The aim of this paper is designing a decision-making system (DMS) for temperature management of the satellite plates in the presence of actuators faults. The thermal stresses caused by solar radiation pressure perturbations is considered as a threat to the mission of satellites. In this paper, a new mechanism is used, which includes 4 fluidic momentum controller (FMC) actuators for sustaining the situation and performing various satellite missions in a pyramid. In this case, it is assumed that the satellite's plates are exposed to solar perturbations, and as a result, various faults have occurred for satellite actuators. To detect and isolate the defect of each actuator, recordable data from satellite and actuators are stored and feature extraction of these data is executed by linear differentiation analysis methods and analysis of the main components. To evaluate these methods, the confidence matrix is used, and the K-nearest neighborhood method is selected as the optimal method. To solve the temperature problem of the plates, the DMS is designed, so that if one of the plates reaches critical temperature, after examining the occurrence of a fault and adopting the appropriate strategy, the plate's rotation of the target plate is in the shadow. As a result, the temperature of the plate with the maximum temperature will reduce. The simulation results show that despite the perturbations and actuators’ faults, the designed DMS can manage the temperature of the plates somehow that does not enter the critical point.