旋转非合作目标终端逼近的姿轨控制研究

刘海龙; 韩旭; 史小平

doi:10.11728/cjss2015.05.603

旋转非合作目标终端逼近的姿轨控制研究

doi: 10.11728/cjss2015.05.603

1.
哈尔滨工业大学控制与仿真中心哈尔滨 150080
2.
上海卫星工程研究所研发中心上海 200240

详细信息

通讯作者:
刘海龙,E-mail:11b904016@hit.edu.cn

中图分类号: V448.2
计量
- 文章访问数: 1044
- HTML全文浏览量: 78
- PDF下载量: 1359
- 被引次数: 0
出版历程
- 收稿日期: 2014-07-26
- 修回日期: 2015-03-02
- 刊出日期: 2015-09-15

Attitude And Translation Control For Spacecraft To Approach To A Tumbling Non-Cooperative Object During The Final Phase

1.
Control and Simulation Center, Harbin Institute of Technology, Harbin 150080

摘要

摘要: 针对旋转非合作目标的终端逼近过程进行研究, 建立了适用于任意偏心率的精确航天器相对运动和姿态动力学模型, 并对传统的直线型同步自旋逼近策略进行改进, 设计了用于保障终端逼近安全性的指数衰减型参考轨迹; 推导了基于比例微分加解耦控制方法的相对轨道和姿态控制律, 通过数值仿真验证了控制器的有效性.
- 相对运动 /
- 非合作目标 /
- 空间交会 /
- 轨道控制 /
- 姿态控制
Abstract: This paper considers the process of motion synchronization of chaser satellite and target satellite in space. The problem of final approach to a non-cooperative tumbling target is studied in this paper. The accurate orbit and attitude dynamics model of two relative motion spacecrafts with arbitrary eccentrics is established. In order to insure the safety of final approach, the traditional linear synchronization rotating approach strategy is improved by designing an exponential decay reference trajectory to decay relative velocity with decreasing relative distance and reach zero when the chaser is hovering. The proportional-derivative-decouple relative attitude controller and relative orbit controller is proposed. The simulation shows the process of the relative velocity of the chaser decay to zero. The stability of the control law is demonstrated through Lyapunov analysis and effectiveness of controller is verified by the numerical simulation.
- Relative motion /
- Non-cooperative target /
- Space rendezvous /
- Orbit control /
- Attitude control

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参考文献(12)

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