摘要
为了研究由C/C-SiC功能梯度材料组成的飞行器前锥在气动载荷作用下的损伤演化过程以及不同的材料分布方式对飞行器结构损伤演化性能的影响,建立了功能梯度材料的弹性损伤本构关系.基于有限元软件ABAQUS的二次开发,将功能梯度材料的损伤本构关系引入飞行器结构性能的数值分析过程中.研究结果表明:气动载荷下的结构损伤演化经历了一个快速上升然后逐渐稳定的过程,损伤演化的速率与结构温度场变化速率密切相关;飞行器前锥前端的损伤演化很快达到稳定,但由于前端材料热导率低且温度梯度较大,热应力和热应变较高,其损伤程度最严重;功能梯度材料指数分布函数参数变化时,飞行器前锥结构损伤演化趋势不受其影响,但损伤值随着参数的增加而减小.
In order to analyze the damage evolution of the aircraft head made of functionally graded materials （FGM） with C/C-SiC in service process under aerodynamic loading and the effect of C/C-SiC distribution in FGM on structural damage evolution, an elastic damage model of FGM was developed and implemented in the numerical analysis of FGM structural damage based on the user subroutine incorporated into the computations software ABAQUS. The results show that the process of damage evolution has a rapid rise and then keeps stable; and the stability of the evolving rate de- pends on the change rate of the temperature. On the surface region, the evolving rate of damage rea- ches to stable condition rapidly and the damage value is much larger than that of inner region of the aircraft because of the larger temperature gradient and the lower thermal conductivity of the material on the surface region, which leads to large thermal stress and thermal strain. The change of the coef- ficient of the distributed gradient exponential function has no effect on the damage evolutionary trend, while the value of the structural damage decreases with the increase of the coefficient.
出处
《东南大学学报（自然科学版）》
EI
CAS
CSCD
北大核心
2013年第1期169-173,共5页
Journal of Southeast University：Natural Science Edition
基金
国家自然科学基金资助项目(11072060)
关键词
损伤
气动载荷
功能梯度材料
用户接口
damage
aerodynamic loads
functionally graded materials
user interfaces
