冲压发动机导弹飞行/推进协调控制  

Flight/propulsion coordinated control of ramjet missile

作　　者：沙建科[1] 徐敏[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《应用力学学报》2015年第6期950-954 1099,1099,共6页Chinese Journal of Applied Mechanics

摘　　要：针对冲压发动机导弹飞行/推进耦合问题,提出了一种基于飞行/推进一体化设计思想的空气舵和发动机推力协调控制方法。采用反馈线性化将纵向控制数学模型进行精确线性化并设计了飞行/推进协调动态逆控制器。仿真结果表明:本文设计的控制器实现了对纵向轨迹的精确跟踪和解耦控制;同时发动机推力参与纵向控制还可增大导弹可用过载,改善导弹飞行控制品质。In order to resolve the ramjet missile flight/propulsion coupled problem, a rudder and ramjet thrust coordinated control method is proposed based on the integrated design of flight/propulsion. The feedback linearization method is utilized to achieve the precision linearization of the longitudinal control model, and the flight/propulsion coordinated decoupling controller is designed based on the dynamic inversion theory. Simulation results show that the controller realized the longitudinal trajectory accurate tracking and decoupling control, meanwhile the ramjet propulsion introduced into the longitudinal control can increase the available overload and improve the quality of the missile flight control.

关 键 词：冲压发动机导弹 飞行/推进耦合 动态逆 协调控制 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]