摘要
基于捷联惯性测量组合和星敏感器的“惯性+星光”复合导航方式综合了两种导航方式的优点,可以实现组合导航的高动态和高精度。研究了惯性/星光组合制导捷联安装的系统误差模型及其可观测度分析方法,计算了在不同位置进行误差分离的系统状态可观测度,并通过数学仿真证明了该分析方法的有效性,可应用于惯性/星光制导方案在线分离惯性失准角和安装误差角的方案快速论证。
The combined navigation system of INS(Inertial Navigation System)/CNS(Celestial Navigation System)is studied.The system error model of INS/CNS based on the strapdown INS installation approach is firstly developed.Then,the observability analysis method of the system error model is investigated,upon which the different observability of error separation at different locations is calculated.Finally,the effectiveness of the proposed analysis method is proved by numerical simulation.The above findings can be well applied to the inertial/starlight guidance scheme to quickly separate the inertial misalignment angle and the installation error angle,and finally achieve the high dynamics and precision.
作者
郭振西
武斌
谢佳
闵昌万
Guo Zhen-xi;Wu Bin;Xie Jia;Min Chang-wan(Science and Technology on Space Physics Laboratory,Beijing,100076)
出处
《导弹与航天运载技术》
CSCD
北大核心
2020年第2期54-57,共4页
Missiles and Space Vehicles
关键词
捷联星光制导
误差分离
可观测度
strapdown starlight guidance
error separation
observability
