贴近度法表征复合材料层合板低能量冲击行为
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摘要
复合材料遭受低能量冲击后其表面损伤是复合材料受冲击后观察以及描述的最直接部位。将复合材料损伤程度划分为5个等级,并且基于模糊贴近度评判方法,建立复合材料低能量冲击表面损伤信息与其损伤级别之间的联系。采用超景深显微镜,对复合材料冲击试件的表面损伤进行观察、记录、分析,结合模糊贴近度评判的方式,建立损伤程度与贴近度阀值之间的数值关系。并且经实例验证,不同的复合材料、不同的厚度在表面损伤表现有相同特征的时候,可通过本文的表征方法判定为相同的损伤级别。
Surface damage is the most direct observation and description of composite after impact. In this paper,the damage degree of composite materials is divided into five grades. Based on the fuzzy closeness evaluation method,the relationship between the damage information and the damage level of the low energy impact surface of composite materials is established. In this paper,the superficial depth microscope is used to observe,record,and analyze the surface damage of composite impact specimens. By combining with the fuzzy assessment method of progress assessment,a numerical relationship between the damage level and the posting progress threshold is established. It is proved that the same damage level can be determined by the characterization method of this paper when the surface damage of different composite materials and different thickness has the same characteristics.
Surface damage is the most direct observation and description of composite after impact. In this paper,the damage degree of composite materials is divided into five grades. Based on the fuzzy closeness evaluation method,the relationship between the damage information and the damage level of the low energy impact surface of composite materials is established. In this paper,the superficial depth microscope is used to observe,record,and analyze the surface damage of composite impact specimens. By combining with the fuzzy assessment method of progress assessment,a numerical relationship between the damage level and the posting progress threshold is established. It is proved that the same damage level can be determined by the characterization method of this paper when the surface damage of different composite materials and different thickness has the same characteristics.
引文
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[3]黎增山,关志东,何为.国产碳纤维增强树脂基复合材料应变不变量性能[J].复合材料学报,2011,28(5):192-196.
[4]Choi I H. Low-velocity impact analysis of composite laminates under initial in-plane load[J]. Composite Structures,2008,86(1):251-257.
[5]Baucom J N,Zikry M A. Low-velocity impact damage progression in woven E-glass composite systems[J]. Composites Part A Applied Science&Manufacturing,2005,36(5):658-664.
[6]陈绍杰.复合材料与B7E7“梦想”飞机[J].航空制造技术,2005(1):34-37.
[7]施军,黄卓.复合材料在海洋船舶中的应用[J].玻璃钢/复合材料,2012(1):269-273.
[8]牛春匀.实用飞机复合材料结构设计与制造[M].北京:航空工业出版社,2010.
[9]何艳斌.航空复合材料典型结构低能量冲击损伤及动力响应研究[D].广州:华南理工大学,2016.
[10]刘向民,姚卫星,陈方.复合材料层合板结构冲击损伤数值模拟的损伤力学模型[J].航空学报,2016,37(10):3054-3063.
[11]胡令金. CFRP层合板低能量冲击损伤研究[D].哈尔滨:哈尔滨工业大学,2014.
[12]陈明,周储伟.低速冲击作用下复合材料层合板永久凹坑数值分析[J].江苏航空,2017(4).
[13]Shi Y,Swait T,Soutis C. Modelling damage evolution in composite laminates subjected to low velocity impact[J]. Composite Structures,2012,94(9):2902-2913.
[14]Standard test method for measuring the damage resistance of a fiber reinforced polymer matrix[S].
[15]Composite to a drop-weight impact event:ASTM D 7136-07[S].2007.
[16]王力,吕大刚,王光远.结构方案设计模糊多属性决策的模糊贴近度方法[J].建筑结构学报,2005,26(3):118-121.
[17]王光远.工程软设计理论[M].北京:科学出版社,1992.
[18]赵宏,马立彦,贾青.基于变异系数法的灰色关联分析模型及其应用[J].黑龙江水利科技,2007,35(2):26-27.