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.
出处
《飞行力学》
CSCD
北大核心
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)
关键词
量子导航
卡尔曼滤波
定位精度
quantum navigation
extended Kalman filter
the positioning precision
