捷联惯导系统空中动态标定技术研究  

A Study of SINS in-flight dynamic calibration Technique

作　　者：任建辉 陈超 李文耀 解芳 

机构地区：[1]北京自动化控制设备研究所,北京100074 [2]西安市临潼区94162部队51分队,西安710614

出　　处：《战术导弹控制技术》2013年第2期18-22,共5页

摘　　要：针对导弹全寿命周期内捷联惯导系统不拆弹标定的应用需求，提出了一种空中动态标定方案。该方案利用导弹挂机飞行运动条件，依据捷联惯导系统级标定的基本原理，使用卡尔曼滤波作为估计手段，依据外部GPS信息作为观测基准，设计飞行机动轨迹对各待标定误差项进行激励。仿真结果表明，该方案可行有效，能够对各项惯性器件误差项进行有效估计，降低对捷联惯导系统定期标定的要求。According to the demand of SINS calibrating without stripping the missile in the whole life-cycle, a SINS in- flight dynamic calibration method is proposed. Based on the missile＇ s embarkation flight motion condition, and according to the principle of system level calibrating, this method used the Kalman filter to excite the inertial parameter error , which used the external GPS information as measuring base and designed the flight maneuver track to incentive parameter pertur- bation. The results of simulations demonstrate the proposed method can achieve high estimating precision and reduce re- quirement of SINS periodic calibration.

关 键 词：捷联惯导 标定 空中动态 不拆弹 

分 类 号：TP391.9[自动化与计算机技术—计算机应用技术]