Perspectives for hybrid propulsion development in Brazil

Authors

  • Susane Ribeiro Gomes Programa de Pós-Graduação de Engenharia Aeronáutica e Mecânica do Instituto de Tecnologia da Aeronáutica (ITA) São Paulo, Brasil
  • Leopoldo Rocco Junior Programa de Pós-Graduação de Engenharia Aeronáutica e Mecânica do Instituto de Tecnologia da Aeronáutica (ITA) São Paulo, Brasil
  • Koshun Iha Programa de Pós-Graduação de Engenharia Aeronáutica e Mecânica do Instituto de Tecnologia da Aeronáutica (ITA) São Paulo, Brasil
  • José Atílio Fritz Fidel Rocco Programa de Pós-Graduação de Engenharia Aeronáutica e Mecânica do Instituto de Tecnologia da Aeronáutica (ITA) São Paulo, Brasil

DOI:

https://doi.org/10.22480/revunifa.2010.23.808

Keywords:

Hybrid rocket motor, Aerospace propulsion, Hybrid Propulsion, Apogee motor

Abstract

The production of small, micro and nano satellites is growing exponentially, as a result, the need for launch vehicles also increases, giving rise to a strong concurrency for a place in this important international market. Hence, developing countries must make the effort to enter this competition, on this decade, while there is still the opportunity. This attempt should comprise the development of a space research program largely related to the development of launch vehicles to fit the demands of placing satellites in low and high orbits. This requirement should motivate the launcher service provider to find an economic way of boosting satellites of different geometries. For this reason, it is not surprising to explore substitute ways to launch small satellites in a suitable time with cheaper costs by the use of hybrid rocket motors, a well-known rocket propulsion system recognized by the relatively smaller production costs and high safety. Therefore, this essay aims to present the viability of this technology, dealing primarily with the design and operational relevant matters, focusing on the development of the hybrid propulsion technology in Brazil.

References

ALTMAN, D. The Encyclopedia of Physical Science and Technology. [S.l.:s.n.], 2001. v.14

ALTMAN, D. ; HUMBLE, R. Hybrid rocket propulsion systems. In: Space Propulsion Analysis and Design. New York. McGraw-Hill, 1995. pp. 365–441.

BURKHARDT, H. et.al. Evaluation of Propulsion Systems for satellite End-Of-Life De-Orbiting. AIAA Journal. [S.l : s.n.]. p. 2002-4208.

CARMICINO, C., Alcuni Aspetti della Balistica Interna di um Endoreattore a Propellenti Ibridi e del Comportamento di Ugelli a Spina Troncata. 2002 Dissertation, Univ. of Naples “Federico II”, Naples, Italy, 2002.

CARMICINO, C.; RUSSO, S. A performance comparison between two different injector configurations in a hybrid rocket. Aerospace Science and Technology, v. 11, n. 1, 2007.

GRANT A. R. et.al. Performance comparison of HTPB-Based solid fuels containing nano-sized energetic powder in a cylindrical hybrid rocket motor. 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2002. 2002-3576

GREINER, B. ; FREDERICK, R. A., Jr., Results of Labscale Hybrid Rocket Motor Investigation, AIAA Paper 92-3301, July 1992.

IMAMURA, T.; SHIMADA, O.; YUASA, S., Effects of Swirling Oxygen Flow on the Performance of a Hybrid Rocket Engine. Proceedings of the 36"’ Karabeyoglu, A., M., Zilliac, G., Cantwell, B., J., De Zilwa, A., Castelluci, P., “Scale-up high regression rate liquefying hybrid rocket motors.” AIAA paper 2003-1162.

JANOVSKY, R. et. al. End-of-life de-orbiting strategies for satellites Deutscher Luft-und-Raumfahrtkongress 2002. DGLR-JT2002-028

KARABEYOGLU, M.; ALTMAN, D., The transient behavior of hybrid rockets. AIAA Paper 97-2936, 1997.

KNUTH, W.H. et al., Experimental investigation of a vortex-driven high-regression rate hybrid rocket engine. AIAA Paper 98-3348, 1998.

MARXMAN, G.A.; GILBERT, G.M., Turbulent boundary layer combustion in the hybrid rocket. In: SYMPOSIUM (INTERN.) ON COMBUSTION, THE COMBUSTION INSTITUTE, 19.,1963, [S.l.]. Anais..., 1963. p. 371-383.

MARXMAN, G. A.; WOOLDRIDGE, C. E., Research on the combustion mechanism of hybrid rockets. Combustion and Propulsion Panel, AGARD, NATO. San Diego: [S.n]. 1965.

RISHA, G.A., et.al. Metals, Energetic Additives, and Special Binders Used in Solid Fuels for Hybrid Rockets. Fundamentals of Hybrid Rocket Combustion in Astronautics and Aeronautics, v. 218, p. 423-442, 2007.

SUTTON, G.P.; BIBLARZ, O., Rocket propulsion elements, 7th ed. [S.l.] : John Wiley & Sons, 2001, Cap. 15.

YUASA, S.. A technique for improving the performance of hybrid rocket engines. Los Angeles: [s.n.], 1999. p 99-2322.

Published

2010-06-01

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How to Cite

Perspectives for hybrid propulsion development in Brazil. The Journal of the University of the Air Force , Rio de Janeiro, v. 23, n. 26, 2010. DOI: 10.22480/revunifa.2010.23.808. Disponível em: https://revistadaunifa.fab.mil.br/index.php/reunifa/article/view/808.. Acesso em: 19 sep. 2024.

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