摘要
核热推进是未来深空探测和星际航行的可靠技术方案。反应堆是核热火箭的能量来源,堆芯的功率分布/核燃料几何构型对氢工质的加热有直接影响,氢工质热工循环决定了核热火箭发动机的动力学品质。基于20世纪美国与前苏联/俄罗斯的典型反应堆方案的研究结果,综述了反应堆燃料元件模块化和低浓缩铀(LEU)化的发展趋势,概述了反应堆在新发展趋势下的技术路径:(1)调整反应堆内慢化剂元件的材料与体积分数;(2)优化反应堆内工质的传热流动特性。分析涉及到的燃料元件、简化模型,探究堆芯内燃料元件冷却剂通道结构的优化设计方案对反应堆出口参数的影响,为提高核热火箭发动机性能参数提供了新思路。
Nuclear thermal propulsion(NTP)is recognized as a reliable technical way of future deep space exploration and interplanetary navigation.The reactor is the energy source for nuclear thermal rockets.The core's power distribution/nuclear fuel geometry design has a direct impact on the propellant's temperature.The nuclear thermal rocket engine's(NTR)performance is determined by the propellant thermodynamic cycle.Based on research results from typical reactor programs in the United States and the former Soviet Union/Russia in the 20th century,the development trend of modularization of reactor fuel elements and low enriched uranium(LEU)was reviewed,and the technical path of reactor under the new development trend was summarized:(1)Adjusting the material and volume fraction of the moderator element in the reactor;(2)Optimizing the heat transfer and flow characteristics of the working fluid in the reactor.The fuel elements were examined,and the model was simplified to investigate the effect of optimum design alternatives for the coolant channel structure of the fuel elements within the core on reactor outlet characteristics.Innovative concepts for future design are presented to increase the performance parameters of NTR.
作者
邵明雪
李晓亮
李小多
蔡开元
吴逊亮
丰松江
SHAO Mingxue;LI Xiaoliang;LI Xiaoduo;CAI Kaiyuan;WU Xunliang;FENG Songjiang(Space Engineering University,Beijing 101416,China)
出处
《固体火箭技术》
CAS
CSCD
北大核心
2024年第5期593-603,共11页
Journal of Solid Rocket Technology
基金
国防科技卓越青年科学基金。
关键词
核热火箭发动机
氢工质热工循环
模块化
低浓缩铀
燃料元件
nuclear thermal rocket
hydrogen thermodynamic cycle
modularization
low-enriched uranium
fuel element
