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|
|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|
|Publication status||Published - Nov 5 2006|