为了提高多手持终端对卫星脉冲机动轨道的实时确定精度，并降低定轨精度对滤波初值的敏感性，提出一种五阶强跟踪球面单形-径向容积卡尔曼滤波(5-STSSRCKF)方法。采用n维正则单形变换群和矩匹配法推导五阶球面单形-径向容积准则，并将该准则嵌入强跟踪滤波(STF)框架。利用STF的等价表示计算次优渐消因子，实现了在滤波稳定时在线实时调整增益矩阵，克服了残差增大时增益矩阵仍保持极小值的缺点，提高了对系统突变状态的跟踪能力。进行了仿真实验，结果表明，当滤波初值误差增大时，已有方法的定轨精度降低为1 798.199 m，而提出的5-STSSRCKF的定轨精度可以维持在8.688 m; 当卫星进行脉冲机动时，已有方法不具备对机动轨道状态的跟踪能力，而5-STSSRCKF的定轨精度仍然维持在8.976 m。实验显示，5-STSSRCKF对滤波初值不敏感，并且对卫星脉冲机动轨道的实时确定精度更高。

To improve real-time determination accuracy of hand-held terminal for a satellite impulse maneuver orbit and to decrease the sensibility of orbit determination precision for an initial filtering value, a Fifty-degree Strong Tracking Spherical Simplex-radial Cubature Kalman Filter(5-STSSRCKF) method was proposed. N-dimensional regular simplex transformation group and moment matching method were used to deduce fifth-degree spherical simplex-radial cubature criterion,then the criterion was embedded into the Strong Tracking Filter Framework(STF). Equivalent representation of the STF was used to calculate suboptimal fading factors. By which,the gain matrix could be online adjusted in real time when the filter was stable.Thus, the disadvantage that gain matrix still maintained small minimal value at the time of increasing residual error was overcome and the tracking capacity for sudden change of system was improved. The simulation were performed,and the experiments experimental results show that if the error of the initial filtering value is increased the orbit determination accuracy of the existing method decreases,while that of to 1 798.199 m; 5-STSSRCKF can be maintained at 8.688 m; when the satellite is subject to impulse maneuver, these existing methods can not be used to track the maneuver orbit, the orbit determination accuracy of 5-STSSRCKF is still maintained at 8.976 m.These results show that 5-STSSRCKF is not sensitive to initial filtering value and has higher real-time determination accuracy for satellite impulse maneuver orbits.