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International Journal of Energetic Materials and Chemical Propulsion

Erscheint 6 Ausgaben pro Jahr

ISSN Druckformat: 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

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DEVELOPMENT OF ABLATIVE THERMAL RESPONSE MODELING OF EPDM-BASED THERMAL PROTECTION SYSTEMS

Volumen 19, Ausgabe 4, 2020, pp. 275-292
DOI: 10.1615/IntJEnergeticMaterialsChemProp.2020033869
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ABSTRAKT

A one-dimensional material response computer code has been developed for the ethylene-propylene-dien-monomer (EPDM)-based thermal protection system, designated as PARC. This surface ablation and pyrolysis code uses blowing wall boundary conditions and a dynamic coordinate system, and is coupled with computational fluid dynamics and thermodynamics programs' databases. A code-to-code comparison with NASA's PATO model shows very good agreement. Validation results are shown to be in good agreement with ablation gauges embedded in a subscale rocket motor. This modeling capability can improve modeling of ablative material performance in solid rocket motors.

REFERENZEN
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  7. Rindal, R.A., (1968) An Analysis of the Coupled Chemically Reacting Boundary Layer and Charring Ablator: Part 6: An Approach for Characterizing Charring Ablator Response with In-Depth Coking Reactions, NASA, Tech. Rep. NASA CR-1065.

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  9. Shilav, R. and Leitner, A., (2018) Modeling of Ablative Thermal Response of Low-Density Thermal Protection System, Proc. 58th Israel Annual Conf. on Aerospace Sciences, Haifa, Israel.

  10. Shilav, R., Leitner, A., and Gany, A., (2018) New Measurement Technique for Thermal Conductivity of Ablative Materials, Int. J. Energetic Mater. Chem. Propuls., 17(3), pp. 171-182.

  11. Scoggins, J.B. and Magin, T.E., (2014) Development of Mutation++: Multicomponent Thermodynamics and Transport Properties for IONized Gases Library in C++, 11th AIAA/ASME Joint Thermo-Physics and Heat Transfer Conf, Atlanta, GA, AIAA Paper 2014-2966.

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REFERENZIERT VON
  1. Shilav Ramin, Gottlieb Levi, Dekel Noa, Re-analysis of the multistep degradation kinetic data of AVCOAT-like thermal protection system, Journal of Thermal Analysis and Calorimetry, 147, 8, 2022. Crossref

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