrition et cancers des voies aero-digestives superieures ...

    African Journals Online (AJOL)

    Head and neck cancer and its treatment are responsible in more than 30% of cases of malnutrition witch can be severe and interfere with the management of these tumors. The aim of this paper is to provide a protocol for nutritional management practices of these cancers. The malnutrition diagnosis requires an examination ...

  19. Aero-Mechanical Coupling in a High-Speed Compressor

    Science.gov (United States)

    2010-02-01

    freedom mass-spring- damper system as χ = ς 2 √ κµ . (51) ς represents the viscous damping, κ is the system stiffness and µ the system mass. χ expresses...between the fluid and structures which are common in modern, high-speed axial compressors. There were two major areas of focus. The first was the...development of measurement technique specifically for the study of these phenomena, termed Blade Image Velocimetry (BIV). The technique can measure fluid and

  20. Reflexive Aero Structures for Enhanced Survivability, Phase II

    Data.gov (United States)

    National Aeronautics and Space Administration — Cornerstone Research Group Inc. (CRG) will develop an advanced reflexive structure technology system to increase the survivability of future systems constructed of...

  1. Aero-Acoustic-Structural Optimization Analysis and Testing, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — This proposal effort is concerned with the development of a novel multidisciplinary optimization scheme and computer software for the effective design of advanced...

  2. Performance optimization of grooved slippers for aero hydraulic pumps

    Directory of Open Access Journals (Sweden)

    Juan Chen

    2016-06-01

    Full Text Available A computational fluid dynamics (CFD simulation method based on 3-D Navier–Stokes equation and Arbitrary Lagrangian–Eulerian (ALE method is presented to analyze the grooved slipper performance of piston pump. The moving domain of grooved slipper is transformed into a fixed reference domain by the ALE method, which makes it convenient to take the effects of rotate speed, body force, temperature, and oil viscosity into account. A geometric model to express the complex structure, which covers the orifice of piston and slipper, vented groove and the oil film, is constructed. Corresponding to different oil film thicknesses calculated in light of hydrostatic equilibrium theory and boundary conditions, a set of simulations is conducted in COMSOL to analyze the pump characteristics and effects of geometry (groove width and radius, orifice size on these characteristics. Furthermore, the mechanics and hydraulics analyses are employed to validate the CFD model, and there is an excellent agreement between simulation and analytical results. The simulation results show that the sealing land radius, orifice size and groove width all dramatically affect the slipper behavior, and an optimum tradeoff among these factors is conducive to optimizing the pump design.

  3. Aero-Elastic Optimization of a 10 MW Wind Turbine

    DEFF Research Database (Denmark)

    Zahle, Frederik; Tibaldi, Carlo; Verelst, David Robert

    2015-01-01

    This article describes a multi-disciplinary optimization and analysis tool for wind turbines that is based on the open-source framework OpenMDAO. Interfaces to several simulation codes have been implemented which allows for a wide variety of problem formulations and combinations of models....... In this article concurrent aeroelastic optimization of a 10 MW wind turbine rotor is carried out with respect to material distribution distribution and planform. The optimizations achieve up to 13% mass reduction while maintaining the same power production compared to the baseline DTU 10MW RWT....

  4. Control of Boundary Layers for Aero-optical Applications

    Science.gov (United States)

    2015-06-23

    with some difficulty) from hot-wire velocity measurements, or computed directly from CFD results (e.g. Wang & Wang, 2012). Several different density...of experimental and computational research, especially applied to supersonic and hypersonic boundary layers; see Smits & Dussauge (1996), Spina et...Duan, L., Beekman, I. and Martin, M.P. (2010) Direct Numerical Simulation of Hypersonic Turbulent Boundary Layers. Part 2. Effect of Wall

  5. Hypersonic CFD applications for the National Aero-Space Plane

    Science.gov (United States)

    Richardson, Pamela F.; Mcclinton, Charles R.; Bittner, Robert D.; Dilley, A. Douglas; Edwards, Kelvin W.

    1989-01-01

    Design and analysis of the NASP depends heavily upon developing the critical technology areas that cover the entire engineering design of the vehicle. These areas include materials, structures, propulsion systems, propellants, integration of airframe and propulsion systems, controls, subsystems, and aerodynamics areas. Currently, verification of many of the classical engineering tools relies heavily on computational fluid dynamics. Advances are being made in the development of CFD codes to accomplish nose-to-tail analyses for hypersonic aircraft. Additional details involving the partial development, analysis, verification, and application of the CFL3D code and the SPARK combustor code are discussed. A nonequilibrium version of CFL3D that is presently being developed and tested is also described. Examples are given of portion calculations for research hypersonic aircraft geometries and comparisons with experiment data show good agreement.

  6. Assessment of Aero-radiometric Data of Southern Anambra Basin ...

    African Journals Online (AJOL)

    ADOWIE PERE

    Potassium and Thorium) were used and processed independently to investigate the Southern. Anambra basin for the .... Based on the Rybach equation (1) above, Uranium produces the .... Geothermal Exploration: State of the Art. Techniques.

  7. Receding-horizon adaptive contyrol of aero-optical wavefronts

    NARCIS (Netherlands)

    Tesch, J.; Gibson, S.; Verhaegen, M.

    2013-01-01

    A new method for adaptive prediction and correction of wavefront errors in adaptive optics (AO) is introduced. The new method is based on receding-horizon control design and an adaptive lattice filter. Experimental results presented illustrate the capability of the new adaptive controller to predict

  8. Reflexive Aero Structures for Enhanced Survivability, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — Cornerstone Research Group Inc. (CRG) proposes to develop an advanced reflexive structure system to increase the survivability of aerostructures. This reflexive...

  9. Overview of NASA Glenn Aero/Mobile Communications Demonstrations

    Science.gov (United States)

    Brooks, David; Hoder, Doug; Wilkins, Ryan

    2004-01-01

    The Glenn Research Center at Lewis Field (GRC) has been involved with several other NASA field centers on various networking and RF communications demonstrations and experiments since 1998. These collaborative experiments investigated communications technologies new to aviation, such as wideband Ku satcom, L-band narrowband satcom, and IP (Internet Protocol), using commercial off-the-shelf (COTS) components These technologies can be used to distribute weather and hazard data, air traffic management and airline fleet management information, and passenger cabin Internet service.

  10. Overview of NASA Glenn Aero/Mobile Communication Demonstrations

    Science.gov (United States)

    Brooks, David; Hoder, Doug; Wilkins, Ryan

    2004-01-01

    The Glenn Research Center at Lewis Field (GRC) has been involved with several other NASA field centers on various networking and RF communications demonstrations and experiments since 1998. These collaborative experiments investigated communications technologies new to aviation, such as wideband Ku satcom, L-band narrowband satcom, and IP (Internet Protocol), using commercial off-the-shelf (COTS) components These technologies can be used to distribute weather and hazard data, air traffic management and airline fleet management information, and passenger cabin Internet service.

  11. Dynamic Systems Analysis for Turbine Based Aero Propulsion Systems

    Science.gov (United States)

    Csank, Jeffrey T.

    2016-01-01

    The aircraft engine design process seeks to optimize the overall system-level performance, weight, and cost for a given concept. Steady-state simulations and data are used to identify trade-offs that should be balanced to optimize the system in a process known as systems analysis. These systems analysis simulations and data may not adequately capture the true performance trade-offs that exist during transient operation. Dynamic systems analysis provides the capability for assessing the dynamic tradeoffs at an earlier stage of the engine design process. The dynamic systems analysis concept, developed tools, and potential benefit are presented in this paper. To provide this capability, the Tool for Turbine Engine Closed-loop Transient Analysis (TTECTrA) was developed to provide the user with an estimate of the closed-loop performance (response time) and operability (high pressure compressor surge margin) for a given engine design and set of control design requirements. TTECTrA along with engine deterioration information, can be used to develop a more generic relationship between performance and operability that can impact the engine design constraints and potentially lead to a more efficient engine.

  12. Aero dynamical and mechanical behaviour of the Savonius rotor

    Energy Technology Data Exchange (ETDEWEB)

    Aouachria, Z. [Batna Univ., (Algeria). Applied Energetic Physics Laboratory

    2009-07-01

    Although the Savonius wind turbine is not as efficient as the traditional Darrieus wind turbine, its rotor design has many advantages such as simple construction; acceptance of wind from all directions; high starting torque; operation at relatively low speed; and easy adaptation to urban sites. These advantages may outweigh its low efficiency and make it suitable for small-scale power requirements such as pumping and rural electrification. This paper presented a study of the aerodynamic behaviour of a Savonius rotor, based on blade pressure measurements. A two-dimensional analysis method was used to determine the aerodynamic strengths, which leads to the Magnus effect and the generation of the vibrations on the rotor. The study explained the vibratory behaviour of the rotor and proposed an antivibration system to protect the machine. 14 refs., 1 tab., 9 figs.

  13. Multidisciplinary Aerospace Systems Optimization: Computational AeroSciences (CAS) Project

    Science.gov (United States)

    Kodiyalam, S.; Sobieski, Jaroslaw S. (Technical Monitor)

    2001-01-01

    The report describes a method for performing optimization of a system whose analysis is so expensive that it is impractical to let the optimization code invoke it directly because excessive computational cost and elapsed time might result. In such situation it is imperative to have user control the number of times the analysis is invoked. The reported method achieves that by two techniques in the Design of Experiment category: a uniform dispersal of the trial design points over a n-dimensional hypersphere and a response surface fitting, and the technique of krigging. Analyses of all the trial designs whose number may be set by the user are performed before activation of the optimization code and the results are stored as a data base. That code is then executed and referred to the above data base. Two applications, one of the airborne laser system, and one of an aircraft optimization illustrate the method application.

  14. Airborne Aero-Optics Laboratory - Transonic (AAOL-T)

    Science.gov (United States)

    2016-10-03

    the complexity of the turret wake are displayed in Figure 33. Figure 33. Visualizations of lambda 2 (vortex identification method), fluctuating...wavefront, the POD modes must span the entire set if the training matrix is full rank. In general, this will be true for experimental data, although the...highest-order modes are likely contaminated with noise. Thus, the value for N will be equal to the number of subapertures in the wavefront matrix for a

  15. Aero-Heating of Shallow Cavities in Hypersonic Freestream Flow

    Science.gov (United States)

    Everhart, Joel L.; Berger, Karen T.; Merski, N. R., Jr.; Woods, William A.; Hollingsworth, Kevin E.; Hyatt, Andrew; Prabhu, Ramadas K.

    2010-01-01

    The purpose of these experiments and analysis was to augment the heating database and tools used for assessment of impact-induced shallow-cavity damage to the thermal protection system of the Space Shuttle Orbiter. The effect of length and depth on the local heating disturbance of rectangular cavities tested at hypersonic freestream conditions has been globally assessed using the two-color phosphor thermography method. These rapid-response experiments were conducted in the Langley 31-Inch Mach 10 Tunnel and were initiated immediately prior to the launch of STS-114, the initial flight in the Space Shuttle Return-To-Flight Program, and continued during the first week of the mission. Previously-designed and numerically-characterized blunted-nose baseline flat plates were used as the test surfaces. Three-dimensional computational predictions of the entire model geometry were used as a check on the design process and the two-dimensional flow assumptions used for the data analysis. The experimental boundary layer state conditions were inferred using the measured heating distributions on a no-cavity test article. Two test plates were developed, each containing 4 equally-spaced spanwise-distributed cavities. The first test plate contained cavities with a constant length-to-depth ratio of 8 with design point depth-to-boundary-layer-thickness ratios of 0.1, 0.2, 0.35, and 0.5. The second test plate contained cavities with a constant design point depth-to-boundary-layer-thickness ratio of 0.35 with length-to-depth ratios of 8, 12, 16, and 20. Cavity design parameters and the test condition matrix were established using the computational predictions. Preliminary results indicate that the floor-averaged Bump Factor (local heating rate nondimensionalized by upstream reference) at the tested conditions is approximately 0.3 with a standard deviation of 0.04 for laminar-in/laminar-out conditions when the cavity length-to-boundary-layer thickness is between 2.5 and 10 and for cavities in the depth-to-boundary-layer-thickness range of 0.3 to 0.8. Over this same range of conditions and parameters, preliminary results also indicate that the maximum Bump Factor on the cavity centerline falls between 2.0 and 2.75, as long as the cavity-exit conditions remain laminar. Cavities with length-to-boundary-layer-thickness ratio less than 2.5 can not be easily classified with this approach and require further analysis.

  16. Detention of Star I Airline's only plane causes havoc / Linas Jegelevicius

    Index Scriptorium Estoniae

    Jegelevicius, Linas

    2010-01-01

    Leedu lennukompanii Star1 Airlines teatas 24. septembril, et peatab kõik oma lennud kuni 2. oktoobrini. Leedu lennuaamet uurib Star1 Airlinesi finantsseisu. Paljud reisijad on jäänud lennujaamadesse. Transpordiminister Eligijus Masiulise sõnul võidakse firmalt Euroopa Liidu reeglite rikkumise tõttu lennulitsents ära võtta

  17. Autotööstuse Delphi juht ravib firmat pankrotiga / Mikk Salu

    Index Scriptorium Estoniae

    Salu, Mikk, 1975-

    2005-01-01

    Maailma suurima autoosade valmistaja Delphi tegevjuht Steve Miller, kes on kuulsaks saanud United Airlines'i ja Bethlehem Steel'i pankrotiga, kuulutas välja Delphi pankroti ning seadis ametiühingud valiku ette: kas kärbitakse palku või lõpetatakse pensionide maksmine. Lisa: Pensionikoorem. Diagramm: Delphi kuulutas välja pankroti

  18. Pool Onistarist kuulub kütusefirma omanikele / Sirje Niitra

    Index Scriptorium Estoniae

    Niitra, Sirje, 1948-

    2001-01-01

    Alkoholikontserni Onistar kiiret tõusu Eesti alkoholiturul toetavad Vene rahvusest ärimeestele kuuluvate kütusefirmade Infast Oil ja Saurix Petroleum omanikud, kellele kuulub pool Eesti viinaturu liidri aktsiatest

  19. Baltics support Kosovo independence / Talis Saule Archdeacon

    Index Scriptorium Estoniae

    Archdeacon, Talis Saule

    2008-01-01

    Balti riigid teatasid päev pärast Kosovo iseseisvuse väljakuulutamist, et toetavad riigi iseseisvust. Eriarvamusi pretsedendi suhtes on venelaste esindajate hulgas ning Euroopa riikide vahel. Baltimaade liidrite põhjendused

  20. Riigi eelarvepoliitika peab olema neutraalne / Joaquin Almunia ; interv. Piret Reiljan

    Index Scriptorium Estoniae

    Almunia, Joaquin, 1948-

    2008-01-01

    Euroopa Komisjoni rahandusvoliniku Joaquin Almunia sõnul peaks Eesti vältima järeleandmisi eelarvepoliitikas, samuti tuleks prioriteediks seada investeeringud, mis toetavad majanduskasvu ning kasutada ära maksimaalselt Euroopa Liidu struktuurifonde

  1. Internetipõhised virtuaal- ja kauglaborid tuuakse loodusainete õpetajateni / Virge Tamme

    Index Scriptorium Estoniae

    Tamme, Virge

    2015-01-01

    TÜ haridusuuenduskeskuses oli 16. märtsil uurimisõpet toetava rahvusvahelise projekti Go-Lab töökoosolek. Projektimeeskond soovib aastaks 2016 avada ligi sada kaugjuhitavat teadus- ja virtuaallaborit, mis toetavad loodusainete õppimist ja õpetamist

  2. Siseriiklikud programmid võrdsete võimaluste loomiseks / Jaan Õunapuu

    Index Scriptorium Estoniae

    Õunapuu, Jaan, 1958-

    2006-01-01

    Ilmunud ka: Peipsi Rannik = Tshudskoje Poberezhje nr. 12 lk. 6, Za narod! 6. jaan. nr. 1 2007 lk. 2. Regionaalminister Jaan Õunapuu riigieelarvest rahastatud programmidest, mis toetavad piirkondade tasakaalustatud arengut

  3. Vastased üritavad koos Haloneni lüüa / Erkki Bahovski

    Index Scriptorium Estoniae

    Bahovski, Erkki, 1970-

    2006-01-01

    Soome presidendivalimistel teise vooru mitte pääsenud Koonderakonna kandidaat Matti Vanhanen, Rootsi rahvapartei kandidaat Henrik Lax ja kristlike demokraatide kandidaat Bjarne Kallis toetavad teise vooru pääsenud Koonderakonna kandidaati Sauli Niinistöd

  4. Noored ootavad revolutsiooni / Silver Meikar

    Index Scriptorium Estoniae

    Meikar, Silver, 1978-

    2006-01-01

    Valgevenes on noored tulnud tänavale, et protestida presidendivalimiste tulemuste vastu. Vt. samas: Venemaa võimud toetavad avalikult Valgevene presidenti Aleksandr Lukashenkat; Lukashenka ülisuur võit

  5. Tony Blairi pikk hüvastijätt / Tiina Tamman

    Index Scriptorium Estoniae

    Tamman, Tiina, 1948-

    2006-01-01

    Tony Blairi teade, et Manchesteris algav Suurbritannia leiboristide aastakonverents jääb talle peaministrina viimaseks, on põhjustanud erakonnas pahameele. Mitmed parlamendiliikmed toetavad rahandusminister Gordon Browni valitsusjuhiks saamist, kuid soovitakse ka juhi valimiste korraldamist

  6. Küttimine võib septembris peatuda. Maaomanikud vs. jahimehed / Ain Alvela ; kommenteerinud Heiki Hepner, Val Rajasaar

    Index Scriptorium Estoniae

    Alvela, Ain, 1967-

    2011-01-01

    Maksumaksjad ja maaomanikud toetavad Eesti jahindust sisuliselt viie miljoni euroga aastas, kuigi keskkonnaspetsialistide hinnangul võiks asi olla vastupidi. Kehtiv jahiseadus ei aita kaasa metsa väärtuse parandamisele. Tabelid

  7. The Hypersonic Revolution. Volume 2. From Scramjet to the National Aero-Space Plane

    Science.gov (United States)

    1995-08-01

    Ord. Aerophysics Lab. $2.7M Lewis Plumbrook HTF 2.8M Langley 8 ft. HTST 1.5M Ramjet Instrumentation 1.1M Phase II A (Garrett) Contract: $20.7M AIM...Shuttle flight proved to be a media event unparalleled in the brief history of Dryden. For the previous week, Johnson and Dryden public affairs officials...had been on hand to meet the demands of the hundreds of media representatives who left plusher locales for the sunny but blustery desert. Those who

  8. HARDWARE AND ALGORITHMIC STRUCTURE OF MULTIPOSITION RADIO RANGEFINDING NAVIGATION AND LANDING AERO-SYSTEM

    Directory of Open Access Journals (Sweden)

    Yaroslav Kondrashov

    2011-03-01

    Full Text Available Abstract. The principles of formation of the structure and functioning algorithms are developed andpresented for multipositioning radio rangefinding land-based system which identifies the location ofcommuter aircrafts in the vertical and horizontal planes by the method of three ranges without usingaltimeter.Keywords: aircraft, commuter airlines, aeronavigation, landing, airborne radio ranging equipment,operation algorithms.

  9. Application of Weakest Link Probabilistic Framework for Fatigue Notch Factor to Aero Engine Materials

    Science.gov (United States)

    2014-08-25

    42 3.1.1 The Physical Metallurgy of Nickel and Its Alloys... metallurgy [88]. . 43 Figure 3.2. Procedural steps of producing turbine disc alloys by powder metallurgy techniques [88... weld fillets, holes for bolts, and rivets. Other forms of discontinuities are caused by the ingestion of foreign objects during operation causing

  10. Design and Aero-elastic Simulation of a 5MW Floating Vertical Axis Wind Turbine

    DEFF Research Database (Denmark)

    Vita, Luca; Schmidt Paulsen, Uwe; Aagaard Madsen, Helge

    2013-01-01

    This paper deals with the design of a 5MW floating offshore Vertical Axis Wind Turbine (VAWT). The design is based on a new offshore wind turbine concept (DeepWind concept), consisting of a Darrieus rotor mounted on a spar buoy support structure, which is anchored to the sea bed with mooring lines......-DTU. The numerical simulations take into account the fully coupled aerodynamic and hydrodynamic loads on the structure, due to wind, waves and currents. The turbine is tested in operative conditions, at different sea states, selected according to the international offshore standards. The research is part...... of the European project DeepWind (2010-2014), which has been financed by the European Union (FP7-Future Emerging Technologies)....

  11. Comparison of Aero-Propulsive Performance Predictions for Distributed Propulsion Configurations

    Science.gov (United States)

    Borer, Nicholas K.; Derlaga, Joseph M.; Deere, Karen A.; Carter, Melissa B.; Viken, Sally A.; Patterson, Michael D.; Litherland, Brandon L.; Stoll, Alex M.

    2017-01-01

    NASA's X-57 "Maxwell" flight demonstrator incorporates distributed electric propulsion technologies in a design that will achieve a significant reduction in energy used in cruise flight. A substantial portion of these energy savings come from beneficial aerodynamic-propulsion interaction. Previous research has shown the benefits of particular instantiations of distributed propulsion, such as the use of wingtip-mounted cruise propellers and leading edge high-lift propellers. However, these benefits have not been reduced to a generalized design or analysis approach suitable for large-scale design exploration. This paper discusses the rapid, "design-order" toolchains developed to investigate the large, complex tradespace of candidate geometries for the X-57. Due to the lack of an appropriate, rigorous set of validation data, the results of these tools were compared to three different computational flow solvers for selected wing and propulsion geometries. The comparisons were conducted using a common input geometry, but otherwise different input grids and, when appropriate, different flow assumptions to bound the comparisons. The results of these studies showed that the X-57 distributed propulsion wing should be able to meet the as-designed performance in cruise flight, while also meeting or exceeding targets for high-lift generation in low-speed flight.

  12. Aerotrace. Measurement of trace species in the exhaust of aero engines

    Energy Technology Data Exchange (ETDEWEB)

    Cottington, R V [DRA, Farnborough (United Kingdom)

    1998-12-31

    There is growing evidence that trace species, both gaseous and particulate, play an important role in the chemistry of the atmosphere. Very little is currently known about the nature and concentration of these species emitted by aircraft engines. The purpose of AEROTRACE, therefore, is to make representative measurements of trace species emissions, such as particulates, hydrocarbon constituents and various nitrogen compounds, from engine combustors over the entire flight altitude range from ground level to cruise conditions. An overview of the programme and progress to date is presented. (author)

  13. 78 FR 49662 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Airplanes

    Science.gov (United States)

    2013-08-15

    ... Community, has issued AD Cancellation Notice No.: 2013-0085-CN, dated April 8, 2013, which cancelled Ente... Cancellation Notice No.: 2013-0085-CN, dated April 8, 2013, and Ente Nazionale per l'Aviazione Civile (ENAC) AD... economic impact, positive or negative, on a substantial number of small entities under the criteria of the...

  14. Assessment of epidemiologic situation in aero-ecological systems of north part of Semipalatinsk test site

    International Nuclear Information System (INIS)

    Ajdarkhanova, G.S.

    2000-01-01

    The vast territories of Central Kazakhstan adjoining to Semipalatinsk test site (STS) are intensively using for agriculture purposes. Radioecological situation of environmental objects in places of active land-using is characterizing by considerable accumulation of artificial radionuclides in local points. In 1965-1988 dynamics of accumulation of 90 Sr, 137 Cs, 131 I, 144 Ce, 210 Po is considered. Most high concentration of these radionuclides corresponds to 1965, 1974, 1986-87 in all objects: soil, water, pasture plants. These processes are explained by emergency situation on STS and Chernobyl accident. In objects of veterinary supervision (meat, milk, bones) increasing of concentrations of 90 Sr, 137 Cs established in 1965-1966, 1968, 1972-1974, 1986-1987. In present time significant territories of Semipalatinsk test site as well as territories of other sites are places for foodstuffs production. In this regard all agricultural zones Of Republic of Kazakhstan demand comprehensive research, exploitation of advanced methods of farms implementation improving environmental, epidemiologic and economical situation in regions

  15. Bridging aero-fracture evolution with the characteristics of the acoustic emissions in a porous medium

    Directory of Open Access Journals (Sweden)

    Semih eTurkaya

    2015-09-01

    Full Text Available The characterization and understanding of rock deformation processes due to fluid flow is a challenging problem with numerous applications. The signature of this problem can be found in Earth Science and Physics, notably with applications in natural hazard understanding, mitigation or forecast (e.g. earthquakes, landslides with hydrological control, volcanic eruptions, or in industrial applications such as hydraulic-fracturing, steam-assisted gravity drainage, CO₂ sequestration operations or soil remediation. Here we investigate the link between the visual deformation and the mechanical wave signals generated due to fluid injection into porous media. In a rectangular Hele-Shaw Cell, side air injection causes burst movement and compaction of grains along with channeling (creation of high permeability channels empty of grains. During the initial compaction and emergence of the main channel, the hydraulic fracturing in the medium generates a large non-impulsive low frequency signal in the frequency range 100 Hz - 10 kHz. When the channel network is established, the relaxation of the surrounding medium causes impulsive aftershock-like events, with high frequency (above 10 kHz acoustic emissions, the rate of which follows an Omori Law. These signals and observations are comparable to seismicity induced by fluid injection. Compared to the data obtained during hydraulic fracturing operations, low frequency seismicity with evolving spectral characteristics have also been observed. An Omori-like decay of microearthquake rates is also often observed after injection shut-in, with a similar exponent p≃0.5 as observed here, where the decay rate of aftershock follows a scaling law dN/dt ∝(t-t₀-p . The physical basis for this modified Omori law is explained by pore pressure diffusion affecting the stress relaxation.

