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International Journal of Energetic Materials and Chemical Propulsion

Published 6 issues per year

ISSN Print: 2150-766X

ISSN Online: 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

CRYOGENIC WASHOUT OF SOLID ROCKET PROPELLANTS

Volume 4, Issue 1-6, 1997, pp. 221-230
DOI: 10.1615/IntJEnergeticMaterialsChemProp.v4.i1-6.260
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ABSTRACT

Cryogenic washout (U.S. Patent No. 5025632) is a process using liquid nitrogen (LN2) as a washout medium to remove propellant from within solid rocket motors. The process is environmentally clean and produces dry, size-reduced particles that are well suited for disposal or for reuse in applications such as commercial explosives.
A prototype cryogenic washout facility has been constructed for washout of Minuteman II Stage 3 solid rocket motors under a contract with the U.S. Air Force. Design support testing on a bench-scale system has been completed. Workup and subscale safety tests are in progress.
The design support testing included laboratory and bench-scale testing on Hazard Class 1.1 and 1.3 propellants. The laboratory tests established that essentially no change in the sensitivity of the test propellants occurred between ambient and cryogenic temperatures.
This paper describes prototype equipment design and presents a summary of the testing performed.

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