轮控航天器的IMM自适应反步变结构容错控制  

IMM Based Adaptive Backstepping Variable Structure Fault-Tolerant Control for Spacecraft with Reaction Wheel Dynamics

作　　者：马广富[1] 王宇雷[1] 李传江[1] 张海博[1] 

机构地区：[1]哈尔滨工业大学控制工程系,哈尔滨150001

出　　处：《宇航学报》2011年第3期502-509,共8页Journal of Astronautics

基　　金：国家自然科学基金(60774062);CAST创新基金项目(20090604)

摘　　要：针对存在飞轮故障、转动惯量不确定性和干扰力矩的轮控航天器姿态机动问题,提出了一种基于交互多模型算法(IMM)的自适应反步变结构容错控制方法。该方法可以有效提高系统控制精度,保证航天器姿态机动误差收敛到系统平衡点的较小邻域;同时有效减小飞轮抖振,降低诊断不确定性对系统的影响。最后在Matlab/Simulink环境下对航天器姿态机动进行了仿真研究,结果表明了提出的控制算法在处理航天器姿态机动问题方面的有效性和可行性。A new adaptive backstepping variable structure control combined with interactive multiple model（IMM） method is proposed in this paper for the attitude maneuver problem of rigid spacecraft in the presence of actuator faults,uncertainties of moment of inertia and external disturbance torques.The algorithm can guarantee attitude maneuver errors converged to a small set around the equilibrium point,limit the chatter of variable structure control caused by actuator faults and reduce the impact of diagnostical uncertainty on system.By using Matlab/Simulink programming,modeling and simulation of spacecraft attitude maneuver are also discussed in the paper.Simulation results demonstrate the effectiveness and feasibility of the proposed control algorithm.

关 键 词：姿态机动 容错控制 自适应反步变结构控制 交互多模型 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]