中国空间科学技术

中国空间科学技术 ›› 2022, Vol. 42 ›› Issue (1): 57-64.doi: 10.16708/j.cnki.1000-758X.2022.0006

• 论文 • 上一篇    下一篇

极低频超大型航天器姿态机动与物理试验验证

袁泉，林瀚峥，张军，魏春岭   

  1. 1 北京控制工程研究所, 北京100190
    2 空间智能控制技术国家级重点实验室，北京100190
  • 出版日期:2022-02-25 发布日期:2022-01-27
  • 基金资助:
    民用航天“超大型空间结构动力学与分布式控制技术”项目（D020213）

Attitude maneuver and physical test of large-scale spacecraft with ultra-low frequency

YUAN Quan，LIN Hanzheng，ZHANG Jun，WEI Chunling   

  1. 1 Beijing Institute of Control Engineering, Beijing 100190, China
    2 National Laboratory of Space Intelligent Control, Beijing 100190, China
  • Published:2022-02-25 Online:2022-01-27

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摘要： 针对具有0.01Hz极低频主模态的超大型航天器的姿态机动问题，给出利用经典的Bang-Bang轨迹规划方法、滤波轨迹规划方法和传统的相平面控制方法进行姿态机动的方案，构建了极低频超大型航天器姿态机动地面物理试验系统，对不同的姿态机动控制方法进行了试验验证。针对不同的姿态机动轨迹规划方法，采用喷气发动机或控制力矩陀螺作为执行机构，构建了5种超大型航天器姿态机动控制方案，即：姿态跟踪控制+Bang-Bang轨迹规划+喷气发动机，姿态跟踪控制+滤波轨迹规划+喷气发动机，姿态跟踪控制+Bang-Bang轨迹规划+控制力矩陀螺，姿态跟踪控制+滤波轨迹规划+控制力矩陀螺，相平面控制+角速度偏置规划+喷气发动机。利用构建的超大型物理试验系统对上述5种方案进行了试验比较，试验结果表明：机动轨迹对挠性变形的影响超过执行机构的影响，姿态跟踪控制+滤波轨迹规划+控制力矩陀螺方案最优，其变形量相对相平面控制方案能减少约81.8%。

关键词: 极低频, 超大型航天器, 姿态机动, 振动抑制, 滤波

Abstract: The attitude maneuver schemes for large-scale spacecraft with ultra-low vibration frequency were designed using Bang-Bang, filter attitude programming and classical phase control. The physical testbed of large-scale spacecraft with ultra-low vibration frequency was established to validate the different control schemes. Using different attitude programming methods and different attitude control actors including jets or control moment gyros, five attitude schemes were designed, i.e. attitude tracking controller with Bang-Bang programming and jets, attitude tracking controller with filter programming and jets, attitude tracking controller with Bang-Bang programming and control moment gyros, attitude tracking controller with filter programming and control moment gyros, phase controller with biased angular velocity and jets. The different control schemes were tested on the physical testbed. It is shown that the scheme of attitude tracking controller with filter programming and control moment gyros has the minimal vibration, whose vibration magnitude is reduced by 81.8% compared with the maximum vibration of classical phase control scheme.

Key words: ultra-low frequency, large-scale spacecraft, attitude control, vibration control, filter