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国际能源材料和化学驱动期刊

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ISSN 打印: 2150-766X

ISSN 在线: 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

HIGH BURNING RATE SOLID ROCKET PROPELLANTS

卷 4, 册 1-6, 1997, pp. 646-660
DOI: 10.1615/IntJEnergeticMaterialsChemProp.v4.i1-6.610
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摘要

The need for high velocity in ground to air missile applications which require a very short time of combustion for the rocket motor and for the thrusters piloting the trajectory, has prompted SNPE to study and develop under governmental funding new minimum and reduced smoke solid propellants with high burning rate which will be able to meet also the high energy and IM requirements. As it has already recently shown Butacene catalysed reduced smoke composite propellants are a good base to achieve high burning rate with a relatively reduced pressure exponent in a large range of operational pressure. The adjustment of the combustion characteristics may be obtained by controlling the content of Butacene in direct relationship with the content of iron, and the content of Ammonium Perchlorate and its particles size. The use of Ultra Fine Ammonium Perchlorate allows to achieve ultra high burning rates, between 50 mm/s to 200 mm/s in a very large range of pressure as the pressure exponent may stay under 0.5 until several hundreds of bars.
Unlike composite propellant for which it is relatively easy to achieve high burning rate as a lot of various catalysts act on the decomposition mechanism of the Ammonium Perchlorate oxidiser, minimum smoke XLDB propellants which use Nitramine (RDX) cannot be accelerated in a efficient way by the use of additives modifying the combustion of this "monopropellant" filler. Very few combustion catalysts of pure RDX exist and they are incompatible with the main energetic ingredients of the XLDB binders. Therefore the only practical ways to achieve high burning rate minimum smoke propellants are :

  • to incorporate ballistic modifiers used in conventional double base propellants such as lead catalysts or more recently SNPE developed unleaded catalysts which act on the decomposition of the binder. But the effects on the burning rate stay at a limited level, which lags far from our goals. The low pressure exponents are nevertheless very attractive.
  • to use new energetic ingredients, binder or filler, which burn by themselves faster than the conventional constituents. Some great results have been obtained with new formulations which use GAP binder and CL 20 as a main filler. Burning rate as high as 40 mm/s at operational pressure will be achievable in the next future if a good compromise with energetic properties and IM objectives may be found.
In conclusion, today, to achieve very high burning rates, specifically required for some thruster grain design, Butacene based reduced smoke propellants with Ultra Fine Ammonium Perchlorate are the only solution. But for the main propulsion which needs medium range of burning rate, minimum smoke propellants are available.

对本文的引用
  1. Anniyappan M., Talawar M. B., Sinha R. K., Murthy K. P. S., Review on Advanced Energetic Materials for Insensitive Munition Formulations, Combustion, Explosion, and Shock Waves, 56, 5, 2020. Crossref

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