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 coustrains. The optimal geometry parameters of the multilayer structures are obtained.%大面积防热结构在航天航空领域应用广泛,其创新结构设计是关键技术之一.航天飞行器的工作条件要求热防护材料与结构同时具备轻质、隔热、抗冲击的特点,因此热防护材料与结构正在朝着一体化的方向发展.基于这种发展趋势,提出了一种轻质多层热防护结构设计方案.以一体化多层防热结构在航天器再入过程中的传热为研究对象,引入大面积防热结构的一维传热假设,依照航天器再入大气层的温度条件,建立了防热结构一维非稳态传热的物理模型和封闭的控制方程,使用差分方法求解方程,进行一维非稳态的传热分析,并采用商业有限元软件ABAQUS的传热分析进行验证.得到了航天器再入大气过程中多层防热结构的各层温度分布,提出了在满足一定的热约束要求的条件下,以轻质多层热防护结构的总重量为目标函数的优化设计方法,得到了多层结构的最优几何参数,并将优化后的结构进行了有限元承载分析.
展开▼
