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International Journal of Energetic Materials and Chemical Propulsion

年間 6 号発行

ISSN 印刷: 2150-766X

ISSN オンライン: 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

DETERMINATION OF SOLID PROPELLANT BURNING RATE SENSITIVITY TO THE INITIAL TEMPERATURE BY THE ULTRASONIC METHOD

巻 3, 発行 1-6, 1994, pp. 642-653
DOI: 10.1615/IntJEnergeticMaterialsChemProp.v3.i1-6.620
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要約

Missile operating characteristics depend strongly on the solid-propellant burning rate sensitivity to the initial temperature, thus it is an important parameter for the propellant manufacturer and the missile designer. Obtaining the sensitivity to initial temperature requires determination of the burning rate with accuracy and running tests through the acceptance specification temperature range.
Nowadays, firing solid-propellant rocket motors with large grains at various initial temperatures is considered too expensive. Only a limited number of tests are made. The burning rate values are deduced from the pressure data with an indirect method specific to each manufacturer. The data obtained are mean values.
At ONERA, an ultrasonic method is applied successfully to determine solid-propellant burning rates at room temperature.[1,2,3] Accuracy is fairly good, but the method cannot be used at various initial temperatures because of wave propagation condition variations with temperature and the unacceptable behavior of the commercial ultrasonic transducer at low temperatures.
The work presented here is the result of a program established to develop ultrasonic method at different initial temperatures in the range of −40°C, +60°C. This work started with the development of an ultrasonic transducer usable at low temperature, followed by determination of ultrasonic wave velocities and dampings in a large temperature range for selected propellants and coupling materials. Finally, the ultrasonic method has been applied to burning tests in a thermally regulated closed vessel.

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