摘要
针对飞机复合材料加筋层压板结构，设计了含有预埋分层缺陷的复合材料加筋层压板的典型试验件以及压缩试验装置，研究了分层缺陷位置和大小对加筋板压缩强度的影响。研究结果表明：分层缺陷会改变加筋板的破坏模式，浅表分层在压缩过程中表现为局部屈曲模态，局部屈曲强度只有其破坏强度的30％～60％，分层直径增加，局部屈曲强度降低。局部屈曲发生后，加筋板尚可进一步承载，直至层板失稳破坏。本文给出的数据和结论对实际飞机结构设计的参数确定和生产过程中的超差问题处理具有重要参考价值。
An experimental investigation of effects of delamination deficiencies on compressive strength of composite reinforced laminates was conducted. The typical specimens of composite reinforced laminate structures with embedded delamination deficiencies, as well as the compression test device, were designed. The effects of delamination position and size on the compressive strength of composite reinforced laminates were investigated in the test. The test results indicate that delamination deficiencies would change the failure mode of composite reinforced laminates; the shallow delamination behaves as a local buckling mode in the compression process; the local buckling strength is approximately 30% ～ 60% of the failure strength of the reinforced laminates; and the local buckling strength would be reduced as the delamination diameter increases. After local buckling occurs, the composite reinforced laminates can still further bear compressive loads until they are buckling ruptured. The data and conclusion given in the paper provide important reference values for future aircraft structure design and outof-tolerance problem disposal.
出处
《飞机设计》
2006年第2期16-20,共5页
Aircraft Design
关键词
复合材料层压板
分层
缺陷
压缩强度
composite laminate
delamination
flaw
compressive strength
