Abstract: The constant pressure combustion temperature is an important parameter for characterizing the energy and combustion characteristics of solid propellant. In order to solve the problem that the material change and phase change cannot be integrated when the temperature span is large in the quantitative calculation of the positive correlation between combustion heat and combustion temperature of solid propellant, and to avoid the problem that the composition of combustion products in the low temperature range and the constant pressure heat capacity （C_p(T)）cannot be determined by the minimum free energy method, the quantitative characterization is carried out according to the positive correlation between the constant pressure explosion heat and the constant pressure combustion temperature of the propellant, and the basic relationship of the calorimetric temperature measurement is established. The constant pressure combustion temperature can be obtained by testing the constant pressure explosion heat of the propellant. The constant pressure combustion temperature and combustion efficiency of SQ-2 propellant and HTPB-R propellant were tested by the calorimetry, and the constant pressure combustion temperature of SQ-2 propellant was measured by the thermocouple method. The comparative results show that the calorimetry can accurately test the constant pressure combustion temperature of propellant. From the point of view of combustion efficiency, the results of calorimetry are consistent with the existing law that the combustion efficiency of aluminum-containing composite propellants is lower than that of double-base propellants, and the test results exhibit better consistency than the thermocouple method.