Interstellar Mission Design of a Fusion-Powered Spacecraft to Proxima b

Abstract

Recent significant developments in power production using nuclear fusion allows for a realistic discussion of fusion propulsion systems for spacecraft. This study provides a framework for large-scale spacecraft missions to Proxima b. The instrumentation included in the payload was defined based on missions with similar science objectives and flight conditions. A case study was conducted for three propulsion systems: the Fusion Driven Rocket (FDR), an Inertial-Electrostatic Confinement (IEC) fusion system, and an Antimatter Initiated Microfusion (AIM) system. Each propulsion system, originally designed for shorter interstellar distances, was tailored specifically for a Proxima b mission and analyzes its performance for 4 fuels: D-D, D-He3, D-T, and p-B11. Additionally, the system performance was examined for a fast and slow flyby of Proxima b, and bounded orbit. The analysis indicated a slow flyby and bounded orbit are most ideal for data collection, and can only be supported by the FDR employing D-He3 with a mission time of 57 years. Future work includes the investigation into the requirements for communication of data back to Earth and the implementation of an autonomous decision-making architecture that guides the spacecraft at extreme distances.