航天器快速绕飞监测的相对姿轨耦合控制  

The Relative Coupling Attitude and Orbit Control of Fast Fly-around with Monitoring Spacecraft

作　　者：张庆展 靳永强[1,2] 康志宇[1,2] 肖余之[1,2] 

机构地区：[1]上海航天技术研究院航天运输与维护总体技术研究中心,上海201109 [2]上海宇航系统工程研究所,上海201109

出　　处：《航天控制》2014年第2期53-59,共7页Aerospace Control

基　　金：上海市科学技术委员会资助课题(13QB1404000)

摘　　要：研究了航天器空间任意方位快速绕飞与监测的相对姿轨耦合控制问题。通过合理绕飞参考系和期望姿态系的定义,将问题转化为绕飞参考系内的相对姿轨跟踪控制。通过设计航天器期望相对位置矢量和求取期望姿态运动规律,建立了符合航天器空间一般物理运动规律的相对运动与姿态指向模型,并给出相应控制律。仿真中以实现与目标轨道异面的快速圆绕飞为例,同时考虑绕飞航天器初始位置不在绕飞面的情况,设计了期望相对位置矢量的运动规律,并加入指数函数引导相对姿轨平滑过渡。考虑相对姿轨控制的强耦合性,绕飞航天器采用冗余推力器配置,并引入伪逆法实现控制指令的动态分配。最后针对示例的数值和可视化仿真验证了算法的正确性。The relative coupling attitude and orbit control on fast fly - around with monitoring from any orientation in space is researched. By defining fly - around reference and desired attitude coordinate system, the problem is transformed to relative attitude and orbit tracking. Through desired relative position vector de- signed and desired attitude motion law calculated, the universal model of general relative motion with moni- toring is established. And the corresponding control law is supplied. By taking non - coplanar circular fly - around in simulation, with considering fly- around spacecraft not in fly- around plane, the desired rela- tive position vector is designed and the index function is added to smooth relative attitude - orbit. With con- sidering coupling, control commands are distributed dynamically by pseudo - inverse algorithm with redun- dant thruster deployment. Through the presentation of numerical simulation and visualization, the effective- ness is validated.

关 键 词：航天器 快速绕飞 监测 相对姿轨耦合控制 期望相对位置矢量 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]