陈祎豪, 鄢建国, 李斐, 杨轩. 利用重力场模型MRO120D分析火星探测器的轨道演化[J]. 武汉大学学报 ( 信息科学版), 2021, 46(6): 880-886. DOI: 10.13203/j.whugis20180506
引用本文: 陈祎豪, 鄢建国, 李斐, 杨轩. 利用重力场模型MRO120D分析火星探测器的轨道演化[J]. 武汉大学学报 ( 信息科学版), 2021, 46(6): 880-886. DOI: 10.13203/j.whugis20180506
CHEN Yihao, YAN Jianguo, LI Fei, YANG Xuan. Orbital Evolution of Mars Probes Using Gravity Field Model MRO120D[J]. Geomatics and Information Science of Wuhan University, 2021, 46(6): 880-886. DOI: 10.13203/j.whugis20180506
Citation: CHEN Yihao, YAN Jianguo, LI Fei, YANG Xuan. Orbital Evolution of Mars Probes Using Gravity Field Model MRO120D[J]. Geomatics and Information Science of Wuhan University, 2021, 46(6): 880-886. DOI: 10.13203/j.whugis20180506

利用重力场模型MRO120D分析火星探测器的轨道演化

Orbital Evolution of Mars Probes Using Gravity Field Model MRO120D

  • 摘要: 针对火星探测器在轨运行时长的问题,使用武汉大学自主研制的火星探测器精密定轨与重力场解算软件系统MAGREAS(Mars gravity recovery and analysis software/system),分别对火星探测器在不同初始轨道高度、不同初始轨道倾角、不同初始轨道偏心率以及不同阶次火星重力场等影响因素下,进行轨道演化的分析。结果表明,小偏心率且轨道高度在250 km及以上的探测器可以长时间运行,在不进行任何调整的情况下运行时间接近两年;初始轨道倾角为90°时,不利于探测器的运行时长;在轨道积分的运算中,火星重力场模型MRO120D可以截取到100阶而不影响计算精度。该成果可以为中国的火星探测工程提供一定参考。

     

    Abstract:
      Objectives   The Chinese Mars probe has been successfully launched and is currently orbiting Mars. This article analyzes several different satellite orbit characteristics in detail to find out the suitable orbits with stable operation characteristics.
      Methods   This paper uses the MAGREAS(Mars gravity recovery and analysis software/system)independently developed by Wuhan University to analyze the evolution of satellite orbits under different initial orbit heights, different initial orbital inclinations, different initial orbital eccentricities, and different orders of Martian gravitational field models. Then we make orbit predictions for the four situations.
      Results   The results show that satellite can run for nearly two years without any orbital adjustment. When the initial orbital inclination is 90°, it does not contribute to the running time of the satellite. In the calculation of orbital integration, the Martian gravity field model can be intercepted to 100 degrees without affecting the calculation accuracy.
      Conclusions   This paper has done a lot of orbit predictions based on different initial orbit elements, and analyzed the evolution characteristics of different satellite orbits. This research can provide a certain reference for China's Mars exploration project.

     

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