摘要
针对某型高超声速飞行器纵向巡航段模型对高度和速度的机动控制问题,研究并比较了采用吸气式超燃冲压发动机与火箭发动机作动力的飞行控制方法上的不同;重点分析了机体-推力耦合特性、高度-速度耦合特性以及超燃冲压发动机工作状态对飞行姿态的巨大影响;提出了油门和升降舵的协调控制方法,并进行了线性二次型控制律设计.通过仿真验证了该设计方法的有效性.
Based on the longitude cruise model of a hypersonic vehicle, the control of the altitude and velocity response is studied. Firstly, the airbreathing ramjet engine is contrasted with rocket engine and the differences of control method in between are proposed. The airframe-propulsion and altitude-velocity integration are mainly analyzed. Then the integrated control of thrust and elevator is proposed, and the control law is designed by linear quadratic regulator. Finally, simulations results show the effectiveness of the proposed methods.
出处
《控制与决策》
EI
CSCD
北大核心
2011年第9期1429-1432,共4页
Control and Decision
基金
国防基础科研项目(07114840)
关键词
吸气式超燃冲压发动机
机体-推力耦合
高度-速度耦合
协调控制
线性二次型
alrbreathing ramjet engine
airframe-propulsion integration
altitude-velocity integration
integrated control
linear quadratic regulator
