初始对准误差对惯性制导误差影响的简化算法  

A Simplified Algorithm for Calculating the Influence of Initial Alignment Error on Inertial Guidance Error

作　　者：刘毅[1] 刘志俭 吕新广[1] 

机构地区：[1]北京航天自动控制研究所 [2]61081部队

出　　处：《航天控制》2006年第2期30-33,共4页Aerospace Control

摘　　要：惯性制导系统初始对准的主要任务是精确确定载体坐标系和制导坐标系之间的初始方向余弦矩阵和载体的初始速度。惯性制导的精度在很大程度上取决于系统初始对准的精度。本文基于初始对准误差引起的惯性导航误差模型,针对近程战术武器系统,在一定精度范围内,忽略引力变化和发射时载体的初始速度,推导出初始对准误差对惯性制导误差影响的简化算法。该算法具有模型清晰,计算简便,易于使用的特点,避免了繁琐的运动学建模和编程计算过程,并且为在项目论证阶段不具备完备的总体数据支持的条件下,进行初始对准精度指标分配提供了理论依据。并经仿真验证,简化算法具有一定的精度。The main tasks of initial alignment of the SINS guidance system are to precisely determine the initial direction cosine matrix between the carrier body coordinate system and the guidance coordinate system, as well as the initial velocity of the carrier. The precision of SINS guidance system mainly lies on the precision of initial alignment. Basing on navigation error model, this paper deduces a simplified algorithm to calculate the impact of the initial alignment errors on the SINS guidance errors of short range tactical weapons, by neglecting gravitation change and initial low velocity in a reasonable precision range. This algorithm, which is simple, pellucid and wieldy, avoids fussy calculation and provides academic foundation of allotting the initial alignment error index without enough missile data support in the project verification phase. Simulation shows the precision of the algorithm.

关 键 词：惯性导航 初始对准 制导工具误差 

分 类 号：V448.23[航空宇航科学与技术—飞行器设计]