Martian Resource Utilization I. Plant Design And Transportation Selection Criteria PETER KALOUPIS+, PETER E. NOLAN++, & ANDREW H. CUTLERw Summary Indigenous Space Materials Utilization (ISMU) provides an opportunity to make Mars exploration mission scenarios more affordable by reducing the initial mass necessary in Low Earth Orbit (LEO). Martian propellant production is discussed in terms of simple design and economic tradeoffs. Fuel and oxidizer combinations included are H2/O 2, CH4IO2, and CO IO ? Process flow diagrams with power and mass flow requirements are presented for a variety of processes, and some design requirements are derived. Maximum allowable plant masses for single use amortization are included. Introduction A significant drawback to any manned Mars mission or sample return scenario is the mass of propellant that is required in LEO to deliver the return propellant to the Martian surface. It was recognized early that one potential way of reducing launch mass was to utilize extraterrestrial resources to make propellant for the return portion of the mission. This reduces the mass required at the Martian surface, and hence reduces the initial launch mass in LEO. It is generally accepted that the predominant cost driver associated with this type of space activity is the mass launched to LEO. Indigenous Space Materials Utilization (ISMU) offers the potential for lower launch mass, and hence lower mission costs. Several studies have discussed the merits of Mars propellant production [1-5]. This paper discusses two potential Mars mission scenarios and the benefits due to ISMU; the Martian environment and its resource pool; and the possible propellant combinations and their relative performance for return from Mars. This provides a framework to compare and contrast various chemical processes in ways that have not been explored in the literature. Conceptual designs for several plants based on available technology were developed and appropriate flow diagrams are presented. Mars Mission Scenarios Potential near term mission scenarios include a sample return mission and a 1 Aerospace and Mechanical Engineering Department, Building 16, University of Arizona, Tucson, AZ, 85721, USA. 11 Materials Science and Engineering Department, 4715 East Fort Lowell, Tucson, AZ, 85712, USA. ttt NASA Space Engineering Research Center, 4717 East Fort Lowell, Tucson, AZ, 85712, ASA.
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