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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

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THEORETICAL STUDY ON THE INFLUENCE OF DEBONDINGS ON SOLID ROCKET MOTOR PERFORMANCE

Volume 21, Numéro 1, 2022, pp. 21-45
DOI: 10.1615/IntJEnergeticMaterialsChemProp.2021039436
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RÉSUMÉ

In solid rocket motors, propellant debondings are very dangerous since they could cause an increment of the burning surface area and anticipate the exposure of case-insulating thermal protection material. Therefore, when a debonding internal zone is discovered, it is of primary importance to guarantee that the solid rocket motor is still able to accomplish the mission within its operational requirements. From a numerical point of view, debondings cannot be evaluated in an analytical, closed form due to their variety of shapes. The present study is aimed at assessing the impact of debondings through the adoption of advanced computer graphic techniques like the offsetting of the solid rocket motor burning surface discretized as a dynamic three-dimensional triangular mesh. Mesh handling algorithms are discussed in detail. Numerical results are obtained through an in-house simulation software which has been developed based on the aforementioned methods.

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