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首页> 外文期刊>Acta astronautica >Advanced modeling of optimal low-thrust lunar pole-sitter trajectories
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Advanced modeling of optimal low-thrust lunar pole-sitter trajectories

机译：最佳低推力月球极地定线轨迹的高级建模

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One immediate and cost-effective solution for lunar south pole coverage is a low-thrust pole-sitter spacecraft. When the spacecraft's fuel is nearly expended, it can also be used as part of a larger constellation that might require more time to deploy. This study examines the feasibility of the lunar pole-sitter from a dynamical standpoint. The model includes the effects of Earth oblateness, solar wind, gravity perturbations, and shadowing on a 500 kg spacecraft equipped with an NSTAR thruster. Lunar librations are also incorporated into path constraints on elevation angle and altitude from a potential ground station at the Shackleton crater. The solutions utilize multiple phases, including transfer-out from the International Space Station and spiral-down into a stable lunar orbit once the pole-sitting period is completed. Computation of the trajectory is based on a 12th-order collocation scheme. A direct transcription routine maximizes the time in the coverage phase, increasing the time span from 387 to 451 days. During this period, the minimum elevation angle relative to the Shackleton crater site is 6°.
机译：一种低推力的极地飞船是解决月球南极覆盖问题的直接且具有成本效益的解决方案。当航天器的燃料几乎耗尽时，它也可以用作更大的星座的一部分，这可能需要更多的时间来部署。这项研究从动力学的角度研究了月球极地保卫者的可行性。该模型在配备NSTAR推进器的500千克航天器上包括地球扁度，太阳风，重力扰动和阴影的影响。月球解放也被纳入沙克尔顿陨石坑潜在地面站对仰角和高度的路径限制中。解决方案利用了多个阶段，包括从国际空间站移出并在极点停留期结束后向下旋入稳定的月球轨道。轨迹的计算基于12阶搭配方案。直接转录程序可将覆盖阶段的时间最大化，从而将时间间隔从387天增加到451天。在此期间，相对于沙克尔顿陨石坑的最小仰角为6°。

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