中国空间科学技术

中国空间科学技术 ›› 2025, Vol. 45 ›› Issue (3): 110-119.doi: 10.16708/j.cnki.1000.758X.2025.0043

• 论文 • 上一篇    下一篇

一种沿指定直线方向逼近的航天器最优控制策略

刘将辉1,2,3, 彭祺擘1，*, 武新峰1   

  1. 1.中国航天员科研训练中心，北京100094
    2.中国载人航天工程办公室，北京100071
    3.北京航空航天大学 宇航学院，北京100083
  • 收稿日期:2024-04-01 修回日期:2024-04-24 录用日期:2024-05-05 发布日期:2025-05-15 出版日期:2025-06-01

An optimal control strategy for spacecraft approaching along a designated straight direction

LIU Jianghui1,2,3，PENG Qibo1,*，WU Xinfeng1   

  1. 1.Astronaut Research and Training Center，Beijing 100094，China
    2.China Manned Space Agency，Beijing 100071，China
    3.School of Astronautics，Beihang University，Beijing 100083，China
  • Received:2024-04-01 Revision received:2024-04-24 Accepted:2024-05-05 Online:2025-05-15 Published:2025-06-01

PDF (PC)

4

摘要： 航天器空间在轨服务技术受到越来越多的关注,空间在轨服务的基础是航天器交会技术，航天器交会的实质是追踪器对目标器的近距离逼近。追踪器在逼近目标器的过程中，应避免与目标器的太阳翼和天线等附件发生碰撞。为了保证逼近过程的安全性，提出了一种沿指定直线方向逼近的航天器最优控制策略。建立了非线性TH（Tschauner-Hempel）方程描述的任意偏心率轨道的两航天器间相对运动模型。引入直线逼近运动坐标系，根据Hamiltonian方程和直线方向逼近运动特点推导了追踪器的最优控制加速度。追踪器既能按照任务需求沿指定方向直线逼近目标器，又保证了能量最优。为了消除影响直线逼近的干扰因素，采用比例微分控制律对所推导的非直线方向的控制加速度进行了修正。为了验证所提控制策略的有效性，分别设置了追踪器沿目标器速度方向直线逼近和沿目标器径向直线逼近这两组场景进行数值仿真。仿真结果表明，所提的控制策略能实现追踪器沿指定直线方向逼近目标器，具有较强的工程应用性，为提高航天器空间在轨服务的成功率和安全性提供了新的思路。

关键词: 航天器交会, 直线逼近, 最优控制, 空间在轨服务, 比例微分

Abstract: The technology of spacecraft’s space on-orbit service has received increasing attention. The basis of space on-orbit service is spacecraft rendezvous technology, and the essence of spacecraft rendezvous is the approach of the chaser to the target in close range. During the process of approaching the target, the chaser should avoid collisions with accessories such as the solar panel and antenna of the target. In order to ensure the safety of the approximation process, an optimal control strategy for spacecraft approaching along a designated straight direction is proposed. The relative motion model between the two spacecraft with arbitrary eccentricity orbit described by nonlinear TH (Tschauner-Hempel) equation is established. The coordinate system of linear approximation motion is introduced, and the optimal control acceleration of the chaser is derived according to the Hamiltonian equation and the characteristics of linear direction approximation motion. The chaser spacecraft can not only approach the target along a designated straight direction according to the mission requirements, but also ensure the optimal energy. In order to eliminate the interference factors that affect the linear approximation, the proportional differential control law is used to correct the derived control acceleration in the non-linear direction. In order to verify the effectiveness of the proposed control strategy, two sets of scenarios are set up for numerical simulation, which are the linear approximation of the chaser along the velocity direction of the target and the linear approximation along the radial direction of the target. The simulation results show that the proposed control strategy can realize the chaser approaching the target along the designated straight direction, which has good engineering applicability and provides a new idea for improving the success rate and safety of spacecraft space on-orbit service.


Key words: spacecraft rendezvous, approach along straight direction, optimal control, space on-orbit service, proportional differential