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人工平动点附近混合推进航天器编队滑模控制保持

贺京九 袁长清 龚胜平 赵磊

贺京九,袁长清,龚胜平,等. 人工平动点附近混合推进航天器编队滑模控制保持[J]. 北京航空航天大学学报,2023,49(5):1222-1230 doi: 10.13700/j.bh.1001-5965.2021.0420
引用本文: 贺京九,袁长清,龚胜平,等. 人工平动点附近混合推进航天器编队滑模控制保持[J]. 北京航空航天大学学报,2023,49(5):1222-1230 doi: 10.13700/j.bh.1001-5965.2021.0420
HE J J,YUAN C Q,GONG S P,et al. Sliding mode control for formation flying near libration points using hybrid propulsion[J]. Journal of Beijing University of Aeronautics and Astronautics,2023,49(5):1222-1230 (in Chinese) doi: 10.13700/j.bh.1001-5965.2021.0420
Citation: HE J J,YUAN C Q,GONG S P,et al. Sliding mode control for formation flying near libration points using hybrid propulsion[J]. Journal of Beijing University of Aeronautics and Astronautics,2023,49(5):1222-1230 (in Chinese) doi: 10.13700/j.bh.1001-5965.2021.0420

人工平动点附近混合推进航天器编队滑模控制保持

doi: 10.13700/j.bh.1001-5965.2021.0420
详细信息
    作者简介:

    贺京九 男,硕士研究生。主要研究方向:航天器动力学与控制

    袁长清 男,博士,教授,硕士生导师。主要研究方向:航天器动力学与控制、库仑编队动力学与控制

    龚胜平 男,博士,教授,博士生导师。主要研究方向:多天体系统动力学和航天器动力学与控制。赵 磊 男,硕士研究生。主要研究方向:航天器动力学与控制

    通讯作者:

    E-mail:ycq02@mails.tsinghua.edu.cn

  • 中图分类号: V448+.2

Sliding mode control for formation flying near libration points using hybrid propulsion

More Information
  • 摘要:

    针对近距离航天器编队在日地系人工L1点附近的飞行控制问题,提出一种将太阳帆推进技术与库仑力编队技术相结合的混合推进控制方法。通过控制从航天器太阳帆相对于主航天器的姿态角调整主从间光压力差,同时与主从间库仑力相配合,既解决仅依靠太阳帆控制而存在的欠驱动问题,又改善了库仑编队的可控性。以太阳帆圆形限制性三体问题(SSCRTBP)模型为基础,给出共线人工平动点位置的计算方法,并构造主航天器运行轨道;引入航天器间库仑力,推导出混合推进编队相对运动方程;设计了固定时间滑模控制策略,以从航天器太阳帆的2个姿态角和主从间电荷积为控制量,对编队构型进行控制,将其与LQR控制策略对比,仿真结果表明:固定时间滑模控制策略在控制精度、所需时间、能量消耗等方面均优于LQR控制策略。在时长3年的任务中,编队仅用23天就展开完毕,保持阶段基线相对误差小于1%,其他两轴误差在厘米量级,整个过程无工质消耗,对于今后开展长期深空探测任务具有重要意义。

     

  • 图 1  相关坐标系

    Figure 1.  Relevant coordinate systems

    图 2  主从式航天器编队

    Figure 2.  Leader-follower spacecraft formations

    图 3  系统固定时间滑模控制结构

    Figure 3.  Structure of fixed-time sliding mode control

    图 4  主航天器参考轨道 (AZ=2×105 km)

    Figure 4.  Reference orbit of leader craft (AZ=2×105 km)

    图 5  相对运动轨迹

    Figure 5.  Relative motion trajectory

    图 6  x轴相对位置误差

    Figure 6.  Relative position error of x axis

    图 7  三轴相对加速度

    Figure 7.  Relative acceleration of 3 axes

    图 8  主从间电荷积

    Figure 8.  Charge product between leader and follower

    图 9  从航天器太阳帆姿态角

    Figure 9.  Attitude angle of follower’s solar sail

    表  1  两种控制方法性能指标

    Table  1.   Performance indicators of two control strategies

    方法ex/mt/[TU]u/mNQF/C2δmax/rad
    本文0.35 0.4101量级10−10量级< π/2
    文献[28]0.670.23102量级10−8量级>π/2
    下载: 导出CSV
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出版历程
  • 收稿日期:  2021-07-26
  • 录用日期:  2021-10-11
  • 网络出版日期:  2021-11-04
  • 整期出版日期:  2023-05-31

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