  16. An Aero-Acoustic Tool for Terminal Area Operations, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — In this highly interconnected world, transportation systems must feature increased flexibility and shorter door-to-door trip times to be successful. Shorter...

  17. Aero-Effected Distributed Adaptive Control of Flexible Aircraft Using Active Bleed, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — The proposed research focuses on the development of a new adaptive control methodology for active control of wing aerodynamic shape to effect distributed aerodynamic...

  18. High Temperature Metallic Seal Development For Aero Propulsion and Gas Turbine Applications

    Science.gov (United States)

    More, Greg; Datta, Amit

    2006-01-01

    A viewgraph presentation on metallic high temperature static seal development at NASA for gas turbine applications is shown. The topics include: 1) High Temperature Static Seal Development; 2) Program Review; 3) Phase IV Innovative Seal with Blade Alloy Spring; 4) Spring Design; 5) Phase IV: Innovative Seal with Blade Alloy Spring; 6) PHase IV: Testing Results; 7) Seal Seating Load; 8) Spring Seal Manufacturing; and 9) Other Applications for HIgh Temperature Spring Design

  19. Aero-Thermo-Structural Design Optimization of Internally Cooled Turbine Blades

    Science.gov (United States)

    Dulikravich, G. S.; Martin, T. J.; Dennis, B. H.; Lee, E.; Han, Z.-X.

    1999-01-01

    A set of robust and computationally affordable inverse shape design and automatic constrained optimization tools have been developed for the improved performance of internally cooled gas turbine blades. The design methods are applicable to the aerodynamics, heat transfer, and thermoelasticity aspects of the turbine blade. Maximum use of the existing proven disciplinary analysis codes is possible with this design approach. Preliminary computational results demonstrate possibilities to design blades with minimized total pressure loss and maximized aerodynamic loading. At the same time, these blades are capable of sustaining significantly higher inlet hot gas temperatures while requiring remarkably lower coolant mass flow rates. These results suggest that it is possible to design internally cooled turbine blades that will cost less to manufacture, will have longer life span, and will perform as good, if not better than, film cooled turbine blades.

  20. Computational Aero-Acoustic Using High-order Finite-Difference Schemes

    DEFF Research Database (Denmark)

    Zhu, Wei Jun; Shen, Wen Zhong; Sørensen, Jens Nørkær

    2007-01-01

    are solved using the in-house flow solver EllipSys2D/3D which is a second-order finite volume code. The acoustic solution is found by solving the acoustic equations using high-order finite difference schemes. The incompressible flow equations and the acoustic equations are solved at the same time levels......In this paper, a high-order technique to accurately predict flow-generated noise is introduced. The technique consists of solving the viscous incompressible flow equations and inviscid acoustic equations using a incompressible/compressible splitting technique. The incompressible flow equations...

  1. Aero-Thermo-Structural Analysis of Inlet for Rocket Based Combined Cycle Engines

    Science.gov (United States)

    Shivakumar, K. N.; Challa, Preeti; Sree, Dave; Reddy, Dhanireddy R. (Technical Monitor)

    2000-01-01

    NASA has been developing advanced space transportation concepts and technologies to make access to space less costly. One such concept is the reusable vehicles with short turn-around times. The NASA Glenn Research Center's concept vehicle is the Trailblazer powered by a rocket-based combined cycle (RBCC) engine. Inlet is one of the most important components of the RBCC engine. This paper presents fluid flow, thermal, and structural analysis of the inlet for Mach 6 free stream velocity for fully supersonic and supercritical with backpressure conditions. The results concluded that the fully supersonic condition was the most severe case and the largest stresses occur in the ceramic matrix composite layer of the inlet cowl. The maximum tensile and the compressive stresses were at least 3.8 and 3.4, respectively, times less than the associated material strength.

  2. System-Level Development of Fault-Tolerant Distributed Aero-Engine Control Architecture, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — NASA's vision for an "intelligent engine" will be realized with the development of a truly distributed control system and reliable smart transducer node components;...

  3. Analyses of the mechanisms of amplitude modulation of aero-acoustic wind turbine sound

    DEFF Research Database (Denmark)

    Fischer, Andreas; Aagaard Madsen, Helge; Kragh, Knud Abildgaard

    2014-01-01

    This paper explores the source mechanism which cause amplitude modulation of the emitted sound of a wind turbine at large distances from the turbine, named as other amplitude modulation. Measurements of the fluctuating surface pressure on a 2.3MW wind turbine showed a considerable variation over...... give further evidence that transient stall is a main mechanism to cause other amplitude modulation. Wind shear was identified as a critical condition to cause angle of attack variations. Dierent control strategies to mitigate other amplitude modulation were proposed....

  4. Impulse Based Substructuring for Coupling Offshore Structures and Wind Turbines in Aero-Elastic Simulations

    NARCIS (Netherlands)

    Van der Valk, P.L.C.; Rixen, D.J.

    2012-01-01

    In order to achieve the goal of 20% renewable energy in 2020, as set by the European Union, large offshore wind farms are either under construction or in development through-out Europe. As many of the "easy" locations are already under development, offshore wind farms are moving further offshore

  5. Recent developments in turbomachinery component materials and manufacturing challenges for aero engine applications

    Science.gov (United States)

    Srinivas, G.; Raghunandana, K.; Satish Shenoy, B.

    2018-02-01

    In the recent years the development of turbomachinery materials performance enhancement plays a vital role especially in aircraft air breathing engines like turbojet engine, turboprop engine, turboshaft engine and turbofan engines. Especially the transonic flow engines required highly sophisticated materials where it can sustain the entire thrust which can create by the engine. The main objective of this paper is to give an overview of the present cost-effective and technological capabilities process for turbomachinery component materials. Especially the main focus is given to study the Electro physical, Photonic additive removal process and Electro chemical process for turbomachinery parts manufacture. The aeronautical propulsion based technologies are reviewed thoroughly where in surface reliability, geometrical precession, and material removal and highly strengthened composite material deposition rates usually difficult to cut dedicated steels, Titanium and Nickel based alloys. In this paper the past aeronautical and propulsion mechanical based manufacturing technologies, current sophisticated technologies and also future challenging material processing techniques are covered. The paper also focuses on the brief description of turbomachinery components of shaping process and coating in aeromechanical applications.

  6. 78 FR 56589 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Airplanes

    Science.gov (United States)

    2013-09-13

    ... friction in the MLG wheel lever sub-assembly. This condition, if not detected and corrected, could lead to... action. We are requiring inspection(s) of the left and right MLG LHF with a report to the manufacturer of the results if cracks are found. We will work with the type certificate holder to evaluate the report...

  7. Design and aero-acoustic analysis of a counter-rotating wind turbine

    Science.gov (United States)

    Agrawal, Vineesh V.

    Wind turbines have become an integral part of the energy business because they are one of the most economical and reliable sources of renewable energy. Conventional wind turbines are capable of capturing less than half of the energy present in the wind. Hence, to make the wind turbines more efficient, it is important to increase their performance. A horizontal axis wind turbine with multiple rotors is one concept that can achieve a higher power conversion rate. Also, a concern for wind energy is the noise generated by wind turbines. Hence, an investigation into the acoustic behavior of a multi-rotor horizontal axis wind turbine is required. In response to the need of a wind turbine design with higher power coefficient, a unique design of a counter-rotating horizontal axis wind turbine (CR-HAWT) is proposed. The Blade Element Momentum (BEM) theory is used to aerodynamically design the blades of the two rotors. Modifications are made to the BEM theory to accommodate the interaction of the two rotors. The tower effect on the noise generation of the downwind rotor is investigated. Predictions are made for the total noise generated by the wind turbine at its design operating conditions. A total power coefficient of 65.2% is predicted for the proposed CR-HAWT design. A low tip speed ratio is chosen to minimize the noise generation. The aeroacoustic analysis of the CR-HAWT shows that the noise generated at its design operating conditions is within an acceptable range. Thus, the CR-HAWT is predicted to be a quiet wind turbine with a high power coefficient, making it highly desirable for small wind turbine applications.

  8. Aero-elastic Stability Analysis for Large-Scale Wind Turbines

    NARCIS (Netherlands)

    Meng, F.

    2011-01-01

    Nowadays, many modern countries are relying heavily on non-renewable resources. One common example of non-renewable resources is fossil fuel. Non-renewable resources are ?nite resources that will eventually dwindle, becoming too expensive or too environmentally damaging to retrieve. In contrast,

  9. New thermal energies in France. Solar, biomass, geothermal and aero-thermal: which perspectives by 2015?

    International Nuclear Information System (INIS)

    2012-01-01

    Whereas thermal renewable energies are to become inescapable, and notably 'green heat' which is acclaimed by real estate professionals as well as by industries, their market is foreseen to grow at a rate of 6 per cent a year until 2015. This high rate is notably due to the soaring price of conventional energies like electricity, gas or oil fuel, but also to environmental constraints related to the reduction of greenhouse gas emissions. A first part proposes an overview of the French market of new sources of thermal renewable energies for a domestic use in 2011, and discusses perspectives by 2015. A detailed analysis of the three main technologies (heat pumps, thermal solar devices, wood fuelled domestic heating devices) is proposed and challenges faced by involved enterprises and possible answers provided by professionals are also detailed. A second part gathers and comments data related to thermal energy production for industrial and collective use (in collective housing and office building): energy production level, legal and regulatory framework, evolution of demand, predictions for the different energy sources (wood energy, geothermal, waste energetic valorisation). It also proposes an analysis of stakes related to these applications. The third part proposes an assessment of the size of the different sectors by presenting key economic figures (turnover, staff, etc.). While the fourth part proposes an overview of leaders for each sector (thermal solar, biomass, and heat pump) and a more detailed presentation of 14 important actors, the fifth and last part proposes a large set of financial and economic indicators of 200 involved operators

  10. Trace elements in aero transported solid particles in urban and rural atmosphere using PIXE

    International Nuclear Information System (INIS)

    Salazar Matarrita, A.

    1997-01-01

    For the present study, multi schedule collectors (type Streaker) were located, in four places selected by their relative location, to possible fountains of identifiable s particles. The cooperation among the Nuclear Laboratory PIXE of the State University of Florida, U.S.A. Permitted the irradiation of the collected samples, using the facilities of the Accelerator Van der Graaff of 4 MeV. The x-rays spectra emission,were valued in the Laboratory LAFNA and the Laboratory PIXE, using the Hex computational code. They were determined among 12 and 15 chemical elements to level of plans, quantity that depends on the place of recollection. The statistical analysis of the data recollected, was carried out applying a nalysis of factors . This statistical program of analysis, permits the regroup of the elements, depending on the systematic variation of the concentrations. A graphic analysis of distribution was carried out, besides, schedule of the hours of I continuous monitoring. This permits to observe its own singularities. Giving the opportunity to determine, possible fountains of origin of the collected particles. (author) [es

  11. Evaluation of Aero Commander sidewall vibration and interior acoustic data: Static operations

    Science.gov (United States)

    Piersol, A. G.; Wilby, E. G.; Wilby, J. F.

    1980-01-01

    Results for the vibration measured at five locations on the fuselage structure during static operations are presented. The analysis was concerned with the magnitude of the vibration and the relative phase between different locations, the frequency response (inertance) functions between the exterior pressure field and the vibration, and the coherent output power functions at interior microphone locations based on sidewall vibration. Fuselage skin panels near the plane of rotation of the propeller accept propeller noise excitation more efficiently than they do exhaust noise.

  12. Verification of aero-elastic offshore wind turbine design codes under IEA Wind Task XXIII

    DEFF Research Database (Denmark)

    Vorpahl, Fabian; Strobel, Michael; Jonkman, Jason M.

    2014-01-01

    with the incident waves, sea current, hydrodynamics and foundation dynamics of the support structure. A large set of time series simulation results such as turbine operational characteristics, external conditions, and load and displacement outputs was compared and interpreted. Load cases were defined and run...... to differences in the model fidelity, aerodynamic implementation, hydrodynamic load discretization and numerical difficulties within the codes. The comparisons resulted in a more thorough understanding of the modeling techniques and better knowledge of when various approximations are not valid.More importantly...... is to summarize the lessons learned and present results that code developers can compare to. The set of benchmark load cases defined and simulated during the course of this project—the raw data for this paper—is available to the offshore wind turbine simulation community and is already being used for testing...

  13. A unified, multifidelity quasi-newton optimization method with application to aero-structural designa

    Science.gov (United States)

    Bryson, Dean Edward

    A model's level of fidelity may be defined as its accuracy in faithfully reproducing a quantity or behavior of interest of a real system. Increasing the fidelity of a model often goes hand in hand with increasing its cost in terms of time, money, or computing resources. The traditional aircraft design process relies upon low-fidelity models for expedience and resource savings. However, the reduced accuracy and reliability of low-fidelity tools often lead to the discovery of design defects or inadequacies late in the design process. These deficiencies result either in costly changes or the acceptance of a configuration that does not meet expectations. The unknown opportunity cost is the discovery of superior vehicles that leverage phenomena unknown to the designer and not illuminated by low-fidelity tools. Multifidelity methods attempt to blend the increased accuracy and reliability of high-fidelity models with the reduced cost of low-fidelity models. In building surrogate models, where mathematical expressions are used to cheaply approximate the behavior of costly data, low-fidelity models may be sampled extensively to resolve the underlying trend, while high-fidelity data are reserved to correct inaccuracies at key locations. Similarly, in design optimization a low-fidelity model may be queried many times in the search for new, better designs, with a high-fidelity model being exercised only once per iteration to evaluate the candidate design. In this dissertation, a new multifidelity, gradient-based optimization algorithm is proposed. It differs from the standard trust region approach in several ways, stemming from the new method maintaining an approximation of the inverse Hessian, that is the underlying curvature of the design problem. Whereas the typical trust region approach performs a full sub-optimization using the low-fidelity model at every iteration, the new technique finds a suitable descent direction and focuses the search along it, reducing the number of low-fidelity evaluations required. This narrowing of the search domain also alleviates the burden on the surrogate model corrections between the low- and high-fidelity data. Rather than requiring the surrogate to be accurate in a hyper-volume bounded by the trust region, the model needs only to be accurate along the forward-looking search direction. Maintaining the approximate inverse Hessian also allows the multifidelity algorithm to revert to high-fidelity optimization at any time. In contrast, the standard approach has no memory of the previously-computed high-fidelity data. The primary disadvantage of the proposed algorithm is that it may require modifications to the optimization software, whereas standard optimizers may be used as black-box drivers in the typical trust region method. A multifidelity, multidisciplinary simulation of aeroelastic vehicle performance is developed to demonstrate the optimization method. The numerical physics models include body-fitted Euler computational fluid dynamics; linear, panel aerodynamics; linear, finite-element computational structural mechanics; and reduced, modal structural bases. A central element of the multifidelity, multidisciplinary framework is a shared parametric, attributed geometric representation that ensures the analysis inputs are consistent between disciplines and fidelities. The attributed geometry also enables the transfer of data between disciplines. The new optimization algorithm, a standard trust region approach, and a single-fidelity quasi-Newton method are compared for a series of analytic test functions, using both polynomial chaos expansions and kriging to correct discrepancies between fidelity levels of data. In the aggregate, the new method requires fewer high-fidelity evaluations than the trust region approach in 51% of cases, and the same number of evaluations in 18%. The new approach also requires fewer low-fidelity evaluations, by up to an order of magnitude, in almost all cases. The efficacy of both multifidelity methods compared to single-fidelity optimization depends significantly on the behavior of the high-fidelity model and the quality of the low-fidelity approximation, though savings are realized in a large number of cases. The multifidelity algorithm is also compared to the single-fidelity quasi-Newton method for complex aeroelastic simulations. The vehicle design problem includes variables for planform shape, structural sizing, and cruise condition with constraints on trim and structural stresses. Considering the objective function reduction versus computational expenditure, the multifidelity process performs better in three of four cases in early iterations. However, the enforcement of a contracting trust region slows the multifidelity progress. Even so, leveraging the approximate inverse Hessian, the optimization can be seamlessly continued using high-fidelity data alone. Ultimately, the proposed new algorithm produced better designs in all four cases. Investigating the return on investment in terms of design improvement per computational hour confirms that the multifidelity advantage is greatest in early iterations, and managing the transition to high-fidelity optimization is critical.

  14. Aero-thermo-dynamic analysis of the Spaceliner-7.1 vehicle in high altitude flight

    Science.gov (United States)

    Zuppardi, Gennaro; Morsa, Luigi; Sippel, Martin; Schwanekamp, Tobias

    2014-12-01

    SpaceLiner, designed by DLR, is a visionary, extremely fast passenger transportation concept. It consists of two stages: a winged booster, a vehicle. After separation of the two stages, the booster makes a controlled re-entry and returns to the launch site. According to the current project, version 7-1 of SpaceLiner (SpaceLiner-7.1), the vehicle should be brought at an altitude of 75 km and then released, undertaking the descent path. In the perspective that the vehicle of SpaceLiner-7.1 could be brought to altitudes higher than 75 km, e.g. 100 km or above and also for a speculative purpose, in this paper the aerodynamic parameters of the SpaceLiner-7.1 vehicle are calculated in the whole transition regime, from continuum low density to free molecular flows. Computer simulations have been carried out by three codes: two DSMC codes, DS3V in the altitude interval 100-250 km for the evaluation of the global aerodynamic coefficients and DS2V at the altitude of 60 km for the evaluation of the heat flux and pressure distributions along the vehicle nose, and the DLR HOTSOSE code for the evaluation of the global aerodynamic coefficients in continuum, hypersonic flow at the altitude of 44.6 km. The effectiveness of the flaps with deflection angle of -35 deg. was evaluated in the above mentioned altitude interval. The vehicle showed longitudinal stability in the whole altitude interval even with no flap. The global bridging formulae verified to be proper for the evaluation of the aerodynamic coefficients in the altitude interval 80-100 km where the computations cannot be fulfilled either by CFD, because of the failure of the classical equations computing the transport coefficients, or by DSMC because of the requirement of very high computer resources both in terms of the core storage (a high number of simulated molecules is needed) and to the very long processing time.

  15. Ballistic impact velocity response of carbon fibre reinforced aluminium alloy laminates for aero-engine

    Science.gov (United States)

    Mohammed, I.; Abu Talib, A. R.; Sultan, M. T. H.; Saadon, S.

    2017-12-01

    Aerospace and other industries use fibre metal laminate composites extensively due to their high specific strength, stiffness and fire resistance, in addition to their capability to be tailored into different forms for specific purposes. The behaviours of such composites under impact loading is another factor to be considered due to the impacts that occur in take-off, landing, during maintenance and operations. The aim of the study is to determine the specific perforation energy and impact strength of the fibre metal laminates of different layering pattern of carbon fibre reinforced aluminium alloy and hybrid laminate composites of carbon fibre and natural fibres (kenaf and flax). The composites are fabricated using the hand lay-up method in a mould with high bonding polymer matrix and compressed by a compression machine, cured at room temperature for one day and post cure in an oven for three hours. The impact tests are conducted using a gun tunnel system with a flat cylindrical bullet fired using a helium gas at a distance of 14 inches to the target. Impact and residual velocity of the projectile are recorded by high speed video camera. Specific perforation energy of carbon fibre reinforced aluminium alloy (CF+AA) for both before and after fire test are higher than the specific perforation energy of the other composites considered before and after fire test respectively. CF +AA before fire test is 55.18% greater than after. The same thing applies to impact strength of the composites where CF +AA before the fire test has the highest percentage of 11.7%, 50.0% and 32.98% as respectively compared to carbon fibre reinforced aluminium alloy (CARALL), carbon fibre reinforced flax aluminium alloy (CAFRALL) and carbon fibre reinforced kenaf aluminium alloy (CAKRALL), and likewise for the composites after fire test. The considered composites in this test can be used in the designated fire zone of an aircraft engine to protect external debris from penetrating the engine shield due to higher values of impact strength and specific perforation energy as highlighted by the test results.

  16. Modeling pressure drop of inclined flow through a heat exchanger for aero-engine applications

    International Nuclear Information System (INIS)

    Missirlis, D.; Yakinthos, K.; Storm, P.; Goulas, A.

    2007-01-01

    In the present work further numerical predictions for the flow field through a specific type of a heat exchanger, which is planned to be used in the exhaust nozzle of aircraft engines. In order to model the flow field through the heat exchanger, a porous medium model is used based on a simple quadratic relation, which connects the pressure drop with the inlet air velocity in the external part of the heat exchanger. The aim of this work is to check the applicability of the quadratic law in a variety of velocity inlet conditions configured by different angles of attack. The check is performed with CFD and the results are compared with new available experimental data for these inlet conditions. A detailed qualitative analysis shows that although the quadratic law has been derived for a zero angle of attack, it performs very well for alternative non-zero angles. These observations are very helpful since this simple pressure drop law can be used for advanced computations where the whole system of the exhaust nozzle together with the heat exchangers can be modeled within a holistic approach

  17. Competitividad del Transporte Aero y Maritimo de Mexico en el Marco del Comercio Exterior

    OpenAIRE

    America I. Zamora Torres; Jose Cesar Lenin Navarro Chavez; Joel Bonales Valencia

    2015-01-01

    Las tendencias del comercio internacional han modificado la estructura de costos, precios, logística, cadenas de suministros y por consiguiente de las ventajas comparativas, estas tendencias de igual manera han definido la competitividad comercial de los países siendo cada vez más relevante el nivel de integración de las redes mundiales de transporte como factor impulsor del comercio internacional. En este trabajo se evalúa, a través del Análisis de Componente Principales, la competitividad d...

  18. Clinical significance identification in the of aero-allergen western Cape

    African Journals Online (AJOL)

    ... pteronyssimus (73%), South African grasses (38%), tree pollens (22,4%), flower and weed pollens (19,6%), cat (27%), dog (12%) and feathers (18,6%). One-third of the 1 372 children screened at Red Cross War Memorial Children's Hospital Allergy Service had positive specific IgE responses to environmental allergens.

  19. MINIVER: Miniature version of real/ideal gas aero-heating and ablation computer program

    Science.gov (United States)

    Hendler, D. R.

    1976-01-01

    Computer code is used to determine heat transfer multiplication factors, special flow field simulation techniques, different heat transfer methods, different transition criteria, crossflow simulation, and more efficient thin skin thickness optimization procedure.

  20. Delineation of a shallow subsurface aquiclude relief with aero electromagnetic data

    Science.gov (United States)

    Römer, A.; Winkler, E.; Bieber, G.; Motschka, K.; Reitner, H.

    2009-04-01

    Within a governmental groundwater remediation project in Austria, a new (overworked) characterization of a large catchment area (600 km2) with aeroelectromagnetics (AEM) was carried out. This catchment area is a large and important zone of subsurface water resources for currently and future municipal and rural water supply. Conflicts in future land use between e.g. agricultura, excavigation of mass materials, city and regional planning, ect. are preassigned and have impacts concerning the quality and quantity of available groundwater. The geology of the investigation area is a typical post-glacial region, characterized by aggradational deposition areas. The thickness of the wide-spread terrace gravels ranges from 10m to 40m, being the preferred ground water aquifer. The subsurface of the investigation area is built up by a Neogen basement, the so called Molasse and is acting as an aquiclude relative to the overlying quaternary sediments. Aeroelectromagnetic data from a former aerogeophysical survey were reinterpreted with a new processing and interpretation approach for the determination of this geological 3 layer case. This aeroelectromagnetic inversion integrates results from borehole data, ground geoelectric surveys and from geological mapping as a priori input information. The inversion result for a measured AEM data value is determined by a combination of geostatistically weighted additional information and likelihood weighted theoretical models. The primary aim of the study was the delineation of the aquiclude relief. The ground water circulation within the different terrace gravels is substantially affected by this Neogen relief. Depressions and prequaternary (tertiary) riverbeds within the Molasse often show other trends of water flow than the surficial, recent vales. The knowledge of the hydrogeological framework is essential for identification and definition of water protection and catchment areas as a decision base for national land use regulations. The result is a topographic model of the aquiclude with a depth resolution of ±5m.

