摘要
针对角速度陀螺故障的低轨三轴稳定卫星因角速度测量数据缺失而导致卫星姿态失控的问题,提出了一种红外地球敏感器修正的角动量反馈控制方法。该方法利用动量轮转速与卫星角速度之间的数值变化关系,以红外地球敏感器实测弦宽为基准,建立角动量反馈控制的最小二乘修正模型,并通过蒙特卡洛方法迭代出角动量反馈控制的最优系数,从而由卫星控制器件中反演出连续的卫星角速度信息,最终实现陀螺故障情况下的卫星三轴稳定姿态控制。仿真结果表明:所提方法能够准确建立动量轮角动量与卫星角速度之间的对应关系,使得卫星姿态控制的稳定性较好;从系统重组的角度为卫星的故障处理提供了新途径,且有效延长了卫星的使用寿命。
An angular momentum feedback control strategy with infrared earth sensor correction is proposed to solve losing control for low earth orbit satellite attitude due to the lost angular velocity measurement for the fault of angular velocity gyroscope. According to the relation between the changing angular velocity and that of momentum wheel on satellite, the least squares correction model of angular momentum feedback control is established based on chord length of infrared earth sensor and the optimal control coefficients are sought out by Monte Carlo algorithm. Then the angular velocity can be obtained from satellite control devices, and the information of satellite with angular velocity gyroscope fault is continuously recovered to realize three-axis-stabilized attitude control finally. It provides a new way for satellite fault treatment in terms of control system recombination to prolong the service life of satellite.
出处
《西安交通大学学报》
EI
CAS
CSCD
北大核心
2014年第4期115-118,共4页
Journal of Xi'an Jiaotong University
基金
国家自然科学基金资助项目(61179010)
关键词
角动量反馈
姿态控制
最小二乘方法
angular momentum feedback attitude control least squares estimation method
