摘要
当前,导弹自动驾驶仪多采用经典设计方法。是在导弹气动参数变化不大、通道间的耦合较小的情况下设计的。为了满足导弹高机动性能要求,常采用大攻角飞行;然而导弹大攻角飞行时,将会出现空气动力学系数不确定性、非线性和通道间的严重耦合问题,这就要求所设计的自动驾驶仪具有较好的鲁棒性。就导弹在大攻角飞行状态下、通道间解耦的基础上,针对空气动力学系数不确定性,用μ方法对俯仰通道驾驶仪进行了设计,仿真表明该方法具有较好的鲁棒性能。
Now most guided missile systems employ classical method to design autopilot based on the assumption that cross-couplings among roll,pitch,yawl channels is small and aerodynamic coefficients isn＇t varied enormously.In order for the missile possessing super maneuverability the high angle of attack to flight is needed.However,there are the uncertain of aerodynamic coefficients and nonlinear and serious cross-couplings among the channels.Above all the reasons,the autopilot designed need to have strong robust.This paper illustrates the application of μ-synthesis to design the pitch-autopilot for high angle of attack missile and decoupled among channels aiming at the uncertainty of aerodynamic coefficients.The simulation presents the strong robust performance using this method.
出处
《火力与指挥控制》
CSCD
北大核心
2010年第4期111-113,117,共4页
Fire Control & Command Control
关键词
大攻角
线性分式变换
方法
鲁棒性能
high angle of attack
linear fraction transformation
μ-synthesis
robust performance
