Integrated optimization design of light-weight multilayer thermal protection structures

The large-area thermal protection structure is widely used in aerial and aerospace fields, in which creative structural design is one of the key technologies. The work conditions of the aerospace structures demand the thermal protection materials and structures should have combined features of light-weight, high thermal resistance and anti-collision stiffness. Thus the thermal protection materials and structures are in the trend of integration. Based on this trend, this paper brings forward a design of the light-weight integrated multilayer thermal protection structures. The heat transfer of integrated multilayer thermal protection structures during the re-entry process of space shuttle is investigated. Based on the assumption of one dimension heat transfer of the large-area thermal protection structures and the temperature conditions of the re-entry process for space shuttle, one-dimension transient heat transfer model and closed equations are established. A numerical difference method is used to solve the equations, and finite element analysis using the commercial software ABAQUS is carried out to identify the validity of the difference method. The temperature distribution of multilayer thermal protection structures is obtained. The integrated optimization design method of light-weight multilayer thermal protection structures is presented aiming at the lightest weight of the structures under given certain thermal constrains. The optimal geometry parameters of the multilayer structures are obtained.