Direct Lyapunov-based control law design for spacecraft attitude maneuvers  

作　　者：HU Likun WANG Qingchao 

机构地区：[1]School of Astronautics, Harbin Institute of Technology, Harbin 150001, China

出　　处：《Progress in Natural Science:Materials International》2006年第11期1188-1192,共5页自然科学进展·国际材料（英文版）

基　　金：Supported by National Natural Science Foundation of China (Grant No .60274002)

摘　　要：A direct Lyapunov-hased control law is presented to perform on-orbit stability for spacecraft attitude maneuvers. Spacecraft attitude kinematic equations and dynamic equations are coupled, nonlinear, multi-input multi-output（MIMO）, which baffles controller design. Orbit angular rates are taken into account in kinematic equations and influence of gravity gradient moments and disturbance moments on the spacecraft attitude in dynamic equations is considered to approach the practical environment, which enhance the problem complexity to some extent. Based on attitude tracking errors and angular rates, a Lyapunov function is constructed, through which the stabilizing feedback control law is deduced via Lie derivation of the Lyapunov function. The proposed method can deal with the ease that the spacecraft is subjected to mass property variations or eentroidal inertia matrix variations due to fuel assumption or flexibility, and disturbanee moments, which shows the proposed controller is robust for spacecraft attitude maneuvers. The unlimited controller and the limited controller are taken into account respectively in simulations. Simulation results are demonstrated to validate effectiveness and feasibility of the proposed method.A direct Lyapunov-based control law is presented to perform on-orbit stability for spacecraft attitude maneuvers. Spacecraft attitude kinematic equations and dynamic equations are coupled, nonlinear, multi-input multi-output(MIMO), which baffles controller design. Orbit angular rates are taken into account in kinematic equations and influence of gravity gradient moments and disturbance moments on the spacecraft attitude in dynamic equations is considered to approach the practical environment, which enhance the problem complexity to some extent. Based on attitude tracking errors and angular rates, a Lyapunov function is constructed, through which the stabilizing feedback control law is deduced via Lie derivation of the Lyapunov function. The proposed method can deal with the case that the spacecraft is subjected to mass property variations or centroidal inertia matrix variations due to fuel assumption or flexibility, and disturbance moments, which shows the proposed controller is robust for spacecraft attitude maneuvers. The unlimited controller and the limited controller are taken into account respectively in simulations. Simulation results are demonstrated to validate effectiveness and feasibility of the proposed method.

关 键 词：spacecraft attitude control direct Lyapunov function nonlinear control Lie derivative 

分 类 号：V448[航空宇航科学与技术—飞行器设计]