Thermodynamic Mathematical Models of an in-Situ Rocket Propellent System for Mars

Overview

Our study investigates an in-situ resource utilization model for rocket propellant production on Martian. Using carbon dioxide and water resources available on Mars, the ISRU is able to produce liquid methane and oxygen, to form oxygen-methane, an efficient rocket fuel for return trips back to Earth. We found that the compressor work to liquefy oxygen was energy efficient and not feasible on Mars. Martian diurnal temperatures have massive fluctuations that can have thermodynamic impacts on the liquefaction process. We first tested, using oxygen tanks, the impact on temperature on the creation of supercritical fluids. We found that supercritical fluids have greater liquid to gas ratios at lower temperatures and higher pressures than that of the critical pressure. This indicated that Martian temperatures could have an impact on the process of liquefaction. An open source MATLAB code simulates the ISRU process for rocket propellant production. We validated each set of the code to ensure chemically our simulation would be viable. We then simulated the oxygen liquefaction process and found the compressor work (W10) at different temperatures and pressures along an assigned interval, accounting for Boyle's law. We modeled our data using a surface plot, conducted asymptote testing, and conducted polynomial regressions. Our optimized model of the relationship between temperature and pressure demonstrated a 89.42% reduction in compressor work that can be allocated to essential systems on Mars. This study has successfully demonstrated a method of oxygen liquefaction via a compressor on Mars that is both feasible and energy efficient. We have achieved a LEVEL 3 on the NASA Technology Readiness Level scale. We are applying these optimization models further to develop a pressurization system software that can optimize compressor work on Mars.

Competition history

• AJAS 2024 Category not listed

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