针对失控翻滚目标航天器的交会对接控制  

Control for Rendezvous and Docking with a Tumbling Target Spacecraft

作　　者：胡勇[1] 徐李佳[1] 解永春[1] 

机构地区：[1]北京控制工程研究所空间智能控制技术重点实验室,北京100190

出　　处：《宇航学报》2015年第1期47-57,共11页Journal of Astronautics

基　　金：国家重点基础研究发展计划(2013CB733100);国家自然科学基金(61333008;61304027)

摘　　要：研究了一个受控的追踪航天器和一个失控慢速翻滚的目标航天器的末段交会对接控制问题。通过引入基于特征模型的控制方法,设计了相对位置跟踪控制器以及姿态同步控制器,克服了针对目标航天器测量中存在的较大不确定时延,航天器动力学参数的不确定性,以及追踪航天器存在的较大帆板挠性,实现了针对失控自旋目标的末段精确交会对接控制。最后,通过搭建仿真系统进行动力学仿真,进一步验证了本文控制策略的有效性。This paper investigates rendezvous and docking of two spacecrafts,one of which is a controlled chaser and the other is considered to be a passively tumbling target. Controllers for relative position tracking and attitude synchronization are developed by introducing a characteristic model based method. More practical difficulties and constraints,such as uncertain time delay caused by communication or sensing,unknown dynamic parameters,and flexible dynamics of solar array are taken into account. Finally,an example of rendezvous and docking with a tumbling target spacecraft is given to illustrate the efficiency of the proposed approach by using a series of numerical simulations.

关 键 词：特征模型 交会对接 挠性航天器 不确定性 时间延迟 

分 类 号：V526[航空宇航科学与技术—人机与环境工程]