A finite-time control scheme for autonomous body-fixed hovering of a rigid spacecraft over a tumbling asteroid is presented. The relative configuration between the spacecraft and asteroid is described in terms of exponential coordinates on the Lie group SE(3), which is the configuration space for the spacecraft. With a Lyapunov stability analysis, the finite-time convergence of the proposed control scheme for the closed-loop system is proved. Numerical simulations validate the performance of the proposed control scheme.
Finite-time control for spacecraft body-fixed hovering over an asteroid
IEEE Transactions on Aerospace and Electronic Systems ; 51 , 1 ; 506-520
2015-01-01
1636739 byte
Article (Journal)
Electronic Resource
English
Finite-Time Control for Body-Fixed Hovering of Rigid Spacecraft Over an Asteroid (AAS 14-221)
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