GPS/SINS组合导航系统在飞航导弹中的应用

研究了ＧＰＳ／ＳＩＮＳ组合导航系统在飞航导弹制导中的应用。文中着重研究位置速度组合模式的ＧＰＳ／ＳＩＮＳ组合导航系统的构成和算法，简化误差模型，引入衰减记忆滤波。仿真结果表明，组合导航系统较准确地给出导弹的位置、速度和姿态信息，大大提高了制导精度

GPS/SINS Integration for Cruise Missile

In order to increase accuracy of navigation, GPS/SINS integration was considered in recent literature. An improved GPS/SINS integrated navigation system for cruise missile midcourse guidance, which required measuring both position and velocity, was designed. A simplified SINS error model, which only contained 15 states, was used for KALMAN filter. As a result, the amount of computation needed is less by 42% as compared with the traditional algorithms. To avoid the filter being unstable, a declining memory filtering algorithm was introduced in such a way that eq. (23) could be replaced by eq. (29). A cruise missile midcourse guidance system was taken as example. Simulation results were given in Figs.1 and 2. It can be easily seen that the position error is almost always less than 10 m. The results indicate that the proposed algorithm is feasible.