Performance, mechanical and thermal properties of double base rocket propellant including copper oxide as burning rate modifier
Abdel-Ghani, N., Elbeih, A., Helal, F., Hammad, S. (2019). Performance, mechanical and thermal properties of double base rocket propellant including copper oxide as burning rate modifier. EKB Journal Management System, 18(18), 1-6. doi: 10.1088/1757-899X/610/1/012036
Nour Abdel-Ghani; Ahmed Elbeih; Farag Helal; Sara M. Hammad. "Performance, mechanical and thermal properties of double base rocket propellant including copper oxide as burning rate modifier". EKB Journal Management System, 18, 18, 2019, 1-6. doi: 10.1088/1757-899X/610/1/012036
Abdel-Ghani, N., Elbeih, A., Helal, F., Hammad, S. (2019). 'Performance, mechanical and thermal properties of double base rocket propellant including copper oxide as burning rate modifier', EKB Journal Management System, 18(18), pp. 1-6. doi: 10.1088/1757-899X/610/1/012036
Abdel-Ghani, N., Elbeih, A., Helal, F., Hammad, S. Performance, mechanical and thermal properties of double base rocket propellant including copper oxide as burning rate modifier. EKB Journal Management System, 2019; 18(18): 1-6. doi: 10.1088/1757-899X/610/1/012036

Performance, mechanical and thermal properties of double base rocket propellant including copper oxide as burning rate modifier

International Conference on Aerospace Sciences and Aviation Technology
Article 38, Volume 18, Issue 18, April 2019, Page 1-6  XML PDF (565.7 K)
Document Type: Original Article
DOI: 10.1088/1757-899X/610/1/012036
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Authors
Nour Abdel-Ghani1; Ahmed Elbeih2; Farag Helal3; Sara M. Hammad4
1Department of Chemistry, Faculty of Science, Cairo University, Giza, Egypt.
2Military Technical College, Kobry Elkobbah, Cairo, Egypt.
3Science and Technology Center of Excellence (STCE), El- Salam City, Cairo, Egypt.
4Faculty of Pharmacy, Cairo University, Giza, Egypt.
Abstract
In this work, different percentages of Copper oxide have been added to double base rocket propellant (DBRP) as burning rate modifier. A conventional DBRP has been prepared and studied for comparison. The mechanical properties at different temperatures were studied. The heat of combustion and ignition temperature of the samples were measured. The performance represented by the operating pressure and the burning rate were evaluated at 8mm throat diameters. The thermal behavior of the traditional DBRP in comparison with a selected composition containing copper oxide was discussed. It was concluded that the addition of copper oxide in DBRP has positive effect on the mechanical properties of the traditional DBRP while slight increase in the performance properties was observed.
Keywords
solid rocket propellant; copper oxide; performance; mechanical properties
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