捷联惯测组合误差系数分离与补偿方法  

Error coefficients separation and compensation for SIMU

作　　者：解静[1] 肖龙旭[2] 任革学[1] 

机构地区：[1]清华大学航天航空学院,北京100084 [2]第二炮兵装备研究院,北京100085

出　　处：《系统工程与电子技术》2011年第12期2716-2720,共5页Systems Engineering and Electronics

摘　　要：为了解决导弹飞行过程中捷联惯测组合误差系数相对于装订值的漂移问题,进一步提高惯性导航精度,提出了一种捷联惯测组合误差系数的分离和补偿方法。该方法利用真空飞行段导弹仅受地球引力和姿态变化引起的惯性力作用这一受力特点,结合惯测组合部分工具误差系数的射前修正,推导加速度计和陀螺仪输出模型零次项和一次项误差系数的分离模型,计算误差系数漂移引起的惯性导航误差并给出修正方法。试验结果表明,采用该方法可减小惯性导航误差约56%,进一步提高了惯性导航精度。The method of error coefficients separation and compensation for strap-down inertial measure unit （SIMU） is given in order to solve the excursion of SIMU error coefficients in-flight and further improve the inertial navigation precision. The separation model for zero drift values and proportionality coefficients of both aecelerometer and gyroscope is given using the characteristic that the missile is forced earth gravitation and iner tial force by angular rotation only through vacuum flying, combined with several SIMU instrument error coefficients correction models before launching. The inertial navigation error by the excursion of SIMU instrument error coefficients is calculated and the corrected method is given. Experiment result shows that about fifty-six percent decrease in inertial navigation error and an effective improvement in inertial navigation precision via this method.

关 键 词：惯性导航 误差系数分离 导航误差修正 捷联惯测组合 

分 类 号：V44[航空宇航科学与技术—飞行器设计]