火箭推进

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。

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.

引言
1 核热火箭发动机原理
2 系统循环方案分析
3 系统循环方案设计
4 结论与展望

图1 核火箭发动机结构及原理示意图<br/>Fig.1 Schematic view of nuclear thermal rocket engine

图1 核火箭发动机结构及原理示意图
Fig.1 Schematic view of nuclear thermal rocket engine

图2 抽气循环原理图及对应的T-S曲线<br/>Fig.2 Schematic view of bleed cycle and corresponding T-S diagram

图2 抽气循环原理图及对应的T-S曲线
Fig.2 Schematic view of bleed cycle and corresponding T-S diagram

图3 开式膨胀循环原理图及对应的T-S曲线<br/>Fig.3 Schematic view of open expansion cycle and corresponding T-S diagram

图3 开式膨胀循环原理图及对应的T-S曲线
Fig.3 Schematic view of open expansion cycle and corresponding T-S diagram

图4 闭式膨胀循环原理图及对应的T-S曲线<br/>Fig.4 Schematic view of closed expansion cycle and corresponding T-S diagram

图4 闭式膨胀循环原理图及对应的T-S曲线
Fig.4 Schematic view of closed expansion cycle and corresponding T-S diagram

表1 3种循环方案特点比较<br/>Tab.1 Comparison of characteristics for three system cycles

表1 3种循环方案特点比较
Tab.1 Comparison of characteristics for three system cycles

图5 PANES程序计算流程图<br/>Fig.5 Calculation flow chart of PANES program

图5 PANES程序计算流程图
Fig.5 Calculation flow chart of PANES program

图6 氢气核热推进系统方案计算结果<br/>Fig.6 Design of a dual turbo-pump NTP system of hydrogen being propellant

图6 氢气核热推进系统方案计算结果
Fig.6 Design of a dual turbo-pump NTP system of hydrogen being propellant

表2 氨气核热推进系统内的关键节点参数<br/>Tab.2 Major node parameters of ammonia NTP system

表2 氨气核热推进系统内的关键节点参数
Tab.2 Major node parameters of ammonia NTP system

表3 两类核热推进系统性能对比<br/>Tab.3 Comparison of the two designed NTP systems

表3 两类核热推进系统性能对比
Tab.3 Comparison of the two designed NTP systems

图7 氢气核热推进系统和氨气核热推进系统的喷管尺寸对比<br/>Fig.7 Comparison of the nozzle size in H2 NTP system and NH3 NTP system

图7 氢气核热推进系统和氨气核热推进系统的喷管尺寸对比
Fig.7 Comparison of the nozzle size in H2 NTP system and NH3 NTP system

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备注

引言

1 核热火箭发动机原理

2 系统循环方案分析

3 系统循环方案设计

4 结论与展望

期刊信息