基于地理坐标系的惯性导航原理性误差分析  

Principle error analysis of inertial navigation

作　　者：王司[1] 

机构地区：[1]哈尔滨工业大学控制科学与工程系

出　　处：《黑龙江工程学院学报》2006年第2期10-14,共5页Journal of Heilongjiang Institute of Technology

基　　金：武器装备预研基金资助项目(514090101HT0141)

摘　　要：对惯性导航基本方程进行分析,首次指出通常使用的惯性导航基本方程存在原理性误差,推导原理性误差表达式,在地球为圆球形的情况下,提出消除原理性误差的方法。仿真结果表明:对于高速导弹,所提出的原理性加速度误差与有害加速度大小处于同一量级上,已经不容忽略;发射角为45°时,水平原理性误差最大;导弹的加速度和速度越大,水平原理性误差越大;水平原理性误差随着时间的增长而增加。Inertial navigation basic equation is analyzed. It points out that there is principle error in inertial navigation for the first time. Principle error expression is presented. Under the condition that the earth is globe, the way of eliminating principle error is given. Simulations show that the given principle acceleration error is the same order as harmful acceleration for high speed missile and can not be ignored. When launch angle is 45°, the horizontal principle error is maximum. The larger the missile acceleration and velocity are, the larger the horizontal principle error is. The horizontal principle error increases with time elapsing.

关 键 词：惯性导航 原理性误差 地理坐标系 高速导弹 

分 类 号：U666.12[交通运输工程—船舶及航道工程]