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基于SMDO-TLC的高超声速飞行器姿态控制

邵星灵 王宏伦

邵星灵, 王宏伦. 基于SMDO-TLC的高超声速飞行器姿态控制[J]. 北京航空航天大学学报, 2014, 40(11): 1568-1575. doi: 10.13700/j.bh.1001-5965.2013.0731
引用本文: 邵星灵, 王宏伦. 基于SMDO-TLC的高超声速飞行器姿态控制[J]. 北京航空航天大学学报, 2014, 40(11): 1568-1575. doi: 10.13700/j.bh.1001-5965.2013.0731
Shao Xingling, Wang Honglun. Attitude control for hypersonic vehicle based on SMDO-TLC[J]. Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(11): 1568-1575. doi: 10.13700/j.bh.1001-5965.2013.0731(in Chinese)
Citation: Shao Xingling, Wang Honglun. Attitude control for hypersonic vehicle based on SMDO-TLC[J]. Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(11): 1568-1575. doi: 10.13700/j.bh.1001-5965.2013.0731(in Chinese)

基于SMDO-TLC的高超声速飞行器姿态控制

doi: 10.13700/j.bh.1001-5965.2013.0731
基金项目: 国家自然科学基金资助项目(61175084);长江学者和创新团队发展计划资助项目(IRT13004);航空科学基金资助项目
详细信息
    作者简介:

    邵星灵(1988-),男,江苏扬州人,博士生,huanying3557913@sina.com.

  • 中图分类号: V249.1

Attitude control for hypersonic vehicle based on SMDO-TLC

  • 摘要: 针对高超声速飞行器快时变、强耦合以及存在参数不确定和外部干扰情况下的姿态控制问题,同时考虑到执行机构动态和输入受限,提出了基于滑模干扰观测器-轨迹线性化(SMDO-TLC,Sliding-Mode Disturbance Observer-Trajectory Linearization Control)的高超声速姿态控制方法.首先,引入二阶线性微分器(SOLD,Second-Order Linear Differentiator)的概念,通过理论分析指出了当前TLC中采用一阶惯性+伪微分器求取输入指令的微分信号时会存在与SOLD类似的峰值现象,随后利用韩式跟踪微分器求取姿态标称指令及其微分信号,可有效解决过渡过程中执行机构饱和问题;接着,分别在姿态和角速率回路设计二阶滑模干扰观测器,利用符号函数积分来重构内外回路的复合干扰,在此基础上设计补偿控制律,以实现姿态控制器设计.仿真结果表明,所提出的方法能够克服时变干扰及气动参数大范围摄动的影响,同时兼具良好的动态特性与静态品质,能够满足高超声速飞行器的快时变、高精度以及强鲁棒的控制需求.

     

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出版历程
  • 收稿日期:  2014-01-07
  • 网络出版日期:  2014-11-20

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