一种高超声速飞行器鲁棒自适应控制方法

摘要

针对较强参数摄动情况下高超声速飞行器巡航段控制问题,提出一种基于主影响元素分析的鲁棒自适应控制方法.首先在飞行器具有未知参数情况下,使用符号计算工具对系统不确定量进行分离,实现不确定性的建模;进一步使用蒙特卡洛试验方法,确定不确定函数向量的主影响元素,对模型进行简化.然后在滑模控制的基础上,结合参数自适应估值和鲁棒补偿的方法,设计出飞行控制器,实现对未知参数的自适应估值以及对模型误差的补偿,并从理论上证明了系统的稳定性.仿真试验表明,在较大参数摄动情况下,文中所提方法依然可以保证系统的稳定性和跟踪性能.%A robust adaptive control method based on main influence elements analysis is proposed for the hypersonic vehicles in strong parameter perturbations case during the cruise phase.Firstly,under the condition of parameter uncertainties,symbolic calculation tools are used to separate the uncertainty terms,and the uncertainty model is obtained.Furthermore,Monte Carlo method is implemented to determine the main influence elements of the uncertainty function vectors,the uncertainty model is simplified.Secondly,on the basis of the sliding mode control,a flight controller is designed combining the parameter adaptive estimation and robust compensation,then the stability of system is proved theoretically.Lastly,a detailed simulation experiment is carried out,which verifies that the flight controller can guarantee system stability and tracking performance even in case of large parameter perturbations.