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International Journal of Energetic Materials and Chemical Propulsion

Publicado 6 números por año

ISSN Imprimir: 2150-766X

ISSN En Línea: 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

LIQUID OXYGEN VAPORIZATION TECHNIQUES FOR SWIRLING-OXIDIZER-FLOW-TYPE HYBRID ROCKET ENGINES

Volumen 10, Edición 2, 2011, pp. 155-168
DOI: 10.1615/IntJEnergeticMaterialsChemProp.2012001351
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SINOPSIS

The authors have been developing a 1500 N-thrust, swirling-oxidizer-flow-type hybrid rocket engine. The oxygen to which swirl is applied should be in a gaseous state to increase the engine performance. Two methods were proposed to vaporize liquid oxygen (LOX): a regenerative-cooling LOX-vaporization nozzle and a LOX-vaporization burner. We fabricated a LOX-vaporization nozzle with 30 rectangular channels, each with a depth of 1.0 mm, and conducted burning experiments. The experiments showed that rapid ignition and stable combustion without combustion oscillation were achieved, and LOX increased in temperature and sufficiently vaporized while passing through the nozzle. There was no essential problem in vaporizing LOX with the nozzle. The feasibility of the LOX-vaporization burner using combustion of polymethyl methacrylate (PMMA) in LOX was examined from the viewpoint of thermal energy and a preliminary burning experiment was conducted. The burning amount of PMMA to vaporize the LOX propellant for a 1500-N-thrust, hybrid rocket engine was estimated to be at most 3% of the fuel propellant of the rocket. PMMA could burn steadily and safely in LOX and vaporize a large amount of it. The trade-off between the two methods suggested that the vaporization burner had the advantage of a compact and simple structure when compared with the LOX-vaporization nozzle.

CITADO POR
  1. Sakurai Takashi, Tomizawa Tsutomu, Applicability of a LOx Vaporization Preburner for Swirling-Flow Hybrid Rocket Engines, 51st AIAA/SAE/ASEE Joint Propulsion Conference, 2015. Crossref

  2. Kamps Landon T., Sakurai Kazuhito, Ozawa Kohei, Nagata Harunori, Investigation of Graphite Nozzle Erosion in Hybrid Rockets Using N2O/HDPE, AIAA Propulsion and Energy 2019 Forum, 2019. Crossref

  3. Kamps Landon, Hirai Shota, Sakurai Kazuhito, Viscor Tor, Saito Yuji, Guan Raymond, Isochi Hikaru, Adachi Naoto, Itoh Mitsunori, Nagata Harunori, Investigation of Graphite Nozzle Erosion in Hybrid Rockets Using Oxygen/High-Density Polyethylene, Journal of Propulsion and Power, 36, 3, 2020. Crossref

  4. Ozawa Kohei, Shimada Toru, Performance of Mixture-Ratio-Controlled Hybrid Rockets for Nominal Fuel Regression, Journal of Propulsion and Power, 36, 3, 2020. Crossref

  5. Kojima Hiroki, Kamps Landon T., Nobuhara Yuki, Nagata Harunori, Valembois Thomas, Cottenot Camille, Progress Towards Graphite Nozzle Cooling for Throat Erosion Suppression, AIAA AVIATION 2022 Forum, 2022. Crossref

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