摘要
在实际工程应用中,复合材料蜂窝夹层结构的破坏模式受工艺水平及初始缺陷影响较大,但具体影响程度目前尚无明确量化依据。通过开展含不同形状与尺寸缺陷的样件试验,研究了夹层黏接缺陷和面板分层缺陷等典型缺陷对结构承载能力的影响规律。结果表明,相较于分层缺陷位置和形状,分层面积是碳面板强度折减的主导因素;对于夹层结构,随着黏接缺陷面积的增加,其侧压强度与刚度均呈现下降趋势,且下降幅度不受缺陷形状影响。同时,基于试验数据分析结果,给出了蜂窝夹层结构分层与脱黏缺陷许用值,为大承载蜂窝夹层结构的设计、分析和工艺控制提供了重要方法依据。
In practical engineering applications,the failure modes of composite honeycomb sandwich structures are significantly influenced by manufacturing process quality and initial defects.However,quantitative correlations between defect characteristics and structural performance degradation remain inadequately established.This study investigates the effects of typical defects including core-face sheet bonding imperfections and face sheet delamination on the load-bearing capacity through systematic testing of specimens with intentionally introduced defects of varying geometries and dimensions.Key findings reveal that:for carbon fiber face sheets,the delamination area rather than defect location or shape serves as the dominant factor governing strength reduction.In honeycomb sandwich structures,both compressive strength and stiffness exhibit progressive degradation with increasing bonding defect area,with negligible dependence on defect geometry.Building upon experimental data analysis,this work proposes allowable defect thresholds for delamination and debonding in conventional honeycomb sandwich configurations. These empirically validated criteria provide a critical methodological foundation for the design, analysis, and process control of high-load-capacity honeycomb sandwich structures in aerospace applications.
作者
张昊
闫伟
王康康
骆洪志
陈友伟
ZHANG Hao;YAN Wei;WANG Kangkang;LUO Hongzhi;CHEN Youwei(Beijing Institute of Astronautical Systems Engineering,Beijing 100076,China)
出处
《宇航总体技术》
2025年第6期75-82,共8页
Astronautical Systems Engineering Technology
基金
国家部委专用技术科研项目(305060508)。
关键词
夹层结构
复合材料
缺陷
Sandwich structure
Composite
Defects
