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International Journal of Energetic Materials and Chemical Propulsion

Publicado 6 números por año

ISSN Imprimir: 2150-766X

ISSN En Línea: 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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EVALUATION OF THE EFFECTIVENESS OF AN INDUSTRIAL REPAIR PROCEDURE FOR SOLID PROPELLANT GRAINS

Volumen 4, Edición 1-6, 1997, pp. 368-386
DOI: 10.1615/IntJEnergeticMaterialsChemProp.v4.i1-6.370
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SINOPSIS

Voids and defects can exist in solid propellant grains as a result of the manufacturing process, transportation, or storage. For cases where the damage is not too severe, it is possible to salvage the grain segment by employing an appropriate repair. A new repair procedure has been developed by United Technologies/Chemical Systems Division (UT/CSD) for the Titan IV solid rocket motor (SRM) propellant grains. The repair procedure involved removing the damaged region of solid propellant and replacing the cavity with a specially formulated potting compound. This investigation has been undertaken to evaluate the effectiveness of this procedure. A high-pressure windowed test rocket motor was modified and employed as a motor analog to simulate the combustion environment in actual rocket motors. Propellant samples were sized to provide long bum time in order to verify the repair effectiveness throughout the test duration. Repaired propellant samples were tested under several pressure levels to evaluate the repair effectiveness. Additionally, samples with un-repaired slits were also tested to evaluate the propensity for a flame to propagate into a cut defect in order to establish the validity of the repair tests. Based on test results, it was found that the suggested repair procedure was effective enough to prevent the occurrence of flame spreading into repaired regions. The repair procedure evaluated was found to be effective up to the maximum tested pressure level of 8.3 MPa.

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