星光/惯性组合制导方案与位置误差分析  

Celestial/Inertial Combined Guidance Scheme and Position Error Analysis

作　　者：杨颖[1] 王明海[1] 

机构地区：[1]第二炮兵工程学院,陕西西安710025

出　　处：《上海航天》2007年第6期31-33,43,共4页Aerospace Shanghai

摘　　要：根据捷联星光制导双星方案和星光/惯性组合制导基本原理,提出了一种以惯性导航为主、星光制导为辅的导弹组合导航方法。建立了组合导航位置误差计算模型。对星光惯性组合制导精度的分析表明,该法提高了对星光导航测量信息的利用度,改善了导航精度。According to the principle of strapdown celestial guidance of double-star and celestial navigation/inertial navigation combined guidance method, a combined navigation method that the inertial method was the primary and the celestial method was subordinate one for missile was put forward in this paper. The position error calculation model of combined guidance was deduced. The precision analysis of using combined guidance method showed that this method used more information of measurement in celestial navigation with higher navigation accuracy.

关 键 词：星光制导 惯性制导 组合制导 位置误差 精度 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]