This paper presents a means of near asteroid hovering of a rigid spacecraft in the asteroid body-fixed frame with parameter variations and external disturbances. An adaptive finite-time control scheme is proposed, where the upper bounds of the parametric uncertainties and disturbances are not required for controller design. The detailed design principles and a rigorous stability analysis are provided. Finally, a body-fixed hovering maneuver is employed in numerical simulation to verify the effectiveness of the proposed strategy.
Adaptive finite-time control for spacecraft hovering over an asteroid
IEEE Transactions on Aerospace and Electronic Systems ; 52 , 3 ; 1183-1196
2016-06-01
6215119 byte
Article (Journal)
Electronic Resource
English
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