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。
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.
作者
宋俊
SONG Jun(Institute of Nuclear Energy Safety Technology,Hefei Institute of Physical Science,Chinese Academy of Sciences,Hefei 230031,China;Science Island Branch,Graduate School,University of Science and Technology of China,Hefei 230026,China)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2022年第7期1495-1502,共8页
Journal of Aerospace Power
关键词
核聚变
空间推进器
设计构想
火星探测
深空探测
nuclear fusion
space thruster
design concept
Mars exploration
deep-space exploration