  1. Integrated Aero-Servo-Thermo-Propulso-Elasticity (ASTPE) for Hypersonic Scramjet Vehicle Design/Analysis

    Science.gov (United States)

    2009-12-04

    flattening parameter of 0.0033528. In UPTOP, the vehicle’s geocentric latitude, geodetic latitude and longitude (both over an inertial and rotating planet...5sin2 A) (l-5sin2^) 3-3 where J2 = 1.08263x10°, re is the equatorial radius of the Earth, and X is the geocentric latitude. UPTOP incorporates two...computational cost associated with this effectiveness. 3.3.2 Objective Function Calculation Objective and constraint function calculations depend on

  2. 78 FR 69597 - Airworthiness Directives; Piaggio Aero Industries S.p.A Airplanes

    Science.gov (United States)

    2013-11-20

    ...-Italy; phone: +39 010 6481353; fax: +39 010 6481881; email: [email protected] ; Internet..., economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by... Genova-Italy; phone: +39 010 6481353; fax: +39 010 6481881; email: [email protected

  3. 2009 Aero-Metric Inc. Topographic LiDAR: Yukon Flats, Alaska

    Data.gov (United States)

    National Oceanic and Atmospheric Administration, Department of Commerce — This delivery contains point cloud data in LAS 1.2 format, classified in the following manner. Class 1: Unclassified and Class 2: Ground. Overlap points have been...

  4. 2007 Aero-Metric Inc. Topographic LiDAR: Valdez, Alaska

    Data.gov (United States)

    National Oceanic and Atmospheric Administration, Department of Commerce — This project was completed under USGS Contract No. 07CRCN0002, Task Order No. 070020009. This delivery contains point cloud data in LAS 1.1 format, classified in the...

  5. 2009 Aero-Metric Inc. Topographic LiDAR: North Slope Coastal Alaska

    Data.gov (United States)

    National Oceanic and Atmospheric Administration, Department of Commerce — This delivery contains point cloud data in LAS 1.2 format, with Absolute GPS Timestamps. No classification has been completed on these data. The nominal point...

  6. A Preliminary to War: The 1st Aero Squadron and the Mexican Punitive Expedition of 1916

    National Research Council Canada - National Science Library

    Miller, Roger G

    2003-01-01

    .... "Black Jack" Pershing. President Woodrow Wilson had ordered Pershing's force into Mexico in response to a March 9 attack on the tiny border town by the Mexican desperado, Francisco "Pancho" Villa...

  7. Composite adaptive control of belt polishing force for aero-engine blade

    Science.gov (United States)

    Zhsao, Pengbing; Shi, Yaoyao

    2013-09-01

    The existing methods for blade polishing mainly focus on robot polishing and manual grinding. Due to the difficulty in high-precision control of the polishing force, the blade surface precision is very low in robot polishing, in particular, quality of the inlet and exhaust edges can not satisfy the processing requirements. Manual grinding has low efficiency, high labor intensity and unstable processing quality, moreover, the polished surface is vulnerable to burn, and the surface precision and integrity are difficult to ensure. In order to further improve the profile accuracy and surface quality, a pneumatic flexible polishing force-exerting mechanism is designed and a dual-mode switching composite adaptive control(DSCAC) strategy is proposed, which combines Bang-Bang control and model reference adaptive control based on fuzzy neural network(MRACFNN) together. By the mode decision-making mechanism, Bang-Bang control is used to track the control command signal quickly when the actual polishing force is far away from the target value, and MRACFNN is utilized in smaller error ranges to improve the system robustness and control precision. Based on the mathematical model of the force-exerting mechanism, simulation analysis is implemented on DSCAC. Simulation results show that the output polishing force can better track the given signal. Finally, the blade polishing experiments are carried out on the designed polishing equipment. Experimental results show that DSCAC can effectively mitigate the influence of gas compressibility, valve dead-time effect, valve nonlinear flow, cylinder friction, measurement noise and other interference on the control precision of polishing force, which has high control precision, strong robustness, strong anti-interference ability and other advantages compared with MRACFNN. The proposed research achieves high-precision control of the polishing force, effectively improves the blade machining precision and surface consistency, and significantly reduces the surface roughness.

  8. A BRIEF OVERVIEW AND METALLOGRAPHY FOR COMMONLY USED MATERIALS IN AERO JET ENGINE CONSTRUCTION

    Directory of Open Access Journals (Sweden)

    Juraj Belan

    2018-01-01

    Full Text Available Aluminium, titanium, and nickel base alloys are mostly and widely used for aircraft jet engine con-struction. A proper evaluation of its microstructure is important from working safety point of view. To receive a well prepared sample of microstructure, some important steps have to be undertaken. Except for proper grinding and polishing of a sample, structure developing is a significant step, too. In order to develop microstructure various chemical reagents were used to achieve the best results for microstructure evaluation. The chemical reagents were used according to the previous knowledge and some new ones were also tested. Aluminium AK4-1č, titanium VT – 8, and nickel VŽL – 14 and ŽS6 – U alloys were used as an experimental materials. Alloy AK4-1č is used for fan blade produc-tion with working temperatures up to 300°C. It is a forged piece of metal machined down into final shape by five-axe milling machine. Alloy VT – 8 is used for high pressure compressor rotor blade production with working temperatures up to 500°C. Blades are forged as well and finally grinded. Finally nickel base alloys VŽL – 14 and ŽS6 – U are used for turbine blade production with working temperatures up 950°C. Blades for turbine are casted into mould with reducible models.

  9. Scientific Notes from the Central Aero-Hydrodynamic Institute (Selected Articles).

    Science.gov (United States)

    1978-08-14

    I Page 4 2. Ihq cqnsiderably larger iqcrement 9f pitching iscnentv obtineDd on wjqg vith this jete it allows in cerain assigmed/prescribed cbntex-e...f to oth S M [ M (U1+V")~ jaubsiqunatryd by the ndex "o ace ss td tte values of variables That composing particle speed aloqg tlhe axis z can be

  10. A Neural Network Aero Design System for Advanced Turbo-Engines

    Science.gov (United States)

    Sanz, Jose M.

    1999-01-01

    An inverse design method calculates the blade shape that produces a prescribed input pressure distribution. By controlling this input pressure distribution the aerodynamic design objectives can easily be met. Because of the intrinsic relationship between pressure distribution and airfoil physical properties, a neural network can be trained to choose the optimal pressure distribution that would meet a set of physical requirements. The neural network technique works well not only as an interpolating device but also as an extrapolating device to achieve blade designs from a given database. Two validating test cases are discussed.

  11. 77 FR 30371 - Airworthiness Directives; International Aero Engines AG Turbofan Engines

    Science.gov (United States)

    2012-05-23

    .... Request To Allow Special Flight Permits United Airlines and TAM Airlines requested that we allow Special... change the AD. Request To Delay USI Start Time and Repeat Inspection Time TAM Airlines requested that we....C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing...

  12. Research status on aero-acoustic noise from wind turbine blades

    International Nuclear Information System (INIS)

    Yang, B

    2013-01-01

    This paper describes the noise mechanisms and categories of modern large wind turbine and main noise sources. Then the latest progresses in wind turbine noise researches are described from three aspects: noise prediction model, detection of noise sources by microphone array technique and methods for noise reduction. Although the turbine is restricted to horizontal axis wind turbines, the noise prediction model and reduction methods also can be applied to other turbines when the noise mechanisms are similar. Microphone array technique can be applied to locate any kind of noise sources

  13. Engineering method for aero-propulsive characteristics at hypersonic Mach numbers

    Science.gov (United States)

    Goradia, Suresh; Torres, Abel O.; Stack, Sharon H.; Everhart, Joel L.

    1991-01-01

    An engineering method has been developed for the rapid analysis of external aerodynamics and propulsive performance characteristics of airbreathing vehicles at hypersonic Mach numbers. This method, based on the theory of characteristics, has been developed to analyze fuselage-wing body combinations and body flaps with blunt or sharp leading/trailing edges. Arbitrary ratio of specific heat for the flowing medium can be specified in the program. Furthermore, the capability exists in the code to compute the inviscid inlet mass capture and momentum flux. The method is under development for computations of pressure distribution, and flow characteristics in the inlet, along with the effect of viscosity. Correlative studies have been performed for representative hypersonic configurations using the current method. The results of these correlations for various aerodynamics parameters are encouraging.

  14. Opto-mechanical design of optical window for aero-optics effect simulation instruments

    Science.gov (United States)

    Wang, Guo-ming; Dong, Dengfeng; Zhou, Weihu; Ming, Xing; Zhang, Yan

    2016-10-01

    A complete theory is established for opto-mechanical systems design of the window in this paper, which can make the design more rigorous .There are three steps about the design. First, the universal model of aerodynamic environment is established based on the theory of Computational Fluid Dynamics, and the pneumatic pressure distribution and temperature data of optical window surface is obtained when aircraft flies in 5-30km altitude, 0.5-3Ma speed and 0-30°angle of attack. The temperature and pressure distribution values for the maximum constraint is selected as the initial value of external conditions on the optical window surface. Then, the optical window and mechanical structure are designed, which is also divided into two parts: First, mechanical structure which meet requirements of the security and tightness is designed. Finally, rigorous analysis and evaluation are given about the structure of optics and mechanics we have designed. There are two parts to be analyzed. First, the Fluid-Solid-Heat Coupled Model is given based on finite element analysis. And the deformation of the glass and structure can be obtained by the model, which can assess the feasibility of the designed optical windows and ancillary structure; Second, the new optical surface is fitted by Zernike polynomials according to the deformation of the surface of the optical window, which can evaluate imaging quality impact of spectral camera by the deformation of window.

  15. The influence of turbulence on the aero-elastic instability of wind turbines

    DEFF Research Database (Denmark)

    Zhang, Zili; Nielsen, Søren R.K.

    2014-01-01

    Modern multi-megawatt wind turbines are designed with longer and slender blades using new composite materials and advanced fabrication methods. The trend towards lighter and more flexible blades may lead to aeroelastic instability of wind turbines under certain circumstances, thus resulting...... calibrated to the NREL 5 MW baseline wind turbine. Aeroelastic stability of the wind turbine system has been evaluated for various values of the rated generator torque, the rated rotational speed of the rotor, the mean wind speed and the turbulence intensity. Critical turbulence intensity, at which the wind...

  16. Presentations from the Aeroelastic Workshop – latest results from AeroOpt

    DEFF Research Database (Denmark)

    Hansen, Morten Hartvig

    This report contains the slides of the presentations at the Aeroelastic Workshop held at Risø-DTU for the wind energy industry in Denmark on January 27, 2011. The scientific part of the agenda at this workshop was • Anisotropic beam element in HAWC2 for modelling of composite lay-ups (Taeseong Kim...... (Robert Mikkelsen) • Potential of fatigue and extreme load reductions on swept blades using HAWC2 (David Verelst) • Aeroelastic modal analysis of backward swept blades using HAWCStab2 (Morten H. Hansen) • Aeroelastic rotor design minimizing the loads (Christian Bak) • A small study of flat back airfoils...

  17. Rare earth oxide aero- and xerogels. Tuning porosity and catalytic properties

    International Nuclear Information System (INIS)

    Neumann, Bjoern

    2013-11-01

    Heterogeneous catalysts to this day are still largely developed on the basis of trial and error. This is due to the great difficulty of creating custom-designed structures at the nanometer scale using traditional preparation methods. In the course of recent rapid developments in the material sciences, however, it has become possible to create materials with custom-designed properties from the macroscopic down into the nanometer range. The purpose of the present study was to make use of this potential for catalysis. The task was to modify the porosity and composition of selected rare earth oxides that promise well as catalysts with the goal of obtaining good results in terms of oxidative reactions and oxidative coupling. One major focus was on chemical sol-gel methods and in particular on what is referred to as the epoxide addition method. Extensive work was put into the characterisation and catalytic testing of aerogels and xerogels of pure rare earth oxides as well as of hybrid systems of rare earth oxides and aluminium oxide. Furthermore, thin xerogel films and macroporous monoliths were produced, the latter using a direct foaming method. The results of this work confirm the high potential of sol-gel chemistry for making porous materials of variable and controllable porosity and composition available for heterogeneous catalysis and creating more powerful catalysts. [de

  18. Electromagnetic Systems Effects Database (EMSED). AERO 90, Phase II User's Manual

    National Research Council Canada - National Science Library

    Sawires, Kalim

    1998-01-01

    The Electromagnetic Systems Effects Database (EMSED), also called AIRBASE, is a training guide for users not familiar with the AIRBASE database and its operating platform, the Macintosh computer (Mac...

  19. Retrograde and Direct Powered Aero-Gravity-Assist Trajectories around Mars

    Science.gov (United States)

    Murcia, J. O.; Prado, A. F. B. A.; Gomes, V. M.

    2018-04-01

    A Gravity-Assist maneuver is used to reduce fuel consumption and/or trip times in interplanetary missions. It is based in a close approach of a spacecraft to a celestial body. Missions like Voyager and Ulysses used this concept. The present paper performs a study of a maneuver that combines three effects: the gravity of the planet, the application of an impulsive maneuver when the spacecraft is passing by the periapsis and the effects of the atmosphere of the planet. Direct and retrograde trajectories are considered, with particular attention to the differences due to the higher relative velocity between the spacecraft and the atmosphere, which increases the effects of the atmosphere. The planet Mars is used for the numerical examples.

  20. Human-Vehicle Interface for Semi-Autonomous Operation of Uninhabited Aero Vehicles

    Science.gov (United States)

    Jones, Henry L.; Frew, Eric W.; Woodley, Bruce R.; Rock, Stephen M.

    2001-01-01

    The robustness of autonomous robotic systems to unanticipated circumstances is typically insufficient for use in the field. The many skills of human user often fill this gap in robotic capability. To incorporate the human into the system, a useful interaction between man and machine must exist. This interaction should enable useful communication to be exchanged in a natural way between human and robot on a variety of levels. This report describes the current human-robot interaction for the Stanford HUMMINGBIRD autonomous helicopter. In particular, the report discusses the elements of the system that enable multiple levels of communication. An intelligent system agent manages the different inputs given to the helicopter. An advanced user interface gives the user and helicopter a method for exchanging useful information. Using this human-robot interaction, the HUMMINGBIRD has carried out various autonomous search, tracking, and retrieval missions.

  1. Optimal manpower allocation in aircraft line maintenance (Case in GMF AeroAsia)

    Science.gov (United States)

    Puteri, V. E.; Yuniaristanto, Hisjam, M.

    2017-11-01

    This paper presents a mathematical modeling to find the optimal manpower allocation in an aircraft line maintenance. This research focuses on assigning the number and type of manpower that allocated to each service. This study considers the licenced worker or Aircraft Maintenance Engineer Licence (AMEL) and non licenced worker or Aircraft Maintenance Technician (AMT). In this paper, we also consider the relationship of each station in terms of the possibility to transfer the manpower among them. The optimization model considers the number of manpowers needed for each service and the requirement of AMEL worker. This paper aims to determine the optimal manpower allocation using the mathematical modeling. The objective function of the model is to find the minimum employee expenses. The model was solved using the ILOG CPLEX software. The results show that the manpower allocation can meet the manpower need and the all load can be served.

  2. Aerotrace. Measurement of trace species in the exhaust of aero engines

    Energy Technology Data Exchange (ETDEWEB)

    Cottington, R.V. [DRA, Farnborough (United Kingdom)

    1997-12-31

    There is growing evidence that trace species, both gaseous and particulate, play an important role in the chemistry of the atmosphere. Very little is currently known about the nature and concentration of these species emitted by aircraft engines. The purpose of AEROTRACE, therefore, is to make representative measurements of trace species emissions, such as particulates, hydrocarbon constituents and various nitrogen compounds, from engine combustors over the entire flight altitude range from ground level to cruise conditions. An overview of the programme and progress to date is presented. (author)

  3. Aero-Mechanical Design Methodology for Subsonic Civil Transport High-Lift Systems

    Science.gov (United States)

    vanDam, C. P.; Shaw, S. G.; VanderKam, J. C.; Brodeur, R. R.; Rudolph, P. K. C.; Kinney, D.

    2000-01-01

    In today's highly competitive and economically driven commercial aviation market, the trend is to make aircraft systems simpler and to shorten their design cycle which reduces recurring, non-recurring and operating costs. One such system is the high-lift system. A methodology has been developed which merges aerodynamic data with kinematic analysis of the trailing-edge flap mechanism with minimum mechanism definition required. This methodology provides quick and accurate aerodynamic performance prediction for a given flap deployment mechanism early on in the high-lift system preliminary design stage. Sample analysis results for four different deployment mechanisms are presented as well as descriptions of the aerodynamic and mechanism data required for evaluation. Extensions to interactive design capabilities are also discussed.

  4. Effect of external jet-flow deflector geometry on OTW aero-acoustic characteristics

    Science.gov (United States)

    Vonglahn, U.; Groesbeck, D.

    1976-01-01

    The effect of geometry variations in the design of external deflectors for use with over-the-wing (OTW) configurations was studied at model scale and subsonic jet velocities. Included in the variations were deflector size and angle as well as wing size and flap setting. A conical nozzle (5.2-cm diameter) mounted at 0.1 chord above and downstream of the wing leading edges was used. The data indicate that external deflectors provide satisfactory takeoff and approach aerodynamic performance and acoustic characteristics for OTW configurations. These characteristics together with expected good cruise aerodynamics, since external deflectors are storable, may provide optimum OTW design configurations.

  5. Clinical significance identification in the of aero-allergen western Cape

    African Journals Online (AJOL)

    -allergen ... avoidance measures and the selection of patients suitable for immunotherapy. ... continuous volumetric air sampling, using a Burkard spore trap. Mould spore counts .... evidence of asthma, rhinitis and!or eczema. Drops of allergen.

  6. LES/RANS Modeling of Aero-Optical Effects in a Supersonic Cavity Flow

    Science.gov (United States)

    2016-06-13

    7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) 8. PERFORMING ORGANIZATION REPORT NUMBER North Carolina State University 2701 Sullivan Dr...the kinetic energy associated with the tangential velocity component at the interpolation point. The function ),,( BI ddc  that scales the normal... University of Minnesota) provided the DMD code, as well as useful feedback in interpreting its results. The U.S. Government is authorized to

  7. An integrated aerodynamic/propulsion study for generic aero-space planes based on waverider concepts

    Science.gov (United States)

    Emanuel, G.; Rasmussen, M. L.

    1991-01-01

    Research efforts related to the development of a unified aerospace plane analysis based on waverider technology are summarized. Viscous effects on the forebodies of cone-derived waverider configurations were studied. A simple means for determining the average skin friction coefficient of laminar boundary layers was established. This was incorporated into a computer program that provides lift and drag coefficients and lift/drag ratio for on-design waveriders when the temperature and Reynolds number based on length are specified. An effort was made to carry out parabolized Navier-Stokes (PNS) calculations for cone-derived waveriders. When the viscous terms were turned off (in the Euler mode) computations for elliptic cone-derived waveriders could be carried out for a wide range of on-design and off-design situations. Work related to waveriders derived from power law shocks is described in some detail.

  8. The Process of Technology Transfer: A Case Study of the National Aero-Space Plane Program.

    Science.gov (United States)

    1995-09-01

    often characterize qualitative research ( Bryman , 1989:173,178). A final advantage of the case study method is that it is used to develop hypotheses for...November 1992). Bryman , Alan. Research Methods and Organizational Studies. Winchester MA: Unwin Hyman Inc., 1989. Chapman, Richard L. "The Federal...and C. William Emory. Business Research Methods . Chicago: Richard D. Irwin Inc., 1995. Creighton, J.W., J.A. Jolly, and T.A. Buckles. "The Manager’s

  9. Experience with Aero- and Fluid-Dynamic Testing for Engineering and CFD Validation

    Science.gov (United States)

    Ross, James C.

    2016-01-01

    Ever since computations have been used to simulate aerodynamics the need to ensure that the computations adequately represent real life has followed. Many experiments have been performed specifically for validation and as computational methods have improved, so have the validation experiments. Validation is also a moving target because computational methods improve requiring validation for the new aspect of flow physics that the computations aim to capture. Concurrently, new measurement techniques are being developed that can help capture more detailed flow features pressure sensitive paint (PSP) and particle image velocimetry (PIV) come to mind. This paper will present various wind-tunnel tests the author has been involved with and how they were used for validation of various kinds of CFD. A particular focus is the application of advanced measurement techniques to flow fields (and geometries) that had proven to be difficult to predict computationally. Many of these difficult flow problems arose from engineering and development problems that needed to be solved for a particular vehicle or research program. In some cases the experiments required to solve the engineering problems were refined to provide valuable CFD validation data in addition to the primary engineering data. All of these experiments have provided physical insight and validation data for a wide range of aerodynamic and acoustic phenomena for vehicles ranging from tractor-trailers to crewed spacecraft.

  10. Hyaluronic Acid: Perspectives in Upper Aero-Digestive Tract. A Systematic Review.

    Directory of Open Access Journals (Sweden)

    Manuele Casale

    Full Text Available To date, topical therapies guarantee a better delivery of high concentrations of pharmacologic agents to the mucosa of the upper aerodigestive tract (UADT. The use of topical drugs, which are able to reduce mucosal inflammation and to improve healing tissues, can represent a relevant therapeutic advance. Topical sodium hyaluronate (SH has recently been recognized as adjuvant treatment in the chronic inflammatory disease of the UADT.The aim of our work was to review the published literature regarding all the potential therapeutic effects of SH in the chronic inflammatory disease of UADT.Relevant published studies were searched in Pubmed, Google Scholar, Ovid using keywords ("sodium hyaluronate" and "upper airways" or Medical Subject Headings.At the end of our selection process, sixteen publications have been included. Six of them in the post-operative period of nasal-sinus surgery, 2 of them in pediatric patients affected by recurrent upper respiratory tract infections, 4 of them in reducing symptoms and preventing exacerbations of chronic upper airways in adult population, 4 of them in patients with chronic inflammatory disease of UADT, including gastro-esophageal reflux disease (GERD.Topical administration of SH plays a pivotkey role in the postoperative phase of patients undergoing FESS and nasal surgery, and positive results are generally observed in all the patients suffering from UADT chronic inflammatory disease.

  11. Individual hollow and mesoporous aero-graphitic microtube based devices for gas sensing applications

    Science.gov (United States)

    Lupan, Oleg; Postica, Vasile; Marx, Janik; Mecklenburg, Matthias; Mishra, Yogendra K.; Schulte, Karl; Fiedler, Bodo; Adelung, Rainer

    2017-06-01

    In this work, individual hollow and mesoporous graphitic microtubes were integrated into electronic devices using a FIB/SEM system and were investigated as gas and vapor sensors by applying different bias voltages (in the range of 10 mV-1 V). By increasing the bias voltage, a slight current enhancement is observed, which is mainly attributed to the self-heating effect. A different behavior of ammonia NH3 vapor sensing by increasing the applied bias voltage for hollow and mesoporous microtubes with diameters down to 300 nm is reported. In the case of the hollow microtube, an increase in the response was observed, while a reverse effect has been noticed for the mesoporous microtube. It might be explained on the basis of the higher specific surface area (SSA) of the mesoporous microtube compared to the hollow one. Thus, at room temperature when the surface chemical reaction rate (k) prevails on the gas diffusion rate (DK) the structures with a larger SSA possess a higher response. By increasing the bias voltage, i.e., the overall temperature of the structure, DK becomes a limiting step in the gas response. Therefore, at higher bias voltages the larger pores will facilitate an enhanced gas diffusion, i.e., a higher gas response. The present study demonstrates the importance of the material porosity towards gas sensing applications.

