Adaptive Feedback Linearization Control of a Flexible Spacecraft

Base on a kind of model estimator, this paper presents an adaptive feedback linearization control for the large-angle rotational maneuver and vibration suppression of a flexible spacecraft. The model estimator provides the approximate model information through the measure of system input variable, output variable (pitch angle) and its time derivative. The integral actions included can not only compensate of the entire dynamics of the system which is assumed to be unknown, but also ensure that the steady state error in the regulation of pitch angle is equal to zero. In addition, the control law is easy to implement. Simulation results are presented to show that, compared with differential geometric feedback linearization control and variable structure adaptive control, the adaptive feedback linearization control designed is superior in resisting external disturbances and adapting the uncertainties of system model. It improves robustness and adaptability of the flexible spacecraft attitude control systems greatly