Basic concepts of base configuration and module structure for a mars habitat

Paper number

IAC-06-A3.P.3.05

Author

Mr. Uwe Derz, RWTH Aachen, Germany

Coauthor

Mr. Fabian Preller, Germany

Coauthor

Mr. Stephan Zajac, Germany

Coauthor

Mr. Daniel Noelke, RWTH Aachen - Institut fuer Leichtbau, Germany

Coauthor

Mr. Sebastian Willems, RWTH Aachen, Germany

Year

2006

Abstract

Within the Pre-Phase A study already existing and actual planned habitats have been analysed, focused on structural elements. Based on the mission related objectives and the top-level requirements, a first scenario has been defined where several emergency habitat modules and additional modules without life support systems can be adapted together to a habitat complex. Different methods of arranging these modules to the complex and dividing up habitat’s  performance to the several modules has been investigated to get a habitat complex design, which is safe (especially in partially mission failure), light and easy expandable at low costs. For safety, it is very important to separate redundant systems physically to make it possible to abandon parts of the complex and to increase thereby the chance of survival. The expandability can be fulfilled in two different ways. Because of the fact that additional modules are provided with life support by the already landed modules and therefore do not need life support systems they can be built lighter or the saved mass can be used for additional payload.\\
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Furthermore inflatable module connection tunnels had been examined under the aspects of low weight, shelf life at low volume and easy inflation. A standard module design, which is used for emergency/life supporting modules as well as additional modules, has been defined. Life-critical systems like pressure shell and radiation protection systems have been dimensioned. For this, very different aspects as need of structural stability and capacitance, a most effectively protection of the crew and psychological needed features like windows had to be considered. Because of relative high module masses in comparison with unmanned missions, a new Mars entry, descent and landing system has also been designed. Therefore criteria as weight, acceleration and heat loads, partial system failure and the use of possible new technologies like inflatable aero shells, parachute clustering and cryogenic rocket engines for terminal decent have been investigated.

Abstract document

IAC-06-A3.P.3.05.pdf

Manuscript document

IAC-06-A3.P.3.05.pdf (🔒 authorized access only).

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