飞轮安装偏差的过驱动航天器有限时间姿态控制  

Finite time attitude control for over-activated spacecraft with reaction wheel misalignment

作　　者：张爱华[1,2] 胡庆雷[1] 霍星[1,2] 

机构地区：[1]哈尔滨工业大学航天学院,哈尔滨150001 [2]渤海大学工学院,辽宁锦州121001

出　　处：《控制与决策》2014年第1期27-32,共6页Control and Decision

基　　金：国家自然科学基金项目(61304149;61273175);教育部新世纪优秀人才计划项目(NCET-11-0801);中央高校基本科研业务费专项资金项目(HIT.BRETIII.201212);黑龙江省青年科学基金项目(QC2012C024)

摘　　要：针对反作用飞轮安装存在偏差的过驱动航天器姿态跟踪问题,提出一种有限时间姿态补偿控制策略.通过设计自适应滑模控制器保证实现对不确定性转动惯量与外部干扰的鲁棒控制,同时实现对飞轮安装偏差的补偿控制,并应用Lyapunov稳定性理论证明了该控制器能够在有限时间内实现姿态跟踪控制.最后,将该控制器应用于某型航天器的姿态跟踪控制,仿真结果验证了所提出方法的有效性.A finite-time control scheme is presented to address the attitude tracking problem of over-actuated spacecraft, in which reaction wheel misalignment, external disturbance and uncertain mass of moment inertia are considered. A finite time controller using adaptive sliding mode control technique is developed. It can guarantee finite-time reachability of the given attitude motion even in the presence of external disturbance＇s, and uncertainties in the configuration matrix due to reaction wheel misaiignment and mass of moment inertia. Numerical simulation results of an application to spacecraft show the effectiveness of the proposed attitude tracking control law.

关 键 词：航天器 安装偏差 姿态控制 有限时间 自适应滑模控制 

分 类 号：TP273[自动化与计算机技术—检测技术与自动化装置]