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.