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

作　　者：陈旸[1] 王君 苏晓东[1] 晏亮[2] 管冬雪 CHEN Yang;WANG Jun;SU Xiaodong;YAN Liang;GUAN Dongxue(Beijing Institute of Space Long March Vehicle,Beijing 100076,China;Beijing Aerospace Times Laser Inertial Technology Company Limited,Beijing 100094,China)

机构地区：[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

出　　处：《海军工程大学学报》2024年第3期97-102,共6页Journal of Naval University of Engineering

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。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 navigation algorithms were deduced.Secondly,the rotation vector algorithms using pre-angular and calculation 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 analyses 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 

分 类 号：TK427[动力工程及工程热物理—动力机械及工程]