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International Journal of Energetic Materials and Chemical Propulsion

Publication de 6  numéros par an

ISSN Imprimer: 2150-766X

ISSN En ligne: 2150-7678

The Impact Factor measures the average number of citations received in a particular year by papers published in the journal during the two preceding years. 2017 Journal Citation Reports (Clarivate Analytics, 2018) IF: 0.7 To calculate the five year Impact Factor, citations are counted in 2017 to the previous five years and divided by the source items published in the previous five years. 2017 Journal Citation Reports (Clarivate Analytics, 2018) 5-Year IF: 0.7 The Immediacy Index is the average number of times an article is cited in the year it is published. The journal Immediacy Index indicates how quickly articles in a journal are cited. Immediacy Index: 0.1 The Eigenfactor score, developed by Jevin West and Carl Bergstrom at the University of Washington, is a rating of the total importance of a scientific journal. Journals are rated according to the number of incoming citations, with citations from highly ranked journals weighted to make a larger contribution to the eigenfactor than those from poorly ranked journals. Eigenfactor: 0.00016 The Journal Citation Indicator (JCI) is a single measurement of the field-normalized citation impact of journals in the Web of Science Core Collection across disciplines. The key words here are that the metric is normalized and cross-disciplinary. JCI: 0.18 SJR: 0.313 SNIP: 0.6 CiteScore™:: 1.6 H-Index: 16

Indexed in

90% HYDROGEN PEROXIDE/POLYETHYLENE HYBRID ROCKET

Volume 7, Numéro 4, 2008, pp. 263-280
DOI: 10.1615/IntJEnergeticMaterialsChemProp.v7.i4.10
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RÉSUMÉ

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.

RÉFÉRENCES
  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.

CITÉ PAR
  1. Dyrda David M., Mechentel Flora S., Cantwell Brian J., Karp Ashley C., Rabinovitch Jason, Jens Elizabeth T., Diode Laser Ignition of a Poly(Methyl Methacrylate) and Gaseous Oxygen Hybrid Motor, Journal of Propulsion and Power, 36, 5, 2020. Crossref

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