摘要
导弹在大攻角再入飞行过程中,偏航通道和滚动通道存在着气动交连耦合,当耦合影响较大时,采用传统的把耦合项当作随机干扰的办法来处理,容易造成系统失稳。因此采用基于H∞混合灵敏度解耦控制的方法对通道间进行解耦,对于H∞混合灵敏度加权函数,通过遗传算法优化获得,并推导了H∞混合灵敏度标准型的建立过程和遗传算法优化加权函数的步骤。应用该方法,对导弹大攻角飞行过程中通道间的解耦控制进行设计。仿真表明,对参数不确定性的耦合系统,该方法具有良好的解耦性和鲁棒稳定性。
Aerodynamic coupling is existed between yawing channel and roll channel in the process of large attack angle reentry of missile. Traditional method that regards the coupling as random disturbance can cause instability when the coupling is bigger. The method of H∞ mixed sensitivity decoupling control is adopted to decouple the coupling of channels, and the method of genetic algorithm is adopted to optimize the weigh function of H∞ mixed sensitivity. The establishing process of standard type of H∞ mixed sensitivity and optimizing steps of weigh function based on genetic algorithm are deduced. Coupling between channels is decoupled in the process of large attack angle flight of missile by the decoupling controller. The simulation results show that the method has good decoupling and robust stability for parametric uncertainties system.
出处
《航天控制》
CSCD
北大核心
2007年第3期28-32,共5页
Aerospace Control
关键词
大攻角再入
H∞混合灵敏度
解耦
遗传算法
Large attack angle reentry
H∞ mixed sensitivity
Decoupling
Genetic algorithm