  12. Direct-Current Forced Interruption and Breaking Performance of Spiral-Type Contacts in Aero Applications

    Directory of Open Access Journals (Sweden)

    Wenlei Huo

    2017-05-01

    Full Text Available This paper analyses the transient characteristics and breaking performance of direct-current (DC forced-interruption vacuum interrupters in 270 V power-supply systems. Three stages are identified in forced interruption: the DC-arcing stage, current-commutation stage, and voltage-recovery stage. During the current-commutation stage, the reverse peak-current coefficient k, which is a key design factor, is used to calculate the rate of current at zero-crossing (di/dt. MATLAB/Simulink simulation models are established to obtain the transient characteristics influenced by the forced-commutation branch parameters and the coefficient k. To study the breaking performance of spiral-type contacts, experiments are conducted for different contact materials and arcing times for currents less than 3.5 kA. During the DC-arcing stage, a locally intensive burning arc is observed in the CuW80 contact; however, it is not observed in the CuCr50 contact. On examining the re-ignition interruption results of the CuW80 contact, the intensive burning arc is found to be positioned within a possible re-ignition region. When the arcing time is longer than 1 ms, the intensive burning arc occurs and affects the breaking performance of the spiral-type contacts. If the DC-arcing stage is prolonged, the total arcing energy increases, which leads to a lower breaking capacity.

  13. STRUCTURAL SCALE LIFE PREDICTION OF AERO STRUCTURES EXPERIENCING COMBINED EXTREME ENVIRONMENTS

    Science.gov (United States)

    2017-07-01

    complex loading environments. Today’s state of the art methods cannot address structural reliability under combined environment conditions due to...probabilistically assess the structural life under complex loading environments. Today’s state of the art methods cannot address structural reliability...Institute of Aeronautics and Astronautics, San Diego, CA, January 4th‐8th, 2016. Clark, L. D., Bae, H., Gobal, K., and Penmetsa, R., “ Engineering

  14. Keeleauhinnad 2014 / Jüri Valge

    Index Scriptorium Estoniae

    Valge, Jüri, 1948-

    2014-01-01

    Keeleteo auhinna vääriliseks tunnistati Tallinna ülikooli ja Rocca al Mare kooli koostöös valminud "Lapse keelelist arengut toetavad mängud", mille autorid on Reili Argus ja Cattre Hein. Wiedemanni auhinna sai rahvaluuleteadlane Arvo Krikmann saavutuste eest eesti keele uurimises, õpetamises, kasutamises ja propageerimises. Ka nominentidest

  15. Märgakem probleemidega last! / Kristjan Paas, Kaire Tamm

    Index Scriptorium Estoniae

    Paas, Kristjan

    2003-01-01

    2002. a. viis Riigikontroll läbi auditi - koolides ja alaealiste komisjonides läbi viidud küsitlusuuringus selgitati koolikohustuse täitmisega seotud küsimusi, õpilaste koolist puudumist, klassikursuse kordamist. Koolikohustuse mittetäitmise põhjused, täitmist toetavad võimalused.

  16. Eesti transpordi infrastruktuuri ootavad suured toetused / Tanel Tang

    Index Scriptorium Estoniae

    Tang, Tanel

    2003-01-01

    EL-iga liitumisel avanevad Eestile Euroopa Regionaalarengu fond (ERDF) ja Ühtekuuluvusfond, mis tähendab transpordisektorile miljardite kroonide suurust abi maanteede, raudteede, lennujaamade ning sadamate ehitamiseks ja rekonstrueerimiseks. Vt. samas: Eestile tulnud abi PHARE ja ISPA fondist ; Ühtekuuluvusfond ja Euroopa regionaalarengu fond (ERDF) toetavad Eestit miljonite kroonidega. Diagramm: EL-i abi Eesti transpordisektorile

  17. Sakslased tulevad! Ärevad ajad Tallinnas Von Krahli Teatris

    Index Scriptorium Estoniae

    2001-01-01

    Von Krahli Teater ja Showcase Beat Le Mot valmistuvad oma esimeseks koostööprojektiks - lavastuseks "Pirates", kus osalevad mõlema teatri näitlejad ja tehnikud. Ühisprojekti toetavad Goethe Instituut, Hamburgi Linnavalitsus ja Eesti Kultuurkapital

  18. Stipendiumid siirdeuuringuteks

    Index Scriptorium Estoniae

    2005-01-01

    Tartu Ülikooli Euroopa Kolledži siirdeuuringu programmist, mida Avatud Eesti Fond ja Lennart Meri Fond toetavad 135 000 krooniga. Toetussumma sisaldab kolm 25 000 krooni suurust stipendiumi, mis antakse Ukraina üliõpilastele, kes soovivad 2006. a. kevadsemestril õppida Euroopa Kolledžis

  19. Teadlased katsetavad ettevõtlusega / Väinu Rozental

    Index Scriptorium Estoniae

    Rozental, Väinu, 1957-

    2004-01-01

    Tartu Ülikoolist välja kasvanud teadusmahukad spin-off-ettevõtted on üldjuhul edukad vaid siis, kui firmat juhib majandusharidusega tegevjuht, mitte teadlane. Diagramm. Vt. samas: Ärimehed toetavad meditsiinitehnikat. Tartu Ülikoolist võrsunud teadusmahukad ettevõtted

  20. USA toetus Eestile

    Index Scriptorium Estoniae

    2007-01-01

    Ameerika Ühendriikide riigisekretär Condoleezza Rice kinnitas 3. mail 2007 telefonikõnes president Toomas Hendrik Ilvesele USA toetust Eestile ning tõsist muret Venemaa käitumise üle oma naaberriigi suhtes. Ilmunud ka: Meie Kodu 9. mai 2007, lk. 2, pealk.: USA riigisekretär Vabariigi Presidendile: Ühendriigid toetavad Eestit

  1. Surmanuhtlus kõrgeima võimaliku karistusmäärana : [bakalaureusetöö] / Katrin Roosmaa ; Tartu Ülikool, õigusteaduskond ; juhendaja: Silvia Kaugia

    Index Scriptorium Estoniae

    Roosmaa, Katrin, 1984-

    2007-01-01

    Surmanuhtluse olemus ja selle karistusliigiga sanktsioneeritud teod Eestis lähiminevikus, surmanuhtluse määramine ja täideviimine kuni 1998. a.-ni, surmanuhtluse kaotamise direktiiv ning seda toetavad ja mittetoetavad riigid, levinumad poolt- ja vastuargumendid, Eesti elanikkonna suhtumine

  2. IT-firmad pääsevad pooleks aastaks Silicon Valleysse / Holger Roonemaa

    Index Scriptorium Estoniae

    Roonemaa, Holger

    2010-01-01

    Tehnopol ja EAS toetavad nn. start-up-firmade saatmist pooleks aastaks USA-sse Silicon Valleysse kogemusi omandama, programm on mõeldud eelkõige neile ettevõtetele, kel on oma toode või teenus valmis ja kes soovivad sellega maailmaturule minna

  3. "Ega Kruuda pole koi poiss old!" / Madis Jürgen

    Index Scriptorium Estoniae

    Jürgen, Madis, 1962-

    2007-01-01

    Mitmed ärimees Oliver Kruuda naabrid Helbe tänavas toetavad ärimehe tööd võsa muutmisel haljasalaks ning paluvad keskkonnaministeeriumile, Tallinna keskkonnaametile ja Nõmme linnaosa valitsusele saadetud kirjas abi O. Kruuda korrastustööde jätkamiseks Helbe tänava piirkonnas. Linnaosa vanema Rainer Vakra arvamus

  4. Bush skazal ne sovsem to, tshto skazal

    Index Scriptorium Estoniae

    2006-01-01

    USA abivälisminister Euroopa ja Euraasia küsimustes Daniel Fried teatas, et NATO riigid toetavad Gruusia, Moldova ja Aserbaidžaani territoriaalset terviklikkust, kuid ei luba neil seda taastada relva abil. Abiminister selgitab, mida pidas USA president George W. Bush silmas, kui ta avaldas Riia tippkohtumisel toetust Gruusiale tema püüdlustes liituda NATO-ga

  5. Res Publica nõuab rea võimulubaduste täitmist / Rasmus Kagge

    Index Scriptorium Estoniae

    Kagge, Rasmus, 1977-

    2005-01-01

    Res Publica lubas koalitsioonipartneritele mitte minna koalitsioonileppe kallale, kui nad toetavad toppama jäänud lubaduste täitmist - haridusreformi, presidendi otsevalimiste seadustamist, riigikontrollile ka omavalitsuste kontrollimiseks õiguse andmist ja lapsevanema tulumaksuvaba miinimumi kahekordistamist alates pere teisest lapsest. Lisa: Võimuliitlaste soovid

  6. Saksamaal võidab toetust utoopia : raha jagamine ilma tööta / Külli-Riin Tigasson

    Index Scriptorium Estoniae

    Tigasson, Külli-Riin, 1975-

    2007-01-01

    Saksamaal toetavad mitmed poliitikud utoopilist ideed: ära kaotada kõik sotsiaaltoetused ning asendada need 700-1500-eurose riikliku kuusissetulekuga, mida makstaks kõigile Saksa kodanikele, sõltumata sellest, kas nad töötavad või mitte. Vt. samas: Kas Milton Friedman eksis?

  7. Poola saab tülis Venemaaga kogu EL-i oma selja taha / Krister Paris

    Index Scriptorium Estoniae

    Paris, Krister, 1977-

    2006-01-01

    EL-i eesistujamaa Soome lubas Poolale lisada Venemaa kehtestatud impordikeelu Poola lihatoodetele EL-i ja Venemaa läbirääkimiste ametlikku päevakorda. Impordikeelu kiiret lõpetamist toetavad Prantsusmaa ja Leedu. Lisa: Poola püüdlused "vastuvõetamatud"

  8. Frequency and time variable parametric forces in a generalized linear aero-elastic model with two degrees of freedom

    Czech Academy of Sciences Publication Activity Database

    Náprstek, Jiří; Pospíšil, Stanislav

    2013-01-01

    Roč. 20, č. 5 (2013), s. 355-367 ISSN 1802-1484 R&D Projects: GA ČR(CZ) GA103/09/0094; GA AV ČR(CZ) IAA200710902 Institutional support: RVO:68378297 Keywords : flutter derivatives * indicial functions * non-symmetric systems * dynamic stability Subject RIV: JM - Building Engineering http://www.engineeringmechanics.cz/obsahy.html?R=20&C=5

  9. 75 FR 43105 - Airworthiness Directives; PIAGGIO AERO INDUSTRIES S.p.A Model PIAGGIO P-180 Airplanes

    Science.gov (United States)

    2010-07-23

    ... beams and the rear pressurized bulkhead. If left uncorrected, long term fatigue stress could locally... send any written relevant data, views, or arguments about this proposed AD. Send your comments to an... term fatigue stress could locally weaken the structure, compromising the fuselage structural integrity...

  10. Aero-acoustics prediction of a vertical axis wind turbine using Large Eddy Simulation and acoustic analogy

    International Nuclear Information System (INIS)

    Ghasemian, Masoud; Nejat, Amir

    2015-01-01

    Operating wind turbines generate tonal and broadband noises affecting the living environment adversely; especially small wind turbines located in the vicinity of human living places. Therefore, it is important to determine the level of noise pollution of such type of wind turbine installation. The current study carries out numerical prediction for aerodynamic noise radiated from an H-Darrieus Vertical Axis Wind Turbine. Incompressible LES (Large Eddy Simulation) is conducted to obtain the instantaneous turbulent flow field. The noise predictions are performed by the Ffowcs Williams and Hawkings (FW–H) acoustic analogy formulation. Simulations are performed for five different tip-speed ratios. First, the mean torque coefficient is compared with the experimental data, and good agreement is observed. Then, the research focuses on the broadband noises of the turbulent boundary layers and the tonal noises due to blade passing frequency. The contribution of the thickness, loading and quadrupole noises are investigated, separately. The results indicate a direct relation between the strength of the radiated noise and the rotational speed. Furthermore, the effect of receiver distance on the OASPL (Overall Sound Pressure Level) is investigated. It is concluded that the OASPL varies with a logarithmic trend with the receiver distance as it was expected. - Highlights: • Large Eddy Simulation has been used to predict the turbulent flow field. • The Ffowcs Williams and Hawkings method was employed to predict radiated noise. • There is a direct relation between the radiated noise and the tip speed ratio. • The quadrupole noises have negligible effect on the tonal noises

  11. Dynamics of Atmospheric Aerosol Number Size Distributions in the Eastern Mediterranean During the "SUB-AERO" Project.

    Czech Academy of Sciences Publication Activity Database

    Ždímal, Vladimír; Smolík, Jiří; Eleftheriadis, K.; Wagner, Zdeněk; Housiadas, Ch.; Mihalopoulos, N.; Mikuška, Pavel; Večeřa, Zbyněk; Kopanakis, I.; Lazaridis, M.

    2011-01-01

    Roč. 241, 1-4 (2011), s. 133-146 ISSN 0049-6979 Grant - others:SUBAERO(XE) EVK2-CT-1999O-00052 Institutional research plan: CEZ:AV0Z40720504; CEZ:AV0Z40310501 Keywords : nucleation events * aerosols * particulate matter Subject RIV: CF - Physical ; Theoretical Chemistry Impact factor: 1.625, year: 2011

  12. A Program of Research and Education to Advance the Design, Synthesis, and Optimization of Aero-Space System Concepts

    Science.gov (United States)

    Sandusky, Robert

    2002-01-01

    Since its inception in December 1999, the program has provided support for a total of 11 Graduate Research Scholar Assistants, of these, 6 have completed their MS degree program. The program has generated 3 MS theses and a total of 4 publications/presentations.

  13. Flow visualization and aero-optics in simulated environments; Proceedings of the Meeting, Orlando, FL, May 21, 22, 1987

    International Nuclear Information System (INIS)

    Bentley, H.T. III.

    1987-01-01

    The present conference on high speed aerooptics facilities, aerodynamic holography, and photooptical techniques gives attention to the prediction of image degradation through a turbulent medium, wind tunnel studies of optical beam degradation through heterogeneous aerodynamic flows, wavelength effects on images formed through turbulence, holographic visualizations of hypersonic flow viscous interactions, holographic interferometry for gas flow pattern studies, and a holographic flow field analysis of Spacelab-3 crystal growth experiments. Also discussed are the interferometric reconstruction of continuous flow fields, the flow visualization of turbine film cooling flows, the use of the phosphor technique for remote thermometry in a combustor, pulsed laser cinematography of deflagration, and a digital image sequence analysis for optical flow computation in flame propagation visualization

  14. Radiative forcing by aerosols as derived from the AeroCom present-day and pre-industrial simulations

    Directory of Open Access Journals (Sweden)

    M. Schulz

    2006-01-01

    Full Text Available Nine different global models with detailed aerosol modules have independently produced instantaneous direct radiative forcing due to anthropogenic aerosols. The anthropogenic impact is derived from the difference of two model simulations with prescribed aerosol emissions, one for present-day and one for pre-industrial conditions. The difference in the solar energy budget at the top of the atmosphere (ToA yields a new harmonized estimate for the aerosol direct radiative forcing (RF under all-sky conditions. On a global annual basis RF is −0.22 Wm−2, ranging from +0.04 to −0.41 Wm−2, with a standard deviation of ±0.16 Wm−2. Anthropogenic nitrate and dust are not included in this estimate. No model shows a significant positive all-sky RF. The corresponding clear-sky RF is −0.68 Wm−2. The cloud-sky RF was derived based on all-sky and clear-sky RF and modelled cloud cover. It was significantly different from zero and ranged between −0.16 and +0.34 Wm−2. A sensitivity analysis shows that the total aerosol RF is influenced by considerable diversity in simulated residence times, mass extinction coefficients and most importantly forcing efficiencies (forcing per unit optical depth. The clear-sky forcing efficiency (forcing per unit optical depth has diversity comparable to that for the all-sky/ clear-sky forcing ratio. While the diversity in clear-sky forcing efficiency is impacted by factors such as aerosol absorption, size, and surface albedo, we can show that the all-sky/clear-sky forcing ratio is important because all-sky forcing estimates require proper representation of cloud fields and the correct relative altitude placement between absorbing aerosol and clouds. The analysis of the sulphate RF shows that long sulphate residence times are compensated by low mass extinction coefficients and vice versa. This is explained by more sulphate particle humidity growth and thus higher extinction in those models where short-lived sulphate is present at lower altitude and vice versa. Solar atmospheric forcing within the atmospheric column is estimated at +0.82±0.17 Wm−2. The local annual average maxima of atmospheric forcing exceed +5 Wm−2 confirming the regional character of aerosol impacts on climate. The annual average surface forcing is −1.02±0.23 Wm−2. With the current uncertainties in the modelling of the radiative forcing due to the direct aerosol effect we show here that an estimate from one model is not sufficient but a combination of several model estimates is necessary to provide a mean and to explore the uncertainty.

  15. Nonlinear Parameter-Varying AeroServoElastic Reduced Order Model for Aerostructural Sensing and Control, Phase II

    Data.gov (United States)

    National Aeronautics and Space Administration — The overall goal of the project is to develop reliable reduced order modeling technologies to automatically generate parameter-varying (PV), aeroservoelastic (ASE)...

  16. Aero-thermal optimization of in-flight electro-thermal ice protection systems in transient de-icing mode

    International Nuclear Information System (INIS)

    Pourbagian, Mahdi; Habashi, Wagdi G.

    2015-01-01

    Highlights: • We introduce an efficient methodology for the optimization of a de-icing system. • We can replace the expensive CHT simulation by ROM without loosing much accuracy. • We propose different criteria affecting the energy usage and aerodynamic performance. • These criteria can significantly improve the performance of the de-icing system. - Abstract: Even if electro-thermal ice protection systems (IPS) consume less energy when operating in de-icing mode than in anti-icing mode, they still need to be optimized for energy usage. The optimization, however, should also take into account the effect of the de-icing system on the aerodynamic performance. The present work offers an optimization framework in which both thermal and aerodynamic viewpoints are taken into account in formulating various objective and constraint functions by considering the energy consumption, the thickness, the volume, the shape and the location of the accreted ice on the surface as the key parameters affecting the energy usage and the aerodynamic performance. The design variables include the power density and the activation time of the electric heating blankets. A derivative-free technique, called the mesh adaptive direct search (MADS) method, is used to carry out the optimization process, which would normally need a large number of unsteady conjugate heat transfer (CHT) calculations for the IPS simulation. To avoid such prohibitive computations, reduced-order modeling (ROM) is used to construct simplified low-dimensional CHT models. The approach is illustrated through several test cases, in which different combinations of objective and constraint functions, design variables and cycling sequence patterns are examined. In these test cases, the energy consumption is significantly reduced compared to the experiments by improving the spatial and temporal distribution of the thermal energy usage. The results show the benefits of the approach in bringing energy, safety and aerodynamic considerations together in designing de-icing systems

  17. Nonlinear Parameter-Varying AeroServoElastic Reduced Order Model for Aerostructural Sensing and Control, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — The overall goal of the project is to develop reliable reduced order modeling technologies to automatically generate nonlinear, parameter-varying (PV),...

  18. The influence of fully nonlinear wave forces on aero-hydro-elastic calculations of monopile wind turbines

    DEFF Research Database (Denmark)

    Schløer, Signe; Bredmose, Henrik; Bingham, Harry B.

    2016-01-01

    The response of an offshore wind turbine tower and its monopile foundation has been investigated when exposed to linear and fully nonlinear irregular waves on four different water depths. The investigation focuses on the consequences of including full nonlinearity in the wave kinematics. The line...

  19. Intercomparison and evaluation of global aerosol microphysical properties among AeroCom models of a range of complexity

    Directory of Open Access Journals (Sweden)

    G. W. Mann

    2014-05-01

    Full Text Available Many of the next generation of global climate models will include aerosol schemes which explicitly simulate the microphysical processes that determine the particle size distribution. These models enable aerosol optical properties and cloud condensation nuclei (CCN concentrations to be determined by fundamental aerosol processes, which should lead to a more physically based simulation of aerosol direct and indirect radiative forcings. This study examines the global variation in particle size distribution simulated by 12 global aerosol microphysics models to quantify model diversity and to identify any common biases against observations. Evaluation against size distribution measurements from a new European network of aerosol supersites shows that the mean model agrees quite well with the observations at many sites on the annual mean, but there are some seasonal biases common to many sites. In particular, at many of these European sites, the accumulation mode number concentration is biased low during winter and Aitken mode concentrations tend to be overestimated in winter and underestimated in summer. At high northern latitudes, the models strongly underpredict Aitken and accumulation particle concentrations compared to the measurements, consistent with previous studies that have highlighted the poor performance of global aerosol models in the Arctic. In the marine boundary layer, the models capture the observed meridional variation in the size distribution, which is dominated by the Aitken mode at high latitudes, with an increasing concentration of accumulation particles with decreasing latitude. Considering vertical profiles, the models reproduce the observed peak in total particle concentrations in the upper troposphere due to new particle formation, although modelled peak concentrations tend to be biased high over Europe. Overall, the multi-model-mean data set simulates the global variation of the particle size distribution with a good degree of skill, suggesting that most of the individual global aerosol microphysics models are performing well, although the large model diversity indicates that some models are in poor agreement with the observations. Further work is required to better constrain size-resolved primary and secondary particle number sources, and an improved understanding of nucleation and growth (e.g. the role of nitrate and secondary organics will improve the fidelity of simulated particle size distributions.

  20. HAWC2 and BeamDyn: Comparison Between Beam Structural Models for Aero-Servo-Elastic Frameworks

    DEFF Research Database (Denmark)

    Pavese, Christian; Wang, Qi; Kim, Taeseong

    2015-01-01

    approaches to model the structural behaviour of modern wind turbine blades in operation. Through a series of benchmarking structural cases of increasing complexity, the capability of the two codes to simulate highly nonlinear effects is investigated and analyzed. Results show that even though...... the geometrically exact beam theory can better model effects such as very large deflections, rotations, and structural couplings, an approach based on a multi-body formulation assembled through linear elements is capable of computing accurate solutions for typical nonlinear beam theory benchmarking cases....

  1. Effect of the Infectious Bursal Disease Vaccine on the Aero-Anaerobic Enteric Bacterial Flora of Chickens

    Directory of Open Access Journals (Sweden)

    F. A. Kembi

    2001-03-01

    Full Text Available The enteric bacterial flora of birds was examined after vaccination with the infectious bursal disease (IBD vaccine via the ocular and oral routes. Throughout the test period, the bacterial loads were higher in the test groups than in the control (p < 0.05. However, significant differences between the two test groups only occurred in the first three weeks postvaccination. The bacteria isolates included Salmonella sp., Edwardsiella sp., Escherichia sp. and Klebsiella sp. in the test and control groups.

  2. An Investigation into the Comparative Costs of Additive Manufacture vs. Machine from Solid for Aero Engine Parts

    Science.gov (United States)

    2006-05-01

    welding power sources are not totally efficient at converting power drawn from the wall into heat energy used for the welding process . TIG sources are...Powder bed + Laser • Wire + Laser • Wire + Electron Beam • Wire + TIG Each system has its own unique attributes in terms of process variables...relative economics of producing a near net shape by Additive Manufacturing (AM) processes compared with traditional machine from solid processes (MFS

  3. Ultra High Temperature and Multifunctional Ceramic Matrix Composite – Coating Systems for Light-Weight Space and Aero Systems

    Data.gov (United States)

    National Aeronautics and Space Administration — Revolutionary ultra-high temperature, high mechanical loading capable, oxidation resistant, durable ceramic coatings and light-weight fiber-reinforced Ceramic Matrix...

  4. Intercomparison and Evaluation of Aerosol Microphysical Properties among AeroCom Global Models of a Range of Complexity

    Czech Academy of Sciences Publication Activity Database

    Mann, G.W.; Carslaw, K.S.; Reddington, C.L.; Pringle, K.J.; Schulz, M.; Asmi, A.; Spracklen, D.V.; Ridley, D.A.; Woodhouse, M.T.; Lee, L.A.; Zhang, K.; Ghan, S.H.; Easter, R.C.; Liu, X.; Stier, P.; Lee, Y.H.; Adams, P.J.; Tost, H.; Lelieveld, J.; Bauer, S.E.; Tsigaridis, K.; van Noije, T.P.C.; Strunk, A.; Vignati, E.; Bellouin, N.; Dalvi, M.; Johnson, C.E.; Bergman, T.; Kokkola, H.; von Salzen, K.; Yu, F.; Luo, G.; Petzold, A.; Heintzenberger, J.; Clarke, A.; Ogren, J.A.; Gras, J.; Baltensperger, U.; Kaminski, U.; Jennings, S.G.; O'Dowd, C.D.; Harrison, R. M.; Beddows, D.C.S.; Kulmala, M.; Viisanen, Y.; Ulevicius, V.; Mihalopoulos, N.; Ždímal, Vladimír; Fiebich, M.; Hansson, H.-C.; Swietlicki, E.; Henzig, J.S.

