Analysis of fusion propulsion system for Earth-to-Mars mission

Abstract

The high-performance space propulsion system is required for deep space exploration, such as Mars and Jupiter missions. The fusion propulsion system has an extraordinary performance of ultra-high specific impulse, high specific power, and moderate thrust, which can reflect its advantages in future deep space exploration missions. In this study, analysis has been conducted to investigate the technical requirements of the fusion propulsion system for the Earth-to-Mars mission. An analytical model based on Williams’s assumption was adopted and solved by using the MATLAB code. Critical parameters such as specific impulse, specific power, mission time, and payload ratio for Mars rendezvous missions were analyzed. The qualitative and quantitative analysis results show that in order to reach Mars within one month with a payload ratio higher than 10 %, the specific power ranging from 5 to 15 kW/kg and the specific impulse of 10000 s is required. These parameters will take entirely inherent advantage of the fusion propulsion system. Moreover, the fusion propulsion system can operate under the optimal condition, including a wide range of the specific power (1−100 kW/kg) and the specific impulse (10000–200000 s). Based on a comprehensive analysis of the space mission performance, it is possible to provide a significant reference for the development of the fusion space propulsion system.