| 高超声速飞行器的终端滑模姿态控制 |
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| 引用本文： | 管萍,蒋恒,戈新生. 高超声速飞行器的终端滑模姿态控制[J]. 导弹与航天运载技术, 2017, 0(6): 60-64. DOI: 10.7654/j.issn.1004-7182.20170614 |
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| 作者姓名： | 管萍 蒋恒 戈新生 |
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| 作者单位： | 北京信息科技大学,北京,100192 |
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| 摘 要： | 针对具有高度非线性、强耦合、含较大不确定性特点的高超声速飞行器,设计了终端滑模控制器,并应用于高超声速飞行器的姿态控制中。对飞行器姿态控制系统的慢回路设计PID控制律,快回路设计终端滑模控制律。终端滑模控制对系统参数的变化不灵敏,具有良好的鲁棒性。并利用李雅普诺夫稳定性理论证明整个闭环系统的稳定性。仿真结果表明,在气动参数大范围摄动的情况下,该控制系统对于高超声速飞行器姿态角信号指令具有良好的跟踪性能。
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| 关 键 词： | 高超声速飞行器 气动参数 不确定性 终端滑模控制 姿态控制 |
Terminal Sliding Mode Attitude Control for Hypersonic Vehicles |
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| Abstract: | A terminal sliding mode controller is applied to the attitude control of hypersonic vehicle,which has the characteristics of high nonlinearity,strong coupling and greater uncertainty.The PID control law is designed for the slow loop of the aircraft attitude control system,and the terminal sliding mode control law is designed for the fast loop.The terminal sliding mode control is not sensitive to the parameters of the system,and has good robustness.And the stability of the closed-loop is proved by the Lyapunov theory.The simulation results show that this control system has the good tracking performance for the desired attitude angle of hypersonic vehicles,in the case of a wide range of aerodynamic parameters perturbation. |
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| Keywords: | Hypersonic vehicle Aerodynamic parameter Uncertainties Terminal sliding mode control Attitude control |
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