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Adaptive control and stabilization of elastic spacecraft

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2 Author(s)
S. N. Singh ; Dept. of Electr. & Comput. Eng., Nevada Univ., Las Vegas, NV, USA ; A. D. de Araujo

This work treats the question of large angle rotational maneuver and stabilization of an elastic spacecraft (spacecraft-beam-tip body configuration). It is assumed that the parameters of the system are completely unknown. An adaptive control law is derived for the rotational maneuver of the spacecraft. Using the adaptive controller, asymptotically decoupled control of the pitch angle of the space vehicle is accomplished, however this maneuver causes elastic deformation of the beam connecting the orbiter and tip body. For the stabilization of the zero dynamics (flexible dynamics), a stabilizer is designed using elastic mode velocity feedback. In the closed-loop system including the adaptive controller and the stabilizer, reference pitch angle trajectory tracking and vibration suppression are accomplished. Simulation results are presented to show the maneuver capability of the control system

Published in:

IEEE Transactions on Aerospace and Electronic Systems  (Volume:35 ,  Issue: 1 )