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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

IMPROVEMENTS TO MODELING OF HOT FRAGMENT CONDUCTIVE IGNITION OF NITRAMINE-BASED PROPELLANTS

Volumen 4, Edición 1-6, 1997, pp. 1093-1103
DOI: 10.1615/IntJEnergeticMaterialsChemProp.v4.i1-6.1010
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SINOPSIS

Hot fragments generated during the impact of shaped charge jets may penetrate the cartridge casing and induce propellant ignition. To simulate hot fragment conductive ignition, a comprehensive model has been formulated and validated by conducting detailed experiments. The model has been based on an assumed decomposition behavior of the various binder ingredients contained in the nitramine-composite propellant. The objective of this work is to describe the effects of incorporating an improved knowledge about the thermal decomposition behavior of these binder ingredients into the existing model. Rapid thermolysis experiments have revealed that essentially no decomposition occurs of the major ingredients CAB and ATEC over the range of temperatures from 450 to 600 K. The use of these findings has enabled an improved predictive capability of the propellant's rate of gasification, as well as the of the location of the Go/No-Go ignition boundary for both partially and fully confined enclosures. It should also be noted that the use of different reactions among CH2O and NO2 for describing the ignition event has shown only a limited impact on the location of Go/No-Go ignition boundary.

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