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捷联惯性/大视场星光组合导航方法研究
引用本文:李双喜,张宗梅,张俊.捷联惯性/大视场星光组合导航方法研究[J].航天控制,2011,29(2):7-9.
作者姓名:李双喜  张宗梅  张俊
作者单位:1. 北京航天自动控制研究所,北京,100854
2. 北京航天自动控制研究所,北京100854;宇航智能控制技术国防科技重点实验室,北京100854
摘    要:近年来,使用星敏感器的导弹、火箭惯性组合导航成为国内外研究的热点.本文对捷联惯性/大视场星光组合导航方法进行了研究,建立了卡尔曼滤波方程,并利用SINS误差转移矩阵方法估计主动段导航误差.数学仿真表明:捷联惯性/大视场星光组合导航方法不仅可以修正姿态角偏差和陀螺常值漂移,还可以对主动段的速度、位置误差有很好的估计效果.

关 键 词:捷联惯性  大视场  星敏感器  卡尔曼滤波  组合导航

The Research on Integrated Navigation Method of SINS/Star with Large View Field Star Tracker
LI Shuangxi,ZHANG Zongmei,ZHANG Jun.The Research on Integrated Navigation Method of SINS/Star with Large View Field Star Tracker[J].Aerospace Control,2011,29(2):7-9.
Authors:LI Shuangxi  ZHANG Zongmei  ZHANG Jun
Institution:LI Shuangxi1 ZHANG Zongmei1,2 ZHANG Jun1,21.Beijing Aerospace Automatic Control Institute,Beijing 100854,China2.National Aerospace Intelligence Control Technology Laboratory,China
Abstract:Recently,the integrated navigation using star tracker in missiles and rockets becomes a hotspot in both domestic and oversea.The integrated navigation method of SINS/Star with large view field star tracker is studied and the Kalman filter equation is established in this paper.Using the SINS error transfer matrix method,the navigation error of ballistic missile in ascend phase is also estimated.The simulation results show that the integrated navigation method of SINS/Star with large view field star tracker c...
Keywords:SINS  Large view field  Star tracker  Kalman filter  Integrated navigation  
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