在轨卫星GPS导航实时高精度定轨控制仿真

发布时间：2018-03-07 11:41

本文选题：测码伪距　切入点：超快速星历　出处：《计算机仿真》2017年07期 　论文类型：期刊论文

【摘要】：目前越来越多的应用需要依赖高精度的实时卫星轨道数据,由于目前GPS接收机所使用的广播星历精度不高和星上处理器性能有限等原因,实时定轨的精度不是很理想。针对这种情况,提出了一种新的星载GPS实时定轨方法。上述方法采用工程应用背景,使用IGS发布的超快速星历代替广播星历,以相位平滑后的测码伪距作为主要观测量,结合简化的动力学模型,通过扩展卡尔曼滤波器进行低轨卫星轨道的实时解算。为了验证其性能,使用上述算法对CHAMP卫星的在轨实际观测数据进行模拟实时处理,结果表明,改进方法不仅计算量小,而且定轨精度高。
[Abstract]:At present, more and more applications need to rely on real-time satellite orbit data with high accuracy. Due to the low accuracy of broadcast ephemeris and limited performance of on-board processors used in GPS receivers, The accuracy of real-time orbit determination is not ideal. In view of this situation, a new real-time orbit determination method for spaceborne GPS is proposed. Using the background of engineering application, the super-fast ephemeris issued by IGS is used to replace the broadcast ephemeris. Taking the pseudo-range of the measured code after phase smoothing as the main observation quantity and combining the simplified dynamic model, the real time calculation of Leo satellite orbit is carried out by extended Kalman filter. In order to verify its performance, The above algorithm is used to simulate the real time observation data of CHAMP satellite in orbit. The results show that the improved method not only has a small amount of calculation, but also has high orbit determination accuracy.
【作者单位】：上海卫星工程研究所;
【分类号】：P228.4

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