基于GPS的弹载捷联惯导动基座传递对准技术

Transfer alignment for missile-borne SINS using airborne GPS on moving base

针对载机未装备主惯导系统的弹载捷联惯导初始对准问题,提出了一种基于机载GPS信息的动基座传递对准算法。首先利用惯性凝固思想设计了基于比力积分和GPS速度信息的惯性系粗对准算法,粗略估计弹载惯导的初始姿态;然后通过分析惯导系统在惯性系下的导航误差方程,设计了基于GPS信息的"速度+位置"匹配卡尔曼滤波精对准算法,对粗对准误差做进一步估计补偿。车载试验结果为:与车载激光捷联惯导输出相比,水平和方位对准精度分别为6'和18'。试验验证了该算法的有效性,为未装备机载主惯导的弹载捷联惯导的快速初始化提供了工程应用参考。

A novel transfer alignment algorithm（TA） utilizing airborne GPS measuring information was presented to solve the problem in initial alignment of missile-borne Strapdown Inertial Navigation System（SINS） for combat aircrafts equipped without master SINS.The TA procedure is divided into two steps：1） The inertial coarse alignment is implemented,in which an inertia freezing methodology is emploied to roughly initialize the missile＇s attitudes using specific force integration and GPS velocity.2） The coarse initialization is refined through a velocity plus position matching Kalman filter.Land vehicle testing experiment was conducted,and the level and azimuth misalignment of TA were 6＇and 18＇,respectively.The results indicate that the proposed algorithm is effective and therefore has an important reference value for practical applications.