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

作　　者：王楠[1] 王龙[1] 

机构地区：[1]中国空空导弹研究院,河南洛阳471000

出　　处：《现代电子技术》2011年第20期93-95,共3页Modern Electronics Technique

基　　金：航空科学基金项目(20090112006)

摘　　要：针对新一代远程空空导弹的特点,研究了在导弹发射惯性坐标系下,基于伪距/伪距率的GPS/SINS紧组合导航算法,推导了该坐标系下的惯导一阶误差传播方程,建立了该坐标系下GPS/SINS组合导航系统的状态方程和量测方程,并进行了相关数学仿真验证。仿真结果表明,在该坐标系中GPS/SINS紧组合导航算法有较高的导航精度。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 

分 类 号：TN966-34[电子电信—信号与信息处理] V249.32[电子电信—信息与通信工程]