核聚变空间推进器的初步需求分析

宋俊

doi:10.13224/j.cnki.jasp.20210122

核聚变空间推进器的初步需求分析

doi: 10.13224/j.cnki.jasp.20210122

宋俊^{1, 2}

1.
中国科学院合肥物质科学研究院核能安全技术研究所，合肥 230031
2.
中国科学技术大学研究生院科学岛分院，合肥 230026

详细信息

作者简介:
宋俊（1993-），男，博士生，主要从事聚变新概念和空间推进器研究。

中图分类号: V439
计量
- 文章访问数: 63
- HTML浏览量: 5
- PDF量: 25
- 被引次数: 0
出版历程
- 收稿日期: 2021-03-18

Preliminary analysis on the demand of nuclear fusion space thruster

SONG Jun^{1, 2}

1.
Institute of Nuclear Energy Safety Technology，Hefei Institute of Physical Science，Chinese Academy of Sciences，Hefei 230031，China
2.
Science Island Branch，Graduate School，University of Science and Technology of China，Hefei 230026，China

摘要

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。
- 核聚变 /
- 空间推进器 /
- 设计构想 /
- 火星探测 /
- 深空探测
Abstract:
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.
- nuclear fusion /
- space thruster /
- design concept /
- Mars exploration /
- deep⁃space exploration
注释:

1) 张雪

HTML

图 1 标准速度增量、有效载荷份额与标准喷气速度关系

Figure 1. Relationship between standard speed increment,payload ratio and standard exhaust velocity

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图 2 火星对接任务性能参数依赖关系

Figure 2. Dependence on performance parameters of Mars rendezvous missions

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图 3 火星往返任务性能参数依赖关系

Figure 3. Dependence on performance parameters of Mars round trip missions

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图 4 不同燃料比率的中子功率份额

Figure 4. Neutron ratio of different fuel ratio

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表 1 不同核聚变等离子体推进器概念的性能参数

Table 1. Performance parameters of different nuclear fusion plasma thruster concepts

核聚变约束概念	比功率/（kW/kg）	比冲/s	推进系统质量/t
惯性静电约束（IEC）	0.02	3 000	300
气动磁镜（GDM）	133	142 000	1 500
球马克	5.75	20 000	1 033
碰撞束FRC概念	1.5	1.4 $\times$ 10⁶	33
FRC概念	1	10³~10⁶	1 100
悬浮偶极子	1	10⁴	1 300
球形托卡马克	8.7	35 435	1 690
惯性约束聚变	71	270 000	757
磁化靶聚变	16.8	70 485	121
脉冲Z箍缩	16.2	19 436	598

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表 2 几种参数适中的核聚变空间推进器性能参数组合方案

Table 2. Several moderate combinations scheme of performance parameters for nuclear fusion space thruster

参数		火星对接	火星对接	火星对接	火星往返
假设参数	距离S/m	7.48 $\times$ 10¹⁰	7.48 $\times$ 10¹⁰	7.48 $\times$ 10¹⁰	7.48 $\times$ 10¹⁰
假设参数	聚变输出功率/10⁹ W	1	2	3	2
输入参数	结构质量/t	200	200	200	200
	比冲/s	10 000	20 000	20 000	20 000
	比功率/（kW/kg）	5	10	15	10
	磁喷嘴效率η	0.8	0.8	0.8	0.8
输出参数	标准速度比c/V_c	0.632	0.818	0.769	0.632
	推进剂质量分数	0.645	0.347	0.433	0.645
	结构质量分数	0.257	0.232	0.312	0.098
	推进剂质量/t	501	299	338	501
	初始发射质量/t	778	861	782	778
	推进剂流量/(kg/s)	0.166	0.083	0.125	0.083
	有效载荷质量/t	76	262	244	76
	有效载荷份额	0.098	0.421	0.312	0.098
	任务时间/d	34.9	41.6	31.4	69.8

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参考文献(32)

