近地航天器量子导航定位卡尔曼滤波算法研究  

Study on Kalman kilter algorithm for the near-earth spacecraft quantum positioning system

作　　者：王志刚[1,2] 邓逸凡[1,2] 杨绚[1,2] 

机构地区：[1]西北工业大学航天学院,陕西西安710072 [2]航天飞行动力学技术国家重点实验室,陕西西安710072

出　　处：《飞行力学》2016年第5期69-72,共4页Flight Dynamics

基　　金：航天科技创新基金资助(CASC-1314-05-12)

摘　　要：针对近地航天器量子导航定位系统,为了进一步提高其定位精度,利用滤波技术将QPS测量值结合航天器的运动模型进行状态量的滤波估计。给出了基于基线干涉原理的量子定位系统观测方程和以二体运动为主的航天器轨道运动模型,在此基础上详细推导了扩展卡尔曼滤波处理过程,并针对该模型进行了仿真。仿真结果表明,基于EKF的量子导航定位精度有明显提高。In order to improve the precision of spacecraft＇s quantum positioning system（ QPS）,the filter technique was used to combine the QPS observation value with the spacecraft＇s motion model to perform filtering estimation of the state variables. The QPS observation equation based on baseline interferometer method and the orbital motion model of the spacecraft was put forward. Furthermore,the process of the extended Kalman filter（ EKF） using in this case was derived in detail. The simulation results show that the QPS based on EKF had obvious higher precision than the original one.

关 键 词：量子导航 卡尔曼滤波 定位精度 

分 类 号：V448.23[航空宇航科学与技术—飞行器设计] P228.1[天文地球—大地测量学与测量工程]