Slewing maneuver control of flexible spacecraft by output feedback

Abstract

In this paper, control law design for single axis slewing maneuver of flexible spacecraft model is discussed. The control objective is attitude maneuver and simultaneous vibration control. Control law design is based upon the Lyapunov stability theory to achieve a stabilizing closed-loop system. Weighted combination of sub-structure energy is taken as a Lyapunov function to lead to a globally stabilizing controller. The approach in this study is an extension of previous studies with a different choice of Lyapunov function. The new controller provides extra degree of freedom in selecting feedback gain parameters to enhance closed-loop dynamic response. Estimation of the internal reaction torque between adjacent structures is discussed with simulation results.