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A suitable method for calculating theoretical energetic performances of a composite propellant was investigated and successfully verified. This method is based on generally accepted hypotheses, consistent and simple calculation of the chemical equilibrium in a predominantly gaseous, multi-component reactive mixture, and on an appropriate numerical scheme involving the propellant formula and the assigned rocket motor operating conditions. Acomputer program, which permits the calculation of the equilibrium composition of the combustion products and the theoretical energetic performances of composite propellants has been developed. The results of the calculations have been compared with data obtained by the programs OPHELIE, MICROPEP, and the program SPP, as documented in the NASA-Lewis Code, which is presently a world-wide standard. All comparisons gave satisfactory agreement.