The study carried out in this article presents a numerical modelling of an aircraft brake system. This model is used to perform the identification of the preponderant thermal parameters in an aircraft brake during its braking phase and then during its cooling phase. Using this appropriate thermal model and temperature measurements on a dedicated test bench, the thermal parameters of the different braking phases are identified. During the braking phase, the generated heat flux by friction are estimated based on a temporal parameterization. This allows to find the evolution of the heat flux and thus to have the control of the temperatures in the system at the end of this short stage. The temperature field calculated using the parameters identified during this phase is consistent with the measurements taken on the experimental setup. Moreover, the identification of the thermal energy by inverse method corresponds to the measurement carried out with the bench of the degraded mechanical energy, which validates the results. After this braking phase, the hot brake is cooled down causing a heat transfer in the whole wheel. This phase is much longer than the first one. The different transfer mechanisms are then studied in order to determine precisely the evolution of the temperatures. During the cooling process, the emissivities and the different contact resistances play an important role in the thermal behavior of the brake and the wheel. The identification of these parameters allows to find the temperature evolutions measured on the test bench. The values identified are physically consistent. These results are corroborated by a numerical study to determine the confidence interval of the identified parameters as a function of the measurement noise.