    2014-01-01

    Roč. 14, č. 9 (2014), s. 4679-4713 ISSN 1680-7316 Institutional support: RVO:67985858 Keywords : global climate models * aerosol processes * particle size distributions Subject RIV: CF - Physical ; Theoretical Chemistry Impact factor: 5.053, year: 2014

  5. Solid Oxide Fuel Cell/Turbine Hybrid Power System for Advanced Aero-propulsion and Power, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — Solid oxide fuel cell (SOFC)/ gas turbine hybrid power systems (HPSs) have been recognized by federal agencies and other entities as having the potential to operate...

  6. Human or natural forcing in the geo morphological process in Pocitos and Ramirez beaches. 80 years of aero photographic records

    International Nuclear Information System (INIS)

    Gutierrez, O.; Panario, D.

    2012-01-01

    This work is about the Ramirez and Pocitos sand-beaches evolution (Montevideo), in order to know their tendencies and the natural or anthropogenic forcing s. For this analysis were used multi temporal remote sensing, GIS (sand cycle) and historical background techniques. The data were processed by statistics, various shoreline proxy records as well as the correlations with climatic variables (precipitation, wind patterns) and Parana and Uruguay rivers flooding

  7. A Potential Treatment for Post-Flight Orthostatic Intolerance in Aero-Space Crews: Autogenic-Feedback Training

    Science.gov (United States)

    Cowings, P. S.; Toscano, W. B.; Miller, N. E.; Pickering, T. G.; Shapiro, D.

    1994-01-01

    Postflight orthostatic intolerance has been identified as a serious biomedical problem associated with long duration exposure to microgravity in space. High priority has been given to the development of countermeasures for this disorder which are both effective and practical. A considerable body of clinical research has demonstrated that people can be taught to increase their own blood pressure voluntarily and that this is an effective treatment for chronic Orthostatic intolerance in paralyzed patients. The present pilot study was designed to examine the feasibility of adding training in control of blood pressure to an existing preflight training program designed to facilitate astronaut adaptation to microgravity. Using in operant conditioning procedure, Autogenic-Feedback Training (AFT), three men and two women participated in four to nine (15-30 training sessions). At the end of training ranged between 20 and 50 mm Hg under both supine and 450 head-up tilt conditions. These findings suggest that AFT may be a useful alternative treatment or supplement to existing approaches for preventing postflight Orthostatic intolerance. Further, the use of operant conditioning methods for training cardiovascular responses may contribute to the general understanding of the mechanisms of orthostatic intolerance.

  8. Aero-acoustic simulation of a subsonic hot jet; Simulation aeroacoustique d'un jet chaud subsonique

    Energy Technology Data Exchange (ETDEWEB)

    Biancherin, A.; Rahier, G.; Prieur, J.; Vuillot, F.; Lupoglazoff, N.

    2002-07-01

    This paper presents a numerical simulation of subsonic a hot jet (M 0,7) and its acoustic analysis. The MSD code of the ONERA is used to resolve the Navier-Stokes equations. A detailed study, parametric and theoretical is realized to analyze the influence of the formulation, the position, the part and the nature of the control surface on the acoustic calculation results. The acoustic predictions in far field are compared to measures realized by the ONERA in the anechoic CEPRA 19 wind tunnel. (A.L.B.)

  9. Yip - Development and Application of a High-Speed Three-Dimensional Density Measurement Technique for Aero-Optic Applications

    Science.gov (United States)

    2011-03-25

    APPLICATIONS AFOSR Grant Number: FA9550-08-1-0150 Submitted to: Dr. Douglas R. Smith Civ USAF AFMC AFOSR/ RSA Flow Interactions & Control, Program...starting with a 768 X 768 sized random matrix. 5 10 15 20 25 30 35 40 -15 -10 -5 0 5 10 15 0 0.5 1 1.5 2 2.5 3 3.5 x 10 -6 80 Figure 66

  10. Aero-Optical Wavefront Propagation and Refractive Fluid Interfaces in Large-Reynolds-Number Compressible Turbulent Flows

    National Research Council Canada - National Science Library

    Catrakis, Haris J; Jefferies, Rhett

    2005-01-01

    ... of the refractive field and interfaces. Direct, non-intrusive, and non-integrated imaging of the refractive index field in purely gaseous flows is achieved using laser induced fluorescence of acetone vapor molecularly premixed in air...

  11. Effect of external jet-flow deflector geometry on OTW aero-acoustic characteristics. [Over-The-Wing

    Science.gov (United States)

    Von Glahn, U.; Groesbeck, D.

    1976-01-01

    The effect of geometry variations in the design of external deflectors for use with OTW configurations was studied at model scale and subsonic jet velocities. Included in the variations were deflector size and angle as well as wing size and flap setting. A conical nozzle (5.2-cm diameter) mounted at 0.1 chord above and downstream of the wing leading edges was used. The data indicate that external deflectors provide satisfactory take-off and approach aerodynamic performance and acoustic characteristics for OTW configurations. These characteristics together with expected good cruise aerodynamics, since external deflectors are storable, may provide optimum OTW design configurations.

  12. NASA 20th Century Explorer . . . Into the Sea of Space. A Guide to Careers in Aero-Space Technology.

    Science.gov (United States)

    National Aeronautics and Space Administration, Washington, DC.

    This pamphlet lists career opportunities in aerospace technology announced by the Boards of the U. S. Civil Service for the National Aeronautics and Space Administration (NASA). Information given includes (1) the work of the NASA, (2) technical and administrative specialties in aerospace technology, (3) educational and experience requirements, and…

  13. A Preliminary Study Associated with the Experimental Measurement of the Aero-Optic Characteristics of Hypersonic Configurations

    Science.gov (United States)

    1992-06-01

    and Neubauer , R.A., "Experimental Studies of Pulsed Microwave Breakdown Effects in a Hypersonic Air Plasma," Calspan Report No. AA-2053-Y-2, AFCRL...perhaps 100 jim intervals. For example 16 images will be exposed on 128 x 128 pixels sectors of a 512 x 512 pixel CCD camera , all during a 3.2 ms period of...device uses a laser and CCD camera . Acoustic-optic beam deflectors will scan the LOS during the short duration test, allowing image exposure durations

  14. Numerical simulations of separated flows at moderate Reynolds numbers appropriate for turbine blades and unmanned aero vehicles

    International Nuclear Information System (INIS)

    Castiglioni, G.; Domaradzki, J.A.; Pasquariello, V.; Hickel, S.; Grilli, M.

    2014-01-01

    Highlights: • The present study evaluate LES techniques and IB method to simulate separated flows. • Simulations have been performed with an IB code and a commercial code. • The benchmark flow is a laminar separation bubble around an airfoil. • It is concluded that IB methods are appropriate only for high resolution DNS and LES. • High fidelity LES with 1% of DNS resolution can be performed. - Abstract: Flows over airfoils and blades in rotating machinery, for unmanned and micro-aerial vehicles, wind turbines, and propellers consist of a laminar boundary layer near the leading edge that is often followed by a laminar separation bubble and transition to turbulence further downstream. Typical RANS turbulence models are inadequate for such flows. Direct numerical simulation (DNS) is the most reliable, but is also the most computationally expensive alternative. This work assesses the capability of Immersed Boundary (IB) methods and Large Eddy Simulations (LES) to reduce the computational requirements for such flows and still provide high quality results. Two-dimensional and three-dimensional simulations of a laminar separation bubble on a NACA-0012 airfoil at Re c =5×10 4 at 5° of incidence have been performed with an IB code and a commercial code using body fitted grids. Several Subgrid Scale (SGS) models have been implemented in both codes and their performance evaluated. For the two-dimensional simulations with the IB method the results show good agreement with DNS benchmark data for the pressure coefficient C p and the friction coefficient C f but only when using dissipative numerical schemes. There is evidence that this behavior can be attributed to the ability of dissipative schemes to damp numerical noise coming from the IB. For the three-dimensional simulations the results show a good prediction of the separation point, but inaccurate prediction of the reattachment point unless full DNS resolution is used. The commercial code shows good agreement with the DNS benchmark data in both two and three-dimensional simulations, but the presence of significant, unquantified numerical dissipation prevents a conclusive assessment of the actual prediction capabilities of very coarse LES with low order schemes in general case

  15. 75 FR 50850 - Special Conditions: AeroMech, Incorporated; Hawker Beechcraft Corporation, Model B200 and Other...

    Science.gov (United States)

    2010-08-18

    ... heat the battery can generate during a short circuit of the battery or of its individual cells. (7) Li... inspection requirements to visually check for a battery and/or charger degradation. (vi) The ICA must contain... Lithium Ion Battery AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final special conditions...

  16. 75 FR 33553 - Special Conditions: AeroMech, Incorporated; Hawker Beechcraft Corporation, Model B200 and Other...

    Science.gov (United States)

    2010-06-14

    ... circuit of the battery or of its individual cells. (7) Li-ion battery installations must have-- (i) A... charger degradation. (10) Batteries in a rotating stock (spares) that have experienced degraded charge... Battery AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed special conditions...

  17. Aero thermal test results obtained on the n. C 5 EL 4 Cluster in the atmospheric pressure cell

    International Nuclear Information System (INIS)

    Gasc, B.

    1964-01-01

    In the framework of thermal studies on the EL-4 cluster, the full-scale tests at atmospheric pressure are designed to permit measurement of local values of the wall temperature, of the velocity and of the temperature in the fluid. The experimental results, obtained with the help of an original measuring apparatus, make it possible to follow the changes in these values along the cluster and to predict in much detail the in-pile thermal behaviour. In particular it is shown that changes in the wall temperature along the cluster are greatly influenced by disruption of the flow caused by grids and supports. (author) [fr

  18. A parametric study on supersonic/hypersonic flutter behavior of aero-thermo-elastic geometrically imperfect curved skin panel

    NARCIS (Netherlands)

    Abbas, L.K.; Rui, X.; Marzocca, P.; Abdalla, M.; De Breuker, R.

    2011-01-01

    In this paper, the effect of the system parameters on the flutter of a curved skin panel forced by a supersonic/hypersonic unsteady flow is numerically investigated. The aeroelastic model investigated includes the third-order piston theory aerodynamics for modeling the flow-induced forces and the

  19. Aircraft propulsion and gas turbine engines

    National Research Council Canada - National Science Library

    El-Sayed, Ahmed F

    2008-01-01

    ... . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . xvii xxxi xxxiii xxxv Part I Aero Engines and Gas Turbines . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . C...

  20. 75 FR 6860 - Airworthiness Directives; International Aero Engines AG (IAE) V2500-A1, V2522-A5, V2524-A5, V2525...

    Science.gov (United States)

    2010-02-12

    ... concerning this proposed AD. Using the search function of the Web site, anyone can find and read the comments... engine, combined with engine operation in high temperature and high humidity environments, led to... stage 9 to 12 drum. The depletion of the silver plating led to deposits of silver chloride on the HPC...

  1. Linking the optically monitored channel evolution with tremor like seismic activity during aero-fracturing in a very fine granular medium

    Science.gov (United States)

    Turkaya, Semih; Toussaint, Renaud; Kvalheim Eriksen, Fredrik; Zecevic, Megan; Daniel, Guillaume

    2014-05-01

    The characterization and comprehension of rock deformation processes due to fluid flow is a challenging problem with numerous applications in many fields. This phenomenon has received an ever-increasing attention in Earth Science, Physics, with many applications in natural hazard understanding, mitigation or forecast (e.g. earthquakes, landslides with hydrological control,volcanic eruptions), or in the industry, as CO2 sequestration. Even though the fluids and rocks are relatively easier to understand individually, the coupled behaviour of porous media with a dynamic fluid flow makes the system difficult to comprehend. The dynamic interaction between flow and the porous media, rapid changes in the local porosity due to the compaction and migration of the porous material, fracturing due to the momentum exchange in fast flow, make understanding of such a complex system a challenge. In this study, analogue models are developed to predict and control the mechanical stability of rock and soil formations during the injection or extraction of fluids. The models are constructed and calibrated based on the experimental data acquired. This experimental data obtained from solid-fluid interaction are monitored using a combination of techniques, both from geophysics and from experimental fluid mechanics. The experimental setup consists of a rectangular Hele-Shaw cell with three closed boundaries and one semi-permeable boundary which enables the flow of the fluid but not the solid particles. Non expanding polystyrene beads around 80μm size are used as solid particles and air is used as the intruding fluid. During the experiments, the fluid is injected steadily (or injected and suddenly stopped to see the pushback in a setup with four impermeable boundaries) into the system from the point opposite to the semi-permeable boundary so that the fluid penetrates into the solid and makes a way via creating channels, fractures or directly using the pore network to the semi-permeable boundary. The acoustic signals emitted during the mentioned solid-fluid interactions are recorded by various sensors - i.e. Piezoelectric Shock Accelerometer (Freq. range: 1Hz - 26kHz) and Piezoelectrical Sensors (Freq. range: 100kHz - 1MHz) with a sampling rate of 1MHz - on the Hele-Shaw cell. After the experiment, those signals are compared and investigated further in both time and frequency domains. Moreover, by using different techniques localization of the acoustic emissions are done and compared. Furthermore, during the experiments pictures of the Hele-Shaw cell are taken using a high speed camera. Thus, it is possible to visualize the solid-fluid interaction and to process images to gather information about the mechanical properties of the solid partition. The link between the visual and the mechanical wave signals is investigated. The spectrum of the signal is observed to be strongly affected by the size and shape of deforming channels created during the process. The power of the recorded signal is related to the integrated deformation rate in the process. Fast avalanches and rearrangements of grains at small scales are related to high frequency (above 10 kHz) acoustic emissions.

  2. Diagnostic accuracy of indirect laryngoscopy and x-ray neck in the diagnosis of fish bone impaction in upper aero digestive tract

    International Nuclear Information System (INIS)

    Kundi, N.; Mehmood, T.

    2015-01-01

    This study was aimed at finding the validity of indirect laryngoscopy (IDL) and neck X-Rays in the diagnosis of fish bone impaction. Study Design: Validation study. Place and Duration of Study: CMH Nowshera from August 2012 to February 2013. Material and Methods: A total of 50 patients were selected by consecutive sampling presenting with history of fishbone impaction in aerodigestive tract. IDL examination and neck X-rays were performed and findings were recorded. Those with no fishbone on both the investigations were discharged from hospital with follow up after 03 days. Those with fishbone detected on either of investigations underwent removal. Fishbone easily approachable were removed under local anaesthesia with foreceps and in others Endoscopy (Direct laryngoscopy or Oesophagoscopy) was performed under General Anaesthesia. Sensitivities and specificities of both the modalities were calculated using standard 2/2 Table. ROC curve analysis was carried out and significance level p < 0.05 was taken as significant. Results: In 20 patients no fishbone was found, 26 patients were diagnosed on IDL and in 04 patients fishbone was detected by neck X-Rays. Most common site for fishbone impaction was pharyngeal tonsil. In 22 patients fishbone was removed with foreceps and in 08 patients endoscopy was performed. Diagnostic accuracy for IDL 86% and Neck X-Rays 48% was calculated. ROC curve analysis revealed AUC for IDL 0.933 and Significance level (P) as <0.0001. ROC curve analysis for X-ray gives AUC of 0.567 and Significance level (p) 0.4132. Conclusion: IDL shows higher diagnostic accuracy than neck X-Rays for detection of fishbone in upper aerodigestive tract. Neck X-rays are more useful for impacted foreign bodies in oesophagus. (author)

  3. Aero-acoustic design and test of a multiple splitter exhaust noise suppressor for a 0.914m diameter lift fan

    Science.gov (United States)

    Stimpert, D. L.

    1973-01-01

    A lift fan exhaust suppression system to meet future VTOL aircraft noise goals was designed and tested. The test vehicle was a 1.3 pressure ratio, 36 inch (91.44 cm) diameter lift fan with two chord rotor to stator spacing. A two splitter fan exhaust suppression system thirty inches (76.2 cm) long achieved 10 PNdB exhaust suppression in the aft quadrant compared to a design value of 20 PNdB. It was found that a broadband noise floor limited the realizable suppression. An analytical investigation of broadband noise generated by flow over the treatment surfaces provided very good agreement with the measured suppression levels and noise floor sound power levels. A fan thrust decrement of 22% was measured for the fully suppressed configuration of which 11.1% was attributed to the exhaust suppression hardware.

  4. Validation of an Aero-Acoustic Wind Turbine Noise Model Using Advanced Noise Source Measurements of a 500kW Turbine

    DEFF Research Database (Denmark)

    Bertagnolio, Franck; Aagaard Madsen, Helge; Fischer, Andreas

    2016-01-01

    rotor noise model is presented. It includes the main sources of aeroacoustic noise from wind turbines: turbulent inflow, trailing edge and stall noise. The noise measured by one microphone located directly downstream of the wind turbine is compared to the model predictions at the microphone location....... A good qualitative agreement is found. When wind speed increases, the rotor noise model shows that at high frequencies the stall noise becomes dominant. It also shows that turbulent inflow noise is dominant at low frequencies for all wind speeds and that trailing edge noise is dominant at low wind speeds...

  5. 75 FR 71373 - Airworthiness Directives; International Aero Engines V2500-A1, V2522-A5, V2524-A5, V2525-D5...

    Science.gov (United States)

    2010-11-23

    ...] borescope inspections of high-pressure turbine (HPT) stage 1 blade outer air seal segments for evidence of... evidence of distress. This proposed AD would also require incorporation of improved design stage 1 blade... Compliance Criteria Stage 1 blade Stage 1 blade outer air seal outer air seal Exhaust gas segments hours...

  6. Unsteady Reynolds-averaged Navier-Stokes simulations of inlet distortion in the fan system of a gas-turbine aero-engine

    Science.gov (United States)

    Spotts, Nathan

    As modern trends in commercial aircraft design move toward high-bypass-ratio fan systems of increasing diameter with shorter, nonaxisymmetric nacelle geometries, inlet distortion is becoming common in all operating regimes. The distortion may induce aerodynamic instabilities within the fan system, leading to catastrophic damage to fan blades, should the surge margin be exceeded. Even in the absence of system instability, the heterogeneity of the flow affects aerodynamic performance significantly. Therefore, an understanding of fan-distortion interaction is critical to aircraft engine system design. This thesis research elucidates the complex fluid dynamics and fan-distortion interaction by means of computational fluid dynamics (CFD) modeling of a complete engine fan system; including rotor, stator, spinner, nacelle and nozzle; under conditions typical of those encountered by commercial aircraft. The CFD simulations, based on a Reynolds-averaged Navier-Stokes (RANS) approach, were unsteady, three-dimensional, and of a full-annulus geometry. A thorough, systematic validation has been performed for configurations from a single passage of a rotor to a full-annulus system by comparing the predicted flow characteristics and aerodynamic performance to those found in literature. The original contributions of this research include the integration of a complete engine fan system, based on the NASA rotor 67 transonic stage and representative of the propulsion systems in commercial aircraft, and a benchmark case for unsteady RANS simulations of distorted flow in such a geometry under realistic operating conditions. This study is unique in that the complex flow dynamics, resulting from fan-distortion interaction, were illustrated in a practical geometry under realistic operating conditions. For example, the compressive stage is shown to influence upstream static pressure distributions and thus suppress separation of flow on the nacelle. Knowledge of such flow physics is valuable for engine system design.

  7. Stage-by-Stage and Parallel Flow Path Compressor Modeling for a Variable Cycle Engine, NASA Advanced Air Vehicles Program - Commercial Supersonic Technology Project - AeroServoElasticity

    Science.gov (United States)

    Kopasakis, George; Connolly, Joseph W.; Cheng, Larry

    2015-01-01

    This paper covers the development of stage-by-stage and parallel flow path compressor modeling approaches for a Variable Cycle Engine. The stage-by-stage compressor modeling approach is an extension of a technique for lumped volume dynamics and performance characteristic modeling. It was developed to improve the accuracy of axial compressor dynamics over lumped volume dynamics modeling. The stage-by-stage compressor model presented here is formulated into a parallel flow path model that includes both axial and rotational dynamics. This is done to enable the study of compressor and propulsion system dynamic performance under flow distortion conditions. The approaches utilized here are generic and should be applicable for the modeling of any axial flow compressor design accurate time domain simulations. The objective of this work is as follows. Given the parameters describing the conditions of atmospheric disturbances, and utilizing the derived formulations, directly compute the transfer function poles and zeros describing these disturbances for acoustic velocity, temperature, pressure, and density. Time domain simulations of representative atmospheric turbulence can then be developed by utilizing these computed transfer functions together with the disturbance frequencies of interest.

  8. Advanced Instrumentation for Aero Engine Components: Conference Proceedings of the Propulsion and Energetics Panel Symposium (67th) Held in Philadelphia, Pennsylvania on 19-23 May 1986.

    Science.gov (United States)

    1986-11-01

    8217 un melange do 1 % do DOP dana 1 acool doitudonner uno granulom ~trie plus fine do 0,2 &’m peu diaporshe. Leo ptntes dos courbos u fr x) au travers d’ un...Figu-e 3). Thermal SAPPHIREO CAt IBERS radiation is collected directly from the PTICl F pyrotechnic and guided to a set of calcium fluoride lenses. The...station- naires. Cat article pr6mante donc lea mnoe itudi~s at r~aliS 4 a Par ILONERA (essats soufflerie) at La SNECMA (esas aur machines A 106chelle

  9. Suitability aero-geophysical methods for generating conceptual soil maps and their use in the modeling of process-related susceptibility maps

    Science.gov (United States)

    Tilch, Nils; Römer, Alexander; Jochum, Birgit; Schattauer, Ingrid

    2014-05-01

    In the past years, several times large-scale disasters occurred in Austria, which were characterized not only by flooding, but also by numerous shallow landslides and debris flows. Therefore, for the purpose of risk prevention, national and regional authorities also require more objective and realistic maps with information about spatially variable susceptibility of the geosphere for hazard-relevant gravitational mass movements. There are many and various proven methods and models (e.g. neural networks, logistic regression, heuristic methods) available to create such process-related (e.g. flat gravitational mass movements in soil) suszeptibility maps. But numerous national and international studies show a dependence of the suitability of a method on the quality of process data and parameter maps (f.e. Tilch & Schwarz 2011, Schwarz & Tilch 2011). In this case, it is important that also maps with detailed and process-oriented information on the process-relevant geosphere will be considered. One major disadvantage is that only occasionally area-wide process-relevant information exists. Similarly, in Austria often only soil maps for treeless areas are available. However, in almost all previous studies, randomly existing geological and geotechnical maps were used, which often have been specially adapted to the issues and objectives. This is one reason why very often conceptual soil maps must be derived from geological maps with only hard rock information, which often have a rather low quality. Based on these maps, for example, adjacent areas of different geological composition and process-relevant physical properties are razor sharp delineated, which in nature appears quite rarly. In order to obtain more realistic information about the spatial variability of the process-relevant geosphere (soil cover) and its physical properties, aerogeophysical measurements (electromagnetic, radiometric), carried out by helicopter, from different regions of Austria were interpreted. Previous studies show that, especially with radiometric measurements, the two-dimensional spatial variability of the nature of the process-relevant soil, close to the surface can be determined. In addition, the electromagnetic measurements are more important to obtain three-dimensional information of the deeper geological conditions and to improve the area-specific geological knowledge and understanding. The validation of these measurements is done with terrestrial geoelectrical measurements. So both aspects, radiometric and electromagnetic measurements, are important and subsequently, interpretation of the geophysical results can be used as the parameter maps in the modeling of more realistic susceptibility maps with respect to various processes. Within this presentation, results of geophysical measurements, the outcome and the derived parameter maps, as well as first process-oriented susceptibility maps in terms of gravitational soil mass movements will be presented. As an example results which were obtained with a heuristic method in an area in Vorarlberg (Western Austria) will be shown. References: Schwarz, L. & Tilch, N. (2011): Why are good process data so important for the modelling of landslide susceptibility maps?- EGU-Postersession "Landslide hazard and risk assessment, and landslide management" (NH 3.6), Vienna. [http://www.geologie.ac.at/fileadmin/user_upload/dokumente/pdf/poster/poster_2011_egu_schwarz_tilch_1.pdf] Tilch, N. & Schwarz, L. (2011): Spatial and scale-dependent variability in data quality and their influence on susceptibility maps for gravitational mass movements in soil, modelled by heuristic method.- EGU-Postersession "Landslide hazard and risk assessment, and landslide management" (NH 3.6); Vienna. [http://www.geologie.ac.at/fileadmin/user_upload/dokumente/pdf/poster/poster_2011_egu_tilch_schwarz.pdf

  10. Evaluation of the Effect of Spar Cap Fiber Angle of Bending-Torsion Coupled Blades on the Aero-Structural Performance of Wind Turbines

    DEFF Research Database (Denmark)

    Sener, Ozgun; Farsadi, Touraj; Gozc, M. Ozan

    2018-01-01

    with the fatigue load mitigation in the whole wind turbine system, tower clearances, peak stresses in the blades, and power generation of wind turbines. For this purpose, a full E-glass/epoxy reference blade has been designed, following the inverse design methodology for a 5-MW wind turbine. An E-glass/epoxy blade...... with IBTC, and besides the fiber orientation angle, sectional properties of hybrid blades must be adjusted accordingly using proper number of carbon/epoxy layers in the sections of the blade with IBTC, in order to simultaneously reduce generator power losses and the FEL....

