捷联惯测组合误差系数分离与补偿方法

摘要

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 accelerometer and gyroscope is given using the characteristic that the missile is forced earth gravitation and inertial 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.%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.