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.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
1998年第4期21-27,共7页
Journal of Astronautics
关键词
惯导系统
误差分析
弹性振动
机翼
导弹
Inertial navigation system Error analysis Elastic vibration Lever arm effect
