挠性航天器姿态机动的变结构主动振动抑制
Active vibration suppression in flexible spacecraft with mismatched uncertainty via variable structure control
摘要点击 2651  全文点击 3355  投稿时间:2005-10-29  修订日期:2006-02-23
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DOI编号  10.7641/j.issn.1000-8152.2007.3.001
  2007,24(3):329-336
中文关键词  挠性航天器  变结构输出反馈控制  姿态机动  不匹配不确定性
英文关键词  vibration suppression  variable structure output feedback control (VSOFC)  flexible spacecraft  attitude maneuver  mismatched uncertainty  positive position feedback (PPF)
基金项目  高等学校博士学科点专项科研基金资助项目(20050213010); 国家高技术研究发展计划(863计划)课题资助项目(2004AA735080).
学科分类代码  
作者单位
胡庆雷, 刘亚秋, 马广富 哈尔滨工业大学航天学院, 黑龙江哈尔滨150001;东北林业大学信息与计算机工程学院, 黑龙江哈尔滨150040 
中文摘要
      针对挠性航天器大角度姿态机动的振动抑制问题, 提出了一种双回路鲁棒主动振动控制方法. 首先, 对各低阶振动模态设计正位置反馈补偿器, 增加挠性模态的阻尼, 使其振动能够快速衰减; 然后, 基于变结构输出反馈控制理论, 给出控制器的设计方法. 最后, 将该方法应用于挠性航天器姿态机动控制, 仿真结果表明, 所提出的方法是可行而有效的.
英文摘要
      This investigation is to apply the variable structure output feedback control (VSOFC) and distributed piezoelectric sensor/actuator technology to a large-angle rotational maneuver and vibration control of a flexible spacecraft. Two separate control loops are adopted to satisfy the pointing requirements and simultaneously suppress vibrations. We use the piezoceramics as sensors and actuators to actively suppress certain flexible modes in designing a positive position feedback (PPF) compensator that adds damping to the flexible structures in certain critical modes of the inner feedback loop. Then, a second feedback loop is designed using the variable structure techniques, using only output information, to slew the spacecraft.Compared with conventional methods, the proposed scheme guarantees closed-loop system stability, and yields good performance and robustness in the presence of parametric uncertainties and external disturbance. Simulation results for the spacecraft model show precise trajectory control and vibration suppression.