论文部分内容阅读
低轨卫星轨道预报精度受到大气模型和大气阻力系数精度的制约,给一些高精度的空间和航天任务带来不利影响.提出了一种基于沿迹方向误差发散规律的大气阻力系数计算新方法.首先通过理论推导给出低轨卫星轨道预报中沿迹误差发散的分析表达式,定量描述初值误差和模型误差对沿迹误差的综合影响;提出利用定轨段的基本信息,优选预报段所采用的阻力系数,抑制沿迹误差的发散速率,从而降低沿迹方向预报误差的最大值,提高短期预报精度.以400 km附近的GRACE-A卫星的全弧段星载GPS高精度资料为基础,检验了方法的精度和成功率.结果表明:相对于传统的定轨预报方法,新方法能提高24 h短期预报精度约45%,成功率约71%,总体有效率约86%;方法对低、中、高等3种太阳辐射水平均有效,对于中低等级的地磁扰动也有效,具备较好的应用价值.
The accuracy of LEO satellite orbit prediction is restricted by the accuracy of the atmospheric model and the atmospheric drag coefficient, which will adversely affect some high-precision space and space missions. A new method for calculating the atmospheric drag coefficient based on the error divergence along the track is proposed. Firstly, the analytic expressions of the tracking error divergence in low-orbit satellite orbit forecast are given by theoretical derivation, and the initial effects of the initial error and the model error are quantitatively analyzed. Based on the basic information of the orbit determination section, The drag coefficient is used to suppress the divergence rate of the tracking error so as to reduce the maximum value of the prediction error along the track and improve the short-term forecast accuracy.Based on the high accuracy data of the satellite GRACE-A satellite 400 km near the whole arc, The accuracy and success rate of the method are compared.The results show that compared with the traditional orbit determination method, the new method can improve the short-term forecast accuracy of about 24 h by about 45%, the success rate of about 71% and the overall efficiency of about 86% Middle and high level of three kinds of solar radiation levels are valid for medium and low grade geomagnetic disturbance is also effective, with good application value.