海军工程大学学报
海軍工程大學學報
해군공정대학학보
JOURNAL OF NAVAL UNIVERSITY OF ENGINEERING
2014年
6期
12-16
,共5页
开孔层合板%拉伸强度%失效模式%失效分析
開孔層閤闆%拉伸彊度%失效模式%失效分析
개공층합판%랍신강도%실효모식%실효분석
perforated laminated plate%tensile strength%failure mode%damage analysis
为研究纤维编织工艺、铺层角度和孔径大小对开孔复合材料层合板拉伸强度和失效模式的影响规律，选用正交平纹玻纤层合板（WFL）和单向玻纤层合板（UFL）制作0°和45°铺层开孔拉伸试件，随后进行了试验研究；采用 Abaqus 建立基于二维 Hashion 失效准则的渐进损伤仿真模型，并对试验结果进行了对比，分析了试件的损伤机理。研究结果表明：层合板强度随开孔增大而减小，并且这种变化率随孔径增大而增大，45°铺层的层合板的变化率小于0°铺层，WFL 小于 UFL；WFL 的破坏以纤维断裂为主，裂纹垂直于纤维方向，UFL 以基体开裂为主，裂纹沿纤维方向，孔径则对破坏模式无明显影响；0°铺层 WFL 的破坏是由纤维拉伸失效导致，45°的则由纤维拉伸失效和基体拉伸剪切失效共同导致，0°铺层 UFL 由基体压缩失效导致，45°的则由基体拉伸剪切失效导致；拉伸强度的仿真与试验结果最大误差为14．1％，由此验证了仿真计算方法的有效性。
為研究纖維編織工藝、鋪層角度和孔徑大小對開孔複閤材料層閤闆拉伸彊度和失效模式的影響規律，選用正交平紋玻纖層閤闆（WFL）和單嚮玻纖層閤闆（UFL）製作0°和45°鋪層開孔拉伸試件，隨後進行瞭試驗研究；採用 Abaqus 建立基于二維 Hashion 失效準則的漸進損傷倣真模型，併對試驗結果進行瞭對比，分析瞭試件的損傷機理。研究結果錶明：層閤闆彊度隨開孔增大而減小，併且這種變化率隨孔徑增大而增大，45°鋪層的層閤闆的變化率小于0°鋪層，WFL 小于 UFL；WFL 的破壞以纖維斷裂為主，裂紋垂直于纖維方嚮，UFL 以基體開裂為主，裂紋沿纖維方嚮，孔徑則對破壞模式無明顯影響；0°鋪層 WFL 的破壞是由纖維拉伸失效導緻，45°的則由纖維拉伸失效和基體拉伸剪切失效共同導緻，0°鋪層 UFL 由基體壓縮失效導緻，45°的則由基體拉伸剪切失效導緻；拉伸彊度的倣真與試驗結果最大誤差為14．1％，由此驗證瞭倣真計算方法的有效性。
위연구섬유편직공예、포층각도화공경대소대개공복합재료층합판랍신강도화실효모식적영향규률，선용정교평문파섬층합판（WFL）화단향파섬층합판（UFL）제작0°화45°포층개공랍신시건，수후진행료시험연구；채용 Abaqus 건립기우이유 Hashion 실효준칙적점진손상방진모형，병대시험결과진행료대비，분석료시건적손상궤리。연구결과표명：층합판강도수개공증대이감소，병차저충변화솔수공경증대이증대，45°포층적층합판적변화솔소우0°포층，WFL 소우 UFL；WFL 적파배이섬유단렬위주，렬문수직우섬유방향，UFL 이기체개렬위주，렬문연섬유방향，공경칙대파배모식무명현영향；0°포층 WFL 적파배시유섬유랍신실효도치，45°적칙유섬유랍신실효화기체랍신전절실효공동도치，0°포층 UFL 유기체압축실효도치，45°적칙유기체랍신전절실효도치；랍신강도적방진여시험결과최대오차위14．1％，유차험증료방진계산방법적유효성。
To analyze the impact of the layer orientation and the hole diameter on the tensile strength and failure mode according to the law of fiber weaving,this paper makes the perforated tensile speci-mens with the layer orientation 0°and 45°out of the GFRP with woven fabric (WFL)and unidirec-tional fiber (UFL),and carries out tensile experiments.Based on Hashion failure criteria,this paper adopts Abaqus to establish a progressive damage model,compares the simulated results with experi-mental results,and analyzes the failure mechanism of specimens.The results show that the tensile strength decreases as the hole diameter grows,and the changing rate increases with it,and that the laminated plate with the layer orientation 45° is lower than that with the layer orientation 0°,and WFL is lower than UFL.WFL is subjected to the fiber tensile fracture and the crack is perpendicular to the fiber direction,while UFL is subjected to matrix cracking and the crack is parallel to the fiber direction,but the hole diameter has little impact on failure mode.The fractures of WFL with the layer orientation 0°and 45°are respectively caused by the fiber tensile failure,and the fiber tensile failure and matrix tensile-shear failure.The fractures of UFL with 0°and 45°are respectively caused by the matrix compressed failure,and the matrix tensile-shear failure.The maximum error 14.1% between the stimulation and the experiment results of tensile strength verifies that the simulating method is ef-fective.
