摘要
基于双行轨道根数和简化普适摄动算法,提出平均轨道根数与密切轨道根数的互换算法。以在轨Tan-DEM-X编队的双星为例进行仿真。与传统的只考虑J2项摄动短周期影响的转换算法相比,本文提出的互换算法精度更高：由平均轨道根数转换的密切轨道根数与STK 8软件给出的结果一致;由密切轨道根数转换的平均轨道根数与北美防空司令部公布的双行轨道根数一致。仿真结果表明该互换方法具有科学性和工程应用价值。
Mean orbital elements play a key role in design and simulation of distributed spacecraft formation flight and satellite constellations. This paper proposes transformation algorithms between the mean and osculating orbital elements based on TLE （Two Line Elements） and SGP4 （Simplified General Perturbations 4）. Numerical simulation is done with the on-orbit TanDEM-X formation satellites as an example. The presented transformation algorithms have higher accuracy in comparison with conventional algorithms that only take into account the short term influences of J2 perturbations. The calculated osculating orbital elements are coherent with the results generated by STK 8. Moreover, the calculated mean orbital elements are coherent with TLE data issued by NORAD （North American Aerospace Defense Command）. Simulation results show that the proposed method is scientific and has practical application value.
出处
《飞行器测控学报》
2012年第2期77-81,共5页
Journal of Spacecraft TT&C Technology
基金
国家高技术研究发展计划(2010AA7026053)
关键词
平均轨道根数
密切轨道根数
双行轨道根数
简化普适摄动
转换算法
Mean Orbital Elements
Osculating Orbital Elements
Two Line Elements （TLE）
Simplified General Perturbations 4 （SGP4） lTransformation Algorithms
