导弹飞行中无陀螺惯导系统的误差分析  

Error Analysis of Non-gyro Inertial Navigation System During Missile Flies

作　　者：施闻明[1] 杨晓东[1] 徐彬[1] 

机构地区：[1]海军潜艇学院,山东青岛266071

出　　处：《弹箭与制导学报》2007年第2期103-106,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：导弹飞行时,无陀螺惯导系统存在模型误差和系统误差。通过研究系统的数学模型,分析了系统的模型误差;在一种9加速度计配置方案的研究基础上,采用线性化Kalman滤波,抑制系统误差的积累。仿真结果表明,线性化Kalman滤波对系统误差有较好的抑制作用。When missile is flying, non-gyro inertial system has model error and system error. Model error of system is analyzed by investigating math model of system. On the basis of investigating distribution scheme of nine accelerometers, accumulation system error is controlled by linearization Kalman filter. The simulation result shows that linearization Kalman filter has good effect on controlling system error.

关 键 词：惯性导航 无陀螺 KALMAN滤波 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]