Conceptual design: Dependence of parameterization on design performance of three-stage hybrid rocket-Reference-Cited by-同舟云学术

Conceptual design: Dependence of parameterization on design performance of three-stage hybrid rocket

Published:2014 Issue:5 Volume:9 Page:JFST0071-JFST0071
ISSN:1880-5558
Container-title:Journal of Fluid Science and Technology
language:en
Short-container-title:JFST

Author:

KANAZAKI Masahiro¹,KANAMORI Fumio¹,KITAGAWA Yosuke¹,NAKAMIYA Masaki²,KITAGAWA Koki³,SHIMADA Toru³

Affiliation:

1. Faculty of System Design, Tokyo Metropolitan University

2. Research Institute for Sustainable Humanosphere, Kyoto University

3. Institute of Space and Astronautical Science/Japan Aerospace Exploration Agency

Publisher

Japan Society of Mechanical Engineers

Subject

Fluid Flow and Transfer Processes,Mechanical Engineering

Link

https://www.jstage.jst.go.jp/article/jfst/9/5/9_2014jfst0071/_pdf

Reference6 articles.

1. Hikone, S., Hasegawa, T. and Nakagawa, I., Regression rate characteristics and combustion mechanism of some hybrid rocket fuels, AJCCP2010, Miyazaki, (2010).

2. Humble, R., Henry. G. and Larson, W., Space propulsion analysis and design, Learning Solutions, New York, (1995).

3. Kanazaki, M., Obayashi, S. and Nakahashi, K., Exhaust manifold design with tapered pipes using divided range MOGA, Engineering Optimization, Taylor&Francis, Vol. 36, No. 2, (2004), pp. 149-164.

4. Kitagawa,Y., Kitagawa, K., Nakamiya, M., Kanazaki, M. and Shimada, T., Multi-stage hybrid rocket conceptual design for micro-satellites launch using genetic algorithm, Transaction of JSASS, Vol. 4, No. 55, (2012), pp. 229-236.

5. Thicksten, Z., Macklin, F. and Campbell, J., Handling considerations of Nitrous Oxide in hybrid rocket motor testing, AIAA Paper 2008-4830, (2008).

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