CNS/SINS姿态组合导航系统仿真

Simulation of the CNS/SINS Posture Integrated Navigation SystemSimulation System

针对大部分飞行器导航采用地理坐标系导航,天文导航在地理坐标系下姿态解算依赖导航位置而容易发生精度发散的问题,文章研究了地理坐标系下,天文/惯性姿态组合导航系统滤波算法,以有效提高导航系统的精度。首先,对天文/惯性组合导航系统数学模型进行分析;然后,用Matlab软件根据实际情况设定参数并获得仿真数据,在仿真数据的基础上进行标准的卡尔曼滤波的仿真研究。仿真结果表明,当惯导与天文导航进行姿态组合后,各导航参数精度明显提高,在短期内可认为是收敛的,但仿真时间较长后,各导航参数出现缓慢的发散趋势。

Lots of aircrafts using the geographic coordinate to navigate and celestial navigation calculate posture relies on the location of carrier, and the accuracy of the parameters is easy to divergence. According to this problem, in this paper the filtering algorithm of CNS/SINS posture integrated navigation system in the geographic coordinate was studied to en- hance the precision of the navigation system. Firstly, the mathematic models of the CNS/SINS integrated navigation system was analyzed, and it was simulated was done using Matlab. Then the parameters were set according to the practical of the flight vehicle and the simulating data was obtaied, and the simulating research was using Kalman filter based on the simu- lating data. The results showed that when using the CNS/SINS posture integrated navigation, the precision of parameters was improved clearly and convergent in the short term. But the parameters trended dfvergent when simulation time was long.