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International Journal of Energetic Materials and Chemical Propulsion

Published 6 issues per year

ISSN Print: 2150-766X

ISSN Online: 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

GLYCIDYL AZIDE POLYMER AND POLYETHYLENE GLYCOL MIXTURES AS HYBRID ROCKET FUELS

Volume 11, Issue 2, 2012, pp. 97-106
DOI: 10.1615/IntJEnergeticMaterialsChemProp.2012001456
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ABSTRACT

Two types of hybrid rocket motors that use mixtures of glycidyl azide polymer (GAP) and polyethelene glycol (PEG) as the solid fuel are proposed and the combustion characteristics are presented. GAP and PEG mixtures in which the PEG concentrations are lower than a critical value between 40 and 50 mass% can sustain self-combustibility and can be used as a solid fuel for gas hybrid rocket systems, while mixtures with higher PEG concentrations and without self-combustibility can be employed as a solid fuel for traditional hybrid rockets. Thrust control and tailoring using changes in both the oxidizer/fuel (O/F) ratio and grain composition were investigated for the gas hybrid system, and successful control was accomplished in experiments. Firing tests were conducted of a traditional hybrid rocket motor as functions of the oxygen mass flux and burning pressure. The effect of GAP is obvious, and GAP enhances the regression rates of the solid fuel grain, and an effect of pressure was also found. The distributed flame model is discussed briefly here to explain the regression rate increase by GAP.

CITED BY
  1. CHIBA Kazuhisa, KANAZAKI Masahiro, NAKAMIYA Masaki, KITAGAWA Koki, SHIMADA Toru, Conceptual Design of Single-Stage Hybrid Rocket for Scientific Observation in View of Fuels Using Design Informatics, AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 13, 2014. Crossref

  2. Chiba Kazuhisa, Yoda Hideyuki, Ito Shoma, Kanazaki Masahiro, Watanabe Shin'ya, Kitagawa Koki, Shimada Toru, Ascendancy of Extinction-Reignition on Single-Stage Hybrid Sounding Rocket in View of Fuels, 57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2016. Crossref

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