高精度模型下Halo轨道设计研究

Study on Halo Orbit Design Under High Precision Model

针对未来地月L2点Halo轨道空间站长期停泊任务,研究了高精度模型下Halo轨道设计方法。首先,详细推导了圆型限制性三体问题(Circular Restricted Three Body Problem,CR3BP)质心会合坐标系与高精度模型地心J2000坐标系之间的转换关系,并在此基础上,将CR3BP下的闭合Halo轨道转换到地心J2000坐标系得到了高精度模型下Halo轨道迭代初值。其次,采用序列二次规划(Sequence Quadratic Program,SQP)构造多层迭代格式,在高精度模型下对初值进行逐层修正。最后,通过仿真测试,验证了该方法的可行性与有效性。该研究结果可为未来平动点任务标称轨道设计方案的制定提供参考。

For the long-term operational mission of the Halo orbit space station at the Earth-Moon L2 point in the future,the Halo orbit design method under the high precision model is studied. Firstly,the transformation relationship between the circular restricted three body problem (CR3BP) barycentric centroid coordinate system and the high-precision model geocentric J2000 coordinate system is deduced in details,and the closed Halo orbit under CR3BP is converted to the geocentric J2000 coordinate system,the iteration initial value of the Halo orbit for the high-precision model is obtained. Secondly,the sequential quadratic program (SQP) is used to construct a multi-layer iterative scheme and the initial value is corrected layer by layer in a high?precision model. Finally,through the simulation test,the feasibility and effectiveness of the method described in the article are verified. The research results can provide reference for the design of the nominal orbit design scheme for the future libration points.