Factors Affecting Burning Rate of Hydroxy Terminated Polybutadiene Propellant
Osman, A., Abuuznien, M., Abdallah, B. (2013). Factors Affecting Burning Rate of Hydroxy Terminated Polybutadiene Propellant. EKB Journal Management System, 15(AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 15 – May 28 - 30, 2013), 1-7. doi: 10.21608/asat.2013.22049
A. A. E. Osman; M. H. M. Abuuznien; B. K. Abdallah. "Factors Affecting Burning Rate of Hydroxy Terminated Polybutadiene Propellant". EKB Journal Management System, 15, AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 15 – May 28 - 30, 2013, 2013, 1-7. doi: 10.21608/asat.2013.22049
Osman, A., Abuuznien, M., Abdallah, B. (2013). 'Factors Affecting Burning Rate of Hydroxy Terminated Polybutadiene Propellant', EKB Journal Management System, 15(AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 15 – May 28 - 30, 2013), pp. 1-7. doi: 10.21608/asat.2013.22049
Osman, A., Abuuznien, M., Abdallah, B. Factors Affecting Burning Rate of Hydroxy Terminated Polybutadiene Propellant. EKB Journal Management System, 2013; 15(AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 15 – May 28 - 30, 2013): 1-7. doi: 10.21608/asat.2013.22049

Factors Affecting Burning Rate of Hydroxy Terminated Polybutadiene Propellant

International Conference on Aerospace Sciences and Aviation Technology
Article 18, Volume 15, AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 15 – May 28 - 30, 2013, May 2013, Page 1-7  XML PDF (224.74 K)
Document Type: Original Article
DOI: 10.21608/asat.2013.22049
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Authors
A. A. E. Osman1; M. H. M. Abuuznien2; B. K. Abdallah3
1Lecturer, Chemical Engineering Dep., Karary University, Sudan.
2Associate Professor, Head of Dep. of Chemical Engineering, Karary University, Sudan.
3Associate Professor, Chemical Engineering Dep., Karary University, Sudan.
Abstract
Burning rate is one of the most important characteristics of rocket propellants and it is affected by many factors including composition, pressure, initial temperature, oxidizer particles size and burning rate modifier. This research aims to study experimentally the effects of combustion chamber pressure, initial temperature and particles size of the oxidizer material
on the burning rate of solid composite propellant. Besides, study theoretically the effect of composition and catalyst used. In addition, this research aims to show the relationship between these factors and the burning rate in order to evaluate factor that is more effective on burning rate, so to calculate of burning rate as a function of this factor. Accordingly, this
could be used to achieve ballistics characteristics required for rocket motor design and performance.
Keywords
Composite Propellant; Burning rate
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