Dynamics of a Satellite with Flexible Appendages in the Coulomb Interaction
2017; American Institute of Aeronautics and Astronautics; Volume: 41; Issue: 2 Linguagem: Inglês
10.2514/1.g002832
ISSN1533-3884
Autores Tópico(s)Astro and Planetary Science
ResumoNo AccessEngineering NoteDynamics of a Satellite with Flexible Appendages in the Coulomb InteractionVladimir S. AslanovVladimir S. AslanovSamara National Research University, 443086 Samara, Russia*Head, Theoretical Mechanics Department, 34 Moskovskoe Shosse; .Search for more papers by this authorPublished Online:12 Aug 2017https://doi.org/10.2514/1.G002832SectionsRead Now ToolsAdd to favoritesDownload citationTrack citations ShareShare onFacebookTwitterLinked InRedditEmail About References [1] Cover J. H., Knauer W. and Maurer H. A., “Lightweight Reflecting Structures Utilizing Electrostatic Inflation,” U.S. Patent 3,546,706, Oct. 1966. Google Scholar[2] King L. B., Parker G. G., Deshmukh S. and Chong J.-H., “Spacecraft Formation-Flying Using Inter-Vehicle Coulomb Forces,” NIAC (NASA Inst. for Advanced Concepts) Final Rept. for Phase 1, 2002. Google Scholar[3] King L. B., Parker G. 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Aslanov15 September 2019 | Journal of Guidance, Control, and Dynamics, Vol. 42, No. 12Exact solutions and adiabatic invariants for equations of satellite attitude motion under Coulomb torque27 September 2017 | Nonlinear Dynamics, Vol. 90, No. 4 What's Popular Volume 41, Number 2February 2018 CrossmarkInformationCopyright © 2017 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the ISSN 0731-5090 (print) or 1533-3884 (online) to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp. TopicsAerospace SciencesAstrodynamicsAstronauticsAttitude ControlOrbital PropertySatellitesSpace DebrisSpace OrbitSpace Systems and VehiclesSpacecrafts KeywordsSatellite PropulsionSpace DebrisKinetic EnergyFinite Element SolutionNumerical SimulationAttitude Control SystemNumerical IntegrationMathematical ModelsFormation FlyingTransverse VibrationsAcknowledgmentThis study was supported by the Russian Foundation for Basic Research (RFBR15-01-01456-A).PDF Received13 February 2017Accepted2 July 2017Published online12 August 2017
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