C/SiC复合材料轴套渐进损伤分析

Progressive damage analysis of C/SiC composite shaft sleeve

以C/SiC为代表的陶瓷基复合材料以其优异的耐热、承载性能以及轻质特性,已成为先进飞行器关键承载部件设计选用的主要材料。基于实体型复合材料结构非线性强度失效模型及渐进损伤分析方法,采用ABAQUS软件对复杂受力情况下C/SiC陶瓷基复合材料副翼轴套的结构强度进行了预示,考核了某型号飞行器副翼关键部位在飞行力、热载荷作用下的承载能力,模拟了其在复杂受力情形下的渐进损伤过程。并开展相关地面试验,通过对试验与数值结果的对比分析,验证了数值分析方法的准确性和可行性。

Ceramic matrix composites with the represent of C/SiC have been used as the predominant materials in the design of key load bearing components of advanced flight vehicles because of their excellent heat resistance, bearing capability and lightweight property. Based upon nonlinear strength failure model and progressive damage analysis method of bulk composites, this paper presents the structural strength prediction of C/SiC ceramic-matrix composite shaft sleeve under complicated mechanical environment by using the software of ABAQUS. The carrying capacity of the key part of aileron for vehicle under the combined action of flight force load thermal load is assessed, and the corresponding progressive damage process is simulated. In addition, related ground test is carried out. Numerical simulation and test verification indicate that the numerical method is accurate and feasible.