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国际能源材料和化学驱动期刊

每年出版 6 

ISSN 打印: 2150-766X

ISSN 在线: 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

Ignition and Unsteady Combustion of AP-based Composite Propellants in Subscale Solid Rocket Motors

卷 4, 册 1-6, 1997, pp. 1046-1061
DOI: 10.1615/IntJEnergeticMaterialsChemProp.v4.i1-6.970
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摘要

The description of the unsteady combustion mechanisms of solid propellants and the numerical solution of the solid rocket internal flow are the two key factors in determining the unsteady behavior during the ignition transient inside a solid rocket motor. The objective of this study is to develop a numerical tool able to predict the flow-solid propellant interaction responsible for the ignition process. The numerical package developed for the simulations comprises a multi-dimensional CFD code using a k-∈ turbulence model which is associated with two main components: a one-dimensional unsteady heat conduction analytical solution for the propellant surface temperature or burning rate and a one-dimensional Couette flow solution for the wall boundary layer. In addition, one considers that an ignition propagation occurs by conduction at the gas side propellant surface when the critical inflammation conditions to sustain such a propagation are satisfied.
This paper presents the details of the modules created to simulate the ignition transient period and the applications conducted to predict the ignition delay and the flow field in selected subscale solid rocket motor configurations.

对本文的引用
  1. Francois Laurent, Dupays Joël, Massot Marc, A new simulation strategy for solid rocket motor ignition: coupling a CFD code with a one-dimensional boundary flame model, verification against a fully resolved approach, AIAA Propulsion and Energy 2021 Forum, 2021. Crossref

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