EQUULEUS Trajectory Design
EQUULEUS Trajectory Design
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DOI：
10.1007/s40295-019-00206-y
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发表时间：
2020-01-24
影响因子：
1.8
通讯作者：
Funase, Ryu
中科院分区：
文献类型：
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作者：
Oguri, Kenshiro;Oshima, Kenta;Funase, Ryu
介绍了EQUULEUS（EQUIIBRIUm Lunar-Earth point 6 U）航天器的轨道设计，旨在验证CubeSats在地月空间的轨道控制能力。该使命计划从地月L2（EML 2）天平动点轨道观测月球的远侧。“平衡”轨道设计需要对发射条件、误差和推力水平等使命设计参数的不确定性作出反应。主要的挑战是在EML 2上快速设计科学轨道，并在立方体卫星有限的推进能力范围内从部署后轨道向科学轨道进行低能量转移。为了克服这一挑战，我们开发了一种系统的轨道设计方法，1）在全星历模型中设计了超过13，000个EML 2准晕轨道，并进行了统计保持成本评估，以及2）使用月球飞掠和太阳摄动识别低能量转移到科学轨道的家庭。该方法已成功地应用于EQUULEUS的轨道设计。
This paper presents the trajectory design for EQUilibriUm Lunar-Earth point 6U Spacecraft (EQUULEUS), which aims to demonstrate orbit control capability of CubeSats in the cislunar space. The mission plans to observe the far side of the Moon from an Earth-Moon L2 (EML2) libration point orbit. The EQUULEUS trajectory design needs to react to uncertainties of mission design parameters such as the launch conditions, errors, and thrust levels. The main challenge is to quickly design science orbits at EML2 and low-energy transfers from the post-deployment trajectory to the science orbits within the CubeSat's limited propulsion capabilities. To overcome this challenge, we develop a systematic trajectory design approach that 1) designs over 13,000 EML2 quasi-halo orbits in a full-ephemeris model with a statistical stationkeeping cost evaluation, and 2) identifies families of low-energy transfers to the science orbits using lunar flybys and solar perturbations. The approach is successfully applied for the trajectory design of EQUULEUS.