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International Journal of Energetic Materials and Chemical Propulsion
ESCI SJR: 0.28 SNIP: 0.421 CiteScore™: 0.9

ISSN Imprimir: 2150-766X
ISSN On-line: 2150-7678

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.v7.i4.10
pages 263-280

90% HYDROGEN PEROXIDE/POLYETHYLENE HYBRID ROCKET

Nobuo Tsujikado
Dept. of Aeronautics and Astronautics, Faculty of Engineering, Tokai University, 1117 Kitakaname, Hiratsuka, Kanagawa, 259-1292
Atsushi Ishihara
2Dept. of Human Robotics, Faculty of Engineering, Saitama Institute of Technology 1690 Fusaiji, Fukaya, Saitama, 369-0293

RESUMO

The 90% rocket-grade hydrogen peroxide (R/G HP), concentrated by distillation from Japanese domestic production of 60% commercial grade HP, has been applied to single- and multi-perforation polyethylene (PE) experimental hybrid rocket solid fuel. HP decomposition had been performed with modified three-way catalyst, but auto ignition of solid fuel did not take place due to the accumulated stabilizer in the course of distillation that suppresses the decomposition. So, the solid fuel ignited with the assistance of igniter plug and JP-4-fueled liquid rocket torch. In order to find the oxidizer mass flux for sustaining hybrid rocket combustion, large fuel length/burning port diameter ratio (L/D=35) with transparent polymethylmetacrylate (PMMA) solid fuel small hybrid rocket studies have also been carried out. The oxidizer mass flux has to be over the flux that extends diffusion flame up to the aft end of the solid fuel. The required minimum oxidizer mass flux was confirmed for the multi-perforation solid fuel grain. Comparing with solid propellant rocket grain, multi-spoke wagon wheel and multi-hexagonal perforation solid fuel grain designs were discussed. Modified three-way catalysts utilized for decomposing the R/G HP were powerful even for the commercial grade (C/G); though, it was much too active for R/G HP and there were often steam blast explosions. In order to solve potential danger of a three-way catalyst, improved ignition devices have been developed without using a three-way catalyst.

Referências

  1. Tsujikado, N., Koshimae, M., Ishikawa, R., Kitahara, K. and Ishihara, A., Experimental Studies on Air Turbo Ramjet Engines for Hypersonic Flight Vehicle (Part III).

  2. Tsujikado, N., Koshimae, M., Ishikawa, R., Kitahara, K. and Ishihara, A., An Application of Commercial Grade Hydrogen Peroxide for Hybrid/Liquid Rocket Engine (II).

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

  4. Ventura, M.C. and Heister, S.D., Hydrogen Peroxide as an Alternate Oxidizer for a Hybrid Rocket Booster.

  5. Rusek, J.J., New Decomposition Catalyst and Characterization Techniques for Rocket-Grade Hydrogen Peroxide.

  6. Tsujikado, N., Koshimae, M., Ishikawa, R., Kitahara, K. and Ishihara, A., An Experimental Study of Hybrid/Liquid Rocket Engine Applied Rocket Grade Hydrogen Peroxide.

  7. Tsujikado, N., and Ishihara, A., 90% Hydrogen Peroxide/Polyethylene Solid Fuel Hybrid Rocket Engine.

  8. Pourpoint, T.L. and Anderson, W.E., Environmental Effect on Hypergolic Ignition.


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