飞机结构用复合材料的力学性能要求

Property Requirements of Composite Systems Applicable to Aircraft Structures

本文从飞机结构完整性要求出发提出了对聚合物基复合材料性能的具体要求,特别是在湿热和抗冲击性能方面的要求。为了降低全尺寸结构静强度验证中对湿热环境影响考虑的技术难度,建议提高对湿态玻璃化转变温度的要求;为了满足含冲击损伤(通常用一定深度的凹坑来描述)结构的剩余强度要求,适用于飞机主结构的复合材料体系应当是用静压痕试验得到易于产生表面凹坑同时损伤面积较小的材料体系。

The special requirements of polymer matrix composite systems applicable to aircraft structures are proposed according to aircraft structural integrity requirements,particularly for hydrothermal properties and capabilities to withstand impact.In order to reduce the degree of difficulty of static strength verification test of full-scale structures,it is suggested to increase glass transition temperature of epoxy matrix composite systems.In order to meet the residual strength requirement of structures with impact damage,the composite materials suitable to the primary structures are the materials for which barely visible surface dent with smaller damage area should be introduced easily.