Design Options for NASA’s Lunar Surface Access Module
- Paper number
IAC-06-D2.7.-A3.7.06
- Author
Mr. Paul Wooster, Massachussets Institute of Technology (MIT), United States
- Coauthor
Mr. Wilfried Hofstetter, Massachussets Institute of Technology (MIT), United States
- Coauthor
Prof. Edward Crawley, Massachussets Institute of Technology (MIT), United States
- Year
2006
- Abstract
NASA’s Vision for Space Exploration calls for Human Lunar Exploration (HLE) as a stepping stone to the human exploration of Mars. In the context of the Exploration Systems Architecture Study carried out in 2005, NASA has developed a system architecture for HLE, with an emphasis towards short duration missions. Within the architecture, the Crew Exploration Vehicle (CEV) and the associated Crew Launch Vehicle (CLV) are currently under development. The Cargo Launch Vehicle (CaLV) design is relatively mature due to its extensive commonality with elements of the Space Shuttle launch system. The Lunar Surface Access Module (LSAM), which will provide transportation to and from the lunar surface, is defined on a high level, but will not be developed for several years. LSAM design and performance have a major impact on the life-cycle cost and capabilities of a lunar campaign, as elements of the LSAM are used for both crew and cargo transportation to and from the lunar surface. In this paper we describe the process and the results of a systematical analysis of LSAM design options within the assumptions and constraints of the ESAS architecture. The basis of the analysis is a comprehensive enumeration of the system-level LSAM design space, and subsequent detailed design of feasible options on the subsystem level. Special emphasis is placed on design choices that directly lead to reductions in HLE fixed and / or variable recurring cost and development cost, such as commonality with other system used in the lunar architecture (e.g. the CEV), legacy from past programs, reusability of LSAM elements, options that enable significant accretion of assets on the lunar surface, and designs that enable a 1-launch solution (CaLV only). In general, two major families of LSAM designs can be distinguished: the first one is driven by crew transportation to the surface and back, and offers only a very limited capability to sustain surface sorties. The second one is oriented towards supporting a sortie with significant surface operations. The LSAM design options are then evaluated in terms of life-cycle cost and performance for a range of HLE scenarios. Each scenario consists of a traffic model describing the number and mission types (such as sortie, base crew rotation, base logistics) carried out over a fixed time interval. Investigation of LSAM designs over a wide range of HLE scenarios allows for the identification of robust system designs and is the basis for HLE architectural decisions.
- Abstract document
- Manuscript document
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