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International Journal of Energetic Materials and Chemical Propulsion

Erscheint 6 Ausgaben pro Jahr

ISSN Druckformat: 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

CHARACTERIZATION OF NOZZLE EROSION BEHAVIOR UNDER ROCKET MOTOR OPERATING CONDITIONS

Volumen 9, Ausgabe 6, 2010, pp. 533-548
DOI: 10.1615/IntJEnergeticMaterialsChemProp.2011001444
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ABSTRAKT

The performance deterioration of solid-rocket motors caused by nozzle throat erosion becomes more severe with increased operating pressure from higher rates of heat and mass transfer from the core flow to the nozzle surface. Understanding of the rocket nozzle throat erosion processes and developing methods for mitigation of erosion rate can allow motor operation pressures to be substantially higher than those of the existing propulsion systems. Two test rigs have been utilized in the study of nozzle throat erosion phenomena for G-90 grade graphite: an instrumented solid propellant motor (ISPM) and a solid-propellant rocket motor simulator (RMS). The X-ray translucent nozzle assembly used for the RMS and ISPM allows the real-time imaging of the nozzle throat station. It also has a feature for incorporating a nozzle boundary-layer control system to mitigate nozzle throat erosion rates. The RMS is a gaseous reactant combustor, which allows for control of product species compositions, their flow rates, and combustor operating pressure. The erosion process of G-90 graphite was also evaluated in the ISPM using both non-metallized and metallized composite solid propellants at nominal chamber pressures up to 26 MPa. A dimensionless nozzle throat erosion rate correlation in terms of the effective oxidizer mass fraction, chamber pressure, Reynolds number, and nozzle radius of curvature was developed for non-metallized propellant and RMS motor tests. The calculated erosion rates from the correlation showed agreement within ± 0.05 mm/s of the experimentally determined values. A separate correlation for nozzle erosion rates under metallized propellant heating was also developed. This correlation showed diffusion-limited behavior, since the oxidizer concentration effect is not important.

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