航天推进技术研究院主办
[1]吉宇,毛晨瑞,孙俊,等.核热火箭发动机系统循环方案分析与设计[J].火箭推进,2022,48(01):14-21.
JI Yu,MAO Chenrui,SUN Jun,et al.Analysis and design of system cycle for nuclear thermal rocket engine[J].Journal of Rocket Propulsion,2022,48(01):14-21.
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JI Yu,MAO Chenrui,SUN Jun,et al.Analysis and design of system cycle for nuclear thermal rocket engine[J].Journal of Rocket Propulsion,2022,48(01):14-21.
核热火箭发动机系统循环方案分析与设计
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
48
期数:
2022年01期
页码:
14-21
栏目:
研究与设计
出版日期:
2022-02-28
- Title:
- Analysis and design of system cycle for nuclear thermal rocket engine
- 文章编号:
- 1672-9374(2022)01-0014-08
- 分类号:
- V439.5
- 文献标志码:
- A
- 摘要:
- 核热火箭发动机是未来实现载人火星探测的首选动力方案,其具备高比冲、大推力和长工作寿命等优点。我国在此方面研究较少,亟需开展核热推进技术理论及方法的研究。核热火箭发动机系统循环分析与设计是关键问题之一,对推进系统总体设计有重要意义。分析了3种可用于核热火箭发动机系统循环的方案特点,基于闭式膨胀循环设计了比冲为910 s 的氢气核热推进系统和比冲为390 s的氨气核热推进系统方案,对比发现氢气系统更适合于载人深空探测,而氨气系统在推进剂长期在轨储存和对涡轮泵及反应堆的设计要求等方面有一定的优势,可胜任轨道高度变化相对较小的长期多次空间探测任务,作为液氧甲烷发动机的补充和替代。此外,结合设计过程以及核火箭发动机与化学火箭发动机的差异,围绕系统循环分析与设计提出了几点研究内容,为我国核热推进系统的发展提供参考。
- Abstract:
- Nuclear Thermal Propulsion(NTP)is a leading candidate for manned Mars exploration,which offers the advantages of high specific impulse,high thrust and long sustained lifetime for propulsion technology. Due to the limited research in China,it is desiderated to promote the related studies on the theory and methods about NTP. System cycle analysis is one of the major problems,which significantly benefits the overall design of the propulsion system. In this work,the principles,pros and cons of three main cycles for NTP engine were analyzed. Based on the closed expansion cycle,a hydrogen NTP system with Isp being 910 s and another ammonia NTP system with Isp being 390 s were designed. Further,the merits and faults of these two systems were also analyzed,which indicated that the H2 NTP system is more suitable for manned deep space exploration. For the NH3 NTP systems,it has advantageous in long-term in-orbit storage of propellant,design difficulty of turbo-pump and nuclear reactor. And it could serve as the substitution of liquid methane oxide engine,being qualified for the long-term and multiple exploration missions with relatively small orbit altitude change. In addition,combining the design procedure and the difference between the cycles of NTP engine and that of chemical engine,several key fundamental issues related to cycle design were proposed,which could provide references for the R&D of NTP engine in our country.
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备注/Memo
收稿日期:2021-07-11; 修回日期:2021-08-13
基金项目:博士后面上基金(2020M680586); 清华大学“水木学者”计划项目(2020SM057)
作者简介:吉宇(1994—),男,博士,助理研究员,研究领域为核热推进技术。
更新日期/Last Update:
1900-01-01