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升力式高超声速再入飞行器气动力、气动热耦合环境复杂,不确定性和干扰较大,一般采用直接力/气动力的复合控制方式。针对飞行环境特点和不同控制机理构成的复合控制模式,提出了一种基于模糊PID的直接力/气动力复合控制方法,该方法通过对气动力控制与直接力控制两个子系统分别设计模糊PID控制器,并设计了一种复合控制方案。最后针对某型升力式高超声速再入飞行器的纵向姿态复合控制进行了仿真验证,仿真中综合考虑了气动参数的误差、测量误差、大气干扰与大气环境的不确定性。仿真结果表明,所设计的模糊PID控制器较传统的PID控制器具有更好的控制性能,更强的鲁棒性和自适应能力。
Lifting hypersonic reentry vehicle aerodynamic, aerodynamic coupling of complex environment, large uncertainty and interference, the general direct force / aerodynamic composite control. Aiming at the compound control mode of flight environment and different control mechanisms, a direct force / aerodynamic compound control method based on fuzzy PID is proposed. The fuzzy PID control is designed respectively for the two subsystems of aerodynamic force control and direct force control And designed a compound control scheme. At last, the longitudinal attitude compound control of a certain type of hypersonic reentry vehicle is simulated. The simulation considers the uncertainty of aerodynamic parameters, measurement error, atmospheric interference and atmospheric environment. The simulation results show that the designed fuzzy PID controller has better control performance, stronger robustness and self-adaptability than the traditional PID controller.