Kompozit Roket Yakıtının Yanma Hızı Üzerine Ortam Basıncının ve Başlangıç Sıcaklığının Etkileri
[ X ]
Tarih
2023
Yazarlar
Dergi Başlığı
Dergi ISSN
Cilt Başlığı
Yayıncı
Kırıkkale Üniversitesi
Erişim Hakkı
info:eu-repo/semantics/openAccess
Özet
Rocket 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.
Rocket 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.
Rocket 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.
Açıklama
Anahtar Kelimeler
Katı roket yakıtı, Kompozit roket yakıtı, Yanma hızı, Yanma ısısı, Strand burner, Solid rocket propellant, composite rocket propellant, burning rate, combustion heat, strand burner, Katı roket yakıtı, Kompozit roket yakıtı, Yanma hızı, Yanma ısısı, Strand burner, Materials Engineering (Other)
Kaynak
Uluslararası Mühendislik Araştırma ve Geliştirme Dergisi
WoS Q Değeri
Scopus Q Değeri
Cilt
1
Sayı
2-371
