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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

COMBUSTION BEHAVIOR OF BORON-BASED SOLID PROPELLANTS IN A DUCTED ROCKET

Volumen 2, Ausgabe 1-6, 1993, pp. 386-401
DOI: 10.1615/IntJEnergeticMaterialsChemProp.v2.i1-6.230
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ABSTRAKT

This paper presents results of experimental studies on airbreathing combustion of high boron-loaded solid propellants in connected-pipe ducted rockets at reduced and full-scale motor (chamber diameter: 0.100 m and 0.180 m) . Tests have been performed with lateral-shifted air inlet combustors. Previously, this configuration has been demonstrated more favorably for the ignition and complete burning of boron particles. The boron particle combustion is estimated in terms of total combustion efficiency based on injected mixture equivalent ratio.
At a small scale (D = 0.100 m), the effects on the combustion efficiency of different parameters which are the K ratio (fuel grain area to injection throat area), the chamber pressure and air inlet temperature were studied. To exactly evaluate the capability of boron-ducted rockets, tests have been performed at a larger and more representative scale (D = 0.180 m) in simulated low-altitude flight conditions. Based on the results from reduced scale studies, the full-scale engine tests have been defined. The obtained results from investigations on choked and unchoked gas generator configurations are given. Finally, both configurations are also compared with an integrated ducted rocket without boron.

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