摘要
对约束开裂复合材料层板给出随裂纹密度变化的刚度衰减公式。构造了裂纹密度与损伤区应力的关系函数,借助这一函数可由损伤区应力直接预测其刚度衰减。引入两次转轴变换方法,将刚度衰减公式由90°基体开裂推广到应用于±θ层的基体开裂。
Stiffness degradation formulas are given for a composite laminate with constrained cracking.Because the formulas are expressed as a function ofcrack density,the relation between crack density and stresses in the damage zone is constructed so as to predict the stiffness degrada- tion directly from the stress distribution in damage zone. The generalization of the stiffness deg- radation formulas is made for any angle-plied lamina by rotating the coordinate axes twice.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1994年第3期303-309,共7页
Acta Aeronautica et Astronautica Sinica
基金
航空科学基金
关键词
复合材料层板
裂纹密度
斜交铺层
composite laminate,matrix cracking, crack density,stiffness degradation,angle-plied lamina