考虑执行故障的高超声速飞行器有限时间控制设计  

Finite time control of hypersonic aircraft considering execution faults

作　　者：徐长吉 郭杰[1] Xu Changji;Guo Jie(School of Aerospace Engineering of Beijing Institute of Technology,Beijing 100081,China)

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《空天技术》2023年第6期76-87,共12页Aerospace Technology

摘　　要：针对弹性高超声速飞行器在控制层面存在外部干扰、执行机构故障等影响飞行器控制性能的问题,为实现弹性飞行器控制的有限时间收敛,提出了一种快速跟踪控制器,分别针对速度和高度采用预设性能控制方案,用以提高控制性能。在控制器研究中,提供了预先设定的瞬态和稳态跟踪误差边界用以限制超调,提高控制性能。此外,为了估计总扰动,引入了滑模观测器。同时,在高度跟踪的反向设计中将四阶系统分解,分步设计控制器,以此避免了虚拟控制器的高阶运算。为了实现控制系统的有限时间收敛,引入了非奇异快速终端滑模技术和齐次性方法来设计控制律,确保速度和高度跟踪误差在有限时间内收敛。最后,利用高超声速飞行器模型进行了仿真实验,仿真结果验证了控制器的有效性。Aiming at the problems of external interference and actuator failure in the control plane of elastic hypersonic aircraft,in order to achieve the limited time convergence of the control problem of elastic aircraft,a fast-tracking controller is proposed,which adopts a preset performance control scheme for speed and altitude to improve the control performance.In the study of the controller,preset transient and steady-state tracking error bounds are provided to limit overshoot and improve control performance.In addition,to estimate the total perturbation,a sliding mode observer is introduced.Meanwhile,the fourth-order system is decomposed in the reverse design of height tracking and the controller is designed in steps as a way to avoid the higher-order operation of the virtual controller.In order to achieve finite time convergence of the control system,the author introduces the non-singular fast terminal sliding mode technology and homogeneity method are introduced to design the control law,which ensures that the speed and height tracking error converge in a limited time.Finally,the simulation experiments are carried out using the hypersonic vehicle model,and the simulation results verify the effectiveness of the controller.

关 键 词：高超声速飞行器 执行故障 终端滑模 状态观测器 齐次性方法 预设性能控制 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]