过载自动驾驶仪分析研究  

Analysis of Lateral Acceleration Autopilot

作　　者：李玉林[1] 李晅 杨树兴[1] 

机构地区：[1]北京理工大学,北京100081 [2]中国兵器工业总体部,北京100089

出　　处：《战术导弹技术》2008年第6期63-68,共6页Tactical Missile Technology

摘　　要：对过载自动驾驶仪的固有特性进行了研究.通过数学推导得出尾舵控制导弹过载自动驾驶仪具有非最小相位特性,仿真结果证明也是如此.过载自动驾驶仪是典型的0型系统,存在稳态误差.稳态误差与导弹速度、加速度反馈回路增益、弹体开环气动增益及舵系统增益有关,而与角速度反馈回路增益无关;主反馈回路可提供一定的相位超前,这有利于设计舵机伺服系统.Inherent characteristic of lateral acceleration autopilot is studied. The conclusion that the lateral acceleration autopilot of tail fin-control missile behaving non-minimum phase is made by mathematics formulae and the simulation results show that is true. The lateral acceleration autopilot is type 0 system and has steady state error which depends on missile velocity, acceleration feedback loop gain, open-loop aerodynamic gain and rudder system gain, and is independent of angle rate feedback gain. The main feedback loop can provide some phase advance which is good for designing rudder servo system.

关 键 词：过载自动驾驶仪 相位超前 非最小相位系统 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]