Propulsion system design for Mars ascent vehicles by using the in-situ CO2

Abstract

CO2 is a major combustion product arises from the combination of carbon as the fuel and oxygen as the oxidizer. However, CO2 can burn with metallic powders that makes it interesting compound for the combustion applications. Although Metal CO2 combustion has been studied by many researchers, process has not been evaluated for practical rocket applications. Therefore, this research aims to present ignition characteristics of the CO2 in actual hybrid rockets. Propellant combination of Para f fin/ Metal CO2 is selected to accomplish the combustion. In addition, combustion feasibility of CO2 is evaluated for Mars Ascent Vehicles. Hybrid propulsion system by using Para f fin/ Metal CO2 propellant combination is totally feasible for Mars Ascent Vehicles. In-situ propellant combination provides significant cost savings as well as ease of manufacturing on Mars. In-situ propellant mass optimization provides that only 20% fuel (paraffin wax) and 40% oxidizer (nitrous oxide) are needed to be brought from the Earth. It means that Para f fin/ Metal CO2 / CO2 propellant combination uses 80% Mg and 60% CO2 for a practical MAV system. Furthermore, 240 kg Mars Sounding Rocket is designed by using Para f fin/ Metal CO2 / CO2 for ballistic hopper missions.