Control laws for orbital parameters of rigid satellite system considering nonholonomic constraint

Koki Fujita, Shinji Hokamoto

研究成果: Chapter in Book/Report/Conference proceedingConference contribution

抄録

This study deals with orbital control of a rigid coplanar dumbbell-type satellite system. While most of the previous work for orbital transfer aim at changing just one parameter of the orbital elements, by applying a nonlinear method, this study proposes two control laws to change an orbit into a prescribed one defined by its orbital elements: semi-major axis (equivalent to semilatus rectum), eccentricity and argument of pericenter. First controller is developed from a two-step approach combining a solution for a chained formed system and numerical modification based on motion planning. Another is a feedback controller, which can compensate model uncertainty or disturbance. These two controllers can be combined to a complementary control technique. The effectiveness of the proposed control laws are demonstrated through a series of numerical simulations.

本文言語英語
ホスト出版物のタイトルCollection of Technical Papers - AIAA Guidance, Navigation, and Control Conference 2007
出版社American Institute of Aeronautics and Astronautics Inc.
ページ5073-5085
ページ数13
ISBN(印刷版)1563479044, 9781563479045
DOI
出版ステータス出版済み - 2007
イベントAIAA Guidance, Navigation, and Control Conference 2007 - Hilton Head, SC, 米国
継続期間: 8 20 20078 23 2007

出版物シリーズ

名前Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference 2007
5

その他

その他AIAA Guidance, Navigation, and Control Conference 2007
国/地域米国
CityHilton Head, SC
Period8/20/078/23/07

All Science Journal Classification (ASJC) codes

  • 航空宇宙工学
  • 制御およびシステム工学
  • 電子工学および電気工学

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