论文部分内容阅读
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。
Based on the vector Lyapunov function method, the integrated guidance and control law of the landing section of hypersonic vehicle was designed. First of all, according to the three-degree-of-freedom kinematics and dynamics model, the drag acceleration dynamics model and the attitude dynamics equation of the hovercraft landing section, considering the uncertainties and possible disturbances in the aircraft dynamics equations, The guidance and control integrated nonlinear full coupling model is deduced. Then, the above nonlinear full coupling model is abstracted into a class of MIMO systems with uncertainties and strong nonlinearities. For such systems, a robust controller is designed by using the vector Lyapunov function method. Finally, the validity of the proposed controller is verified through simulation.