弹性机翼对机载导弹子惯导系统导航精度的影响分析  

ANALYSIS ON INFLUENCE OF ELASTIC WING ON ACCURACY OF INERTIAL NAVIGATION SUBSYSTEM IN AIRBORNE MISSILE

作　　者：崔乃刚[1] 林晓辉[1] 田鸿堂 徐伯夏 

机构地区：[1]哈尔滨工业大学 [2]天津8357所

出　　处：《宇航学报》1998年第4期21-27,共7页Journal of Astronautics

摘　　要：弹性机翼的振动及杆臂效应会引起机载导弹加速度计输出中的附加干扰加速度，从而引起导弹子惯导系统的导航参数误差。本文通过建立机翼弹性振动模型及惯导误差传播模型，从理论上分析了机翼弹性振动及杆臂效应对子惯导系统导航精度的影响，并进行了计算机仿真研究。The Vibration and lever arm effects of elastic wing cause an additional interference acceleration existed in the output of an accelerometer mounted in the airborne missile,and can lead to navigation errors of inertial subsystem.In this paper,by modelling the elastic wing vibration and inertial navigation error transmission equations, the influence of vibration and lever arm effects of the elastic wing on the accuracy of inertial navigation subsystem is analysed theoretically.The simulation results are given.

关 键 词：惯导系统 误差分析 弹性振动 机翼 导弹 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]