Finite element dynamic modeling and attitude control for a slender flexible spacecraft

Abstract This paper aims to study the dynamic modeling and attitude control of a kind slender flexible spacecraft. The basic structure this spacecraft is different from traditional center rigid body with appendages, but bodies at both ends, which are connected by truss structure. Firstly, finite element method adopted establish model spacecraft, vibration frequency damping obtained. unconstrained modes obtained through mathematical analysis, analysis domain analysis. In addition, nonlinear sliding surface angular velocity constraint designed. On basis, an adaptive mode (ASM) controller proposed, stability close-loop system under proved, verified simulation.