Backstepping-based attitude maneuver control and active vibration reduction of flexible spacecraft

Abstract

A novel hybrid robust control design method is investigated for a three-axis-rotational maneuver and vibration stabilization of a spacecraft with flexible appendages. Based on the backstepping , a robust attitude control law is derived to control the attitude motion of spacecraft. For actively suppressing the induced vibration, strain rate feedback control methods are presented by using piezoelectric materials as additional sensors and actuators bonded on the surface of the flexible appendages. Numerical simulations demonstrate the feasibility and effectiveness of the control strategy. Index Terms -Flexible spacecraft; Backstepping; Attitude maneuvering.( )Then we introduce the following new variables: