摘要
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。
According to the strict aero dynamic heating and force environment, which had the characters of strong uncertainty of flight parameters, reaction-jet/aerodynamic compound control system is usually used in lifting hypersonic reentry flight. A reaction-jet/aerodynamic compound control system based on fuzzy PID control is developed.The scheme designs fuzzy PID controller for each subsystems. Simulation results show that the proposed fuzzy PID controller provides better control performance, better robustness, and better adaptive ability than traditional PID controller.
出处
《系统仿真学报》
CAS
CSCD
北大核心
2010年第A01期146-148,共3页
Journal of System Simulation
基金
航天支撑基金项目
