现代电子技术2011，Vol.34Issue(20)：93-95,3.
惯性系下GPS/SINS紧组合导航算法研究
Research of GPS/SINS Tightly Integrated Navigation Algorithm in Inertial Coordinate
摘要
Abstract
In view of the characteristics of the long-distance AAM, the GPS/SINS tightly integrated navigation algorithm based on pseudo-range/pseudo-range rate in the missile inertial coordinate is studied. The first-order error spread equations were derived in ile inertial coordinate. The state equations and measurement equations for GPS/SINS tightly integrated navigation system are established. The simulation results indicate that this GPS/ SINS algorithm can improve navigation accuracy effectively.关键词
伪距/伪距率/GPS/SINS/导弹惯性系Key words
pseudo-range/ pseudo-range rates GPS/SINS/ missile inertial coordinate分类
信息技术与安全科学引用本文复制引用
王楠,王龙..惯性系下GPS/SINS紧组合导航算法研究[J].现代电子技术,2011,34(20):93-95,3.基金项目
航空科学基金项目(20090112006) （20090112006）
