一种发射系下旋转弹的捷联惯导算法
A strapdown inertial navigation algorithm of spinning missile in launch coordinate system
陈旸 1王君 1苏晓东 1晏亮 2管冬雪2
作者信息
- 1. 北京航天长征飞行器研究所,北京 100076
- 2. 北京航天时代激光导航技术有限责任公司,北京 100094
- 折叠
摘要
为了提高旋转弹的姿态测量精度,提出了一种发射系下的旋转弹捷联导航算法.首先,推导了发射系导航更新方程;然后,利用传感器测量的前周期角速率对姿态更新算法进行优化,推导了基于角速率的旋转矢量更新算法及其算法误差;最后,采用陀螺仪标度因数的提升方法,实现了捷联惯导姿态测量精度有效的提高.通过对双子样、优化双子样算法在自旋运动条件下的数学仿真、基于转台的半实物仿真试验进行了验证.试验结果表明:在自旋机动条件下,相较于传统双子样算法,基于发射系的旋转弹捷联导航算法具有更高的精度,验证了算法在工程应用实现的正确性和有效性.
Abstract
Aiming at the improvement of the accuracy in attitude algorithm of spinning missile,a strapdown inertial navigation algorithm in launch coordinate system was proposed.Firstly,the navi-gation algorithms were deduced.Secondly,the rotation vector algorithms using pre-angular and calcu-lation errors were deduced.Finally,by using the improvement method for scaling factor,the attitude measurement was better realized.The mathematical simulation and semi-physical simulation for ana-lyses of two-sample,optimal two-sample are made.The results indicate that the performance of the optimal algorithm using pre-angular increment is better than traditional algorithm.The test verified the correctness and effectiveness of the algorithm.
关键词
旋转弹/优化双子样算法/发射系/标度因数提升Key words
spinning missile/optimal two-sample algorithm/launch coordinate system/improved scaling factor引用本文复制引用
出版年
2024
NETL
NSTL
万方数据