Impact resistance performances of resin matrix composite single lap joints reinforced by Z-pin

被引：0
|
作者：
Xu A. [1 ]
Li Y. [1 ]
Huan D. [1 ]
Chu Q. [1 ]
Zhou X. [1 ]
机构：
[1] College of Material Science and Technology, Nanjing University of Aeronautics and Astronautics, Nanjing
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2018年 / 33卷 / 03期
关键词：
After-impact shear strength; Composites; Finite element simulation; Low velocity impact; Single lap joints; Z-pin reinforced resin matrix;
D O I：
10.13224/j.cnki.jasp.2018.03.021
中图分类号：
学科分类号：
摘要：
To study the impact resistance performances of resin matrix composite joints reinforced by Z-pin, single lap joint specimens reinforced by Z-pin were prepared. The crack propagation along Z-pin/laminates interface was compared with different resins matrix of Z-pin. Z-pin pullout and lap shear tests were carried out to study the after-impact pullout strength of Z-pin and after-impact shear strength of single lap joint, respectively. The ultrasonic C-scan method combined with finite element simulation was utilized to explore the delamination damage area of joint interface. The results showed that compared with the BMI resin matrix Z-pin, the resistance performance between epoxy Z-pin/epoxy laminates was stronger at the same impact energy. With the increase of impact energy, the crack propagation was more significant. Z-pin reinforced resin matrix composites remarkably reduced delamination damage area and improved the after-inpact shear strength. The delamination damage area of joint reinforced by Z-pin was 40%, and its reduction of after-impact shear strength was 24.89% when Z-pin's volume fraction was 1.5% and diameter was 0.5 mm. With the increase of Z-pin volume fraction, the delamination damage area decreased gradually, while the after-impact shear strength increased firstly and then decreased. The damage area of lap surface increased as the increment of Z-pin diameter while the after-impact shear strength decreased. The results of finite element modeling were consistent with the test results. © 2018, Editorial Department of Journal of Aerospace Power. All right reserved.
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页码：671 / 682
页数：11
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