Mass estimation model for Brayton cycle space nuclear power systems

被引：0
|
作者：
You E. [1 ]
She D. [1 ]
Shi L. [1 ]
机构：
[1] Key Laboratory of Advanced Reactor Engineering and Safety of Ministry of Education, Collaborative Innovation Center of Advanced Nuclear Energy Technology, Institute of Nuclear and New Energy Technology, Tsinghua University, Beijing
来源：
Shi, Lei (shlinet@tsinghua.edu.cn) | 2018年 / Tsinghua University卷 / 58期
关键词：
Brayton rotating unit; Mass estimation; Nuclear power system; Space application; Specific mass;
D O I：
10.16511/j.cnki.qhdxxb.2018.25.007
中图分类号：
学科分类号：
摘要：
Due to their high power and long lifetimes, nuclear power systems are being considered for long space missions in the future. Unlike current terrestrial nuclear facilities, the system mass and size are very important for space applications and define the system performance. A mass estimation model for closed Brayton cycles is studied in this paper. The MATLAB code SPRBC was used to calculate the total mass and the specific mass of a Brayton cycle space power system, including the heaviest components of the nuclear reactor, the shielding, the Brayton rotating unit, the regenerator and the heat radiator. The specific mass is nearly 30 kg/kWe for a system with hundreds of kilowatts electric power and less than 10 kg/kWe for megawatt systems. A 1.76 MW system had a specific mass of 6.14 kg/kWe and a radiator area of about 665 m2. The total mass was nearly 10.8 t, with the nuclear reactor be 22.5% of the mass, the shielding being 22% and the Brayton rotating unit being 26.4%. © 2018, Tsinghua University Press. All right reserved.
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页码：450 / 455
页数：5
相关论文
共 14 条
  • [1] Buden D., Summary of space nuclear reactor power systems (1983-1992), Tenth Symposium on Space Nuclear Power and Propulsion. Albuquerque, USA: Idaho National Engineering Laboratory, pp. 51-57, (1993)
  • [2] Bennett G.L., A look at the Soviet space nuclear power program, Energy Conversion Engineering Conference. Washington DC, USA: National Aeronautics and Space Administration, pp. 1187-1195, (1989)
  • [3] Ei-Genk M.S., Deployment history and design considerations for space reactor power systems, Acta Astronautica, 64, 9, pp. 833-849, (2009)
  • [4] Ei-Genk M.S., Space nuclear reactor power system concepts with static and dynamic energy conversion, Energy Conversion and Management, 49, 3, pp. 402-411, (2008)
  • [5] NASA, Prometheus project final report, (2005)
  • [6] Ruault J., Masson F., Worms J., Et al., MEGAHIT: Update on the advanced propulsion roadmap for HORIZON2020, Rome, Italy: European Commission, (2014)
  • [7] Fuller R.L., Closed brayton cycle power conversion unit for fission surface power phase I final report, (2010)
  • [8] Juhasz A.J., Analysis and numerical optimization of gas turbine space power systems with nuclear fission reactor heat sources, (2005)
  • [9] Miyazaki K., Takahashi K., Sasaki T., Et al., Study on specific mass of nuclear electric propulsion system with closed cycle MHD generator, 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference. Cleveland, USA: American Institute of Aeronautics and Astronautics, pp. 1-11, (2014)
  • [10] Marshall A.C., RSMASS-D models: An improved method for estimating reactor and shield mass for space reactor applications, (1997)
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