图书馆订阅: Guest
Begell Digital Portal Begell 数字图书馆 电子图书 期刊 参考文献及会议录 研究收集
国际能源材料和化学驱动期刊
ESCI SJR: 0.149 SNIP: 0.16 CiteScore™: 0.29

ISSN 打印: 2150-766X
ISSN 在线: 2150-7678

国际能源材料和化学驱动期刊

DOI: 10.1615/IntJEnergeticMaterialsChemProp.v8.i6.10
pages 473-488

A STUDY OF HYBRID RAMJET PERFORMANCE

Ichiro Nakagawa
Department of Aeronautics and Astronautics,Tokai University 1117 Kitakaname Hiratsuka Kanagawa 259-1292, Japan

ABSTRACT

A hybrid ramjet is proposed in this paper. It is the combined engine of a liquid-fuel ramjet and a ducted rocket. The high Isp performance and the wide fuel flow control range of a liquid fuel ramjet, and the high ram burner ignitability and stability of a ducted rocket are expected. The hybrid ramjet fuel control range was proved to be twice compared with that of a ducted rocket. The optimal burning rate characteristics of the solid fuel were investigated. The same burning rate characteristics as the normal solid propellant for a solid rocket were sufficient for the fuel flow control of the hybrid ramjet. Theoretical performance calculations about the hybrid ramjet were conducted. As the ratio of the liquid to the solid fuel flow rate increases, the Isp becomes higher. When it is 3 to 1, Isp is 68% higher than that of a ducted rocket. Direct connect combustion tests were also conducted with only solid fuels, which contain boron. The ram burner ignitability was proved to be good.

REFERENCES

  1. Kubota, N., Miyata, K., Kuwahara, T., Mitsuno, M., and Nakagawa, I., Enegetic Solid Fuels for Ducted Rockets.

  2. Markstein, G.H., Combustion of Metals.

  3. Nihon Kagaku Gakkai, Kagakubinran Kisohen.

  4. Hikita, T. and Akita, K., Nensyogairon.

  5. Gordon, S. and McBride, B.J., Computer Program for Calculation of Complex Chemical Equilibrium Compositions and Applications.


Articles with similar content:

LIQUID OXYGEN VAPORIZATION TECHNIQUES FOR SWIRLING-OXIDIZER-FLOW-TYPE HYBRID ROCKET ENGINES
International Journal of Energetic Materials and Chemical Propulsion, Vol.10, 2011, issue 2
Takashi Sakurai, Ikuno Kumazawa, Saburo Yuasa, Koki Kitagawa, Toshiaki Sakurazawa
GLYCIDYL AZIDE POLYMER AND POLYETHYLENE GLYCOL MIXTURES AS HYBRID ROCKET FUELS
International Journal of Energetic Materials and Chemical Propulsion, Vol.11, 2012, issue 2
Koji Fujisato, Yuya Nomura, Motoyasu Kimura, Takeshi Yagishita, Makihito Nishioka, Keiichi Hori, Yutaka Wada
DEVELOPMENT OF TEST FACILITIES FOR 5 KN-THRUST HYBRID ROCKET ENGINES AND A SWIRLING-OXIDIZER-FLOW-TYPE HYBRID ROCKET ENGINE FOR TECHNOLOGY DEMONSTRATION
International Journal of Energetic Materials and Chemical Propulsion, Vol.15, 2016, issue 6
Takashi Sakurai, H. Ando, N. Suzuki, Saburo Yuasa, Koki Kitagawa, A. Takayama, Takeshi Yagishita, N. Shiraishi, S. Hatagaki, R. Yui, T. Shimada
LAGRANGIAN APPROACH TO AXISYMMETRIC SPRAY SIMULATION OF PINTLE INJECTOR FOR LIQUID ROCKET ENGINES
Atomization and Sprays, Vol.28, 2018, issue 5
Kanmaniraja Radhakrishnan, Min Son, Jaye Koo, Keonwoong Lee
COMBUSTION CHARACTERISTICS IN A GASEOUS HYDROGEN/OXYGEN SMALL THRUSTER
International Journal of Energetic Materials and Chemical Propulsion, Vol.4, 1997, issue 1-6
Saburo Yuasa, Satoshi Kubota, Masumi Fujita