Optimization of the Mars Ascent Vehicle for Human Space Exploration

摘要

This paper presents an analysis of the ascent stage to be used in future humanmissions toMars, commonly knownnas theMars Ascent Vehicle. The focus of the analysis is to minimize the initial mass, which must be delivered to low-nEarth orbit to have a fully functioning Mars Ascent Vehicle. At the end of the surface mission, the Mars AscentnVehicle takes the astronauts from theMartian surface to the orbiting Earth Return Vehicle. Systems analysis toolsnare used to help identify themost influentialmass drivers. Themain focus of the analysis is on the optimization of thenpropulsion system, including the type of propellant, oxidizer-to-fuel ratio, type of feed system, nozzle area ratio, andninitial thrust-to-weight ratio of the system. A full factorial analysis shows that oxygen/hydrogen, pump-fed enginesnwith a two-stage cryocooler are the best option for a mission scenario for propellant brought from Earth. If in-situnresource utilization is used to produce the necessary propellant on theMartian surface, oxygen/methane pump-fednengines become the best option in terms of minimizing the initial mass in low Earth orbit.