大攻角飞行空空导弹鲁棒自动驾驶仪设计  

Robust Autopilot Design for High Angle of Attack Air-to-Air Missile

作　　者：张举[1] 祝小平[1] 

机构地区：[1]西北工业大学,西安710072

出　　处：《火力与指挥控制》2010年第4期111-113,117,共4页Fire Control & Command Control

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.

关 键 词：大攻角 线性分式变换 方法 鲁棒性能 

分 类 号：V448[航空宇航科学与技术—飞行器设计]