旋转弹导航算法研究

摘要

The adaptability of traditional navigation algorithm to spinning missile is studied.The reason of its limitation is analyzed.Based on the analysis,three different methods are brought forward,which are based on body coordinate,semi-body coordinate and quaternion kinematics respectively.The availability of the three methods for spinning missile is validated with simulation results.%首先仿真分析了传统导航算法对旋转弹的适应性,并对其局限性产生的原因进行了分析.基于此,提出了3种不同的思路,分别为基于弹体系、准弹体系和四元数运动学的四元数更新算法,并进行了仿真分析.结果表明,这3种思路对提高旋转弹导航精度都起到了有利的作用.