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高超声速飞行器控制系统具有非常突出的强耦合、强非线性、时变的力学特性,在其研究与设计过程中,需要处理高速飞行带来的弹性形变、多输入多输出、气动参数不确定以及高温高热等原因导致的各种传感器故障和部分作动器故障等一系列问题,因此该类飞行器控制系统的研究与设计面临着传统飞行器控制系统研究所未有的困难和挑战.针对高超声速飞行器飞行过程中遇到的部分作动器故障问题,本文提出了非线性观测器与控制器一体化设计的高超声速飞行器自适应反演容错控制方法.首先将飞行器作动器故障模型转换为一类状态不能完全测量,且具有未知参数和未知控制增益的SISO输出反馈非线性最小相位系统,然后,基于改进的K-滤波器理论对状态向量进行重构,在系统只有输出可以测量的情况下,设计了一种新型观测器,确定出收敛的状态向量,设计出强自适应能力的控制器,保证了系统所有信号的有界性.在自适应反演设计时,采用动态面设计方法,引入一阶滤波器,得到虚拟控制量的微分,消除传统反演设计中的“项数膨胀”问题,用Lyapunov稳定性定理保证误差一致有界.仿真实验验证了该算法的有效性.最后以高超声速飞行器纵向通道为例,验证了上述理论.
Hypersonic vehicle control system has a very prominent strong coupling, strong nonlinear, time-varying mechanical properties, in its research and design process, the need to deal with high-speed flight caused by the elastic deformation, multiple input multiple output, the uncertainty of the aerodynamic parameters and High temperature and high heat caused by a variety of sensor failure and part of the actuator failure and a series of problems, so this type of aircraft control system research and design is facing the traditional aircraft control system Institute of the difficulties and challenges for hypersonic vehicles In this paper, an adaptive inversion fault tolerant control method for hypersonic vehicle is proposed, which integrates nonlinear observer and controller.Firstly, the fault models of aircraft actuators are converted into a class Then the SISO output feedback nonlinear minimum phase system with unknown parameters and unknown control gains can not be fully measured. Then, the state vector is reconstructed based on the improved K-filter theory. When the output of the system can only be measured, A new observer is designed to determine the convergent state vector and to design a strong observer Adaptive controller ensures the boundedness of all the signals in the system.In the adaptive inversion design, the dynamic surface design method is introduced and the first-order filter is introduced to obtain the differential of the virtual control volume, “Expansion of the number of items ”, the Lyapunov stability theorem is used to ensure that the error is uniform and bounded. Simulation results show the effectiveness of the algorithm. Finally, the above theory is verified by taking the longitudinal channel of hypersonic vehicle as an example.