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针对高超声速飞行器非线性动力学系统中所特有的输出非线性、状态向量强耦合等特性,综合考虑了飞行中的不确定性、具有复杂非线性输出、状态向量不完全可测量等因素,提出一种基于Lyapunov法的滑模观测器和控制器设计方法,用于解决高超声速飞行器迎角观测器不能精确测量的问题.首先在观测器设计过程中,利用过载输出滑模面构造了Lyapunov函数,确定出观测器收敛的条件,并基于线性化理论求出观测器增益矩阵.然后在控制器设计过程中,采用基于动态面的自适应反演方法设计出控制律,用多层神经网络调节函数逼近系统中的高频未建模动态,设计鲁棒项函数解决了逼近误差的影响问题,并进行了稳定性分析和仿真验证.
In view of the characteristics of hypereutectic nonlinear dynamics such as output nonlinearity and strong coupling of state vector, the uncertainties in flight, complex nonlinear output and incomplete measurement of state vector are all considered A sliding mode observer and controller design method based on Lyapunov method is proposed to solve the inaccurate measurement problem of the hypersonic aircraft’s angle of attack observer.First, in the observer design process, the Lyapunov function , The condition of observer convergence is determined and the observer gain matrix is obtained based on the linearization theory.And then in the process of controller design, adaptive control method based on dynamic surface is used to design the control law and to use multi-layer neural network to adjust The function approximates the high frequency unmodeled dynamics in the system. The robust function is designed to solve the problem of the influence of approximation errors. The stability analysis and simulation are also carried out.