气动磁镜聚变推进器的火星探测任务分析

宋俊; 张晨; 杨文杰; 曾秋孙; 陈志斌

doi:10.13224/j.cnki.jasp.20200510

气动磁镜聚变推进器的火星探测任务分析

doi: 10.13224/j.cnki.jasp.20200510

宋俊^1,2,,
张晨³,
杨文杰^1,2,
曾秋孙¹,
陈志斌^1, ,

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
3.
中国科学院空间应用工程与技术中心，北京 100094

基金项目: 安徽省自然科学基金（1908085MA17）；安徽省重点研究与开发计划国际科技合作专项（202004b11020032）；国家重点研发计划（2018YFB1900605）

详细信息

作者简介:
宋俊（1993-），男，博士生，主要从事聚变新概念相关技术研究。E-mail：jun.song@inest.cas.cn

通讯作者:
陈志斌（1982-），男，副研究员，博士，主要从事聚变热工流体与工程技术研究。E-mail：zhibin.chen@inest.cas.cn

中图分类号: V439
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- 文章访问数: 402
- HTML浏览量: 99
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- 被引次数: 0
出版历程
- 收稿日期: 2020-11-26
- 刊出日期: 2021-09-28

Analysis of Mars exploration mission based on gas-dynamic-mirror fusion thruster

SONG Jun^{1,2
,},
ZHANG Chen³,
YANG Wenjie^1,2,
ZENG Qiusun¹,
CHEN Zhibin^{1
, ,}

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
3.
Technology and Engineering Center for Space Utilization，Chinese Academy of Sciences，Beijing 100094，China

摘要

摘要: 将气动磁镜聚变概念拓展到空间推进器应用，分析了不同等离子体密度和氢推进剂质量流率下聚变推进器的比冲和推力变化范围，理论计算表明其比冲可达10 000 s以上，推力最高可达几十牛。在此基础上，进一步采用气动磁镜聚变推进器对地火转移任务进行了数值仿真。假设推进器初始质量为100 t，仿真结果表明:当飞行时间在282.42~639.76 d变化时，剩余质量从88.59 t提升至98.24 t。相关分析表明基于气动磁镜的聚变空间推进器通过调节比冲和推力组合方式，可以很好地满足未来火星载人和货运任务对飞行时间和有效载荷份额的不同需求，是未来高性能空间推进器发展的一种候选方案。
- 气动磁镜 /
- 空间应用 /
- 聚变推进器 /
- 火星探测 /
- 轨道优化
Abstract: The gas-dynamic-mirror based fusion concept was expanded into space propulsion applications to analyze the range of specific impulse and thrust under different plasma density and hydrogen propellant mass flow rates.The theoretical calculation showed that the highest specific impulse can be above 10 000 s，and thrust up to dozens of Newton.On this basis，the fusion thruster based on the gas dynamic mirror was further used to simulate the Mars exploration mission.Assuming the initial mass of the thruster was 100 t，the simulation results showed that the residual mass increased from 88.59 to 98.24 t when the mission flight time varied from 282.42 to 639.76 d.The analysis showed that the fusion space thruster based on the gas dynamic mirror can well meet the requirements of future manned and cargo Mars missions by adjusting the specific impulse and thrust，making it an option for the development of high-performance space thrusters in the future.
- gas dynamic mirror /
- space applications /
- fusion thruster /
- Mars exploration /
- orbital optimization

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参考文献(34)

