Effects of Ambient Pressure and Initial Temperature on the Burning Rate of Composite Rocket Propellant

Salih Uğur Bayça; Murat Demir

Makale detayları

Effects of Ambient Pressure and Initial Temperature on the Burning Rate of Composite Rocket Propellant

Yazarlar:

Salih Uğur Bayça | Murat Demir

Yayıncı:

Kirikkale University

Ana Başlıklar:

Materials Engineering (Other)

Dergi:

International Journal of Engineering Research and Development Vol.15 Issue 2, pp.371-377

Belge Tipi:

Makale

Yayın Tarihi:

7/2023

Belge Dili:

Türkçe

Document ID (Org No.):

2001284754

pISSN:

1308-5506

Anahtar kelimeler:

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.

 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.

Makale detayları

Effects of Ambient Pressure and Initial Temperature on the Burning Rate of Composite Rocket Propellant

Yazarlar:

Salih Uğur Bayça | Murat Demir

Yayıncı:

Kirikkale University

Ana Başlıklar:

Materials Engineering (Other)

Dergi:

International Journal of Engineering Research and Development Vol.15 Issue 2, pp.371-377

Belge Tipi:

Makale

Yayın Tarihi:

7/2023

Belge Dili:

Türkçe

Document ID (Org No.):

2001284754

pISSN:

1308-5506

Solid rocket propellant

composite rocket propellant

burning rate

combustion heat

strand burner

Katı roket yakıtı

Kompozit roket yakıtı

Yanma hızı

Yanma ısısı

Strand burner

Katı roket yakıtı

Kompozit roket yakıtı

Yanma hızı

Yanma ısısı

Strand burner

Sayı

Makale detayları

Yazarlar: Salih Uğur Bayça | Murat Demir

Yayıncı: Kirikkale University

Ana Başlıklar: Materials Engineering (Other)

Dergi: International Journal of Engineering Research and Development Vol.15 Issue 2, pp.371-377

Belge Tipi: Makale

Yayın Tarihi: 7/2023

Belge Dili: Türkçe

Document ID (Org No.): 2001284754

pISSN: 1308-5506

Sayı

Yazarlar:

Salih Uğur Bayça | Murat Demir

Yayıncı:

Kirikkale University

Ana Başlıklar:

Materials Engineering (Other)

Dergi:

International Journal of Engineering Research and Development Vol.15 Issue 2, pp.371-377

Belge Tipi:

Makale

Yayın Tarihi:

7/2023

Belge Dili:

Türkçe

Document ID (Org No.):

2001284754

pISSN:

1308-5506