Preliminary analysis on the demand of nuclear fusion space thruster

Jun SONG

doi:10.13224/j.cnki.jasp.20210122

Chinese

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Preliminary analysis on the demand of nuclear fusion space thruster

Rocket Engine | 更新时间：2025-04-07

- Preliminary analysis on the demand of nuclear fusion space thruster
- Journal of Aerospace Power Vol. 37, Issue 7, Pages: 1495-1502(2022)
- 作者机构：
  
  1.中国科学院合肥物质科学研究院核能安全技术研究所，合肥 230031
  2.中国科学技术大学研究生院科学岛分院，合肥 230026
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.20210122
  CLC：
- 稿件说明：
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Jun SONG. Preliminary analysis on the demand of nuclear fusion space thruster[J]. Journal of Aerospace Power, 2022, 37(7): 1495-1502.
DOI：

Jun SONG. 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.

摘要

参考一种简化的、解析近似的计算模型，以地球到火星的对接任务和往返任务为例，对核聚变等离子体推进器性能关键参数如推进系统质量、比冲、任务时间、有效载荷份额及比功率等进行分析，得出了任务时间和有效载荷质量份额与聚变堆芯输出功率、推进器结构质量和比冲的依赖关系。在此基础上，结合核聚变地面商业堆的相关进展，对现有的技术做合理适当外推，理论计算表明：飞行任务能够在1~2个月内达到目的星球同时可携带超过10%的有效载荷份额，并提出了未来核聚变空间推进器的初步参数方案和设计构想，总体上能够为未来核聚变空间推进技术的发展提供一定的参考。

Abstract

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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references

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