飞机复合材料层压板结构中的广义强度准则

通过对经典复合材料结构强度理论和准则在层压板上的适用性计算和试验对比研究，指出了在层压板上采用经典强度理论所得计算结果与试验结果的差异。并分析了产生这种差异的原因，主要是经典强度准则表达武中采用的无拉剪耦合假设和层与层之间理想粘接假设，只适用于单层板或正交各向异性板。本文提出了一种广义强度准则的思想，其核心是放松正交各向异性约束条件和通过试验测定强度参数，而在实际飞机结构中的准正交各向异性层压板结构设计上仍可使用经典层压板强度准则。

General strength criterion in composite laminated structures of aircraft

The classical structural strength criterions of composite and their applicability on laminates were studied by both calculation and experiment. The results appeared great differences. The main reason came from the assumptions of non-tension-shear coupling whose is correct only for lamina and orthotropic laminates, and realistic bond between layers. In this paper, the general strength criterion was put forward, whose main idea is the application of classical laminated theory on quasi-orthotropic laminates in practical aircraft structural design by releasing orthotropic restriction conditions and measuring strength parameters experimentally.