THEORETICAL AND PRACTICAL EVALUATION OF BURNING RATE OF DOUBLE BASE ROCKET PROPELLANTS | ||||
| International Conference on Aerospace Sciences and Aviation Technology | ||||
| Article 11, Volume 5, ASAT CONFERENCE 4 - 6 May 1993, CAIRO, May 1993, Page 123-132 PDF (1.35 MB) | ||||
| Document Type: Original Article | ||||
| DOI: 10.21608/asat.1993.25613 | ||||
 View on SCiNiTO | ||||
| Author | ||||
| M. A. SADEK | ||||
| Chemical engineering branch, M.T.C., Cairo, EGYPT. | ||||
| Abstract | ||||
| Homogeneous propellants are still often used in small-to medium-sized rockets because of their smokeless qualities and the possibilities they offer of particular shapes and small burning thickness through rolling and extruding process. The study of burning rate characteristics is an important factor limiting the practical application of these propellants. In this work, the burning rate characteristics of a homogeneous double base propellant containing nitrocellulose, nitroglycerine, dinitrotoluene, centralite, dibutyl phthalate,calcium carbonate and vasiline as ingredients are determined experimentally and discussed. The nature of the burning rate is explained by the physical and chemical properties of the propellant. A simplified gas-phase model is used to evaluate the burning rate characteristics using a computer program. The obtained results were compared to those practically determined. | ||||
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