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聚变空间推进器磁喷嘴初步分析
宋俊1,2,蒋洁琼1
1.中国科学院合肥物质科学研究院 核能安全技术研究所,安徽 合肥 230031;2.中国科学技术大学 研究生院科学岛分院,安徽 合肥 230026
摘要:
为了提高深空探测任务的范围和能力,亟需发展高性能的聚变空间推进器,而其中最为关键的子系统是磁喷嘴。首先介绍了聚变空间推进器的主要工作原理,并分析了核聚变地面发电应用中的偏滤器和空间推进应用中磁喷嘴系统的差异与联系。在此基础上,通过参考一种简化的磁喷嘴性能计算模型,初步评估了推力为1~1000N,比冲为104~105s,聚变传输功率为100MW~10GW研究范围内,不同推进性能需求与磁喷嘴系统磁喉处磁场大小、库区等离子体密度及推进剂质量流量的依赖关系。相关定性及定量分析结果能够为未来核聚变空间推进器磁喷嘴系统的物理和工程设计提供一定的参考。
关键词:  深空探测  核聚变  空间推进器  磁喷嘴  偏滤器
DOI:10.13675/j.cnki.tjjs.210445
分类号:V439
基金项目:
Preliminary Analysis on Magnetic Nozzle of Fusion Space Thruster
SONG Jun1,2, JIANG Jie-qiong1
1.Institute of Nuclear Energy Technology,Hefei Institutes of Physical Science,Chinese Academy of Sciences Chinese, Hefei 230031,China;2.Science Island Branch of the Graduate School,University of Science and Technology of China,Hefei 230026,China
Abstract:
It is urgent to develop high performance fusion space thrusters to improve the range and capability of deep space exploration missions, among which the most critical subsystem is the magnetic nozzle. The main working principle of fusion space thruster is introduced, and the differences and relations between the divertor used in ground fusion power generation and the magnetic nozzle selected by fusion space propulsion are analyzed. On this basis, a simplified calculation model for the performance of magnetic nozzles is then used to preliminarily evaluate the dependence of different propulsion performance requirements on the magnetic field at the throat of the magnetic nozzle system, the plasma density in the reservoir area, and the mass flow rate of propellant, when the thrust range is 1~1000N, the specific impulse range is 104~105s, and the fusion transmission power range is 100MW~10GW. The results of qualitative and quantitative analysis can provide certain references for the physical and engineering design of the magnetic nozzle system of nuclear fusion space thrusters in the future.
Key words:  Deep space exploration  Nuclear fusion  Space thruster  Magnetic nozzle  Divertor