Optimal Design of Electrically Fed Hybrid Mars Ascent Vehicle

The optimal design of the propulsion system for a potential Mars Ascent Vehicle is analyzed, in context Sample Return Mission. has to perform an initial ascent phase from surface and then circularize into 170 km orbit. A two-stage launcher taken account: same hybrid rocket engine considered both stages order limit development costs. cluster two, three or four engines employed first stage, whereas single always used second stage. Concerning feeding system, alternatives are consideration, namely blow down, regulated electric turbo-pump feed system. latter employs motor drive oxidizer turbopump, power supplied by lithium batteries. All options resulted viable configurations (payloads range 70–100 kg), making alternative worth considering sample return mission. use determines highest vehicle performance with estimated 10–25% payload gain respect gas-pressure systems.