摘要
针对航天器星体和快反镜两级系统中的快反镜指向控制误差问题,提出了一种快反镜闭环控制系统指向控制误差分析方法。首先,建立了带有高阶谐振的快反镜动力学模型,在考虑各影响因素的情况下设计了其闭环控制系统;然后,推导了各影响因素至快反镜指向的传递函数,并以各影响因素为输入进行仿真,研究其对快反镜指向控制误差的影响。仿真结果表明,快反镜指向总误差小于0.01″,星体指向误差和快反镜姿态测量误差是影响快反镜指向误差的主要因素。
To slove the problem of pointing control error of fine steering mirror in the two-stage system of base and fine steering mirror of spacecraft, an analytical method for the pointing control error of the closed-loop control system of fine steering mirror is presented in this paper. First, the dynamic model of fine steering mirror with high-order resonance is established and the closed-loop control system is designed considering various influencing factors. Then, the transfer function from each influencing factor to the pointing attitude of the fine steering mirror is derived, and the influence of each factor on the pointing control error of fine steering mirror is studied by using each factor as the input. The simulation results show that the total error of the fine steering mirror is less than 0.01″, and the base pointing error and the attitude measurement error are the main factors.
作者
冯甜甜
高晶敏
张科备
FENG Tiantian;GAO Jingmin;ZHANG Kebei(Beijing Information Science&Technology University,Beijing 100192,China;Beijing Institute of Control Engineering,Beijing 100190,China)
出处
《北京信息科技大学学报（自然科学版）》
2019年第1期28-33,共6页
Journal of Beijing Information Science and Technology University
基金
民用航天技术预先研究项目(D020103)
关键词
快反镜
闭环控制系统
指向控制误差
星体指向误差
姿态测量误差
fast steering mirror
closed-loop control system
pointing control error
base pointing error
attitude measurement error
