基于非线性观测器的一种偏置动量卫星姿态控制方法  

Attitude Control for Momentum Biased Satellite Based on Nonlinear State Observer

作　　者：杨思亮[1] 徐世杰[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《航天控制》2009年第3期12-16,共5页Aerospace Control

摘　　要：研究一类交叉转动惯量较大的偏置动量卫星的姿态控制问题。根据卫星质量分布的特点进行适当简化,建立非线性动力学模型,并基于该模型设计一种非线性偏航观测器。利用该观测器的观测信息进行卫星的姿态控制。整个系统采用动量轮和反作用飞轮作为执行机构,同时卫星三轴均配置磁力矩器为动量轮和反作用飞轮卸载。数值仿真结果表明,在传统的控制方法中,惯量积的存在导致系统控制精度降低和偏航角稳态误差较大,文中提出的控制方案可以很好地完成这类卫星的姿态控制任务。Attitude control problem for a kind of momentum biased satellites with big product of inertia is discussed in this paper. Nonlinear dynamics equations are founded according to the inertia characteristics of the satellite. Based on the mathematics model, a nonlinear state observer is designed. The satellite takes momentum wheel and reaction wheels as actuators. Magnetic torque rods are used to remove the excessive momentum of wheels. The existence of the product of inertia causes low control accuracy in the traditional method. The control scheme proposed in this paper could complete this kind of attitude control missions very well. Numerical simulation results demonstrate the correctness and validity of this method.

关 键 词：姿态控制 偏置动量 非线性状态观测器 

分 类 号：V488.2[航空宇航科学技术]