海洋学研究 ›› 2022, Vol. 40 ›› Issue (1): 53-63.DOI: 10.3969/j.issn.1001-909X.2022.01.006

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HY-1C卫星运行轨道的计算研究

轨道数据是卫星资料处理过程涉及的重要参数，高质量HY-1C卫星产品离不开准确的轨道计算。本文从两行报(Two-Line Orbital Element，TLE)中提取数据，使用STK(Satellite Tool Kit)软件准确模拟出卫星轨道并输出星历表，通过比较两种计算HY-1C卫星轨道算法的精度，评估摄动因素对轨道计算的影响。方法一未考虑摄动，以参考时间的轨道根数为基础外推出观测时间的星历参数，进而计算卫星轨道数据；方法二采用考虑摄动的SGP4模型进行轨道计算。结果表明摄动对轨道计算结果影响明显：不考虑摄动的算法随着时间的推移误差显著增大，0.5 h内位置和速度误差分别小于10 km和10 m/s；考虑摄动的SGP4模型算法计算速度快、计算精度高且稳定性好，24 h内位置和速度误差分别小于68 m和0.051 m/s。因此，SGP4模型算法可用于近轨卫星HY-1C的高精度轨道计算。


  

  1. 1.上海交通大学海洋学院，上海 200240； 
    2.卫星海洋环境动力学国家重点实验室，浙江 杭州 310012；
    3.自然资源部第二海洋研究所，浙江 杭州 310012； 
    4.南方海洋科学与工程广东省实验室(广州)，
    广东 广州 511458； 
    5.浙江大学海洋学院，浙江 舟山 316021
  • 出版日期:2022-03-15 发布日期:2022-03-15
  • 通讯作者: 毛志华 (1966-)，男，研究员，主要从事海洋遥感方面的研究
  • 基金资助:
    国家重点研发计划(2016YFC1400901)；南方海洋科学与工程广东省实验室(广州)人才团队引进重大专项(GML2019ZD0602)；国家自然科学基金(41621064, 41476156)；高分辨率对地观测系统重大专项(05-Y30B01-9001-19/20-2)

Study on orbit calculation of HY-1C satellite

  • Online:2022-03-15 Published:2022-03-15

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摘要： 轨道数据是卫星资料处理过程涉及的重要参数，高质量HY1C卫星产品离不开准确的轨道计算。本文从两行报(TwoLine Orbital Element，TLE)中提取数据，使用STK(Satellite Tool Kit)软件准确模拟出卫星轨道并输出星历表，通过比较两种计算HY1C卫星轨道算法的精度，评估摄动因素对轨道计算的影响。方法一未考虑摄动，以参考时间的轨道根数为基础外推出观测时间的星历参数，进而计算卫星轨道数据；方法二采用考虑摄动的SGP4模型进行轨道计算。结果表明摄动对轨道计算结果影响明显：不考虑摄动的算法随着时间的推移误差显著增大，0.5 h内位置和速度误差分别小于10 km和10 m/s；考虑摄动的SGP4模型算法计算速度快、计算精度高且稳定性好，24 h内位置和速度误差分别小于68 m和0.051 m/s。因此，SGP4模型算法可用于近轨卫星HY1C的高精度轨道计算。


关键词: 轨道计算, 两行报, 摄动, SGP4模型, STK软件

Abstract: Orbital data are important parameters involved in the satellite data processing and HY1C satellite products with high quality are inseparable from the accurate calculation of the orbit. In this study, data were extracted from the TLE (TwoLine Orbital Element) and used to accurately simulate satellite orbit based on STK (Satellite Tool Kit) software. The ephemeris was outputted to compare the accuracy of two satellite orbit algorithms of HY1C and evaluate the influence of perturbation factors on orbit calculation. Method one uses an algorithm which does not consider perturbation factors and extrapolates the ephemeris parameters of the observation time based on the orbit elements of the reference time, and then calculates the satellite orbit data. Method two adopts the SGP4 model which considers perturbation to calculate the orbit data. The results show that perturbation has a significant impact on the orbit calculation. The algorithm error without considering the perturbation increases significantly with the passage of time, and the position errors are less than 10 km with the speed errors less than 10 m/s in half an hour. While SGP4 model algorithm runs fast with high calculation accuracy and good stability, the position and speed errors within 24 hours are less than 68 m and 0.051 m/s respectively. Therefore, SGP4 model algorithm can be used for the highprecision orbit calculation of the loworbit satellite HY1C.


Key words: orbit calculation, TLE, perturbation, SGP4 model, STK software

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