中文摘要：

基于向量Lyapunov函数方法,设计了高超声速飞行器着陆段一体化导引与控制律。首先,根据高超声速飞行器着陆段三自由度运动学与动力学模型、阻力加速度动力学模型、姿态动力学方程,在考虑飞行器动力学方程中的不确定因素及可能存在的扰动因素的情况下,推导出制导与控制一体化非线性全耦合模型。然后,将上述非线性全耦合模型抽象为一类具有不确定性和强非线性的MIMO系统,针对该类系统,利用向量Lyapunov函数方法设计鲁棒控制器。最后,通过仿真计算对所提出控制器的有效性进行了检验。

英文摘要：

Based on the control vector Lyapunov function theory,an integrated guidance and controller is proposed in approach and landing phase of hypersonic vehicle. First,considering the model uncertainty and the external disturbances,the integrated nonlinear model is presented based on 3D dynamics and rotational motion of hypersonic vehicle. Then,the integrated model is abstracted into a class of MIMO systems with model parameter uncertainty and strong nonlinearity. And by utilizing control vector Lyapunov function theory,a robust controller is designed for the class of MIMO systems. Finally,the numerical simulation is used to validate the effectiveness of the proposed design approach.