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挠性航天器姿态机动直接自适应主动振动控制

刘敏 徐世杰 韩潮

刘敏, 徐世杰, 韩潮等 . 挠性航天器姿态机动直接自适应主动振动控制[J]. 北京航空航天大学学报, 2013, 39(3): 285-289.
引用本文: 刘敏, 徐世杰, 韩潮等 . 挠性航天器姿态机动直接自适应主动振动控制[J]. 北京航空航天大学学报, 2013, 39(3): 285-289.
Liu Min, Xu Shijie, Han Chaoet al. Active vibration control and attitude maneuver of flexible spacecraft via direct adaptive control method[J]. Journal of Beijing University of Aeronautics and Astronautics, 2013, 39(3): 285-289. (in Chinese)
Citation: Liu Min, Xu Shijie, Han Chaoet al. Active vibration control and attitude maneuver of flexible spacecraft via direct adaptive control method[J]. Journal of Beijing University of Aeronautics and Astronautics, 2013, 39(3): 285-289. (in Chinese)

挠性航天器姿态机动直接自适应主动振动控制

基金项目: 国家自然科学基金资助项目(10902003)
详细信息
    作者简介:

    刘敏(1984-),男,湖南衡阳人,博士生,liumin@sa.buaa.edu.cn.

  • 中图分类号: V448.22+3

Active vibration control and attitude maneuver of flexible spacecraft via direct adaptive control method

  • 摘要: 针对具有压电陶瓷自敏执行机构的挠性航天器,基于直接自适应控制方法,设计了姿态机动主动振动控制器.首先,验证了在执行机构与敏感器同位安装时,挠性航天器系统的近似严格正实性;然后,设计了挠性航天器的直接自适应姿态机动主动振动控制器,使得航天器输出渐近跟踪具有理想控制性能的参考模型输出;最后,在多组仿真条件下进行了挠性航天器直接自适应姿态机动控制数值仿真.理论分析与仿真结果表明,该方法对航天器惯量和挠性附件模态的不确定性具有强鲁棒性,能够实现对多阶模态的同时控制,对挠性航天器的姿态机动主动振动控制是有效的.

     

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出版历程
  • 收稿日期:  2012-02-13
  • 网络出版日期:  2013-03-31

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