单轴旋转捷联惯导系统初始对准误差分析  

Error Analysis for Initial Alignment of Single-axis Rotating SINS

作　　者：赵晓伟[1] 孙谦[1] 陈鸿跃 

机构地区：[1]北京航天发射技术研究所,北京100076

出　　处：《导弹与航天运载技术》2014年第4期58-62,共5页Missiles and Space Vehicles

摘　　要：为提高车载捷联惯导系统的方位对准精度,基于单轴旋转捷联惯导系统,给出单轴旋转捷联惯导系统方位角误差传播方程,提出影响方位对准精度的陀螺常值漂移误差、IMU安装误差、刻度因数误差、随机漂移误差、旋转机构测角误差、旋转轴运动误差、加速度计尺寸效应误差等误差源。根据方位角误差传播方程分析各误差源导致的方位角误差。针对各项误差源对寻北结果的不同影响提出相应的误差控制方法,减小了方位对准误差。For purpose of improving the precision of azimuth alignment, based on single-axis rotating strap-down inertial navigation system, the azimuth angle error propagating equation is offered. The paper points out the errors that affect the precision of azimuth alignment. The errors mainly include constant gyro drift, IMU installation error, scale factor error, random drift, the measurement error of angle sensor, the moving error of rotation axis, accelerometer size effect error. By analyzing these errors, aiming at the different influence resulting from different source error, the error control methods are put forward and these methods reduce the error of azimuth alignment.

关 键 词：单轴旋转 方位对准 误差传播方程 捷联惯导系统 

分 类 号：V249.3[航空宇航科学与技术—飞行器设计]