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针对某高超声速飞行器纵向不稳定,对飞行条件变化和自身参数变化的高度敏感性,飞行高度和马赫数变化范围大以及存在参数不确定性等特点,提出了基于线性矩阵不等式(LMI)的一种改进的状态反馈H∞控制器对飞行器的高度和迎角进行跟踪。该方法将高超声速飞行器不确定性参数转化为一种多胞型的参数空间,这样的多胞型参数空间将包含2N(N为不确定参数的个数)个顶点,该方法保证系统的状态矩阵和输入矩阵在上述的多胞型参数空间内摄动时的鲁棒性。在23200米和马赫数为6的巡航条件下进行仿真,同时考虑外界大气紊流干扰。仿真结果表明,该方法对上述多胞型不确定性参数变化具有较强的鲁棒性,同时能保证对指令信号有较好的跟踪效果。
Aiming at the characteristics of a hypersonic vehicle’s longitudinal instability, its high sensitivity to the variation of flight conditions and its own parameters, the large range of flight altitude and Mach number, and the existence of parameter uncertainty, a new method based on linear matrix inequality (LMI) Improved state feedback H∞ controller tracks aircraft altitude and angle of attack. The method converts the hypersonic vehicle uncertainty parameter into a multi-cell parameter space, and the multi-cell parameter space contains 2N (N is the number of uncertain parameters) vertices. The method guarantees the state of the system The robustness of matrices and input matrices when perturbed in the above-mentioned multi-cell parameter space. Simulations were conducted at 23,200 meters and a Mach number of 6, taking into account turbulence in the outside world. The simulation results show that this method is robust to the variation of the multi-cell uncertainties mentioned above, and at the same time it can ensure a good tracking effect on the command signals.