南京航空航天大学学报（英文版）2005，Vol.22Issue(2)：115-118,4.
用于弹道导弹的GPS/SST/SINS组合导航滤波算法实现
REALIZATION OF GPS/SST/SINS INTEGRATED NAVIGATION FILTER ALGORITHM FOR BALLISTIC MISSILE
康国华 1刘建业 1祝燕华 1熊智1
作者信息
- 1. 南京航空航天大学自动化学院,南京,210016,中国
- 折叠
摘要
Abstract
Considering the domestic single navigation system of the ballistic missile, a new filter method is presented. The method integrates the information of the strapdown star tracker (SST) attitude, the position and the velocity of a high speed GPS with a strapdown inertial navigation system (SINS) information into one filter, thus improving the precision of the attitude, the velocity, and the position. Finally, the GPS/SST/SINS simulation platform is designed. Simulation results demonstrate that the filter is robust and reliable, and the precision rises to the comparative level abroad.关键词
组合导航/星光跟踪仪/弹道导弹/定位系统Key words
integrated navigation/SST/ballistic missile/location system分类
航空航天引用本文复制引用
康国华,刘建业,祝燕华,熊智..用于弹道导弹的GPS/SST/SINS组合导航滤波算法实现[J].南京航空航天大学学报（英文版）,2005,22(2):115-118,4.
