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International Journal of Energetic Materials and Chemical Propulsion

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ISSN Печать: 2150-766X

ISSN Онлайн: 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

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EXPERIMENTAL STUDIES OF ALUMINUM AGGLOMERATION IN SOLID ROCKET MOTORS

Том 4, Выпуск 1-6, 1997, pp. 693-705
DOI: 10.1615/IntJEnergeticMaterialsChemProp.v4.i1-6.650
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Краткое описание

In a solid propellant containing an inert binder (polybutadiene), an oxidizer (ammonium perchlorate) and aluminum (15/ 20%), Al is introduced during the propellant formulation as single particles, the median diameter of which is typically between 5 and 40 microns. During the propellant combustion, some of the aluminum particles leave the combustion surface without agglomeration, while others coalesce and give globules, with diameters very different from the initial particle sizes. The relative proportions of unagglomerated particles and globules are poorly known.
The diameter and the mass fraction of large globules which leave the combustion surface immediately govern the Al combustion time and the diameter and mass fraction of the large Al2O3 caps. Understanding of this last point is essential for large motors because these residues are liable to form Al2O3 slag which accumulates at the motor aft end.
The experimental set-up is a pressurizable bomb (<10 MPa). The sample combustion surface is filmed with a high speed camera (≈ 2000 f/s). Film utilization allows the determination of Al globule diameters just before ignition. For a classical composite propellant, a median value of 125 μm was found, the combustion pressure being 4 MPa. By modifying some parameters (propellant formulation, combustion pressure), some factors able to modify the globule size were determined.

ЦИТИРОВАНО В
  1. De Luca Luigi T., Galfetti Luciano, Maggi Filippo, Colombo Giovanni, Paravan Christian, Reina Alice, Dossi Stefano, Fassina Marco, Sossi Andrea, Characterization and Combustion of Aluminum Nanopowders in Energetic Systems, in Metal Nanopowders, 2014. Crossref

  2. Genot Aurélien, Gallier Stany, Schuller Thierry, An analytical model for acoustic induced heat release disturbances from aluminum combustion in solid rocket motors, 2018 Joint Propulsion Conference, 2018. Crossref

  3. Yoon Jisang, Lee Kookjin, Kim Daeyu, Park Namho, Ko Seungwon, Yoon Woongsup, Study of Aluminum Agglomeration Model During Solid Propellant Combustion, Journal of the Korean Society of Propulsion Engineers, 23, 2, 2019. Crossref

  4. Cerri Sara, Galfetti Luciano, De Luca Luigi, D'Andrea Bruno, Cianfanelli Stefano, Experimental Investigation of the CCPs of Micro Aluminized Solid Rocket Propellants, 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference &amp; Exhibit, 2007. Crossref

  5. Wang X., Jackson T.L., Buckmaster J., Numerical simulation of the 3-dimensional combustion of aluminized heterogeneous propellants, Proceedings of the Combustion Institute, 31, 2, 2007. Crossref

  6. Genot Aurelien, Gallier Stany, Schuller Thierry, Model for Acoustic Induced Aluminum Combustion Fluctuations in Solid Rocket Motors, Journal of Propulsion and Power, 35, 4, 2019. Crossref

  7. Li Lian-bo, Chen Xiong, Zhou Chang-sheng, Li Wei-xuan, Zhu Min, Experimental and model investigation on agglomeration of aluminized fuel-rich propellant in solid fuel ramjet, Combustion and Flame, 219, 2020. Crossref

  8. Grossi Marco, Bianchi Daniele, Favini Bernardo, Vega P80 SRM Pressure Oscillations Analysis by means of Q1D Model, AIAA AVIATION 2022 Forum, 2022. Crossref

  9. Grossi Marco, Sereno Alessio, Bianchi Daniele, Favini Bernardo, Numerical Simulation of Multiphase Flows in Solid Rocket Motors Nozzles, AIAA AVIATION 2022 Forum, 2022. Crossref

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