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混杂纤维复合材料层板的抗弹冲击性能
易凯1, 孙建波1, 杨智勇1, 杨坚2, 贺晔红2
1.航天材料及工艺研究所,北京 100076;2.中国航发沈阳黎明航空发动机有限责任公司,沈阳 110043
摘要:
为了考察混杂纤维复合材料层板的抗弹冲击性能,采用碳纤维织物或玻璃纤维织物与芳纶纤维织物复合材料层共固化的方式,利用热压罐成型工艺制备了几种具有不同面密度及铺层结构的混杂纤维复合材料层板,并进行抗弹冲击性能测试、表观形貌观察和无损检测分析。结果表明:纯芳纶纤维及混杂纤维复合材料层板的钢弹冲击破坏模式相同,均为表层剪切破坏,中间层分层破坏,背层拉伸断裂破坏;层间混杂顺序对复合材料层板的分层缺陷面积有较大影响,当碳纤维层作为背层时,层板的分层缺陷面积为12 863.6 mm2小于玻璃纤维层作为背层时(17 400.5 mm2);当芳纶层作为背板时,混杂纤维复合材料层板冲击后分层缺陷面积与纯芳纶的相当( 14 151.0~14 927.0 mm2)。混杂纤维复合材料对层板的抗弹冲击性能有较大影响,混杂后复合材料的弹道极限速度(v50)均有一定程度的提高,其中玻璃纤维/芳纶复合材料的v50从纯芳纶复合材料层板的193.08提高至204.33 m/s。将碳纤维层或玻璃纤维层作为着弹面层的混杂纤维复合材料层板具有更优异的抗弹冲击性能,其贯穿比吸能(BPI)均优于纯芳纶复合材料层板。
关键词:  芳纶纤维  碳纤维  玻璃纤维  混杂纤维  抗弹冲击性能  破坏形貌  破坏模式
DOI:10.12044/j.issn.1007-2330.2019.01.016
分类号:
基金项目:
Ballistic Impact Resistance of Hybrid Composite Materials
YI Kai1, SUN Jianbo1, YANG Zhiyong1, YANG Jian2, HE Yehong2
1.Aerospace Research Institute of Materials & Processing Technology,Beijing 100076;2.AECC Shenyang Liming Aero-Engine Co.,LTD.,Shenyang 110043
Abstract:
In order to investigate the ballistic impact resistance of hybrid composite laminates,hybrid fiber composite laminates with different areal densities and different layup structures were prepared by autoclave co-cured process by using carbon fiber fabric composite layer or glass fiber fabric composite layer combined with aramid fiber fabric composite layer.Through the ballistic impact performance test,the ballistic limit speed v50 and the ballistic performance indicator(BPI,specific energy absorption of penetration) of the hybrid composite laminates were obtained. The morphology and non-destructive testing results indicate that the failure mode of pure aramid composite laminates and hybrid composite laminates after impact are the same.The surface layer of the laminates is shear failure, the intermediate layer is delamination failure,and the back layer is tensile fracture failure.The interlaminar layer sequence has a great influence on the delamination defect area of the hybrid composite laminate.When the carbon fiber layer is used as the back layer, the defect area of hybrid laminate is 12 863.6 mm 2 smaller than that of the glass fiber layer as the back layer which is 17 400.5 mm2;when the aramid layer is used as the back layer, the area of defect of the hybrid composite layer after impact is equivalent to the defect area of the pure aramid composite laminate in the range of 14 151.0 to 14 927.0 mm2.The test results show that the hybrid composite material has a great influence on the ballistic impact resistance of the composite laminates. The v50 of the hybrid composite laminates has a certain degree of improvement.The v50 of the glass fiber/aramid composite laminate has an increment from 193.88 to 204.33 m/s compared to the v50 of pure aramid composite laminate.The hybrid fiber composite laminate with carbon fiber layer or glass fiber layer as the surface layer has better ballistic impact resistance, and their BPI is superior to pure aramid composite laminate.The test results have certain guiding significance for the design and application of hybrid fiber composites in ballistic impact.
Key words:  Aramid fiber  Carbon fiber  Hybrid fiber  Ballistic impact properties  Failure morphology  Failure mode