  11. Merenje prelaznih opterećenja na dva modela u aero tunelu t-38 / Measurement of transient loads on two models

    Directory of Open Access Journals (Sweden)

    Aleksandar Vitić

    2008-07-01

    Full Text Available Pri ispitivanju modela u "rafalnom" aerotunelu sa prekidnim dejstvom T-38, na Mahovim brojevima većim od 2, moraju se uzeti u obzir prelazne pojave koje se javljaju na početku i na kraju rada aerotunela. To su stanja kada su model i aerovaga izloženi velikim aerodinamičkim silama i momentima. Ova kombinovana opterećenja mogu oštetiti modele i aerovage, pa bi bilo potrebno unapred znati kolike se vrednosti očekuju za pojedine konfiguracije modela, kako bi se izvršio pravilan izbor aerovage i odgovarajućih materijala za izradu modela. U tu svrhu postoje dijagrami koji pružaju mogućnost procene ovih opterećenja. Dijagrami su dobijeni na osnovu ispitivanja nekoliko različitih modela na Mahovim brojevima većim od 2. U radu su prikazana merenja prelaznih opterećenja na još dva modela, a rezultati su upoređeni sa već postojećim dijagramima. / The T-38 wind tunnel is a blow down, intermittent-run type of wind tunnels. During model testing in the this type of wind tunnels, at Mach numbers higher than 2, transient loads which appear during the starting and stopping of the wind tunnel runs must be taken into consideration. These are the conditions when a model and the wind tunnel balance are exposed to large aerodynamic forces and moments. These combined loads can damage models and wind tunnel balances, and, for this reason, it is very important to determine them in advance for any particular model configuration so that an appropriate wind tunnel balance and materials for model manufacturing can be chosen. For that purpose there are graphs which give possibilities to estimate these loads. The graphs are based on experiments with a number of different models at Mach numbers higher than 2. This paper gives the measurements of transient loads on two more models and the results are compared with the already existing graphs.

  12. Advanced Technology for Aero Gas Turbine Components: Conference Proceedings Held at the Propulsion and Energetics Panel (69th) Symposium in Paris (France) on 4-8 May 1987

    Science.gov (United States)

    1987-09-01

    Simuitaniment, Ia forte composante tangentielle de l’coulement absolu en sortie du mobile doit Otre annulbe, ce qui corres pond A une diviation de...calculs quasi-tridimensionnpls. Le essais a froid de la turbine sur le banc et len ensais correnpondants A chaud sur le turbomoteur permettent d...0.5Re 0 e 6 .10 6 (A froid ) Rapport de la vitesse p~riph~rique sur la vitesse de jet U er/V.j = 0.69 3 - PREDIMENSIONNEMENT DE LA TURBINE RADIALE

  13. 75 FR 30268 - Airworthiness Directives; AeroSpace Technologies of Australia Pty Ltd Models N22B, N22S, and N24A...

    Science.gov (United States)

    2010-06-01

    ... cap, near the wing strut attachment. We are issuing this AD to require actions to correct the unsafe... City, Missouri 64106; telephone: (816) 329-4059; fax: (816) 329-4090; e-mail: [email protected] strut attachment. Amendment 1 adopts the manufacturer's latest service bulletin. Its new inspection...

  14. Environmental Assessment for Conversion of the Existing Aero Club Runway to Emergency Helipad for David Grant Medical Center Travis Air Force Base, Fairfield, California

    Science.gov (United States)

    2010-07-01

    FT Potential Ambystoma californiense California tiger salamander FT Known Branchinecta conservatio Conservancy fairy shrimp FE Potential Elaphrus...elderberry longhorn beetle FT Potential Branchinecta lynchi Vernal pool fairy shrimp FT Known Lepidurus packardi Vernal pool tadpole shrimp FE...Area. During 2008 vernal pool invertebrate monitoring, CTS larvae were discovered in the northeastern part of Travis AFB, in the Castle Terrace

  15. A study on the strength of leg extention and leg curl exercise measured with the "Tremax System" and the "ADR" (Aero Dynamic Resistance System)

    OpenAIRE

    安藤, 勝英

    1995-01-01

    This is a study on the nature of the extensor and flexor muscles by the leg extention and leg curl exercise. The strength of the static muscles were measured with the "Tremax system" and for the strength of the dynamic muscles the "ADR" was used. Measuring the strength of the extensor muscles at bar no.1 to 4 of the Tremax System,it comes to a maximum at bar no.2 (extention 60°) but it declines radically when approaching extention 0°. Compared to the extensor muscles, the flexor muscules show...

  16. Integrated smart bearings for next generation aero-engines Part 1: Development of a sensor suite for automatic bearing health monitoring

    OpenAIRE

    Bashir, Imran; Wang, Ling; Harvey, Terence; Zaghari, Bahareh; Weddell, Alexander; White, Neil

    2017-01-01

    The development of smart bearing solutions will contribute to increased aircraft engine reliability, allowing the early detection of bearing failure through robust health monitoring. This project aims to develop intelligent bearing systems for an Ultra High Propulsion Efficiency (UHPE) ground test demonstrator, where a fully integrated self-powered wireless sensing system will be developed for future aircraft. This paper provides a comprehensive review of the state-of-the-art smart bearing te...

  17. Application of the Aero-Hydro-Elastic Model, HAWC2-WAMIT, to Offshore Data from Floating Power Plants Hybrid Wind- and Wave-Energy Test Platform, P37

    DEFF Research Database (Denmark)

    Bellew, Sarah; Yde, Anders; Verelst, David Robert

    2014-01-01

    numerical models, which can combine the aerodynamic, hydrodynamic, structural exibility and mooring components. Very little oshore data exists, however, in order to validate these numerical models. Floating Power Plant are the developers of a oating, hybrid wind- and wave-energy device. The device uses...... the pitching wave energy devices, not only to increase and smooth the power output from the platform, but also to take the energy from the waves in a controlled manner, resulting in a stable platform for the wind turbine and a safe harbour for O&M. They are currently developing the nal design for their rst...... full-scale prototype, the P80, which has a width of 80 m. As part of the development, Floating Power Plant have completed 4 oshore test-phases (totalling over 2 years oshore operation) on a 37 m wide scaled test device, the P37. This paper focuses on the comparison of one of the leading numerical...

  18. ETUDE DES ALTERATIONS EPIGENETIQUES DANS LES CANCERS DES VOIES AERO-DIGESTIVES SUPERIEURES (VADS). IMPLICATION DANS LE DISGNOSTIC, LE SUIVI ET LE PRONOSTIC DES PATIENTS

    OpenAIRE

    Righini, Christian Adrien

    2006-01-01

    Studies in UADTs tumors biology have been performed to better understand the carcinogenesis and to find biomarkers that could have a prognostic value or an early detection benefit. In carcinogenesis of tumors of the UADTs, 2 main types of modifications have been identified at the cellular level: genetic and epigenetic alterations. Our work focused on methylation of tumor suppressor genes in tumors and saliva. Sixteen genes have thus been analyzed; we were then able to define a 6-gene methylat...

  19. Study of the processes of radionuclides transfer, heavy metals and aero-particles among the solid, dissolved phase and the air

    International Nuclear Information System (INIS)

    Romero G, E. T.; Ordonez R, E.; Reyes G, L. R.; Jose Y, M.

    2010-01-01

    In this chapter the investigations developed in the Instituto Nacional de Investigaciones Nucleares (ININ) are presented, in collaboration with specialists in diverse fields of the science. In the first place, is presented the objective and an introduction of each one of the following projects: Study of the uranium migration through the not saturated area, and Synthesis and characterization of phosphate materials by conventional techniques, projects developed under the direction and collaboration of the Ph D. Eduardo Ordonez Regil. Identification of the chemical-morphologic composition of painting mural pigments: the blue Mayan, indigo blue, the secret of the color, and investigation of the physiochemical components of the asphaltenes and malthenes of heavy crudes and vacuum residual, with the supervision of the Ph D. Miguel Jose Yacaman. Evaluation of the water quality and type of sediments of the lake-crater The Pool: one of the seven stars of Santiago Valley, Guanajuato; Study of the sorption kinetics of Cr(Vi) in floor of a container of chromium residuals in Buenavista, Guanajuato, Mexico; Investigation of the underground water hydrochemistry of the basin of the Avenues River in Pachuca de Soto, Hidalgo, and Characterization of the particle material and modeled of the dispersion and pollutants transport in the air of the Metropolitan Area of the Toluca Valley, projects carried out under the direction and collaboration of the Ph D. Lazaro Raymundo Reyes Gutierrez. Finally, is presented the most representative of the obtained results, as well as a discussion of the same ones. (Author)

  20. 75 FR 1731 - Airworthiness Directives; Sicma Aero Seat 9140, 9166, 9173, 9174, 9184, 9188, 9196, 91B7, 91B8...

    Science.gov (United States)

    2010-01-13

    ... invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed... life limit is introduced on the links. On 9g seats also affected by this problem, stronger unlimited... unlimited life limits have been developed and their installation has been rendered mandatory. However, on...

  1. Incorporation of sweep in a transonic fan design using a 3D blade-row geometry package intended for aero-structural-manufacturing optimization

    OpenAIRE

    Abdelhamid, Hazen Fahmy

    1997-01-01

    Approved for public release; distribution is unlimited A new 3D blade row geometry package was developed and implemented. In the new representation the blade is described by six Bezier surfaces two of which represent the pressure and suction surfaces with sixteen points each. The leading and trailing edges are each represented by two Bezier surfaces. Only one extra parameter is required (in addition to the pressure and suction surfaces parameters) to define each of the leading and trailing...

  2. Experimental Characterization of the Structural Dynamics and Aero-Structural Sensitivity of a Hawkmoth Wing Toward the Development of Design Rules for Flapping-Wing Micro Air Vehicles

    Science.gov (United States)

    2013-03-01

    complexity. As any undergraduate biology textbook will attest, animal morphology is a product of competing demands for survival of the species......sample of paper used in the paper beam, clamp validation study. The test determined a Modulus of Elasticity , E, of approximately 3 GPa

  3. Solar photovoltaic research and development program of the Air Force Aero Propulsion Laboratory. [silicon solar cell applicable to satellite power systems

    Science.gov (United States)

    Wise, J.

    1979-01-01

    Progress is reported in the following areas: laser weapon effects, solar silicon solar cell concepts, and high voltage hardened, high power system technology. Emphasis is placed on solar cells with increased energy conversion efficiency and radiation resistance characteristics for application to satellite power systems.

  4. Development of aero-space structural Ni3Al-based alloys for service at temperature above 1000 oC in air without protection coating

    International Nuclear Information System (INIS)

    Kablov, E.N.; Buntushkin, V.P.; Povarova, K.B.; Kasanskaya, N.K.

    2001-01-01

    The principles of alloying are developed for alloys based on the γ' phase Ni 3 Al and realized for the design of a high-temperature alloy VKNA-1V destined for a wide range of 'hot' GTE articles (e.g., flaps, nozzle vanes, turbine rotor blades, elements of flame tubes, and other complex thin-wall articles) produced by vacuum investment casting. Owing to a fortunate combination of the selected boron-free alloying system (Ni-AI-Cr-W-Mo-Zr-C), the presence of a ductile structure constituent such as nickel-based γ solid solution (∼10 wt%) and directed columnar or single crystal structure the alloy is characterized by high ductility at room (El=14-35 %), middle and high temperatures (El=18-31 % at 673-1473 K), by a melting temperature (solidus) as high as T m = 1613 K, a density of at most 7930 kg /m 3 , high short term and long term strength at temperatures 1273-1573 K (σ 100 =110 MPa at 1373 K). Alloy has a high oxidation resistance at temperatures up to 1573 K and is resistant to stress corrosion and general atmospheric corrosion. New VKNA-1V Ni 3 Al-based alloy with equiaxed grained, directional solidification (DS), or single crystal structures can be produced by conventional cast processes used for investment casting of nickel superalloys, including the process of high-gradient DS. Compared to nickel analogs, the alloy is relatively cheap and do not need in protective coating up to 1573 K in air. (author)

  5. Vacuum Plasma Spray Formed High Transition Temperature Shape Memory Alloys, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — Smart materials control of aero-surfaces based on shape memory alloys (SMA) is seeing increased use for improving of future subsonic fixed wing aircraft aero-surface...

  6. Soome vajab kõrgete hindade ja madalate palkadega Eestit / Tõnis Erilaid

    Index Scriptorium Estoniae

    Erilaid, Tõnis, 1943-

    2001-01-01

    Soome valitsus saatis Brüsselisse kirja, milles paneb ette tõsta Euroopa Liidus alkoholi ja tubakasaaduste miinimumaktsiisi. Finnair annab siseriiklikud liinid üle tütarfirmale Aero Airlines, mille enamusaktsiad kuuluvad Eestis registreeritud Aero Holdingule

  7. Soomlaste Finnair sulges eile oma Eesti lennufirma / Lauri Linnamäe

    Index Scriptorium Estoniae

    Linnamäe, Lauri

    2008-01-01

    Finnairi Eesti tütarfirma Aero Airlines lõpetas oma lennud nii Tallinna-Helsingi vahel kui ka Soome siseliinidel, Eesti ja Soome vahelised lennud võtab üle Soome firma Finncomm Airlines. Lisa: Aero Airlines

  8. 典型使用条件对发动机涡轮叶片蠕变寿命消耗的影响研究%Impact of Typical Operating Conditions on Creep Life Consumption for Aero Engine Turbine Blade

    Institute of Scientific and Technical Information of China (English)

    李本威; 赵勇; 蒋科艺; 李钊

    2017-01-01

    为开展发动机涡轮叶片使用寿命监视及掌握典型使用条件对高压涡轮叶片蠕变寿命消耗的影响规律,利用发动机性能仿真程序与使用载荷多场耦合分析方法建立了涡轮叶片寿命消耗综合分析模型,并通过引入寿命消耗因子,定量给出了飞行高度、环境温度、飞行马赫数、高压转子转速等使用条件对涡轮叶片温度与应力以及蠕变寿命消耗的影响规律.结果表明,各使用因素均对涡轮叶片的蠕变寿命消耗具有较大影响,其中以高压转子转速的影响最大,转速升高1%其对数寿命消耗因子升高约0.4.%In order to develop turbine blade life usage monitoring and understand impact of typical operat?ing conditions on creep life consumption of high pressure turbine blade, an integrated turbine blade life con?sumption analysis model was established based on engine performance simulation model and multi-field conju?gate method. Through introducing the life consumption factor , quantitative impact of typical operating condi?tions,such as flight altitude,ambient temperature,flight Mach number and high pressure rotor speed,on tur?bine blade temperature,stress and creep life consumption was found. Results show that operating condition in?deed has a significant impact on turbine blade creep life consumption , among which the high pressure rotor speed has the maximal impact that logarithmic life consumption factor increases about 0.4 with rotor speed raise 1%.

  9. Aero radiometric relay of the areas including in the photo map: Sierra de los Rios (C 15), Fraile Muerto (Page E-16) and Cerro de Las Cuentas (Page E- 17) Cerro Largo district

    International Nuclear Information System (INIS)

    De Leone, H; Rossi, P; Massa, E; Spoturno, J.

    1976-01-01

    The present work constitutes the second part of the report realised on the aerorradimetric relief of the Long Hill Department. 1,325 km of in detail regular prospection were arrived at end on the photo-plans Died Frayle, Hill of Cuentas and Mountain range of the Rivers. This constitutes a 59% of the total of the areas released in all the campaign. A series took place in addition to aircraft reconnaissances on the photo-plans Step Pereira, Cordobes and Cerrezuelo covering 480 km, on the departments of Long Hill and bordering areas of the department of Peach tree. These works took place between days 8 of November to the 8 of December of 1970 being developed in this period, the making a flight, elaboration of the cintilometricos registries and interpretation of the same. The work area includes/understands the flights inclusively number 16 to the 26 and 30 and 31 flights in agreement can be seen in the advance plane. Scale 1:100.000

  10. The Hypersonic Revolution. Case Studies in the History of Hypersonic Technology. Volume III: The Quest for the Orbital Jet: The National Aero-Space Plane Program (1983-1995)

    National Research Council Canada - National Science Library

    Schwelkart, Larry

    1998-01-01

    ... that could fly fast enough to attain orbital velocity, is considered a success by many of the participants.1 They contend that by "showing up," NASP survived long enough to produce what many deem critical technologies for hypersonic flight...

  11. Computational Aerodynamics and Aeroacoustics for Wind Turbines

    DEFF Research Database (Denmark)

    Shen, Wen Zhong

    and applied to laminar flows. An aero-acoustic formulation for turbulent flows was in [15] developed for Large Eddy Simulation (LES), Unsteady Reynolds Averaged Navier-Stokes Simulation (URANS) and Detached Eddy Simulation (DES). In [16] a collocated grid / finite volume method for aero-acoustic computations...... with Computational Aero-Acoustics (CAA). With the spread of wind turbines near urban areas, there is an increasing need for accurate predictions of aerodynamically generated noise. Indeed, noise has become one of the most important issues for further development of wind power, and the ability of controlling...... and aero-acoustics of wind turbines. The papers are written in the period from 1997 to 2008 and numbered according to the list in page v. The work consists of two parts: an aerodynamic part based on Computational Fluid Dynamics and an aero-acoustic part based on Computational Aero Acoustics for wind...

  12. Research Institute for Autonomous Precision Guided Systems

    National Research Council Canada - National Science Library

    Rogacki, John R

    2007-01-01

    ... actuators, development of a visualization lab for modeling vision based guidance algorithms, concept development of a rapid prototyping and aero characterization lab, vision based control of autonomous...

  13. A Velocity Prediction Procedure for Sailing Yachts with a hydrodynamic Model based on integrated fully coupled RANSE-Free-Surface Simulations

    NARCIS (Netherlands)

    Boehm, C.

    2014-01-01

    One of the most important tools in today's sailing yacht design is the Velocity Prediction Program (VPP). VPPs calculate boat speed from the equilibrium of aero- and hydrodynamic flow forces. Consequently their accuracy is linked to the accuracy of the aero- and hydrodynamic data used to represent a

  14. Laminar separation bubbles: Dynamics and control

    Indian Academy of Sciences (India)

    e-mail: {diwan,onr}@aero.iisc.ernet.in. Abstract. ... of thin aerofoils, on gas turbine blades and on low Reynolds number micro-aero-vehicle wings. ... Surface and smoke flow visualisation techniques were employed to measure the length and ...

  15. 76 FR 28626 - Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model...

    Science.gov (United States)

    2011-05-18

    ... LM Aero believed that there should be a differentiation between the repetitive inspection intervals for Taper-Lok fastened joints (original production configuration) and the inspection intervals for Hi-Tigue fasteners installed in cold-worked holes. LM Aero pointed out that this differentiation is...

  16. Diagnostic monitoring of drivetrain in a 5 MW spar-type floating wind turbine using Hilbert spectral analysis

    DEFF Research Database (Denmark)

    Ghane, Mahdi; Nejad, Amir R.; Blanke, Mogens

    2017-01-01

    and condition monitoring approaches; using analytical tools, therefore, is one of the promising approaches in this regard. In this study, forces and moments on the main shaft are obtained from the global response analysis using an aero-hydro-servo-elastic code, SIMO-RIFLEX-AeroDyn. Then, they are utilized...

  17. Dynamic behavior of parked wind turbine at extreme wind speed

    DEFF Research Database (Denmark)

    Totsuka, Yoshitaka; Imamura, Hiroshi; Yde, Anders

    2016-01-01

    of standstill and idling is analyzed by time domain simulations using two different coupled aero-hydro-servo-elastic codes. Trend in modern wind turbines is development of bigger, lighter and more flexible rotors where vibration issues may cause aero-elastic instabilities which have a serious impact...

  18. 75 FR 44306 - Fifth Meeting: RTCA Special Committee 223: Airport Surface Wireless Communications

    Science.gov (United States)

    2010-07-28

    ....--Overview of AeroMACS test and evaluation results summary--Mr. Ward Hall. 0930 a.m.--Selected AeroMACS fixed...-Chair: Mr. Ward Hall, ITT Corporation. 0915 a.m.--Agenda Overview. Fill out lunch orders. 0930 a.m...

  19. Pengelolaan Media Sosial Oleh Unit Corporate Communication PT GMF Aeroasia

    Directory of Open Access Journals (Sweden)

    Fajar Syuderajat

    2017-10-01

    Full Text Available Studi ini berjudul:  Pengelolaan  Media  Sosial  oleh  Unit Corporate Communication PT GMF AeroAsia. Seiring dengan meningkatknya jumlah pengguna social media telah melahirkan media baru bagi bidang komunikasi khususnya dunia public relations. Kesempatan ini kemudian dimanfaatkan oleh PT GMF AeroAsia untuk memanfaatkan media sosial yang dijadikan sebagai media komunikasi dengan memberikan  informasi  seputar  dunia  aviasi  dan  bidang  MRO  (maintenance, repair,  organization  PT  GMF AeroAsia.   Tujuan studi ini, untuk mengetahui pengelolaan media sosial yang digunakan PT GMF AeroAsia sebagai strategi komunikasi brand awareness dengan konsep  teori yang digunakan dalam penelitian ini adalah New Media Theory yang berhubungan dengan media sosial. Metode pendekatan penulisan kualitatif dan bersifat deskriptif. Hasil dari studi ini mengatakan bahwa pengelolaan media sosial PT GMF AeroAsia oleh Corporate Communication memilih facebook, instagram, youtube, dan linkedin. Penanganan langsung dilakukan oleh tim digital aktivasi dengan konten-konten yang terlebih dahulu disetujui oleh kepala divisi Corporate Communication.   Kesimpulan, PT GMF AeroAsia menggunakan facebook, instagram, youtube, dan linkedin sesuai dengan segmentasi perusahaan yang lebih menekankan B-to-B. Meskipun banyak sekali follower pada media sosial tersebut namun untuk respon atau feedback kurang mendapatkan perhatian, sehingga terkesan lambat dalam menanggapi. Kata kunci: corporate communication;  media sosial; PT GMF AeroAsia.

  20. C-Band Airport Surface Communications System Standards Development, Phase I

    Science.gov (United States)

    Hall, Edward; Isaacs, James; Zelkin, Natalie; Henriksen. Steve

    2010-01-01

    This document is being provided as part of ITT's NASA Glenn Research Center Aerospace Communication Systems Technical Support (ACSTS) contract NNC05CA85C, Task 7: "New ATM Requirements--Future Communications, C-Band and L-Band Communications Standard Development." The proposed future C-band (5091- to 5150-MHz) airport surface communication system, referred to as the Aeronautical Mobile Airport Communications System (AeroMACS), is anticipated to increase overall air-to-ground data communications systems capacity by using a new spectrum (i.e., not very high frequency (VHF)). Although some critical services could be supported, AeroMACS will also target noncritical services, such as weather advisory and aeronautical information services as part of an airborne System Wide Information Management (SWIM) program. AeroMACS is to be designed and implemented in a manner that will not disrupt other services operating in the C-band. This report defines the AeroMACS concepts of use, high-level system requirements, and architecture; the performance of supporting system analyses; the development of AeroMACS test and demonstration plans; and the establishment of an operational AeroMACS capability in support of C-band aeronautical data communications standards to be advanced in both international (International Civil Aviation Organization, ICAO) and national (RTCA) forums. This includes the development of system parameter profile recommendations for AeroMACS based on existing Institute of Electrical and Electronics Engineering (IEEE) 802.16e- 2009 standards

  1. Analysis on metallogenetic conditions of sandstone-type uranium deposit in Minhe Basin

    International Nuclear Information System (INIS)

    Jiang Minzhong; Wang Huaiwu

    2002-01-01

    Little uranium prospecting has been performed so far in Minhe basin. However, at the marginal areas of the basin uranium mineralizations and lots of aero-radioactive anomalies have been found before, and the basin shows some prospecting potential. Based on the regional geological setting, by means of interpretation of high-precision aero-magnetic, aero-radiometric and Bouguer gravimetric data, and combined with hydrodynamic, lithofacies-palaeographic and paleo-climatic analyses, authors make a comprehensive evaluation of metallogenic conditions for sandstone-type uranium deposits, and propose metallogenically favourable areas in the basin

  2. Pengelolaan Media Sosial Oleh Unit Corporate Communication PT GMF Aeroasia

    OpenAIRE

    Fajar Syuderajat

    2017-01-01

    Studi ini berjudul:  Pengelolaan  Media  Sosial  oleh  Unit Corporate Communication PT GMF AeroAsia. Seiring dengan meningkatknya jumlah pengguna social media telah melahirkan media baru bagi bidang komunikasi khususnya dunia public relations. Kesempatan ini kemudian dimanfaatkan oleh PT GMF AeroAsia untuk memanfaatkan media sosial yang dijadikan sebagai media komunikasi dengan memberikan  informasi  seputar  dunia  aviasi  dan  bidang  MRO  (maintenance, repair,  organization)  PT  GMF AeroA...

