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International Journal of Energetic Materials and Chemical Propulsion

Publicou 6 edições por ano

ISSN Imprimir: 2150-766X

ISSN On-line: 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

CHARGE DESIGN AND NON-ACOUSTIC INSTABILITY OF SOLID ROCKET MOTOR

Volume 5, Edição 1-6, 2002, pp. 903-917
DOI: 10.1615/IntJEnergeticMaterialsChemProp.v5.i1-6.920
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RESUMO

The goal of this paper is to make a correlation between non-acoustic low frequency instability of combustion in a solid rocket motor (SRM) and geometrical characteristics of the charge and motor cavity. The problem is considered in detail for SRM having end-burning or tubular charge. The analysis is carried out using an original model of unsteady combustion in SRM. This model allows the flame temperature and the temperature distribution in gas flow to fluctuate with pressure in combustion chamber (the Mache effect). A laminar one-dimensional gas flow (without dissipation and mixing) is assumed and described using the Lagrangian approach. The propellant unsteady combustion is formulated in framework of Zel'dovich phenomenological approach. Emphasis is on dependence of the critical conditions of stable combustion on the Mache effect and on sizes of pre-nozzle volume and propellant channel. The analysis shows that the instability region is wider for SRM with a charge channel than for motor with end-buming charge, at the same free volume of motor cavity. A pre-nozzle volume stabilizes the combustion process. The boundary of instability depends mainly on the pre-nozzle part of the cavity but is not sensitive to the channel volume of propellant charge.

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