Transportation Infrastructure Options for Moon Exploration

Paper number

IAC-06-D2.7.-A3.7.08

Author

Mr. Philippe Augros, EADS Astrium, France

Year

2006

Abstract

Exploration of the Moon, Mars and beyond is on the agenda of Europe as well as of the United States. This paper addresses the several transportation options that can be envisaged in Europe for relatively near term or for longer term and ambitious lunar exploration scenarios.
The first option corresponds to the capability of using the flight proven Ariane 5 ECA and its potential improved version featuring the reignitable Vinci engine. The capability of transfer into L1 Libration point, Low Lunar Orbit (LLO) and to the lunar surface is presented. Ariane 5 provides a payload capability of roughly 2 metric tons to these three targets (payload meaning the mass remaining after removing the mass of the propulsion stage).
Another potential option using a dual launch approach with two existing launchers, such as an Ariane 5 and another launcher with similar performance, and assembly in LEO of a lunar stack has been analyzed but is shown to be not so attractive, increasing only the capability up to 3 metric tons payload. The point is that the heaviest part of the lunar stack is the Earth Departure Stage. It must be launched by the most powerful launcher in case of a cooperation scenario and its corresponding mass limits the mass of the lunar payload. This option could present the interest to develop a lifeboat capability for rescuing astronauts trapped around the Moon or an emergency supply of consumables and other goods to the Moon surface. Anyway, this level of performance is largely insufficient to bring significant elements, such as base modules, to a Moon base. Assembly scenarios involving more than two launches appear unpractical and have not been investigated.
A more ambitious step, corresponding to an active participation into an International human exploration endeavor, is presented with two options: cargo mission and human transportation mission. Assuming a minimum payload mass to be delivered to the lunar surface of 5 metric tons for such participation, the building blocks of the cargo mission are derived including the launcher with a TLI capability of 30 tons (Energia like). Using these elements (capsule derived from the lifeboat, descent stage used for cargo), adapting the remaining insertion stages and developing a 5 tons ascent stage enable also to perform independent human missions with a slightly increased launcher capability of 45 tons in TLI (due to the added manned vehicle with its Earth return stage) corresponding to a launch capability in the 100 metric tons range into LEO.

Abstract document

IAC-06-D2.7.-A3.7.08.pdf

Manuscript document

IAC-06-D2.7.-A3.7.08.pdf (🔒 authorized access only).

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