  3. Achievement report for fiscal 1998 on research and development of multifunction members structure control technologies. Development of advanced surface treatment technologies for methane-fueled aero engines (1. Microstructure control technologies for ultrahigh temperature members); 1998 nendo fukugo kino buzai kozo seigyo gijutsu no kenkyu kaihatsu. Methane nenryo kokukiyo engine buzai no kodo hyomen kako gijutsu kaihatsu (chokoon buzai mikuro kozo seigyo gijutsu)

    Energy Technology Data Exchange (ETDEWEB)

    NONE

    1999-03-01

    The carbon fiber reinforced carbon composite materials (C/C composites) strong at ultrahigh temperatures are taken up. So as to improve on its resistance to oxidation, corrosion, and abrasion as well as on its strength at ultrahigh temperatures, an ion engineering-assisted technique is used to reform the C/C composite surface layer and a technology is developed for thin coating formation on the C/C composite surface. Next, technologies are developed for multifunction coating formation on top of the surface, for defect prevention or removal from the C/C composite, and for adhesion enhancement between the C/C composite fibers and the matrix. Technologies are further developed for evaluating hostile environment withstanding capabilities at ultrahigh temperatures. In this fiscal year, in the study of microstructure controlling multilayer coating technologies, development is conducted of technologies of ion engineering-assisted surface control and reform and of technologies of forming multifunctional coatings high in reliability and resistance to corrosion. In the field of microstructure control composition, 3-dimensional carbon fiber reinforced carbon composite materials are manufactured by way of trial and evaluated, and their behavior under rigorous conditions is evaluated. (NEDO)

  4. Mechanical property tests in hot gas environment for evaluation of life expectancy of aero-engine turbine blades and for assessment of procedures for prolonging service life. Mechanische Pruefung unter Heissgasatmosphaere zur Ermittlung der Lebenserwartung von Fluggasturbinenschaufeln und zur Bewertung von Verfahren zur Lebensdauerverlaengerung

    Energy Technology Data Exchange (ETDEWEB)

    Peichl, L

    1984-01-01

    The aim of this programme was the determination and optimization of mechanical testing procedures in order to enable a service life prediction for turbine blades as well as to measure the life consumption of blades which have already been in service. Under these testing conditions procedures were to be investigated which lead to a prolongation of the service life of the blades. The results have shown that the rig test at constant values of load and temperature, which are typical for service conditions, is sufficient for the laboratory simulation. The life consumption of blades run in the engine can be determined by measuring the residual creep life in the rig test. Using the resulting data the life consumption of a particular blade run in the engine can be estimated by the non-destructive measurement of its elongation. The precision of residual life prediction is raised by respecting the master heat and porosity of the blades. From the investigation of high-temperature corrosion resistant coatings it follows that IN 100 can be protected against the attack of sea salt over its whole creep life by coating with a precious metal modified aluminide or by LPPS- or EB-PVD-MCrAlY-coatings. By aluminising, the cooling channels of turbine blades can be protected against oxidation over more than 700 h in the temperature/load cycling test. However, the coating technique used is only applicable under laboratory conditions. In contrary, internal coating by pulse aluminising, which is compatible to production conditions, showed less oxidation resistance.

  5. A contribution to the thermal and aero-dynamical modelling of the urban micro-climate. Analysis of the water and vegetation impact on the comfort conditions in outdoor spaces; Contribution a la modelisation thermo-aeraulique du microclimat urbain. Caracterisation de l'impact de l'eau et de la vegetation sur les conditions de confort en espaces exterieurs

    Energy Technology Data Exchange (ETDEWEB)

    Vinet, J.

    2000-11-01

    In summer, temperatures in cities may rise, thereby inducing the so-called 'urban heat island' and tremendous consequences on outdoor comfort, health risks, pollutant emission and energy consumption. Replacing vegetation and moist surfaces by concrete or asphalt may enhance these problems. Therefore, the aim of this thesis is to quantify the impact of vegetation and water on urban micro-climate and comfort through numerical modelling; In the first part, a scientific literature review considers various topics applied to our problem such as urban micro-climate, simulations, urbanism, urban forestry and outdoor thermal comfort. This information is relevant to define and interpret further numerical modelling. Numerical simulations based on the coupling of the SOLENE. thermal program and the N3S CFD code are proposed to model wind flow, air and surface temperatures. The theoretical principles, hypothesis and coupling methodology are presented here. This set of numerical tools is combined in order to help urban or landscape planners, architects and engineers, to analyse the impacts of different projects on micro-climate and on outdoor thermal comfort, under hot summer conditions. To illustrate this approach, an open space in Montpellier (southern France) called the 'Place du Millenaire' and designed by Ricardo Bofill is studied, considering various cases (no vegetation, actual vegetation and vegetation in 30 years). The comparative results demonstrate improvements of urban form, micro-climate and outdoor thermal comfort. (author)

  6. Study of the processes of radionuclides transfer, heavy metals and aero-particles among the solid, dissolved phase and the air; Estudio de los procesos de transferencia de radionuclidos, metales pesados y aeroparticulas entre la fase solida, disuelta y el aire

    Energy Technology Data Exchange (ETDEWEB)

    Romero G, E. T.; Ordonez R, E. [ININ, Departamento de Quimica, Carretera Mexico-Toluca s/n, 52750 Ocoyoacac, Estado de Mexico (Mexico); Reyes G, L. R. [Instituto Potosino de Investigacion Cientifica y Tecnologica, Division de Geociencias Aplicadas, Camino a la Presa San Jose 2055, Col. Lomas 4 seccion, 78216 San Luis Potosi (Mexico); Jose Y, M., E-mail: elizabeth.romero@inin.gob.m [University of Texas at San Antonio, Department of Physics and Astronomy, One UTSA Circle, San Antonio TX 78249 (United States)

    2010-07-01

    In this chapter the investigations developed in the Instituto Nacional de Investigaciones Nucleares (ININ) are presented, in collaboration with specialists in diverse fields of the science. In the first place, is presented the objective and an introduction of each one of the following projects: Study of the uranium migration through the not saturated area, and Synthesis and characterization of phosphate materials by conventional techniques, projects developed under the direction and collaboration of the Ph D. Eduardo Ordonez Regil. Identification of the chemical-morphologic composition of painting mural pigments: the blue Mayan, indigo blue, the secret of the color, and investigation of the physiochemical components of the asphaltenes and malthenes of heavy crudes and vacuum residual, with the supervision of the Ph D. Miguel Jose Yacaman. Evaluation of the water quality and type of sediments of the lake-crater The Pool: one of the seven stars of Santiago Valley, Guanajuato; Study of the sorption kinetics of Cr(Vi) in floor of a container of chromium residuals in Buenavista, Guanajuato, Mexico; Investigation of the underground water hydrochemistry of the basin of the Avenues River in Pachuca de Soto, Hidalgo, and Characterization of the particle material and modeled of the dispersion and pollutants transport in the air of the Metropolitan Area of the Toluca Valley, projects carried out under the direction and collaboration of the Ph D. Lazaro Raymundo Reyes Gutierrez. Finally, is presented the most representative of the obtained results, as well as a discussion of the same ones. (Author)

  7. 75 FR 54421 - Sixth Meeting: RTCA Special Committee 223: Airport Surface Wireless Communications

    Science.gov (United States)

    2010-09-07

    ..., 2010 from 0900 a.m.- 1600 p.m. ADDRESSES: The meeting will be held at EUROCONTROL, Rue de la Fusee 96... Applications (FAA) NASA Cleveland Test Bed Test Results (ITT) Channel Model Considerations for AeroMACS (Uni...

  8. Microwave-assisted synthesis of high-loading, highly dispersed Pt ...

    Indian Academy of Sciences (India)

    Keywords. Direct methanol fuel cell; carbon aerogel; Pt; microwave-assisted polyol process; electrocatalyst; ... obtained from the carbonization of the dried organic aero- gel in a ... 12 hours. The dried residue (0·01 g) was mixed with ethanol.

  9. 76 FR 6179 - Eighth Meeting: RTCA Special Committee 223: Airport Surface Wireless Communications

    Science.gov (United States)

    2011-02-03

    ... Review the EUROCAE WG-82 straw man MOPS proposal Discuss MOPS content detail versus referencing other AeroMACS Specs Review RTCA MOPS Drafting Guide and make Work Assignments Wednesday Afternoon--Reconvene...

  10. Biological nitrogen and phosphorus removal by filamentous bacteria ...

    African Journals Online (AJOL)

    the intracellular denitrification intermediates inhibit the aero- bic cytochrome o of ... using an auto-analyzer (Technicon Auto Analyzer AAII, Der- motech South ..... PAO's and deni- trifiers in situ collectively, and using novel molecular techniques.

  11. Evaluation of o-cresol removal using PVA-cryogel-immobilised ...

    African Journals Online (AJOL)

    2014-02-06

    Feb 6, 2014 ... In general, the common techniques for immobilisation of biomass in a polyvinyl ..... PETRUCCIOLI M, DUARTE J and FEDERICI F (2000) High-rate aero- ... WEBER Jr. WJ and MORRIS JC (1963) Kinetics of adsorption on car-.

  12. Purification of cadmium up to 5N+ by vacuum distillation

    Indian Academy of Sciences (India)

    Unknown

    purified Cd as well as raw Cd was done by ICP–OES techniques for 27 impurity ... defence, military and aero-space (Lejbov et al 1989). Other areas of applications include telecommunications, electric vehicle and remote area storage systems.

  13. SUPERALLOYS: AN INTRODUCTION WITH THERMAL ANALYSIS ...

    African Journals Online (AJOL)

    2015-09-01

    Sep 1, 2015 ... In space vehicles: aerodynamically heated skins and rocket engine parts are made from ... chemistry but also to the primary melting, forming and casting techniques. .... (former Volvo Aero Corporation) in Trollhättan, Sweden.

  14. An Integrated Heavy Fuel Piston Engine Ducted Fan Propulsion Unit for Personal Air Vehicles, Phase II

    Data.gov (United States)

    National Aeronautics and Space Administration — The proposed PAVE propulsion system technology demonstration combines an innovative high-speed aero-diesel engine with a novel ducted fan assembly resulting in a low...

  15. An Integrated Heavy Fuel Piston Engine Ducted Fan Propulsion Unit for Personal Air Vehicles, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — The proposed PAVE propulsion system technology demonstration combines an innovative high-speed aero-diesel engine with a novel ducted fan assembly resulting in a low...

  16. Exploiting Formation Flying for Fuel Saving Supersonic Oblique Wing Aircraft

    Science.gov (United States)

    2007-07-01

    used and developed during recent wing / winglet / morphing design programmes (Refs.13-14). By exploiting this method, we have assessed the aerodynamics ...parameters, Propulsion Issues, Size Issues, Aero-elastic effects 15. SUBJECT TERMS EOARD, Control System, Aerodynamics 16...

  17. Resonating Nitrous Oxide Thruster, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — AeroAstro proposes decomposing nitrous oxide (N2O) as an alternative propellant to existing spacecraft propellants. Decomposing N2O can be used as either a high Isp,...

  18. Advanced Chemically-Based Actuation for Active Flow Control, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — The proposed SBIR program by Virtual AeroSurface Technologies (VAST) focuses on the development of a novel variant of pulsed blowing active flow control in which...

  19. 75 FR 14483 - Third Meeting: RTCA Special Committee 223: Airport Surface Wireless Communications

    Science.gov (United States)

    2010-03-25

    .../SC223-005) Special Committee Leadership Designated Federal Official (DFO): Mr. Brent Phillips Co-Chair... Continue AeroMACS Profile definition Wednesday Afternoon--Reconvene Plenary Profiles WG Status Report and...

  20. Airborne Evaluation Facility

    Data.gov (United States)

    Federal Laboratory Consortium — AFRL's Airborne Evaluation Facility (AEF) utilizes Air Force Aero Club resources to conduct test and evaluation of a variety of equipment and concepts. Twin engine...

  1. Mobile intelligent autonomous systems

    National Research Council Canada - National Science Library

    Raol, J. R; Gopal, Ajith K

    2013-01-01

    "Written for systems, mechanical, aero, electrical, civil, industrial, and robotics engineers, this book covers robotics from a theoretical and systems point of view, with an emphasis on the sensor...

  2. 76 FR 11460 - Product Cancellation Order for Certain Pesticide Registrations

    Science.gov (United States)

    2011-03-02

    ... with Preemergent Weed Control. 044446-00053 Kill A Bug II Insect Spray.. Phenothrin 044446-00066 Aero Roach & Ant Insecticide Phenothrin 045188-00002 Harrison Flea and Tick Piperonyl butoxide Shampoo for...

  3. MATHEMATICAL MODEL FOR AEROSOL DEPOSITION IN THE RESPIRATORY TRACT OF THE GUINEA PIG

    Science.gov (United States)

    Laboratory animals are used as surrogates in inhalation exposure studies for: 1) risk assessments of air pollutants; and, (2) evaluations of pharmacologic drugs. erein, a mathematical model is presented which identifies factors affecting the regional distribution of inhaled aeros...

  4. Kõrgelt 2016 / Jürgen Veerme

    Index Scriptorium Estoniae

    Veerme, Jürgen

    2016-01-01

    Snap.ee keskkonnas toimunud aero- ja kõrgelt pildistatud fotode konkursist "Kõrgelt". I koht: Janek Joab "Varjud". II koht: Margus Muts "Ilus Eestimaa". III koht: Siim Teder "Ja järgmisena lähen mina"

  5. 3D Flow Field Measurements using Aerosol Correlation Velocimetry, Phase II

    Data.gov (United States)

    National Aeronautics and Space Administration — AeroMancer Technologies proposes to develop a 3D Global Lidar Airspeed Sensor (3D-LGAS) using Aerosol Correlation Velocimetry for standoff sensing of high-resolution...

  6. 3D Flow Field Measurements using Aerosol Correlation Velocimetry, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — AeroMancer Technology proposes to develop a 3D Lidar Global Airspeed Sensor (3D-GLAS) for remote optical sensing of three-component airspeeds in wind tunnel...

  7. Mesh Independent Probabilistic Residual Life Prediction of Metallic Airframe Structures, Phase I

    Data.gov (United States)

    National Aeronautics and Space Administration — Global Engineering and Materials, Inc. (GEM) along with its team members, Clarkson University and LM Aero, propose to develop a mesh independent probabilistic...

  8. Underwater Ambient Noise. Proceedings of a Conference Held at SACLANTCEN on 11-14 May 1982. Volume 2. Unclassified Papers. Part 1

    Science.gov (United States)

    1982-06-15

    un traitement a bord de la bouee. Pour le reste, ayant retenu une gamme de frequences relativement etendue (20 Hz - 20 kHz) et des fil- tres...qui fait I’objet du programme. La presentation des resultats est delivree sous de nombreuses formes. Les principales sont : - tableau ...Copenhagen FRANCE Bienvenu, G. Thomson-CSF Cagnes-sur-Mer de Raigniac, B. Societe AERO Paris Laval, R. Societe AERO Paris Lucas, GERDSM

  9. 地面効果翼機の性能向上に関する研究

    OpenAIRE

    Yoon, D. H.; Suzuki, Kazuyuki; Endo, Hideyuki; Kohama, Yasuaki; Yoon, D. H.; 鈴木 和幸; 遠藤 秀之; 小濱 泰昭

    2006-01-01

    Aerodynamic performance improvement of the Aero-Train has been conducted both experimentally and numerically. Suction side of the WIG aerofoil tend to separate, because of the existence of the ground surface, and also wing-wing, wing-fuselage interactions appears. Those flow separations limit the lift to drag ratio performance. In order to improve overall Aero-Train performance, optimum wing configuration determination, blowing from the pressure side, and swept forward guide wing configuratio...

  10. HAWCStab2 with super element foundations: A new tool for frequency analysis of offshore wind turbines

    DEFF Research Database (Denmark)

    Henriksen, Lars Christian; Hansen, Anders Melchior; Kragh, Knud Abildgaard

    2013-01-01

    HAWCStab2 is a linear frequency domain aero-elastic tool, developed by DTU Wind Energy, suitable for frequency and stability analysis of horizontal axis 3 bladed wind turbines [1]. This tool has now been extended to also handle complex offshore foundation types, such as jacket structures...... and floating structures with mooring lines, using super elements calculated by the nonlinear time domain aero-elastic code HAWC2 [2,3]....

  11. Eolic energy. Evaluation of the eolic potential of the Atlantic Coast

    International Nuclear Information System (INIS)

    Rodriguez M, H.

    1986-01-01

    The objectives of the study are: Gathering of the available information on winds (speeds stockings and predominant addresses of the wind every hour) in the Colombian Atlantic Costa. Analyze it and to adjust it. Mensuration team characteristic; Speed monthly average; duration and frequency of periods of calm, relative and accumulative monthly frequency and mainly the year, address and distribution of the wind typical curve for energy and power during the year, to determine, the aero generation of potential and the water pumping. The mensurations were made 10, 15, 20, 15 meters on the surface and the Himat gave the primary information, 18 stations were studied with a volume of 1321104 data. The parameters of weibull distribution were determined for every month and for all the stations. San Andres' airport is that of better potential with 2182 kw/m to the square/year, with an annual average of 344.53 w/m to the square that is a very good potential. The maximum of 292 kWh/m to the square is given in December and the minimum of 81.47 kWh/m to the square during September. They are considered good places for aero generation those from 500 kWh/m to the square and they are attractive: Riohacha, Soledad, Cartagena, Valledupar, Santa Marta and Codazzi areas. These places are favorable for the electricity generation in on-line systems with systems already existent or with aero generator-diesel combined systems or solar aero generator-cells. The results of aero generators simulation show the possibility to use these teams clearly. In the case of San Andres factors are had up to 57 percent for aero generators like the Siemens 2000 and the wind worker 10 since the potential is important they are considered convenient to study projects to implement the aero generation and the pumping

  12. Aging Mechanisms and Control. Symposium Part A - Developments in Computational Aero- and Hydro-Acoustics. Symposium Part B - Monitoring and Management of Gas Turbine Fleets for Extended Life and Reduced Costs (Les mecanismes vieillissants et le controle) (Symposium Partie A - Developpements dans le domaine de l’aeroacoustique et I’hydroacoustique numeriques) (Symposium Partie B - Le suivi et la gestion des turbomoteurs en vue du prolongement de l

    Science.gov (United States)

    2003-02-01

    Environmental Medicine 1999; 70 (3, Suppl): A40-5. 40. Castro AP, Aguas AP, Grande NR, Monteiro E, Castelo Branco NAA. Increase in CD8+ and CD4+ T lymphocytes...residual value of the old parts, ie whether they could be reused or not. • The cost of the affected components. • The subsequent reduction in maintenance... reuse potential for developed system parts. A number of systems with similar tasks as the EHM is needed for development, production and repair of the

  13. Aero radiometric relay of the areas including in the photo map: Sierra de los Rios (C 15), Fraile Muerto (Page E-16) and Cerro de Las Cuentas (Page E- 17) Cerro Largo district[Study of Uranium prospection in Uruguay]; Relevamiento aeroradimetrico de areas comprendidas en los fotoplanos: Sierra de los Rios (Hoja C-15), Frayle Muerto (Hoja E- 16), y Cerro de Las Cuentas (Hoja E-17) Departamento de Cerro Largo

    Energy Technology Data Exchange (ETDEWEB)

    De Leone, H; Rossi, P; Massa, E; Spoturno, J

    1976-07-01

    The present work constitutes the second part of the report realised on the aerorradimetric relief of the Long Hill Department. 1,325 km of in detail regular prospection were arrived at end on the photo-plans Died Frayle, Hill of Cuentas and Mountain range of the Rivers. This constitutes a 59% of the total of the areas released in all the campaign. A series took place in addition to aircraft reconnaissances on the photo-plans Step Pereira, Cordobes and Cerrezuelo covering 480 km, on the departments of Long Hill and bordering areas of the department of Peach tree. These works took place between days 8 of November to the 8 of December of 1970 being developed in this period, the making a flight, elaboration of the cintilometricos registries and interpretation of the same. The work area includes/understands the flights inclusively number 16 to the 26 and 30 and 31 flights in agreement can be seen in the advance plane. Scale 1:100.000.

  14. Interference Analysis for an Aeronautical Mobile Airport Communications System

    Science.gov (United States)

    Wilson, Jeffrey D.; Kerczewski, Robert J.

    2011-01-01

    The next generation of aeronautical communications for airport surface applications has been identified through a NASA research program and an international collaborative future communications study. The result, endorsed by both the United States and European regulatory agencies is called AeroMACS (Aeronautical Mobile Airport Communications System) and is based upon the IEEE 802.16e mobile wireless standard. Coordinated efforts to develop appropriate aviation standards for the AeroMACS system are now underway within RTCA (United States) and Eurocae (Europe). AeroMACS will be implemented in a recently allocated frequency band, 5091-5150 MHz. As this band is also occupied by fixed satellite service uplinks, AeroMACS must be designed to avoid interference with this incumbent service. The aspects of AeroMACS operation that present potential interference to the fixed satellite service are under analysis in order to enable the definition of standards that assure that such interference will be avoided. The NASA Glenn Research Center has been involved in this analysis, and the first results of modeling and simulation efforts directed at this analysis are the subject of this presentation.

  15. Development of a Fast Fluid-Structure Coupling Technique for Wind Turbine Computations

    DEFF Research Database (Denmark)

    Sessarego, Matias; Ramos García, Néstor; Shen, Wen Zhong

    2015-01-01

    Fluid-structure interaction simulations are routinely used in the wind energy industry to evaluate the aerodynamic and structural dynamic performance of wind turbines. Most aero-elastic codes in modern times implement a blade element momentum technique to model the rotor aerodynamics and a modal......, multi-body, or finite-element approach to model the turbine structural dynamics. The present paper describes a novel fluid-structure coupling technique which combines a threedimensional viscous-inviscid solver for horizontal-axis wind-turbine aerodynamics, called MIRAS, and the structural dynamics model...... used in the aero-elastic code FLEX5. The new code, MIRASFLEX, in general shows good agreement with the standard aero-elastic codes FLEX5 and FAST for various test cases. The structural model in MIRAS-FLEX acts to reduce the aerodynamic load computed by MIRAS, particularly near the tip and at high wind...

  16. Design of Large Wind Turbines using Fluid-Structure Coupling Technique

    DEFF Research Database (Denmark)

    Sessarego, Matias

    Aerodynamic and structural dynamic performance analysis of modern wind turbines are routinely carried out in the wind energy field using computational tools known as aero-elastic codes. Most aero-elastic codes use the blade element momentum (BEM) technique to model the rotor aerodynamics......-dimensional viscous-inviscid interactive method, MIRAS, with the dynamics model used in the aero-elastic code FLEX5. Following the development of MIRAS-FLEX, a surrogate optimization methodology using MIRAS alone has been developed for the aerodynamic design of wind-turbine rotors. Designing a rotor using...... a computationally expensive MIRAS instead of an inexpensive BEM code represents a challenge, which is resolved by using the proposed surrogate-based approach. The approach is unique because most aerodynamic wind-turbine rotor design codes use the more common and inexpensive BEM technique. As a verification case...

  17. Fluid-structure interaction computations for geometrically resolved rotor simulations using CFD

    DEFF Research Database (Denmark)

    Heinz, Joachim Christian; Sørensen, Niels N.; Zahle, Frederik

    2016-01-01

    fluid dynamics (CFD) solver EllipSys3D. The paper shows that the implemented loose coupling scheme, despite a non-conservative force transfer, maintains a sufficient numerical stability and a second-order time accuracy. The use of a strong coupling is found to be redundant. In a first test case......This paper presents a newly developed high-fidelity fluid–structure interaction simulation tool for geometrically resolved rotor simulations of wind turbines. The tool consists of a partitioned coupling between the structural part of the aero-elastic solver HAWC2 and the finite volume computational......, the newly developed coupling between HAWC2 and EllipSys3D (HAWC2CFD) is utilized to compute the aero-elastic response of the NREL 5-MW reference wind turbine (RWT) under normal operational conditions. A comparison with the low-fidelity but state-of-the-art aero-elastic solver HAWC2 reveals a very good...

