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首页> 外文期刊>International journal of aerospace engineering >Parameter Adaptive Terminal Sliding Mode Control of Flexible Coupling Air-Breathing Hypersonic Vehicle
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Parameter Adaptive Terminal Sliding Mode Control of Flexible Coupling Air-Breathing Hypersonic Vehicle

机译：柔性耦合空气呼吸超音速车辆的参数自适应端子滑动模式控制

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摘要

The highly nonlinear and coupling characteristics of a flexible air-breathing hypersonic vehicle create great challenges to its flight control design. A unique parameter adaptive nonsingular terminal sliding mode method is proposed for longitudinal control law design of a flexible coupling air-breathing hypersonic vehicle. This method uses adaptive reaching law gain instead of the additional adaptive compensation term to handle the uncertainty to improve robustness. The stability of the close loop system is proved via a Lyapunov way. The longitudinal tracking control law for velocity and angle of attack is designed based on a rigid dynamic model of a flexible air-breathing hypersonic vehicle. A strong coupling model of the same vehicle, considering aerodynamic-scramjet engine-flight dynamic-elastic couplings, is established as the verification platform of the designed control law. The remarkable differences of flight dynamic characteristics between this strong coupling model and the rigid body model can be seen, which mean the controller needs to endure very great uncertainty, unmodeled dynamics, and other types of internal disturbance. Simulation results based on the coupling model demonstrate that the designed control law has good performance and acceptable robustness.
机译：灵活的空气呼吸超音速车辆的高度非线性和耦合特性对其飞行控制设计产生了巨大挑战。提出了一种独特的参数自适应非透射端子滑动模式方法，用于纵向控制法设计柔性耦合空气呼吸超声型车辆。该方法使用自适应达到的法律增益而不是附加的自适应补偿项来处理不确定性以改善鲁棒性。通过Lyapunov方式证明了闭环系统的稳定性。基于柔性空气呼吸高超声速车辆的刚性动态模型设计了速度和攻角的纵向跟踪控制规律。考虑到空气动力学 - 斯普拉克喷射发动机飞行动态弹性耦合的相同车辆的强大耦合模型被建立为设计控制法的验证平台。可以看到这种强耦合模型与刚体模型之间的飞行动态特性的显着差异，这意味着控制器需要忍受非常出色的不确定性，未拼件动态和其他类型的内部干扰。基于耦合模型的仿真结果表明，设计的控制法具有良好的性能和可接受的鲁棒性。

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  • 来源
    《International journal of aerospace engineering》 |2020年第2期|9430272.1-9430272.17|共17页
  • 作者

    Chen Haibing; Lin Wei; Ma Tielin; Jin Hengxian; Xu Cheng;

  • 作者单位

    Beihang Univ Sch Transportat Sci & Engn Beijing Peoples R China|Aircraft Engine Integrated Syst Safety Beijing Ke Beijing Peoples R China;

    Beihang Univ Sch Transportat Sci & Engn Beijing Peoples R China;

    Beihang Univ Inst Unmanned Syst Beijing Peoples R China;

    Beihang Univ Sch Energy & Power Engn Beijing Peoples R China;

    Sci & Technol Complex Syst Control & Intelligent Beijing Peoples R China;

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