空空导弹SINS/GPS紧组合导航系统仿真

Simulation Study on SINS/GPS Tightly-coupled Integration Navigation System of Air-to-Air Missile

为了满足空空导弹远程发射要求,采用基于伪距、伪距率的SINS/GPS组合导航系统作为空空导弹的中制导。建立了惯性器件和GPS的误差模型,设计了Kalman组合滤波器,用MATLAB软件对紧组合系统进行了仿真研究。仿真结果表明,紧组合导航系统导航精度满足空空导弹中制导设计要求。

In order to meet the requirement that air-to-air missile could be launched in a long range, SINS/GPS integration navigation system based on pseudorange and pseudorange rate is used as its midcourse guidance. The error model of inertial device and GPS is built, and a Kalman filter for integration is designed, and the integration system is researched through simulation using MATLAB software. The simulation results show that the navigation accuracy of tightly-coupled integration navigation system can satisfy the midcourse guidance design requirement.