摘要
航空复合材料层合板结构在制造和使用过程中,容易产生分层损伤。分层损伤的存在会显著降低结构强度、刚度和稳定性,致使结构提前发生失稳和整体破坏。因此,需要探究分层损伤对复合材料层合板结构力学性能的影响。航空结构易分层部位如何选材亟待解决,分层深度对复合材料结构力学性能影响分析有待完善。为此,针对单分层损伤和冲击损伤(梯度分层损伤),选择4种碳纤维增强环氧树脂基复合材料,开展准静态压缩、低速冲击和冲击后压缩试验,对比含分层损伤4种复合材料层合板结构的压缩剩余强度;结合有限元仿真,探究分层深度对复合材料层合板结构压缩性能的影响趋势,并对产生这一趋势的原因进行分析。研究结果表明,相比于单向预浸料,航空结构在易分层部位选择高强度的织物预浸料会带来更好的效果,压缩剩余强度最大可提高118.31%,分层深度的差异将导致复合材料层合板的承载能力由不同子板的失效行为主导。研究结果深入讨论了分层损伤对航空复合材料层合板结构压缩性能的影响,为航空复合材料结构损伤容限设计提供了研究依据。
Aircraft composite laminates are susceptible to delamination damage throughout their lifecycle,from manu-facturing to in-service operation.The existence of delamination damage results in a significant degradation in structural strength,stiffness,and stability,which can induce early instability and precipitate global failure.Therefore,it is neces-sary to explore the influence of delamination damage on the mechanical properties of composite laminates.Address-ing the material selection for delamination-critical regions in aircraft structures is an imperative research objective.Fur-ther analysis is warranted to understand how delamination depth affects the mechanical behavior of composite struc-tures.Therefore,four kinds of carbon fiber reinforced epoxy resin matrix composites were selected for single delami-nation damage and impact damage(gradient delamination damage).Quasi-static compression,low-velocity impact and compression after impact tests were carried out to compare the compressive residual strength of four composite laminates with delamination damage.Combined with finite element simulation,the influence trend of delamination depth on the compression performance of composite laminates is explored,and the reason for this trend is analyzed.The results show that compared with the unidirectional prepreg,the selection of high strength fabric prepreg in delamination-critical regions of the aircraft structure will bring better results,and the maximum compressive residual strength can be increased by 118.31%.Additionally,different delamination depths will lead to the bearing capacity of composite laminates determined by different sub-plates.The influence of delamination damage on the compressive properties of aircraft composite laminates has been discussed in depth,which provides a research basis for the dam-age tolerance design of aircraft composite structures.
作者
刘子昂
郑锡涛
陈英实
邓天择
马伟杰
LIU Ziang;ZHENG Xitao;CHEN Yingshi;DENG Tianze;MA Weijie(School of Aeronautics,Northwestern Polytechnical University,Xi'an710072,China;National Key Laboratory of Strength and Structural Integrity,Xi'an 710072,China;Aviation Key Lab of Science and Technology on High Performance Electromagnetic Windows,AviC Research Institute for Special Structures of Aeronautical Composite,Jinan 25o023,China)
出处
《航空学报》
北大核心
2025年第21期285-302,共18页
Acta Aeronautica et Astronautica Sinica
基金
国家重点研发计划(2023YFB3709603)
航空科学基金(ASFC-20230015053005)。
关键词
航空复材结构
层合板
分层损伤
压缩性能
分层深度
aircraft composite structures
laminates
delamination damage
compressive properties
delamination depth
