摘要
为了研究不同修补方式和修补参数对平纹编织面板泡沫夹芯结构侧向压缩性能的影响,对完好试验件和单侧面板修补、单侧面板加芯材修补、双侧面板加芯材修补试验件进行侧向压缩试验。试验结果表明:单侧面板修补方式的侧向压缩强度高于其他两种修补方式;单侧面板修补时,面板挖补倾角比例越小,试验件侧向压缩强度越低;附加层重叠宽度对试验件侧向压缩强度影响很大;修补后试验件的侧向压缩模量比完好件均有所提升;单侧面板修补时,改变挖补倾角比例,不影响试验件侧向压缩模量,合适的附加层重叠宽度对试验件侧向压缩模量的提高有积极影响;修补方式和修补参数的变化不影响试验件的破坏模式,平纹编织面板泡沫夹芯复合材料侧向压缩的破坏模式为泡沫芯材破裂后,面板局部无支撑受压弯曲导致的整体结构破坏;面板的破坏形式主要为面板端部弯曲、面板中部弯曲、面板皱折和面板纤维断裂。
In order to study the influence of different repair methods and repair parameters on the edgeside com-pression performance of plain woven panel foam sandwich structure,the edgeside compression test was carried out on the specimen and the repaired specimen.By comparing the test results,the effects of repair methods and repair parameters on the edgeside compression strength and edgeside compression modulus of the plain sandwich woven panel foam sandwich structure are analyzed.The specimen destruction mode is also analyzed in the article.The results show that the edgeside compression strength of single-sided panel repair is higher than that of double-sided panel repair and single-sided panel plus core repair.When single-sided panel repair,the smaller scarf repair angle of the laminate,the lower the edgeside compression strength of the specimen.The overlap width of the overply has a great influence on the edgeside compression strength of the specimen.After the repair,the edgeside compression modulus of the specimen is improved compared with the intact specimen.When the single-sided panel is repaired,changing the proportion of the scarf repair angle does not affect the edgeside of the specimen compression modulus,and suitable overply overlap width has a positive effect on the increase of the edgeside compression modulus of the specimen.Changes in repair methods and repair parameters do not affect the failure mode of the specimen,the edgeside compression of plain-weave panel foam sandwich composites mainly failed after the foam core material rup-tured,and the overall structure of the panel without core material support was compressed.The failure modes of the panel are mainly the bending of the end of the panel,the bending of the middle of the panel,the wrinkling of the panel and the fiber breakage of the panel.
作者
张铁纯
张世秋
王轩
周春苹
王付胜
ZHANG Tie-chun;ZHANG Shi-qiu;WANG Xuan∗;ZHOU Chun-ping;WANG Fu-sheng(College of Aeronautical Engineering,Civil Aviation University of China,Tianjin 300300,China;Aviation Key Lab of Science and Technology on High Performance Electromagnetic Windows,Research Institute for Special Structure of Aeronautical Composite,AVIC,Jinan 250023,China;China Europe Institute of Aeronautical Engineers,Civil Aviation University of China,Tianjin 300300,China)
出处
《复合材料科学与工程》
CAS
北大核心
2021年第3期51-59,共9页
Composites Science and Engineering
基金
航空科学基金(20181867007)
中国民航大学中央高校基本科研业务费项目(3122019099)。
关键词
平纹编织
复合材料
修补
泡沫夹芯结构
侧向压缩
plain weave
composite material
repair
foam sandwich structure
edgewise compression
