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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

REALISATION OF AN ECO-FRIENDLY SOLID PROPELLANT BASED ON HTPB -HMX-AP SYSTEM FOR LAUNCH VEHICLE APPLICATIONS

Volume 4, Edição 1-6, 1997, pp. 129-134
DOI: 10.1615/IntJEnergeticMaterialsChemProp.v4.i1-6.150
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RESUMO

An eco-friendly higher solid loaded HTPB propellant with improved energetics has been realized in small scale by incorporating 10−20% by weight of a high energy material namely, HMX. This propellant with 88% solid loading has given good processability, mechanical properties and reduced pressure index. Pollution due to HCl smoke in the rocket exhaust is reduced by 20 to 30% by weight. This propellant is expected to give a vacuum specific impulse of 293 seconds at an operating pressure of 70 ksc and an area ratio of 10. Sub Scale motors of 2kgs size have been successfully static tested to evaluate the performance.

CITADO POR
  1. Hamed J. O., Ogunleye O. O., Osheku C. A., Optimal design of a composite propellant formulation using response surface methodology, Advances in Materials Science, 17, 1, 2017. Crossref

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