Thermodynamic Cycle Analysis of Mars CO2 Thermal Rocket

In-situ resource utilization (ISRU) is recognized as an enabling technology for exploration of Mars. The collection methods of CO₂ on Mars are analyzed, and an implementation scheme of propulsion utilizes Mars CO₂ in raw form, CO₂ thermal rocket, is proposed. It can be used for attitude control and main propulsion during landing or takeoff, and it may be the potential propulsion for Mars airship, a promising Mars aerial platform capable of flight within the Martian environment. This paper illustrates influencing factors and potential application approaches of the new propulsion, and the cycle characteristic of the new propulsion is analyzed, the results show that the thrust specific power consumption (TSPC) is about the order of magnitude of lN/kW, and variation of performance is mainly concerned with the high side pressure, electric heat temperature etc, and the new propulsion exist an optimum temperature.