| Citation: | SONG Jun.Preliminary analysis on the demand of nuclear fusion space thruster［J］.Journal of Aerospace Power，2022，37（7）：1495‑1502. doi: 10.13224/j.cnki.jasp.20210122
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An analytic approximate calculation model was referenced to conduct a sensitivity analysis of key parameters such as propulsion system mass，specific impulse，mission time，and payload ratio，assuming that the case study was based on the two⁃bum rendezvous and four⁃bum round trip of Earth to Mars missions.The dependence of mission time and payload ratio on fusion power，propulsion system structure mass，and specific impulse was obtained through a detailed analysis.Besides，theoretical calculation showed that the mission can arrive at the destination planet within 1 to 2 months and carry more than 10% payload ratio by combining the related progress of ground commercial fusion reactor and reasonable extrapolation of existing technology； based on that，the preliminary parameters of the future nuclear fusion space propulsion and design scheme was proposed，which can generally provide a certain reference for the development of future nuclear fusion space propulsion technology.
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