针对直升机桨叶受离心力、挥舞和摆振弯曲、扭矩等载荷特性,采用非线性桨叶结构模型,推导了复合材料桨叶蒙皮的广义二维位移方程.在此基础上,基于Stroh理论,应用各向异性界面断裂力学给出桨叶蒙皮大梁粘结面分层裂纹端部的应力与位移通解的渐近表达式.联合其特解,采用边界配置法计算了离心力作用下桨叶蒙皮与大梁之间存在分层裂纹时裂尖的奇异应力及应力强度因子,与采用界面元法计算的结果接近,表明本文方法可有效地分析复合材料桨叶蒙皮大梁问的分层破坏,为研究桨叶分层失效提供依据.
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