宇航学报

宇航学报 ›› 2022, Vol. 43 ›› Issue (5): 628-637.doi: 10.3873/j.issn.1000-1328.2022.05.008

• 制导、导航、控制与电子 • 上一篇    下一篇

安全约束下的空间翻滚目标涡流消旋稳定控制

刘习尧，常海涛，黄攀峰，黄冰潇，翟晨萌
  

  1. 1. 西北工业大学航天飞行动力学技术重点实验室，西安 710072；2. 西北工业大学智能机器人研究中心，西安 710072
  • 收稿日期:2021-04-16 修回日期:2021-11-17 出版日期:2022-05-15 发布日期:2022-05-15
  • 基金资助:
    国家自然科学基金（91848205,61725303）

Stability Control of Eddy Current Detumbling for Space Tumbling Target under Safety Constraint

LIU Xiyao, CHANG Haitao, HUANG Panfeng, HUANG Bingxiao, ZHAI Chenmeng   

  1. 1. National Key Laboratory of Aerospace Flight Dynamics, Northwestern Polytechnical University, Xi’an 710072, China;2. Research Center for Intelligent Robotics, Northwestern Polytechnical University, Xi’an 710072, China
  • Received:2021-04-16 Revised:2021-11-17 Online:2022-05-15 Published:2022-05-15

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摘要： 针对空间翻滚目标涡流消旋任务执行效率低和抵近安全无保证的问题，首先基于椭球包络法给出了服务星机动轨迹的直接线性凸化安全约束，以确保机动过程的安全性和最优轨迹跟踪问题的有限时间可解性；设计了垂直构型下空间消旋任务的抵近期望轨迹以增强服务星消旋力矩的作用强度，缩短任务周期。在此基础上，提出了一种反馈线性化的收缩模型预测控制(FLC MPC)算法，有效跟踪所提出的期望轨迹，并严格保证安全约束及控制输入约束下受控系统的稳定性。最后，利用所提出的控制方法对阿丽亚娜 4火箭上面级进行消旋仿真，结果表明该方法能有效提高消旋效率，并保证服务星的安全稳定。

关键词: color:#000000, font-family:", sans serif", ,tahoma,verdana,helvetica, font-size:12px, font-style:normal, font-weight:400, line-height:18px, text-decoration:none, ">空间翻滚目标；涡流消旋；安全约束；反馈线性化；模型预测控制color:#000000, font-family:", sans serif", ,tahoma,verdana,helvetica, font-size:12px, font-style:normal, font-weight:400, line-height:18px, text-decoration:none, ">

Abstract: In order to solve the problems of low efficiency and no guarantee of approaching safety in the eddy current detumbling task of space tumbling targets, direct linearization convex safety constraints for the maneuver trajectory of the servicer satellite are given based on the ellipsoid envelope method, to ensure the safety of maneuvering process and the finite time solvability of optimal tracking problems. The desired approaching trajectory in perpendicular configuration is designed to enhance the detumbling effect of the servicer satellite and shorten the task period. On this basis, a feedback linearization contractive model predictive control(FLC MPC) algorithm is proposed to effectively track the proposed desired trajectory and strictly guarantees the stability of the controlled system under safety and input constraints. Finally, the proposed control method is used to simulate detumbling of the Ariane 4 launch vehicle upper stage. The simulation results show that the proposed method can effectively improve the detumbling efficiency and ensure the safety and stability of the servicer satellite.

Key words: Space tumbling target, Eddy current detumbling, Safety constraint, Feedback linearization, Model predictive control

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