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针对近空间飞行器(nearspace vehicle,NSV)在高超音速飞行时,气动参数变化剧烈且容易受到外界干扰的特点,研究了NSV纵向轨迹系统的干扰问题,提出了鲁棒自适应动态面的回馈递推控制方法。首先对高度非线性、高度复杂的NSV的纵向运动的模型进行坐标变换,采用输入-输出反馈线性化方法,将其转化为仿射非线性模型;然后通过一阶低通滤波器对控制器设计中的虚拟控制律进行估计,从而避免了对其求导带来的计算膨胀问题;再结合神经网络逼近理论以及虚拟控制器中的鲁棒项,一起消除近空间飞行器的纵向系统中存在的参数摄动不确定和外界干扰。最后通过稳定性分析,表明了该方法在降低系统控制器复杂性的同时仍具有很好的鲁棒性。
Aiming at the characteristics that the aerodynamic parameters of the near-space vehicle (NSV) change violently during the hypersonic flight and are easily disturbed by the outside world, the interference problem of the NSV longitudinal trajectory system is studied and the feedback recursion of the robust adaptive dynamic surface is proposed Control Method. Firstly, the model of longitudinal motion of highly nonlinear and highly complex NSV is transformed by coordinates, and the input-output feedback linearization method is used to convert it into an affine nonlinear model. Then the controller design In order to avoid the computational expansion caused by its derivation. Combined with the neural network approximation theory and robust terms in the virtual controller, the parameters of the longitudinal system of the near-space vehicle are eliminated Perturbation uncertainty and outside interference. Finally, through the stability analysis, this method shows that this method can reduce the complexity of the system controller and still has good robustness.