Experimental investigation of the factors affecting the burning rate of solid rocket propellants

Basit Öğe Kaydı
dc.contributor.authorYaman, Hayri
dc.contributor.authorÇelik, Veli
dc.contributor.authorDeğirmenci, Ercan
dc.date.accessioned2020-06-25T18:12:33Z
dc.date.available2020-06-25T18:12:33Z
dc.date.issued2014
dc.departmentKırıkkale Üniversitesi
dc.description.abstractThe burning rate of the solid rocket propellants is one of the most important factors that determine the performance of the rocket. The burning rate of rocket motors running with solid propellant is called flame regression, which occurs with the ignition in the fuel grain perpendicular to the burning surface. This study investigates the effects of the addition of metal-based high-energy matter (Aluminum) into the content of the propellant produced within the scope of development project. The study starts with the manufacture of propellant samples. For the data input in the burning rate measurement device, the determination process of energy levels of the manufactured propellant samples with a calorimeter is performed. Then, the other data related to the propellants to be measured for the burning rate, such as energy level of the propellant, the propellant density, the maximum combustion temperature, and the physical sizes of the propellants, were inputted to the computer of the burning rate measurement device. The 22 g of the sample propellant to be measured for burning rate was placed in a part of the burning rate measurement device, "closed bomb" which has a capacity of 200 cm(3). Burning rate measurements were performed at the same time in a constant-volume environment under different pressures. The burning rate of the double base propellant without aluminum (DB-1) was compared with other double base fuels in which aluminum was added by 2% (DB-2) and 4% (DB-3). It was found that the burning rates and burning heat of new fuels manufactured by adding aluminum to the content of the standard double base fuel (DB-1) increased. Crown Copyright (C) 2013 Published by Elsevier Ltd. All rights reserved.en_US
dc.description.sponsorshipSAN-TEZMinistry of Science, Industry & Technology - Turkey [00386.STZ.2009-1]; Science, Industry and Technology MinistryMinistry of Science, Industry & Technology - Turkeyen_US
dc.description.sponsorshipThis study was conducted with the support of SAN-TEZ Project coded as 00386.STZ.2009-1. Sample fuels used in this study were produced in the MKE Barutsan Rocket and Explosive Factory. The measurement and testing processes were conducted in the laboratories of MIGYEM (Development and Renewal Directorate of Ammunition Reclamation). The authors thank the Science, Industry and Technology Ministry, which provided financial support, MKE (Mechanical and Chemical Industry Corporation) Barutsan Rocket and Explosive Factory, which was the partner of the project, and MIGYEM, which gave support for testing and measurements.en_US
dc.identifier.citationclosedAccessen_US
dc.identifier.doi10.1016/j.fuel.2013.05.033
dc.identifier.endpage803en_US
dc.identifier.issn0016-2361
dc.identifier.issn1873-7153
dc.identifier.scopus2-s2.0-84885952581
dc.identifier.scopusqualityQ1
dc.identifier.startpage794en_US
dc.identifier.urihttps://doi.org/10.1016/j.fuel.2013.05.033
dc.identifier.urihttps://hdl.handle.net/20.500.12587/5962
dc.identifier.volume115en_US
dc.identifier.wosWOS:000325647000093
dc.identifier.wosqualityQ1
dc.indekslendigikaynakWeb of Science
dc.indekslendigikaynakScopus
dc.language.isoen
dc.publisherElsevier Sci Ltden_US
dc.relation.ispartofFuel
dc.relation.publicationcategoryMakale - Uluslararası Hakemli Dergi - Kurum Öğretim Elemanıen_US
dc.rightsinfo:eu-repo/semantics/closedAccessen_US
dc.subjectBurning rateen_US
dc.subjectSolid rocket propellanten_US
dc.subjectBurning rate measurementen_US
dc.titleExperimental investigation of the factors affecting the burning rate of solid rocket propellantsen_US
dc.typeArticle

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