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

Document Type : Original Article

Authors

1 Department of Chemistry, Faculty of Science, Cairo University, Giza, Egypt.

2 Military Technical College, Kobry Elkobbah, Cairo, Egypt.

3 Science and Technology Center of Excellence (STCE), El- Salam City, Cairo, Egypt.

4 Faculty of Pharmacy, Cairo University, Giza, Egypt.

10.1088/1757-899X/610/1/012036

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

International Conference on Aerospace Sciences and Aviation Technology
Volume 18, Issue 18
18th International Conference on Aerospace Sciences & Aviation Technology 9–11 April 2019
April 2019
Pages 1-6

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