  18. Partitioned Fluid-Structure Interaction for Full Rotor Computations Using CFD

    DEFF Research Database (Denmark)

    Heinz, Joachim Christian

    ) based aerodynamic model which is computationally cheap but includes several limitations and corrections in order to account for three-dimensional and unsteady eects. The present work discusses the development of an aero-elastic simulation tool where high-fidelity computational fluid dynamics (CFD......) is used to model the aerodynamics of the flexible wind turbine rotor. Respective CFD computations are computationally expensive but do not show the limitations of the BEM-based models. It is one of the first times that high-fidelity fluid-structure interaction (FSI) simulations are used to model the aero......-elastic response of an entire wind turbine rotor. The work employs a partitioned FSI coupling between the multi-body-based structural model of the aero-elastic solver HAWC2 and the finite volume CFD solver EllipSys3D. In order to establish an FSI coupling of sufficient time accuracy and sufficient numerical...

  19. REFSIM Handbook of Variable Names.

    Science.gov (United States)

    1982-11-04

    INT2 LREFSEEK R /AERO/ INT4 L: REFSEEK D2THET missile pitch acceleration in degrees/R /AERO/ AER02 M CREFAIR second**2. R /AERO/ AER03 M LREFAIR R...LREFSEEK R /INTERP/ AWM’l L REFSEEK R /INTERP/ ANMh2 CREFSEEK DELA Peak magnitude difference at port and R /CSAS/ AMERCS LREFENW4T starboard. (db/m**2) R...ASE/ GLINT2 L REFD1VMT R /ASE/ INIiT M LIREFSEEK, R /ASE,/ INT2 REFSEEK R /ASE/ INT4 L-RE’SEEK R /ASE/ LOCK2 L-EFSEEK R /ASE/ 1’tLOCK LIREFSEEK DELUhP

  20. Working with Windows Vista at CERN - (IT3T/2007/3)

    CERN Multimedia

    CERN. Geneva

    2007-01-01

    IT3T/2007/3 - Travailler sur Windows Vista au CERN La présentation fournira une introduction à Windows Vista et montrera les nouvelles fonctionnalités comme le nouveau interface d’utilisateur : Windows Aero, le nouveau Windows Desktop Search et les divers améliorations de sécurité comme User Account Control. IT3T/2007/3 - Working with Windows Vista at CERN The presentation will provide a introduction to Windows Vista and demonstrate the new features such as the new Graphical User Interface including Windows Aero, the new Windows Desktop Search and various Security enhancements like the User Account Control.

  1. Remote sensing, airborne radiometric survey and aeromagnetic survey data processing and analysis

    International Nuclear Information System (INIS)

    Dong Xiuzhen; Liu Dechang; Ye Fawang; Xuan Yanxiu

    2009-01-01

    Taking remote sensing data, airborne radiometric data and aero magnetic survey data as an example, the authors elaborate about basic thinking of remote sensing data processing methods, spectral feature analysis and adopted processing methods, also explore the remote sensing data combining with the processing of airborne radiometric survey and aero magnetic survey data, and analyze geological significance of processed image. It is not only useful for geological environment research and uranium prospecting in the study area, but also reference to applications in another area. (authors)

  2. Discussion on the correlation between geophysical and remote sensing information. Primary study on information correlation of research content and concept of post-remote sensing application technology for uranium exploration

    International Nuclear Information System (INIS)

    Ye Fawang; Liu Dechang

    2005-01-01

    Based on the research content of post-remote sensing application technology for uranium exploration, a preliminary discussion on the correlation between RS information and geophysical information from gravity, aero-magnetics, aero-radioactivity is made on five aspects: physical meaning, depth of geological rule meaning, time and phase, planar pattern and inter-reaction mechanism. It creates a good beginner for deeply studying the correlation in quality and quantity between RS information from post-remote sensing application technology and other geologic information. (authors)

  3. Effect of physical exertion on the biological monitoring of exposure to various solvents following exposure by inhalation in human volunteers: II. n-Hexane.

    Science.gov (United States)

    Tardif, Robert; Nadeau, Véronique; Truchon, Ginette; Brochu, Martin

    2007-07-01

    This study evaluated the impact of physical exertion on two n-hexane (HEX) exposure indicators in human volunteers exposed under controlled conditions in an inhalation chamber. A group of four volunteers (two women, two men) were exposed to HEX (50 ppm; 176 mg/m(3)) according to several scenarios involving several periods when volunteers performed either aerobic (AERO), muscular (MUSC), or both AERO/MUSC types of exercise. The target intensities for 30-min exercise periods separated by 15-min rest periods were the following: REST, 50W AERO [time-weighted average intensity including resting period (TWAI): 38W], 50W AERO/MUSC (TWAI: 34W), 100W AERO/MUSC (TWAI: 63W), and 100W AERO (TWAI: 71W) for 7 hr (two 3-hr exposure periods separated by 1 hr without exposure) and 50W MUSC for 3 hr (TWAI: 31W). Alveolar air and urine samples were collected at different time intervals before, during, and after exposure to measure unchanged HEX in expired air (HEX-A) and urinary 2,5-hexanedione (2,5-HD). HEX-A levels during exposures involving AERO activities (TWAI: 38W and 71W) were significantly enhanced (approximately +14%) compared with exposure at rest. MUSC or AERO/MUSC exercises were also associated with higher HEX-A levels but only at some sampling times. In contrast, end-of-exposure (7 hr) urinary 2,5-HD (mean +/- SD) was not modified by physical exertion: 4.14 +/- 1.51 micromol/L (REST), 4.02 +/- 1.52 micromol/L (TWAI 34W), 4.25 +/- 1.53 micromol/L (TWAI 38W), 3.73 +/- 2.09 micromol/L (TWAI 63W), 3.6 +/- 1.34 micromol/L (TWAI 71W) even though a downward trend was observed. Overall, this study showed that HEX kinetics is practically insensitive to moderate variations in workload intensity; only HEX-A levels increased slightly, and urinary 2,5-HD levels remained unchanged despite the fact that all types of physical exercise increased the pulmonary ventilation rate.

  4. A photogrammetric DEM of Greenland based on 1978-1987 aerial photos: validation and integration with laser altimetry and satellite-derived DEMs

    DEFF Research Database (Denmark)

    Korsgaard, Niels Jákup; Kjær, Kurt H.; Nuth, Christopher

    Here we present a DEM of Greenland covering all ice-free terrain and the margins of the GrIS and local glaciers and ice caps. The DEM is based on the 3534 photos used in the aero-triangulation which were recorded by the Danish Geodata Agency (then the Geodetic Institute) in survey campaigns...... spanning the period 1978-1987. The GrIS is covered tens of kilometers into the interior due to the large footprints of the photos (30 x 30 km) and control provided by the aero-triangulation. Thus, the data are ideal for providing information for analysis of ice marginal elevation change and also control...

  5. Inter comparison of two commercially available SODARS

    DEFF Research Database (Denmark)

    Ejsing Jørgensen, Hans; Antoniou, I.

    2002-01-01

    In the present work two SODARs of the phased array type are compared indirectly using the top anemometer readings from the Risoe 125m instrumented meteorology mast. The two SODARs are the AeroVironment 4000 and the Metek DSDPA.90-24.......In the present work two SODARs of the phased array type are compared indirectly using the top anemometer readings from the Risoe 125m instrumented meteorology mast. The two SODARs are the AeroVironment 4000 and the Metek DSDPA.90-24....

  6. Aerosol Characteristics on the Alboran Sea, 9-18 October 1982

    Science.gov (United States)

    1983-12-01

    filter-out scatter due to local aero- sol sources, passing clouds or measurement error and to provide a single value for correlation with meteorological...ifi OCTOBER 17,1982 _:.i0 20 Figure 43: Aero sol Concentrations at Three Size Intervals, 17 October 1982 7S Ul u a: D- J0& .S«a SaJt____...09501 COMFLTAIR, MEDITERRANEAN ATTN: NSAP SCIENCE ADVISOR CODE 03A FPO NEW YORK 09521 COMMANDING OFFICER 31 OCEANO . DEV. SQDN 8-VXN-8 NAVAL AIR

  7. Variations of atmospheric electric field and meteorological parameters in Kamchatka in 1997-2016

    Directory of Open Access Journals (Sweden)

    Smirnov Sergey

    2017-01-01

    Full Text Available Analysis of seasonal and annual variations of aero-electric field at a midlatitudinal observatory Paratunka in Kamchatka was carried out for 1997-2016. Stable seasonal intervals of the highest and the lowest values are observed. Changeability of the annual trend of aero-electric field in the near ground air layer at the observatory located in an active geodynamic region is shown. A large positive trend was changed by a smooth negative one. It is likely to be associated either with radon emanation intensity change in the observatory region or with volcanic activity change in Kamchatka.

  8. Radioactive Contamination Estimation from micro-copters or helicopter Airborne survey: Simulation and real measurements

    International Nuclear Information System (INIS)

    Halevy, I.; Ghelman, M.; Yehuda-Zada, Y.; Manor, A.; Dadon, S.; Sharon, A.; Yaar, I.

    2014-01-01

    One of the main advantages of acquiring aero-radiometric measurements lies in the high collection rate of data over large areas and rough terrain. Typical aero-radiometric system records and saves gamma ray spectrum, correlated with the GPS derived location information in regular time intervals of one to two seconds. Such data can be used to locate radiation anomalies on the ground, map ground contamination or track a radioactive airborne plume. Acquiring spectral data of this type allows separation of natural radioactivity from that of man-made sources and identification of specific isotopes, natural or man-made

  9. Radioactive Contamination Estimation from Micro-Copters or Helicopter Airborne Survey: Simulation and Real Measurements

    International Nuclear Information System (INIS)

    Halevy, I.; Ghelman, M.; Yehuda-Zada, Y.; Manor, A.; Sharon, A.; Yaar, I.

    2014-01-01

    One of the main advantages of acquiring aero-radiometric measurements lies in the high collection rate of data over large areas and rough terrain. Typical aero-radiometric system records and saves gamma ray spectrum, correlated with the GPS derived location information in regular time intervals of one to two seconds. Such data can be used to locate radiation anomalies on the ground, map ground contamination or track a radioactive airborne plume. Acquiring spectral data of this type allows separation of natural radioactivity from that of man-made sources and identification of specific isotopes, natural or man-made

  10. Shape Optimization of Wind Turbine Blades

    DEFF Research Database (Denmark)

    Wang, Xudong; Shen, Wen Zhong; Zhu, Wei Jun

    2009-01-01

    of the rotor. The design variables used in the current study are the blade shape parameters, including chord, twist and relative thickness. To validate the implementation of the aerodynamic/aero-elastic model, the computed aerodynamic results are compared to experimental data for the experimental rotor used...... in the European Commision-sponsored project Model Experiments in Controlled Conditions, (MEXICO) and the computed aero-elastic results are examined against the FLEX code for flow post the Tjereborg 2 MW rotor. To illustrate the optimization technique, three wind turbine rotors of different sizes (the MEXICO 25 k...

  11. Susceptibility of different life stages of Tribolium confusum to pyrethrin aerosol: effects of a flour food source on insecticidal efficacy

    Science.gov (United States)

    Accumulated grain dust and flour residues in flour mills can potentially decrease the efficacy of contact insecticides used for control of adult and immature stages of stored product insects. A study was conducted to evaluate the effects of flour residues on the efficacy of synergized pyrethrin aero...

  12. Rifte Guaritas basin compartmentation in Camaqua

    International Nuclear Information System (INIS)

    Preissler, A; Rolim, S; Philipp, R.

    2010-01-01

    The study contributes to the knowledge of the tectonic evolution of the Guaritas rift basin in Camaqua. Were used aero magnetic geophysical data for modeling the geometry and the depth of the structures and geological units. The research was supported in processing and interpretation of Aster images (EOS-Terra), which were extracted from geophysical models and digital image

  13. Incidental findings of thyroid tissue in cervical lymph nodes: old controversy not yet resolved?

    NARCIS (Netherlands)

    Triantafyllou, A.; Williams, M.D.; Angelos, P.; Shah, J.P.; Westra, W.H.; Hunt, J.L.; Devaney, K.O.; Rinaldo, A.; Slootweg, P.J.; Gnepp, D.R.; Silver, C.; Ferlito, A.

    2016-01-01

    The clinical significance of papillary or follicular thyroid tissue incidentally discovered in cervical lymph nodes during pathological assessment of neck dissections for non-thyroid cancers of the upper aero-digestive tract is critically reviewed. Special emphasis is given to controversies over

  14. CrossTalk: The Journal of Defense Software Engineering. Volume 22, Number 5, July/August 2009

    Science.gov (United States)

    2009-08-01

    acceptance comes an increase in churn and turmoil— as well as budget overruns, canceled pro- jects, and delays. Still, far too many pro- jects fail to...agement positions for more than a decade in telecommunication , IT, aero- space, and transportation. A measure- ment practitioner who has worked for Fortune

  15. Optimized Breech Location in the Harry Diamond Laboratories 4-Inch Gas Gun

    Science.gov (United States)

    1982-04-01

    equation can be deduced from the program, it is camouflaged by changes in notation and is repeated here. PAY/ Ma2 = [u-N/(N +1)](1 —u/N)1 + N/(N + 1...AERO-ASTRONAUTICAL ENGINEERING ATTN PROF TING YI LI 2036 NEIL AVENUE COLUMBUS, OH 43210 OCEANICS, INC ATTN DR. PAUL KAPLAN PLAINVIEW LONG ISLAND

  16. Wind and waves in extreme hurricanes

    NARCIS (Netherlands)

    Holthuijsen, L.H.; Powell, M.D.; Pietrzak, J.D.

    2012-01-01

    Waves breaking at the ocean surface are important to the dynamical, chemical and biological processes at the air-sea interface. The traditional view is that the white capping and aero-dynamical surface roughness increase with wind speed up to a limiting value. This view is fundamental to hurricane

  17. Russia’s Second Wind in Latin America

    Science.gov (United States)

    2011-08-18

    SOV, April 26, 2011 25 “Interview With the head of the Rosoboroneksport Delegation to the Latin American Aero Defense (LAAD) Fair in Rio de Janeiro ...Solimões for about $1 billion. This project comprises 21 exploration blocks over an area of about 48,000 square kilometers in the Solimões river

  18. Design Optimization of a 5 MW Floating Offshore Vertical-axis Wind Turbine

    DEFF Research Database (Denmark)

    Schmidt Paulsen, Uwe; Aagaard Madsen, Helge; Hattel, Jesper Henri

    2013-01-01

    calculations in ANSYS software. The selected profiles are used in the aero dynamic simulation. Furthermore the simulation code will be demonstrated to show the fully development model, integrating the simulation of turbulent wind inflow, actuator cylinder flow model, power controls, hydraulic floater...

  19. A fully coupled method for numerical modeling and dynamic analysis of floating vertical axis wind turbines

    DEFF Research Database (Denmark)

    Cheng, Zhengshun; Aagaard Madsen, Helge; Gao, Zhen

    2017-01-01

    •Aerodynamic modeling of floating VAWTs is established using the Actuator Cylinder (AC) flow method.•A fully coupled aero-hydro-servo-elastic simulation tool, i.e. SIMO-RIFLEX-AC, is developed for floating VAWTs.•The developedsimulation tool is verified to be accurate by a series of code-to-code ...

  20. Integrated simulation challenges with the DeepWind floating vertical axis wind turbine concept

    DEFF Research Database (Denmark)

    Verelst, David; Aagaard Madsen, Helge; Borg, Michael

    2015-01-01

    This paper presents the experiences and challenges with concurrently carrying out numerical model development, integrated simulations and design of a novel floating vertical axis wind turbine, the DeepWind concept. The floating VAWT modelling capabilities of the aero-hydro-elastic HAWC2 simulation...

  1. 2004 Alaska Lidar Mapping

    Data.gov (United States)

    National Oceanic and Atmospheric Administration, Department of Commerce — The data sets are generated using the OPTECH ALTM 70 kHz LIDAR system mounted onboard AeroMap's twin-engine Cessna 320 aircraft. Classified data sets such as this...

  2. Barrier Systems

    NARCIS (Netherlands)

    Heteren, S. van

    2015-01-01

    Barrier-system dynamics are a function of antecedent topography and substrate lithology, Relative sea-level (RSL) changes, sediment availability and type, climate, vegetation type and cover, and various aero- and hydrodynamic processes during fair-weather conditions and extreme events. Global change

  3. CSIR ScienceScope: Aerospace

    CSIR Research Space (South Africa)

    CSIR

    2006-12-01

    Full Text Available gas turbine technology smartens up future aircraft ................29 CSIR activities in light detection and ranging ..............................31 CSIR expertise to contribute to environmentally friendly aircraft aero-engine design... aerofoils for best performance ....................................9 Research in support of flutter-free aircraft ....................................10 CSIR moves into civil aviation research ......................................11 Acumen in advanced...

  4. DEMONSTRATION OF NO-VOC/NO-HAP WOOD FURNITURE COATING SYSTEM

    Science.gov (United States)

    The United States Environmental Protection Agency has contracted with AeroVironment Environmental Services, Inc. and its subcontractor, Adhesives Coating Co., to develop and demonstrate a no-VOC (volatile organic compound)/no-HAP (hazardous air pollutant) wood furniture coating s...

  5. The United States Air Force Expeditionary Center: Airpower from the Ground Up

    Science.gov (United States)

    2010-01-01

    On the bookshelf of the Air Force’s advanced training capabilities, the USAF photo Expeditionary Airmen of the 96th Aero Squadron, American...bookends of this bookshelf is the ability to evolve with the speed of change and thus remain relevant to Airmen charged with over-the-horizon global

  6. A Study of an Effective Offsets Model for Korea

    Science.gov (United States)

    2013-12-01

    Defense and Space EISD Excess Inventory Sales Division EU European Union FMS Foreign Military Sale ISDEFE Ingenieria de Sistemas para la Defensa de ...transfer, including aero-electronic software source code, components purchases, and logistics supply. When EADS recognized its lack of competitiveness

  7. Finnairi streik jätkub / Sirje Rank

    Index Scriptorium Estoniae

    Rank, Sirje, 1966-

    2006-01-01

    Lennufirma Finnair kabiinipersonal streikis firma plaani vastu palgata 500 töötajat oma Eesti tütarfirma Aero Airlines kaudu. Palgakõnelused lahendust ei leidnud. Lisa: Täna neli lendu. Vt. samas: Eesti Post kannatas streigi tõttu; Lemmi Kann. Reisijad üritasid Tallinnas pileteid ümber vahetada; Eesti stjuardessid kauplevad palgatõusu

  8. Flow-induced noise around the a-pillar of an idealized car greenhouse

    NARCIS (Netherlands)

    Snellen, M.; Lier, L.J. van; Rops, C.; Janssens, M.H.A.; Heck, J. van; Strumolo, G.S.

    2002-01-01

    Due to the successes in reducing motor and tire noise as perceived inside cars and trucks, aerodynamically generated noise becomes more and more important. Some time ago the study of aero-acoustics in and around these vehicles was mainly done by wind tunnel test. Nowadays, computational methods

  9. Assessment of autonomous phase unwrapping of isochromatic ...

    Indian Academy of Sciences (India)

    An excellent summary of phase unwrapping techniques applied to ... to fully exploit the advantage of these new developments, in this paper, ..... Madhu K R, Ramesh K 2007 New boundary information encoding and auto ... Ramesh K, Mangal S K 1999 Phase-shifting calculations in 2-D photoelasticity: revisited. J. Aero-.

  10. Fulltext PDF

    Indian Academy of Sciences (India)

    THOLASI

    ing coe± cient,new sti®nesscoe± cient,and new external ... sign lim itations. O ne m ust then take recourse to auto- m atic feedback ..... akn@aero.iitb.ac.in. 1 Refer to work ... tive control techniques for those w ishing to dig deeper into this sub ...

  11. v Micro vegetab obiolog bles so gical q old in J uality Jimma and sa ...

    African Journals Online (AJOL)

    sunny

    cci and aero ..... These were carried out by Gram staining techniques and observing .... horse cart (26.7%), car (23.3%) and humans back ...... Microbiology. The Benjamin puplishing co. Ic., New. York, USA. pp. 274-278. Trias R, Bañeras L, ...

  12. 32 CFR 855.16 - Parking and storage.

    Science.gov (United States)

    2010-07-01

    ... time that an aircraft spends on an installation is at the discretion of the installation commander or a... permitted on a nonexclusive, temporary, or intermittent basis, when compatible with military requirements... consistent with aero club policies. Any such permission may be revoked upon notice, based on military needs...

  13. Effect of complexones and tensides on selectivity of nitrogen dioxide determination in air with a chemiluminescence aerosol detector

    Czech Academy of Sciences Publication Activity Database

    Mikuška, Pavel; Večeřa, Zbyněk

    2000-01-01

    Roč. 410, 1-2 (2000), s. 159-165 ISSN 0003-2670 R&D Projects: GA ČR GA203/98/0943 Grant - others:COPERNICUS(BE) SUB-AERO EVK2-1999-000327 Subject RIV: CB - Analytical Chemistry, Separation Impact factor: 1.849, year: 2000

  14. Altimeter data assimilation in the tropical Indian Ocean using water ...

    Indian Academy of Sciences (India)

    vide a state analysis of the system which is bet- ter than could be ... strated the power of the correlation technique of. Ezer and Mellor ... resolution has been set to nested grid with finer resolution of ... in the model for converting wind to wind stress using bulk aero- .... drostatic connection between change in surface. Figure 3.

  15. Pop nädal : popuudised. Plaadid. Top 20 DAC Deutsche Alternative Charts singlid / Aivar Meos

    Index Scriptorium Estoniae

    Meos, Aivar

    2002-01-01

    Jean Michel Jarre uuest kontsertprojektist "Aero" ja samanimelisest albumist. Inglise kitarripopparite Jesus Jones'i uuest singlist "Come On Home", hitikogumikust "Never Enough" ja kontserttuurist koos DVDga. Suri 34-aastane bändi Alice in Chains juhtfiguur, laulja ja kitarrist Layne Staley. Filmimuusika heliplaadist "The Royal Tenenbaums"

  16. Joint Department of Defense, Advance Planning Briefing to Industry, Held at Kissimmee, Florida, on 30 April - 2 May 1996

    Science.gov (United States)

    1996-05-01

    Systems 17 Motion Bases Upgraded Aero Misc > Contact Info • AMC, Lt Col Letica , Phone (618) 256-5696 L8 Upgrade Flow Plan Advance Planning Briefing...Projected Schedule: FY 05 > Requirement Document: AMMP >• Projected Program Size: ? < $40M > Funding Status/Stability: > POCs: • AMC, Lt Col Letica

  17. Effects of processing variables on the sensitometric properties of Eastman Kodak film type 2445

    Science.gov (United States)

    Weinstein, M. S.

    1972-01-01

    The sensitometric characteristics of Kodak color negative film Type 2445 with processing in a 1411 versamat with Kodak aero-neg. color process chemicals are described. These characteristics were determined for various combinations of machine speed, prehardener temperature, and first developer temperature.

  18. Determination of nitrate in water by flow-injection analysis

    Czech Academy of Sciences Publication Activity Database

    Mikuška, Pavel; Večeřa, Zbyněk

    2001-01-01

    Roč. 8, č. 1 (2001), s. 115-120 ISSN 1231-7098 R&D Projects: GA ČR GA203/98/0943 Grant - others:COPERNICUS(BE) SUB-AERO EVK2-1999-000327 Institutional research plan: CEZ:AV0Z4031919 Keywords : nitrate * chemiluminescence * water Subject RIV: CB - Analytical Chemistry, Separation

  19. rights reserved Geophysical Identification of Hydrothermally Altered ...

    African Journals Online (AJOL)

    ADOWIE PERE

    the pole to the magnetic data aided in mapping of various hydrothermally altered structures that may favour gold mineralisation. The interpretation of the aero data set has enhanced a lot of ... water serves as a concentrating, transporting and depositing agent through faults (structures) to the earth's surface. Hydrothermal ...

  20. Design of a facility for studying shock-cell noise on single and coaxial jets

    NARCIS (Netherlands)

    Guariglia, Daniel; Rubio Carpio, A.; Schram, Christophe

    2018-01-01

    Shock-cell noise occurs in aero-engines when the nozzle exhaust is supersonic and shock-cells are present in the jet. In commercial turbofan engines, at cruise, the secondary flow is often supersonic underexpanded, with the formation of annular shock-cells in the jet and consequent onset of