Orbital control of satellite systems using nonholonomic control theory

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

抄録

This study deals with orbital control of a rigid dumbbell-type satellite system. While most of the previous works for orbital transfer aim at changing just one parameter of the orbital element or the orbital energy, in this study the system is transferred by using its inner force into a prescribed orbit defined as a set of orbital elements: semilatus rectum, eccentricity, and argument of pericenter. By applying nonlinear control theories, it is shown that the satellite system is controllable except its pericenter and its apocenter in the elliptic orbit. Then, this paper transforms the nonlinear governing equations into a canonical system, called 'a chained system', and demonstrates that a specified orbit is accomplished by appropriately shaped time histories of control inputs.

本文言語英語
ホスト出版物のタイトルAstrodynamics 2005 - Advances in the Astronautical Sciences - Proceedings of the AAS/AIAA Astrodynamics Conference
ページ1533-1544
ページ数12
出版ステータス出版済み - 2006
イベントAstrodynamics 2005 - Advances in the Astronautical Sciences - Proceedings of the AAS/AIAA Astrodynamics Conference - South Lake Tahoe, CA, 米国
継続期間: 8 7 20058 11 2005

出版物シリーズ

名前Advances in the Astronautical Sciences
123 II
ISSN(印刷版)0065-3438

その他

その他Astrodynamics 2005 - Advances in the Astronautical Sciences - Proceedings of the AAS/AIAA Astrodynamics Conference
国/地域米国
CitySouth Lake Tahoe, CA
Period8/7/058/11/05

All Science Journal Classification (ASJC) codes

  • 航空宇宙工学
  • 宇宙惑星科学

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