Date of Award

Fall 2011

Document Type

Thesis

Degree Name

Master of Science (MS)

Department

Mechanical & Aerospace Engineering

Program/Concentration

Aerospace Engineering

Committee Director

Robert L. Ash

Committee Member

Thomas E. Alberts

Committee Member

Brett A. Newman

Call Number for Print

Special Collections; LD4331.E535 A475 2011

Abstract

This thesis proposes a fixed Mars base architecture consisting of the following interconnected elements: landing area, power generation, in-situ resource utilization (ISRU), robotic repair and assembly, and a scientific research laboratoiy. The base architecture that has been put forward can be expanded readily to include future elements such as a sustainable human habitat. The base architecture approach was developed assuming that serial Earth-launched lander missions were too expensive and too slow going forward in effecting the systematic exploration of a planet whose surface area constitutes nearly the same area as the land mass of Earth. The fixed base architecture facilitates the demonstration and use of the following technologies; large-scale fixed solar power arrays, in-situ propellant production (ISPP), in-situ methane-oxygen propelled vehicles, and in-situ hydrogen fueled balloon systems (heavy litter balloons and small weather balloons) for greatly expanded access to the varied and widely-dispersed areas of greatest scientific interest on Mars. The fixed base also facilitates the development of ISRU produced materials, and self-replicating robotic devices. Many of the base elements can utilize natural Martian resources for the majority of their operations. For example, the ISPP system will produce the hydrogen, methane, and oxygen using a Sabatier reactor, water electrolysis, processed water extracted from the Martian surface ice, and carbon dioxide extracted from the Martian atmosphere. Indigenous hydrogen will fuel the balloon systems and resupply fuel cell energy storage systems, and locally derived methane and oxygen will fuel rovers/hoppers and the Mars Ascent Vehicle (MAV) for return trips to Earth, eliminating a significant propellant mass requirement at Earth. This approach can virtually eliminate the risk of contaminating Mars with terrestrial organisms, since the Earth-transported hardware systems can meet stringent sterilization criteria, and nearly all of the consumables needed at Mars can be produced from Mars materials. Combining these advanced technologies will enable the exploration of Mars to be potentially more cost, mass, and risk efficient.

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DOI

10.25777/cem5-0z95

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