Bayça, Salih UğurDemir, Murat2025-01-212025-01-2120231308-5514https://dergipark.org.tr/tr/download/article-file/2808593https://dergipark.org.tr/tr/pub/umagd/issue/76084/1213570https://doi.org/10.29137/umagd.1213570https://hdl.handle.net/20.500.12587/20197Rocket 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.trinfo:eu-repo/semantics/openAccessKatı roket yakıtıKompozit roket yakıtıYanma hızıYanma ısısıStrand burnerSolid rocket propellantcomposite rocket propellantburning ratecombustion heatstrand burnerKatı roket yakıtıKompozit roket yakıtıYanma hızıYanma ısısıStrand burnerMaterials Engineering (Other)Article12-37137710.29137/umagd.12135701213570