Low-thrust orbit-raising trajectories considering eclipse constraints

dc.contributor.authorSreesawet, Suwat
dc.contributor.authorDutta, Atri
dc.date.accessioned2016-04-05T13:47:36Z
dc.date.available2016-04-05T13:47:36Z
dc.date.issued2015
dc.descriptionClick on the link to access the article (may not be free).en_US
dc.description.abstractMany-revolution electric orbit-raising trajectories make numerous passages through the shadow of the Earth. The paper presents a new algorithm to determine the minimum-time trajectory of the spacecraft during orbit-raising. Standard two-body problem and cylindrical shadow model are assumed. The proposed methodology breaks the minimum-time orbit-raising problem into a series of optimization sub-problems, with each sub-problem attempting to maximize the proximity to the Geostationary orbit at the end of the time horizon. We present results for planar and non-planar orbit-raising scenarios and demonstrate the benefits of the algorithm.en_US
dc.identifier.citationSreesawet, Suwat; Dutta, Atri. 2015. Low-thrust orbit-raising trajectories considering eclipse constraints. Advances in the Astronautical Sciences Spaceflight Mechanics, vol. 155:pp 1341-1355en_US
dc.identifier.isbn978-0-87703-623-4
dc.identifier.issn1081-6003
dc.identifier.otherWOS:000371647200080
dc.identifier.urihttp://www.univelt.com/book=5132
dc.identifier.urihttp://hdl.handle.net/10057/11996
dc.language.isoen_USen_US
dc.publisherUnivelt, Inc.en_US
dc.relation.ispartofseriesAdvances in the Astronautical Sciences Spaceflight Mechanics;v.155
dc.rights.holderCopyright © 2010, Univelt, Inc. All rights reserved.en_US
dc.subjectElectric propulsionen_US
dc.subjectTransfersen_US
dc.subjectDesignen_US
dc.titleLow-thrust orbit-raising trajectories considering eclipse constraintsen_US
dc.typeConference paperen_US
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