摘要
针对空天飞机热防护系统与机体的连接结构进行结构热载与强度计算,依据典型的金属蜂窝面板隔热结构形式建立连接结构的三维精细有限元模型,详细分析连接区的热边界条件,包括连接件和被连接复合材料蒙皮的对流换热边界与接触传热边界;以再入过程中空天飞机表面气动加热为输入计算连接区的温度场分布,分析由温度所引起的结构热应力;结合复合材料损伤累积算法和准静态完全热力耦合分析技术,计算连接结构中复合材料蒙皮的挤压强度。结果表明热应力的存在可以提高连接初始损伤强度,但由于改变了最终损伤模式,会导致极限强度的降低。
This Paper analyzes the thermal load and strength of a connecting structure in the aerospace plane＇s thermal protection system. A three-dimensional finite element model of connecting structure is established based on,a typical metal honeycomb panel thermal protection structure. The convective heat transfer boundary and contact heat transfer boundary in the FEM model is also studied in detail. Furthermore, in this paper, it analyzes the temperature distribution of the connecting area under the action of aerodynamic heating in the space plane＇s reentry process, and the thermal stress caused by the temperature. Finally, a thermo-mechanical coupled analysis for the connection structure strength degradation is conducted. The results show that the presence of the thermal stress can increase the initial connecting strength, but reduce ultimate connecting strength due to the changes of the final damage patterns.
出处
《导弹与航天运载技术》
北大核心
2012年第6期1-4,9,共5页
Missiles and Space Vehicles
关键词
空天飞机
热防护
热载
强度
Space plane
Thermal protection
Thermal load
Strength