[1]	刘川,刘俊,邱鑫,等.火星探测器推进系统初步设想[J].火箭推进,2014,40（2）:44-48.
[2]	何伟锋,向红军,蔡国飙.核火箭原理、发展及应用[J].火箭推进,2005,31（2）:37-43.
[3]	廖宏图.核推进的空间应用浅析[J].火箭推进,2016,42（3）:6-14.
[4]	吉宇,孙俊,石磊.核热推进系统热工过程及堆芯关键技术分析[J].原子能科学技术,2017,51（12）:2171-2176.
[5]	王浩泽,左安军,霍红磊,等.110kN核热火箭发动机系统方案选取与参数优化研究[J].原子能科学技术,2019,53（1）:30-37.
[6]	解家春,霍红磊,苏著亭,等.核热推进技术发展综述[J].深空探测学报,2017,4（5）:417-429.
[7]	张梦龙,张悦,王宝和.空间核推进系统综述与展望[J].兵器装备工程学报,2018,39（9）:96-100.
[8]	刘佳,康小录,张岩,等.基于核电的大功率霍尔电推进系统设计及分析[J].原子能科学技术,2019,53（1）:9-15.
[9]	高剑,郭键,赵守智.用于核电推进的30kWe反应堆电源堆芯设计[J].核科学与工程,2018,38（3）:347-352.
[10]	SEMENKINA V.Overview of electric propulsion activity in Russia[C]∥Proceedings of the 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Fort Lauderdale,US:AIAA,2004:3330-3338.
[11]	朱安文,刘磊,马世俊,等.空间核动力在深空探测中的应用及发展综述[J].深空探测学报,2017,4（5）:397-404.
[12]	CLARK J.Analysis of crewed missions enabled by a Bi modal nuclear thermal electric propulsion system[D].Columbus:The Ohio State University,2019.
[13]	WILLIAMS C.Application of recommended design practices for conceptual nuclear fusion space propulsion systems[C]∥Proceedings of the 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Fort Lauderdale,US:AIAA,2004:3534-3556.
[14]	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.
[15]	ADAMS R,CASSIBRY J.The need for fusion propul sion research[C]∥Proceedings of the 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Tucson,US:AIAA,2005:4140-4150.
[16]	SANTARIUS J F.Fusion space propulsion:a shorter time frame than you think[C]∥Proceedings of the 53rd Joint Army-Navy-NASA-Air Force （JANNAF） Propulsion Meeting.Monterey,US:Fusion Technology Institute,2005:5-8.
[17]	THIO F,TURCHI P,SANTARIUS J.A summary of the NASA Fusion Propulsion Workshop 2000[C]∥Proceedings of the 37th Joint Propulsion Conference and Exhibit.Salt Lake City,US:AIAA,2000:2001:3669.
[18]	邓柏权.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.
[19]	陈志,冯开明,邓柏权,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.
[20]	KAMMASH T,LEE M.Gas dynamic fusion propulsion system for space exploration[J].Journal of Propulsion and Power,1995,11（3）:544-553.
[21]	KAMMASH T,GALBRAITH D L.Improved physics model for the gas dynamic mirror fusion propulsion system[J].Journal of propulsion and power,1998,14（1）:24-28.
[22]	EMRICH W J,Jr,KAMMASH T.Performance optimization of the gas dynamic mirror propulsion system[C]∥Proceedings of the AIP （American Institute of Physics） Conference.Sturovo,US:American Institute of Physics,2000:1420-1424.
[23]	EMRICH W J,Jr.First results of the gas dynamic mirror fusion propulsion experiment[C]∥Proceedings of the AIP Conference.Albuquerque,US:American Institute of Physics,2003:483-489.
[24]	OHLANDT C J R.A computational magnetohydrodynamic model of a gasdynamic fusion space propulsion system[D].Ann Arbor，US:University of Michigan,2011.
[25]	STOCKETT P.Feasibility and design requirements of fission powered magnetic fusion propulsion systems for a manned mars mission[D].West Lafayette,US:Purdue University,2019.
[26]	杜红飞,陈德鸿,蒋洁琼,等.基于GDT的14MeV中子源初步设计研究[J].核科学与工程,2012,32（1）:68-73.
[27]	曾秋孙.高能量增益GDT 聚变中子源物理设计研究[D].合肥:中国科学技术大学,2018.
[28]	LONG K F.Deep space propulsion:a roadmap to inter stellar flight[M].New York:Springer-Verlag New York,2012.
[29]	GERWIN R.Characterization of plasma flow through magnetic nozzles [R].AFSC （Air Force Space Command）Astronautics Laboratory Report AL-TR-89-092,1990.
[30]	HIVELY L M.Convenient computational forms for Maxwellian reactivities[J].Nuclear Fusion,1977,17（4）:873-876.
[31]	IVANOV A A,PRIKHODKO V V.Gas dynamic trap:experimental results and future prospects [J].Physics-Uspekhi,2017,60（5）:509-533.
[32]	李鉴.连续推力轨道机动优化方法研究[D].北京:北京航空航天大学,2013.
[33]	GAO Y,KLUEVER C.Low-thrust interplanetary orbit transfers using hybrid trajectory optimization method with multiple shooting[C]∥Proceedings of the AIAA/AAS Astrodynamics Specialist Conference and Exhibit.Rhode Island,US:AIAA,2004:5088-5109.
[34]	OZIMEK M,HOWELL K.Low-thrust transfers in the earth-moon system including applications to libration point orbits[J].Journal of Guidance,Control,and Dynamics,2010,33（2）:533-549.