摘要
主要研究导弹发射升空以后,通过星敏感器测星实现对捷联惯导系统中陀螺仪误差参数的实时修正技术。从传统的星光制导原理出发,通过对数学平台系失调角的分析,论证了基于单星敏感器情况下的陀螺仪误差参数分离方法,并给出了具体的仿真结果,对实际系统的使用具有一定的指导意义。
The real-time correction of gyroscope error parameter in SINS by star sensor was researched. According to the basic starlight-guide theory, by analyzing the misalign angle of inertial reference, the separation method of gyroscope error parameter correction under single star sensor was demonstrated, and then the particular results of simulation were given. Above method and results are worth to reference for the engineering system.
出处
《现代防御技术》
北大核心
2006年第1期33-36,共4页
Modern Defence Technology
关键词
星敏感器
陀螺仪误差参数
实时修正
Star sensor
Gyroscope error parameter
Real-time correction
