弹道导弹惯性测量系统精度指标自适应分配方法

Adaptive Assignment Method for Accuracy Index of Ballistic Missile Inertial Measurement System

对弹道导弹惯性测量系统进行误差分析和精度指标分配是保证导航精度和武器作战性能的一项重要任务。针对目前惯性导航系统误差分析不全面、精度评估准则单一以及精度指标分配方法不准确的不足,提出了一种弹道导弹惯性测量系统精度指标自适应分配方法,能够按照误差项对精度的影响合理化分配精度指标。该方法首先分析了影响导航精度的所有误差项,并对比各误差项对导航精度的影响。其次,根据总体精度要求值和各误差源在落点精度中的占比,对每项误差系数进行自适应分配,通过逐次调整落点精度中占比最大误差项,最终实现精度指标要求下的最优误差系数指标。在精度指标自适应分配方法基础上,根据落点分布方向性,提出了一种横纵方向误差不等时的精度指标分配方法,更加突出方向性差异。由落点精度模拟可知,经自适应调整后,导弹落点的圆概率误差值(Circular Error Probable, CEP)和横纵向误差值均收敛到精度要求范围内,同时各项误差系数引起的落点精度占比更均匀,该方法为工程设计人员提供了设计依据与思路。

It is an important task that error assessment and error allocation of inertial measurement system of ballistic missile to ensure the navigation accuracy and the operational performance of weapon. Aiming at the shortcomings of incomplete error assessment, single accuracy evaluation criterion and inaccurate error allocation method of inertial navigation system, a method of error assessment and allocation of inertial measurement system based on adaptive algorithm is proposed in this paper, which could reasonably allocate the accuracy index according to the influence of error term on accuracy. Firstly, all the error terms that affect the navigation accuracy are analyzed, and the influence of each error term on the navigation accuracy is compared. Secondly, based on the accuracy requirements and the navigation parameters error ratios, each error coefficient is adaptively allocated, the instrument errors with adaptive algorithm are successively adjusted until the navigation parameter errors satisfy the hitting accuracy requirements. Meanwhile, based on the adaptive allocation method of accuracy index and the directivity of the distribution of the falling point, a method of accuracy index allocation with different horizontal and vertical errors is proposed, which highlights the difference of directivity. From the simulation of impact point accuracy, it could be seen that after adaptive adjustment, the circular error probable(CEP) and the transverse and longitudinal error of the missile impact point converge to the required accuracy range, and the proportion of the impact point accuracy caused by various error coefficients is more uniform. This method provides design basis and ideas for engineering designers.