Abstract
This study deals with orbital transfer of a rigid satellite system into a specified orbit by using its inner force generated in the system. First, the governing equations of the system are shown, and their non-integrability is proven by applying a nonlinear control theory. Subsequently, it is also shown that the system is controllable except its pericenter and its apocenter in an elliptic orbit. Then, this paper proposes a two-step approach, combining a solution for a ‘chained’ system and numerical modification based on ‘motion planning.’ Finally, computational simulations verify that orbital transfer to a specified orbit is accomplished successfully by applying the proposed approach.
Translated title of the contribution | A Study on Orbital Transfer of a Rigid Satellite System Using Its Nonholonomic Constraint |
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Original language | Japanese |
Pages (from-to) | 477-484 |
Number of pages | 8 |
Journal | 日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences |
Volume | 54 |
Issue number | 634 |
DOIs | |
Publication status | Published - Nov 5 2006 |