The invention relates to a thermal protection system optimization design method and module based on an agent model, and the method comprises the steps: carrying out the finite element analysis on thebasis of a small sample, carrying out the fitting of a response surface model, carrying out the large optimization analysis on the response surface model, greatly reducing the calculation amount, andimproving the efficiency. Meanwhile, a linear constant differential equation set of the thermal protection analysis model is solved by adopting a time integration method, so that the resolving time issaved; According to the invention, geometric dimensions are also considered; A thermal analysis model is established under the influence of a plurality of optimization variables of the density, the specific heat capacity, the heat conductivity and the surface radiance of the thermal protection system on thermal protection, so that the thermal protection system optimization design has higher precision, and a more scientific and accurate basis is provided for the thermal protection system design of the hypersonic flight vehicle; In addition, the method effectively reduces the design allowance of the thermal protection system, reduces the weight of the thermal protection system and reduces the power consumption of the aircraft.