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Williamson, W.E.
Sandia Labs., Albuquerque, N.Mex. (USA)1976
Sandia Labs., Albuquerque, N.Mex. (USA)1976
AbstractAbstract
[en] The NRV (Nosetip Recovery Vehicle) program at Sandia Laboratories is designed to recover the nose section from a sphere cone reentry vehicle after it has flown a near ICBM reentry trajectory. Both mass jettison and parachutes are used to reduce the velocity of the RV near the end of the trajectory to a sufficiently low level that the vehicle may land intact. The design problem of determining mass jettison time and parachute deployment time in order to ensure that the vehicle does land intact is considered. The problem is formulated as a min-max optimization problem where the design parameters are to be selected to minimize the maximum possible deviation in the design criteria due to uncertainties in the system. The results of the study indicate that the optimal choice of the design parameters ensures that the maximum deviation in the design criteria is within acceptable bounds. This analytically ensures the feasibility of recovery for NRV
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1976; 7 p; AIAA atmospheric flight mechanics conference; Dallas, Texas, United States of America (USA); 7 Jun 1976; CONF-760606--1; Available from NTIS; Available from NTIS. $3.50.
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AbstractAbstract
No abstract available
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European Space Agency ESA, Paris (France); 113 p; 2009; p. 28; Workshop on Cross-Scale Coupling in Plasmas; Rende, Cosenza (Italy); 9-11 Mar 2009; Available from http://www.fis.unical.it/astroplasmi/cross-scale/abstract_book/abstract_book.pdf
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AbstractAbstract
No abstract available
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Science and technology series, Volume 30; 1973; 529 p; American Astronautical Society; Tarzana, CA; Meeting of the American Association for the Advancement of Science; Washington, District of Columbia, USA; 27 Dec 1972; CONF-721236--
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AbstractAbstract
[en] Electron sources can be used to control the potential of spacecraft and rockets. The plasma current collected by these bodies can be measured; the average value of the emitted current gives information about the density and temperature of the ambient medium. It is shown that in addition, the fluctuation of this current can disclose the existence of waves propagated in the surrounding plasma
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European Space Agency, 92 - Neuilly-sur-Seine (France); p. 221-226; 1976; p. 221-226; 3. Symposium on European programmes on sounding-rocket and balloon research in the auroral zone; Schloss Elmau, Germany, F.R; 3 - 7 May 1976; Published by ESA Scientific and Technical Publications Branch, ESTEC, Noordwijk, the Netherlands
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Luchkov, B.I.; Markin, P.D.
Scientific session of NRNU MEPHI-2013. Abstracts. In three volumes. Volume 2. Problems of fundamental science. Strategic information technologies2013
Scientific session of NRNU MEPHI-2013. Abstracts. In three volumes. Volume 2. Problems of fundamental science. Strategic information technologies2013
AbstractAbstract
No abstract available
Original Title
Blizkie zvezdy kak istochniki gamma-vspleskov
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Source
Ministerstvo Obrazovaniya i Nauki Rossijskoj Federatsii, Moscow (Russian Federation); Gosudarstvennaya Korporatsiya po Atomnoj Ehnergii Rosatom, Moscow (Russian Federation); Natsional'nyj Issledovatel'skij Yadernyj Univ. MIFI, Moscow (Russian Federation); 364 p; ISBN 978-5-7262-1787-1;
; 2013; p. 123; Scientific session of NRNU MEPHI-2013; Nauchnaya sessiya NIYaU MIFI-2013; Moscow (Russian Federation); 2013

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Lai, Shu T
CERN - European Organization for Nuclear Research, Geneva (Switzerland)
Proceedings of Joint INFN-CERN-EuCARD-AccNet Workshop on Electron-Cloud Effects2013
CERN - European Organization for Nuclear Research, Geneva (Switzerland)
Proceedings of Joint INFN-CERN-EuCARD-AccNet Workshop on Electron-Cloud Effects2013
AbstractAbstract
[en] This paper presents an overview of the roles played by incoming and outgoing electrons in spacecraft surface and stresses the importance of surface conditions for spacecraft charging. The balance between the incoming electron current from the ambient plasma and the outgoing currents of secondary electrons, backscattered electrons, and photoelectrons from the surfaces determines the surface potential. Since surface conditions significantly affect the outgoing currents, the critical temperature and the surface potential are also significantly affected. As a corollary, high level differential charging of adjacent surfaces with very different surface conditions is a space hazard. (author)
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Source
Cimino, R; Rumolo, Giovanni; Zimmermann, Frank (European Organization for Nuclear Research, Geneva (Switzerland)) (eds.); CERN - European Organization for Nuclear Research, Geneva (Switzerland); 286 p; ISBN 978-92-9083-386-4;
; 2013; p. 165-168; Joint INFN-CERN-EuCARD-AccNet Workshop on Electron-Cloud Effects; La Biodola, Isola d'Elba (Italy); 5-9 Jun 2012; ISSN 0007-8328;
; Available on-line: http://cds.cern.ch/record/1601947/files/arXiv:1309.4660.pdf; Available on-line: http://cds.cern.ch/record/1529710/files/arXiv:1403.3292.pdf; Country of input: International Atomic Energy Agency (IAEA); DOI: 10.5170/CERN-2013-002.165; Copyright (c) 2013 CERN; This is an open access publication distributed under the terms of the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.


