航空学报 > 2023, Vol. 44 Issue (15): 528494-528494   doi: 10.7527/S1000-6893.2023.28494

高超声速变外形飞行器事件触发有限时间控制

张豪1, 王鹏1(), 汤国建1, 包为民2   

  1. 1.国防科技大学 空天科学学院,长沙  410073
    2.中国航天科技集团,北京  100048
  • 收稿日期:2023-01-10 修回日期:2023-02-16 接受日期:2023-03-13 出版日期:2023-06-30 发布日期:2023-03-31
  • 通讯作者: 王鹏 E-mail:wonderful2035@163.com

Event-triggered fast finite time control for hypersonic morphing vehicles

Hao ZHANG1, Peng WANG1(), Guojian TANG1, Weimin BAO2   

  1. 1.College of Aerospace Science and Engineering,National University of Defense Technology,Changsha  410073,China
    2.China Aerospace Science & Technology Corporation,Beijing  100048,China
  • Received:2023-01-10 Revised:2023-02-16 Accepted:2023-03-13 Online:2023-06-30 Published:2023-03-31
  • Contact: Peng WANG E-mail:wonderful2035@163.com

摘要:

针对高超声速变形飞行器处于变形飞行阶段需要兼顾高性能控制和低资源消耗的问题,提出一种新型事件触发快速有限时间控制方法。将高超声速变形飞行器模型转化为面向控制的模型以便于控制系统设计。使用快速有限时间控制技术设计姿态控制器,保证跟踪误差能够快速收敛。开发切换动态事件触发策略来降低执行机构动作频率,设计的过程已充分考虑并降低潜在的性能损失。使用李雅普诺夫理论证明闭环系统稳定和跟踪误差有限时间收敛。与传统有限时间控制相比,快速有限时间控制提高了闭环系统远离平衡点时收敛速率,事件触发机制有效降低执行机构动作频率。控制方法实现了针对高超声速变形飞行器的高性能控制,降低了飞行器系统资源消耗,未带来明显的性能损失。飞行仿真验证了所设计方法的有效性和优越性。

关键词: 高超声速变形飞行器, 姿态控制, 有限时间控制, 滑模控制, 切换事件触发策略, 动态事件触发策略

Abstract:

This paper proposes a novel event-triggered fast finite time sliding mode control for the hypersonic vehicle with frequent actuator deflection in the morphing phase. The original model of the hypersonic morphing vehicle is transformed into the control-oriented model, which is employed in the controller design. The fast finite time control theory is adopted to develop a control system for the hypersonic morphing phase. The switching dynamic event-triggering mechanism is introduced to reduce the frequency of actuator deflection. Meanwhile, the possible performance loss is fully considered in the procedure. The Lyapunov theory is utilized to prove the stability of the closed-loop system and the convergence of the tracking error. Compared with conventional finite-time control methods, fast finite-time control enhances the convergence rate when the system state is far from the equilibrium point. Furthermore, the event-triggering mechanism effectively reduces the frequency of actuating the actuator without obvious performance loss. Simulation verifies the effectiveness and excellent performance of the controller proposed.

Key words: hypersonic morphing vehicle, attitude control, finite time control, sliding mode control, switching event-triggering mechanism, dynamic event-triggering mechanism

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