Reachability Analysis of Planar Spacecraft Docking with Rotating Body in Close Proximity
2018; American Institute of Aeronautics and Astronautics; Volume: 41; Issue: 6 Linguagem: Inglês
10.2514/1.g003389
ISSN1533-3884
AutoresCostantinos Zagaris, Marcello Romano,
Tópico(s)Aerospace Engineering and Control Systems
ResumoNo AccessEngineering NoteReachability Analysis of Planar Spacecraft Docking with Rotating Body in Close ProximityCostantinos Zagaris and Marcello RomanoCostantinos ZagarisNaval Postgraduate School, Monterey, California 93943 and Marcello RomanoNaval Postgraduate School, Monterey, California 93943Published Online:2 Feb 2018https://doi.org/10.2514/1.G003389SectionsRead Now ToolsAdd to favoritesDownload citationTrack citations ShareShare onFacebookTwitterLinked InRedditEmail About References [1] Ma Z., Ma O. and Shashikanth B. N., "Optimal Control for Spacecraft to Rendezvous with a Tumbling Satellite in a Close Range," Proceedings of the 2006 IEEE/RSJ International Conference on Intelligent Robots and Systems, IEEE Publ., Piscataway, NJ, 2006, pp. 4109–4114. doi:https://doi.org/10.1109/IROS.2006.281877 Google Scholar[2] Boyarko G. 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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. TopicsControl TheoryGuidance, Navigation, and Control SystemsOptimal Control TheorySatellitesSpace Systems and VehiclesSpacecraft DesignSpacecraft DockingSpacecraft Guidance and ControlSpacecraft SystemSpacecrafts KeywordsSpacecraft DockingLinear Time InvariantOptimal ControlCartesian Coordinate SystemComputingSpacecraft RendezvousSpacecraft DynamicsSatellitesMATLABPDF Received16 October 2017Accepted21 December 2017Published online2 February 2018
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