Many space agencies are working on solutions for manned operations on the Moon, both on its surface and in cislunar space. In such a scenario, with stable human presence, a launch facility would be needed and launch vehicles could take advantage of the benefits of the lunar environment. In the present paper missions to Earth (to a geostationary orbit) and to Mars (to an areostationary orbit), from a lunar launch facility, has been studied. The trajectories are analysed by using an ephemeris model, taking into account four attractive bodies (Earth, Moon, Sun and Mars). In the first phase of the two missions, the launcher places the spacecraft on a circular lunar orbit by using liquid, solid or hybrid propulsion systems. The latter solution is analysed assuming in situ propellant production using aluminum and oxygen, elements in which the moon is very rich. In the second phase of both the missions, a minimum energy trajectory is studied, which, exploiting the Luni-Solar perturbations, allows the spacecraft to escape the gravitational field of the Moon. In the mission to Earth, this manoeuver puts the spacecraft on a very high and inclined elliptical orbit. The last phase involves a circularization manoeuvre towards the GEO and transfers are studied for two different initial inclinations, using an electric engine. In the mission to Mars, the escape impulse is used to leave both the Earth-Moon and Sun-Earth systems. The interplanetary phase is analysed for several transfer final times and considering an electric engine with variable specific impulse. Finally, the performance of a lunar launch facility is compared to that of a traditional Earth facility, showing great advantages are obtained in terms of payload ratio.

中文翻译：

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使用月球发射设施执行地球和火星任务

许多航天机构正在研究月球表面和地月空间载人操作的解决方案。在这种情况下，在人类稳定存在的情况下，将需要一个发射设施，运载火箭可以利用月球环境的优势。在本文中，研究了从月球发射设施到地球（地球静止轨道）和火星（地球静止轨道）的任务。通过使用星历模型分析轨迹，考虑到四个有吸引力的天体（地球、月球、太阳和火星）。在两次任务的第一阶段，发射器使用液体、固体或混合推进系统将航天器置于圆形月球轨道上。假设使用铝和氧就地生产推进剂，分析后一种解决方案，其中月亮的元素非常丰富。在这两个任务的第二阶段，研究了最小能量轨迹，该轨迹利用 Luni-Solar 扰动，允许航天器逃离月球的引力场。在前往地球的任务中，这种机动将航天器置于非常高且倾斜的椭圆轨道上。最后一个阶段涉及到 GEO 的环形机动，并使用电动发动机研究两种不同初始倾角的转移。在火星任务中，逃逸冲动用于离开地球-月球和太阳-地球系统。行星际相位分析了几个传输最终时间，并考虑了具有可变比冲的电动发动机。最后，将月球发射设施的性能与传统地球设施的性能进行比较，