[1]	杭观荣,洪鑫,康小录,等.国外空间推进技术现状和发展趋势[J].火箭推进,2013,39（5）:7⁃15. HANG Guanrong,HONG Xin,KANG Xiaolu,et al.Current status and development trend of space propulsion technologies abroad[J].Journal of Rocket Propulsion,2013,39（5）:7⁃15.（in Chinese）
[2]	周成,张笃周,李永,等.空间核电推进技术发展研究[J].空间控制技术与应用,2013,39（5）:1⁃6. ZHOU Cheng,ZHANG Duzhou,LI Yong,et al.On the development of nuclear electric propulsion technology[J].Aerospace Control and Application,2013,39（5）:1⁃6.（in Chinese）
[3]	于登云,孙泽州,孟林智,等.火星探测发展历程与未来展望[J].深空探测学报,2016,3（2）:108⁃113. YU Dengyun,SUN Zezhou,MENG Linzhi,et al.The development process and prospects for mars exploration[J].Journal of Deep Space Exploration,2016,3（2）:108⁃113.（in Chinese）
[4]	洪刚,戚峰,王建明,等.载人登陆火星任务核热推进系统方案研究[J].载人航天,2018,24（1）:102⁃106. HONG Gang,QI Feng,WANG Jianming,et al.Nuclear thermal propulsion system design for manned mars mission[J].Manned Spaceflight,2018,24（1）:102⁃106.（in Chinese）
[5]	钱学森.星际航行概论（精）[M].北京：宇航出版社,2008.
[6]	PAGAN A S,GIl E F,GABRIELLI R A,et al.Study of magnetic confinement configurations for fusion space propulsion[C]∥Proceedings of the 4th CEAS Air & Space Conference.Linköping,Sweden:Linköping University Electronic Press,2013.
[7]	MOECKEL W E.Comparison of advanced propulsion concepts for deep space exploration[J].Journal of Spacecraft and Rockets,1972,9（12）:863⁃868.
[8]	LONG K F.Deep space propulsion:a roadmap to interstellar flight[M].New York,US:Springer Science & Business Media,2011.
[9]	LABAUNE C,BACCOU C,YAHIA V,et al.Laser⁃initiated primary and secondary nuclear reactions in Boron⁃Nitride[J].Scientific Reports,2016,6（1）:1⁃8.
[10]	KAMMASH T,GALBRAITH D L.Antimatter⁃driven fusion propulsion scheme for solar system exploration[J].Journal of Propulsion Power,1992,8（3）:644⁃649.
[11]	邓柏权,EMMERT G A.D⁃3He聚变动力可行性研究[J].核聚变与等离子体物理,1989,9（4）:213⁃220. DENG Baiquan,EMMERT G A.Feasibility study of D⁃3He fusion power[J].Nuclear Fusion and Plasma Physics,1989,9（4）:213⁃220.（in Chinese）
[12]	KAMMASH T,GODFREY T.An open cycle gas core fusion rocket for space exploration[J].Acta Astronautica,1997,41（4）:229⁃237.
[13]	CASSIBRY J,CORTEZ R,STANIC M,et al.Case and development path for fusion propulsion[J].Journal of Spacecraft and Rockets,2015,52（2）:595⁃612.
[14]	SCHULZE N R.Fusion energy for space missions in the 21st century[R].Washington,US:NASA,1991.
[15]	石秉仁.等离子体理论⁃用球形托卡马克建立D⁃3He聚变反应堆的可能性[J].核工业西南物理研究院年报,2004（1）:86⁃88.
[16]	RAZIN Y S,PAJER G,BRETON M,et al.A direct fusion drive for rocket propulsion[J].Acta Astronautica,2014,105（1）:145⁃155.
[17]	ZENG Q S,CHEN D H,WANG M H.High⁃field neutral beam injection for improving the Q of a gas dynamic trap⁃based fusion neutron source[J].Nuclear Fusion,2017,57（12）:126050.1⁃126050.8.
[18]	贺贤土.惯性约束聚变研究进展和展望[J].核科学与工程,2000,20（3）:248⁃251.
[19]	SYKES A,COSTLEY A E,WINDSOR C G,et al.Compact fusion energy based on the spherical tokamak[J].Nuclear Fusion,2017,58（1）:016039.1⁃016039.9.
[20]	COSTLEY A E.On the fusion triple product and fusion power gain of tokamak pilot plants and reactors[J].Nuclear Fusion,2016,56（6）:1⁃7.
[21]	KAMMASH T,GALBRAITH D L.Improved physics model for the gasdynamic mirror fusion propulsion system[J].Journal of propulsion and power,1998,14（1）:24⁃28.
[22]	何也熙,王龙,曾立,等.SUNIST球形托卡马克的研究进展[J].核科学与工程,2003,24（4）:343⁃347. HE Yexi,WANG Long,ZENG Li,et al.Progress on SUNIST spherical tokamak[J].Chinese Journal of Nuclear Science and Engineering,2003,24（4）:343⁃347.（in Chinese）
[23]	RYZHKOV S V.A field⁃reversed magnetic configuration and applications of high⁃temperature FRC plasma[J].Plasma Physics Reports,2011,37（13）:1075⁃1081.
[24]	林木楠.场反位形等离子体装置的研制[D].合肥：中国科学技术大学,2018. LIN Munan.Development of field⁃reversed configuration device[D].Hefei:University of Science and Technology of China,2018.（in Chinese）
[25]	GERWIN R A,MARKLIN G J,SGRO A G,et al.Characterization of plasma flow through magnetic nozzles[R].Los Alamos:Los Alamos National Lab,NM⁃87545,1990.
[26]	WILLIAMS C H.An analytic approximation to very high specific impulse and specific power interplanetary[M].Cleveland,US:NASA Lewis Research Center,1995.
[27]	尹怀勤.长征九号:重型火箭在路上[J].百科知识,2016（6）:20⁃21. YIN Huaqin.Long March 9:heavy rocket on the way[J].Encyclopedic Knowledge,2016（6）:20⁃21.（in Chinese）
[28]	GILLAND J,MARRIOTT D,MIKELLIDES I,et al.Progress on the Godzilla gigawatt MPD plasma accelerator and nozzle for fusion propulsion simulations[C]∥Proceedings of the 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Huntsville,US:AIAA,2003.
[29]	WILLIAMS C H,DUDZINSKI LA,BOROWSKI K,et al.Realizing 2001:a space odyssey piloted spherical torus nuclear fusion propulsion[J].Journal of Spacecraft& Rocket,2005,39（6）:874⁃885.
[30]	候炳林,朱学武.超导在受控核聚变能磁体工程研究中的应用概述[J].科学技术与工程,2005,5（6）:357⁃363. HOU Bingling,ZHU Xuewu.Current status and future technical challenges for the research of superconducting controlled nuclear fusion magnet engineering[J].Science Technology and Engineering,2005,5（6）:357⁃363.（in Chinese）
[31]	陈志,冯开明,邓柏全,等.D⁃3He先进燃料聚变空间核动力推进器的可行性探索[J].科学技术与工程,2005,5（2）:124‑127. CHEN Zhi,FENG Kaiming,DENG Baiquan,et al.The preliminary study of space nuclear power propulsor of D⁃3He advanced fuel fusion[J].Science Technology and Engineering,2005,5（2）:124⁃127.（in Chinese）
[32]	WU Y C.Neutron irradiation and material damage[M].Singapore:Springer,2017.