一种应用输入成型的敏捷卫星快速姿态机动控制方法  

Attitude Maneuver Control Method for Agile Satellite Based on Input Shaping

作　　者：周伟敏[1,2] 廖瑛[1] 杨雅君[1] 朱庆华 

机构地区：[1]国防科学技术大学航天科学与工程学院,长沙410073 [2]上海航天技术研究院,上海201109 [3]上海市空间智能控制技术重点实验室,上海201109 [4]上海航天控制技术研究所,上海201109

出　　处：《航天器工程》2016年第4期27-32,共6页Spacecraft Engineering

基　　金：国家重大航天工程

摘　　要：敏捷卫星对姿态机动能力的快速性和稳定性提出了更高的要求,为此,提出一种应用输入成型的卫星姿态机动控制方法。通过引入比例-微分(PD)反馈加力矩前馈的复合控制,以及采用输入成型器对规划的原始姿态路径控制指令进行调制,使卫星控制后期稳定度得到提高,并能有效抑制挠性部件的振动。数学仿真验证的结果表明:对卫星姿态机动路径的规划和输入成型调制,可以在实现快速机动的同时,有效抑制挠性结构振动,缩短姿态稳定时间,为有效载荷提供更多的可工作时间和高精度、高稳定度的工作环境。An agile satellite puts forward higher requirements for rapidity and stability of satellite attitude maneuver.This paper presents a satellite attitude maneuver control method based on input shaping.The rapidity of attitude maneuver is achieved by using path programming,and PD feedback control and maneuver moment forward control are adopted.Then,the programmed control signals are modulated by input shapers,thereby the stability is improved in end phase of the satellite control process,and the vibration of flexible parts of satellite is restrained during the control process.Simulation results demonstrate that the satellite can realistically achieve fast attitude maneuver and flexible vibration restraint by means of attitude maneuver path programming and input shaping.Meanwhile,the setting time of attitude stabilization is also shorten.It can provide more operable time and higher precision-stabilization condition for the payload.

关 键 词：敏捷卫星 姿态机动 输入成型 路径规划 挠性结构振动抑制 复合控制 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]