Kompozit Roket Yakıtının Yanma Hızı Üzerine Ortam Basıncının ve Başlangıç Sıcaklığının Etkileri

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dc.contributor.authorBayça, Salih Uğur
dc.contributor.authorDemir, Murat
dc.date.accessioned2025-01-21T14:27:52Z
dc.date.available2025-01-21T14:27:52Z
dc.date.issued2023
dc.description.abstractRocket engines using composite rocket propellant are preferred in military applications because they can be stored for a long time and are ready to fire at any time. In this study, the effects of the initial temperature and ambient pressure of the composite rocket propellant on the burning rate were investigated. The combustion temperature of the sample was determined with a closed bomb calorimeter. Burning rate was determined at 241, 294 and 343 K ambient temperatures and using a strand burner device. Burning rate of composite rocket propellant increased with increasing ambient pressure. It was determined that the burning rate increased with the increase in the initial temperature of the combustion chamber.
dc.description.abstractRocket engines using composite rocket propellant are preferred in military applications because they can be stored for a long time and are ready to fire at any time. In this study, the effects of the initial temperature and ambient pressure of the composite rocket propellant on the burning rate were investigated. The combustion temperature of the sample was determined with a closed bomb calorimeter. Burning rate was determined at 241, 294 and 343 K ambient temperatures and using a strand burner device. Burning rate of composite rocket propellant increased with increasing ambient pressure. It was determined that the burning rate increased with the increase in the initial temperature of the combustion chamber.
dc.identifier.dergipark1213570
dc.identifier.doi10.29137/umagd.1213570
dc.identifier.issn1308-5514
dc.identifier.issue2-371
dc.identifier.startpage377
dc.identifier.urihttps://dergipark.org.tr/tr/download/article-file/2808593
dc.identifier.urihttps://dergipark.org.tr/tr/pub/umagd/issue/76084/1213570
dc.identifier.urihttps://doi.org/10.29137/umagd.1213570
dc.identifier.urihttps://hdl.handle.net/20.500.12587/20197
dc.identifier.volume1
dc.language.isotr
dc.publisherKırıkkale Üniversitesi
dc.relation.ispartofUluslararası Mühendislik Araştırma ve Geliştirme Dergisi
dc.relation.publicationcategoryMakale - Ulusal Hakemli Dergi
dc.rightsinfo:eu-repo/semantics/openAccess
dc.snmzKA_20241229
dc.subjectKatı roket yakıtı
dc.subjectKompozit roket yakıtı
dc.subjectYanma hızı
dc.subjectYanma ısısı
dc.subjectStrand burner
dc.subjectSolid rocket propellant
dc.subjectcomposite rocket propellant
dc.subjectburning rate
dc.subjectcombustion heat
dc.subjectstrand burner
dc.subjectKatı roket yakıtı
dc.subjectKompozit roket yakıtı
dc.subjectYanma hızı
dc.subjectYanma ısısı
dc.subjectStrand burner
dc.subjectMaterials Engineering (Other)
dc.titleKompozit Roket Yakıtının Yanma Hızı Üzerine Ortam Basıncının ve Başlangıç Sıcaklığının Etkileri
dc.title.alternativeEffects of Ambient Pressure and Initial Temperature on the Burning Rate of Composite Rocket Propellant
dc.typeArticle

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