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McDowell, J.L.; Williamson, W.E. Jr.
Sandia National Labs., Albuquerque, NM (USA)1982
Sandia National Labs., Albuquerque, NM (USA)1982
AbstractAbstract
[en] Two different mathematical models are used to estimate the aerodynamic coefficients for a reentry vehicle. One model assumes that the aerodynamic coefficients are symmetric and the other does not. An actual reentry vehicle develops an asymmetric shape as the heatshield and nosetip ablate. A comparison of the two models is made as a function of the aerodynamic asymmetry to illustrate the errors made in using the symmetric model when the aerodynamics are asymmetric. The asymmetric model is shown to always be capable of correctly estimating the asymmetric aerodynamic coefficients for the simulations considered in this paper
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1982; 8 p; AIAA atmospheric flight mechanics conference; San Diego, CA (USA); 9 - 11 Aug 1982; CONF-820805--2; Available from NTIS., PC A02/MF A01 as DE82020037
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Hickey, J.R.; Griffin, F.J.
Eppley Lab., Inc., Newport, RI (USA)1984
Eppley Lab., Inc., Newport, RI (USA)1984
AbstractAbstract
[en] In-flight calibration for the solar and Earth flux channels was examined. Earth Radiation on Budget (ERB) channel components were exposed to the space environment and then retrieved and resubmitted to radiometric calibration after exposure. It is suggested that corrections may be applied to ERB results and information will be obtained to aid in the selection of components for future operational solar and Earth radiation budget experiments. To assure that these high accuracy devices are measuring real variations and are not responding to changes induced by the space environment, it is desirable to test such devices radiometrically after exposure to the best approximation of the orbital environment
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Feb 1984; 3 p; Available from NTIS, PC A09/MF A01
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AbstractAbstract
No abstract available
Source
Annual conference on nuclear and space radiation effects; Seattle, Washington, USA; 24 Jul 1972; See CONF-720707--.
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Journal Article
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IEEE (Inst. Elec. Electron. Eng.), Trans. Nucl. Sci; v. NS-19(6); p. 156-159
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Orth, C.D.
Lawrence Livermore National Lab., CA (United States). Funding organisation: USDOE, Washington, DC (United States)1998
Lawrence Livermore National Lab., CA (United States). Funding organisation: USDOE, Washington, DC (United States)1998
AbstractAbstract
[en] In this paper, we indicate how the great advantages that ICF offers for interplanetary propulsion can be accomplished with the VISTA spacecraft concept. The performance of VISTA is expected to surpass that from other realistic technologies for Mars missions if the energy gain achievable for ICF targets is above several hundred. Based on the good performance expected from the U. S. National Ignition Facility (NIF), the requirements for VISTA should be well within the realm of possibility if creative target concepts such as the fast ignitor can be developed. We also indicate that a 6000-ton VISTA can visit any planet in the solar system and return to Earth in about 7 years or less without any significant physiological hazards to astronauts. In concept, VISTA provides such short-duration missions, especially to Mars, that the hazards from cosmic radiation and zero gravity can be reduced to insignificant levels. VISTA therefore represents a significant step forward for space-propulsion concepts
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20 Apr 1998; 15 p; 9. international conference on emerging nuclear energy systems (ICENES '98); Tel Aviv (Israel); 28 Jun - 2 Jul 1998; CONF-980659--; CONTRACT W-7405-ENG-48; W-7405-ENG-48; ALSO AVAILABLE FROM OSTI AS DE98058340; NTIS; US GOVT. PRINTING OFFICE DEP
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