随着我国航空事业的发展,飞行器设计中已愈来愈多地采用先进的碳/环氧复合材料结构。挤压破坏是复合材料机械连接的主要破坏形式。分析其破坏过程,确定出挤压强度,对解决复合材料连接设计问题是非常重要的。 实践表明,测定复合材料构件所能承受的最大挤压应力较易进行,一般均能获得所需结果。但对设计人员来说,更加关心的是许用挤压应力。金属材料许用挤压应力通常是由屈服应力决定的。对于不存在“屈服”点的碳/环氧复合材料确定许用挤压应力,目 With the development of aviation in our country, more and more advanced carbon / epoxy composite structures have been adopted in aircraft design. Extrusion failure is the main form of mechanical damage to composite materials. Analysis of its destruction process, to determine the extrusion strength, to solve the design of composite connections is very important. Practice has shown that the determination of maximum compressive stress that composite components can withstand is easier to perform and generally achieve the desired results. However, designers are more concerned with the use of compressive stress. Metallic material allowable compressive stress is usually determined by yield stress. For the absence of “yield” point carbon / epoxy composites to determine allowable compressive stress, head