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International Journal of Energetic Materials and Chemical Propulsion

Publicou 6 edições por ano

ISSN Imprimir: 2150-766X

ISSN On-line: 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

A LINEAR STABILITY ANALYSIS OF OSCILLATORY COMBUSTION INDUCED BY COMBUSTION TIME DELAYS OF LIQUID OXIDIZER IN HYBRID ROCKET MOTORS

Volume 13, Edição 1, 2014, pp. 83-96
DOI: 10.1615/IntJEnergeticMaterialsChemProp.2014005382
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RESUMO

This paper presents a theoretical analysis of combustion instabilities induced by the combustion time delay of liquid oxidizer in hybrid rocket motors. In order to examine the low-frequency unstable combustion of the motors, the transfer function of the feed system of a hybrid rocket was coupled with that of the full thermal−combustion−gas-dynamic coupled system. This transfer function is applicable to the motors that have a long fuel port length. The linear stability limits and the frequencies of neutral oscillations in the hybrid rocket motors were obtained theoretically, using the coupled transfer function. In addition, we compared these results with results obtained under the assumption that various physical quantities change in bulk mode.

Referências
  1. Karabeyoglu, M. A. , Transient combustion in hybrid rockets.

  2. Karabeyoglu, A., Stevens, J. and Cantwell, B. , Investigation of feed system coupled low frequency combustion instabilities in hybrid rockets.

  3. Kitagawa, K. and Yuasa, S. , Combustion characteristics of a swirling LOX type hybrid rocket engine.

  4. Morita, T., Fujiwara, K., Matsuki, A., Yamaguchi, S., and Shimada, T. , A linear stability analysis of hybrid rocket combustion.

  5. Morita, T., Kitagawa, K., Yuasa, S., Yamaguchi, S., and Shimada, T. , Low-frequency combustion instability induced by the combustion time lag of liquid oxidizer in hybrid rocket motors.

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