单兵导弹捷联惯导系统IMU测量误差模型  

Measurement Error Model of IMU in Strapdown Inertial Guidance System of Manpads Missile

作　　者：李召[1] 张靖[1] 陈尧[1] 

机构地区：[1]北京理工大学,北京100081

出　　处：《战术导弹技术》2009年第4期73-75,共3页Tactical Missile Technology

摘　　要：为了全面深入地研究单兵导弹捷联惯导系统的IMU测量误差传播特性及其对命中精度的影响,在对惯导基本方程简化的基础上建立了捷联惯导系统误差模型.根据导弹飞行距离近的特点,在精度允许的范围内,简化了惯导基本方程,采用四元数法建立了平台漂移模型和加速度误差模型.通过拉氏变换对误差的传播特性进行分析,提出了满足命中精度要求的器件精度范围.Based on simplified basic equation, the SINS error model in flight is set up in order to study the measurement error of IMU in strapdown inertial guidance system of manpads missile, and the influence of the error on hit accuracy is analyzed. The basic equation is simplified in allowable accuracy range due to short range. The platform drift error model and the acceleration error model are set up by using the quaternionic vector. The error spread feature is analyzed, and the allowable sensor accuracy is presented.

关 键 词：单兵导弹 捷联惯导 测量误差 

分 类 号：O212.1[理学—概率论与数理统计] TN966[理学—数学]