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International Journal of Energetic Materials and Chemical Propulsion

年間 6 号発行

ISSN 印刷: 2150-766X

ISSN オンライン: 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

EXPERIMENTAL STUDY OF MICROTHRUSTER HEAT LOSS

巻 8, 発行 4, 2009, pp. 329-344
DOI: 10.1615/IntJEnergeticMaterialsChemProp.v8.i4.60
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要約

Due to the miniature sizes of microthrusters, their combustion efficiency is greatly affected by the relatively large heat loss and short residence time for the reaction products. This leads to a decrease in the gas temperature and completeness of combustion. As a result, the measured specific impulse for microthrusters, as a rule, turns out essentially lower than the theoretical one. To derive data needed for simulating this problem, the current research program has been developed and directed to the determination of the mechanism of energy loss in microthrusters and differentiation of various contributions into total energy loss. The propellant internal ballistic characteristics were obtained at different pressures for a chosen propellant containing a small additive of nanoaluminum. The casing of the microthruster was fabricated in the form of a cylinder made of fused quartz. The inner volume of the combustion chamber was about 0.07 cm3. In order to determine the parameters of heat exchange between the combustion products and combustion chamber walls, the temperature histories of the thruster casing and the combustion gases inside the chamber were recorded with microthermocouples. In addition, approximate mathematical model was developed for estimating the effect of heat loss on the delivered value of specific impulse. The results of preliminary calculations by the model are presented.

参考
  1. Rossi, C. and Esteve, D., Micropyrotechnics, A New Technology for Making Energetic Microsystems, Review and Prospective.

  2. Lee, D.H. and Kwoon, S., Heat Transfer and Quenching Analysis of Combustion in Micro Combustion Vessel.

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