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International Journal of Energetic Materials and Chemical Propulsion

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ISSN Печать: 2150-766X

ISSN Онлайн: 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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MECHANICAL PROPERTIES OF COMPOSITE PROPELLANTS AND EFFECT OF PROPELLANT STRETCH ON ITS BURN RATE

Том 9, Выпуск 3, 2010, pp. 233-247
DOI: 10.1615/IntJEnergeticMaterialsChemProp.v9.i3.40
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Краткое описание

Propellant stretching in combustion leads to an essential increase (up to 50% and more) in burn rate. Analysis of existing research regarding the influence of stretch deformations on propellant burn rate is carried out. It is shown that for composite solid propellants, the basic mechanism of increase in the burn rate under stretch conditions is detachment of the binder from particles of oxidizers, formation of additional burning surfaces, and change of structure in the burn zone. For a description of this effect, a rheological model of composite solid propellant is developed. The model takes into account a detachment of the binder from particles (oxidizers, coolers, metals, etc.) under action of stretch deformations. The criterion describing distinction in behaviors of propellant in stretch conditions with detachment of the binder from particles in comparison with a stretch of the same material without occurrence of internal defects is established. A method for experimental determination of the amount of defects arising in the propellant upon stretching is suggested based on analysis of the diagram of material stretch. A mathematical model of combustion of composite propellant under stretch conditions, taking into account a detachment of the binder from oxidizer particles, and the formation of an additional burning surface is developed. The model considers the heterogeneous structure of the propellant, the burn surface, and the gas phase. Analysis of ignition of the cracks formed on the binder-particle border as a result of detachment of the binder from particles in propellant stretch is carried out. When a burn rate shows little decrease with propellant stretch, an inverse effect can be observed under certain conditions. This effect is connected with incomplete burn-out of oxidizer particles on the propellant burn surface as a result of their detachment from the surface. Parametrical research of composite pro- pellant combustion under the action of stretch deformations is carried out. Results of calculations are compared with well-known experimental data. Correlation between changes in propellant burn rate under stretch conditions and the parameters of the propellant stretch diagram without combustion is established. A method is developed that allows for predicting the change in propellant burn rate under stretch conditions by using the diagram of propellant stretch without combustion.

ЦИТИРОВАНО В
  1. Adel Walid M., Guo-zhu Liang, Study of Cooldown Thermal Loading Effect on the Bore Deformation of Viscoelastic Solid Propellant Grain, 53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017. Crossref

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