The relative navigation based on carrier phase differential GPS for the space station con-comitant spacecraft was investigated in this paper .The system state space model for the relative nav-igation was derived and the GPS integer ambiguities were included in the system state vector .The extended Kalman filter ( EKF) was used to get the optimal estimation of the relative navigation .In addition , the method of combining the float solution and the fixed solution of the GPS integer ambi -guity was presented to improve the accuracy of the relative navigation .The simulation results showed that the accuracy of the relative navigation with combining the float solution and the fixed solution was higher than the relative navigation only with the float solution by EKF .%研究了基于载波相位差分GPS的空间站伴随飞行器相对导航技术,建立了相对导航滤波的系统状态空间模型,并且系统状态向量中包含了GPS整周模糊度;采用扩展卡尔曼滤波EKF实现了相对导航滤波的最优状态估计,并提出了浮点解和定点解相结合的GPS整周模糊度解算方法,以提高相对导航精度. 仿真结果表明,与仅采用EKF对GPS整周模糊度进行最优估计获得浮点解的方法相比,采用浮点解和定点解相结合的GPS整周模糊度解算方法,可有效提高相对导航滤波精度.
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