共 20 条
Mechanical properties of cross-ply and quasi-isotropic composite laminates processed using aligned multi-walled carbon nanotube/epoxy prepreg
被引:21
作者:
Ogasawara, Toshio
[1
]
Hanamitsu, Satoru
[2
]
Ogawa, Takeshi
[2
]
Moon, Sook-Young
[3
]
Shimamura, Yoshinobu
[4
]
Inoue, Yoku
[4
]
机构:
[1] Tokyo Univ Agr & Technol, Dept Mech Syst Engn, 2-24-16 Naka Cho, Koganei, Tokyo 1848588, Japan
[2] Aoyama Gakuin Univ, Dept Mech Engn, Chuo Ku, 5-10-1 Fuchinobe, Sagamihara, Kanagawa 2525258, Japan
[3] Japan Aerosp Explorat Agcy, 6-13-1 Osawa, Mitaka, Tokyo 1810015, Japan
[4] Shizuoka Univ, Fac Engn, Naka Ku, 3-5-1 Jyohoku, Hamamatsu, Shizuoka 4238561, Japan
基金:
日本科学技术振兴机构;
关键词:
carbon nanotubes;
laminate;
polymer-matrix composites (PMCs);
Short-fiber composites;
mechanical properties;
REINFORCED PLASTIC COMPOSITES;
MICROSCOPIC DAMAGE;
NANOCOMPOSITES;
STRENGTH;
SHEETS;
D O I:
10.1080/09243046.2016.1226688
中图分类号:
TB33 [复合材料];
学科分类号:
摘要:
This study examined the processing and mechanical properties of cross-ply and quasi-isotropic composite laminates processed using aligned multi-walled carbon nanotube/epoxy prepreg sheets. Three kinds of CNT/epoxy laminates, ([0 degrees/9 degrees]s, [60 degrees/0 degrees/-60 degrees]s, [0 degrees/45 degrees/90 degrees/-45 degrees]s) were successfully fabricated using aligned CNT/epoxy prepreg sheets. The CNT volume fraction was approximately 10%. No visible void or delamination was observed in composite laminates, and the thickness of each layer was almost equal to that of the prepreg. To evaluate the elastic moduli, E-11, E-22, and G(12), of each ply in the laminates, on -axis and off -axis tensile tests (0 degrees, 45 degrees, 90 degrees) were conducted of aligned CNT/epoxy lamina specimens. The Young's modulus of CNT/epoxy cross-ply and quasi-isotropic laminates agreed with the theoretical values, which were calculated using classical laminate theory and elastic moduli of CNT/epoxy lamina. The respective failure strains of [0 degrees/90 degrees]s, [60 degrees/0 degrees/-60 degrees]s, and [0 degrees/45 degrees/90 degrees/-45 degrees]s laminates are 0.65, 0.92, 0.63%, which are higher than that of 0 degrees composite lamina (0.5%). Results suggest that the failure strain of 0 degrees layer in composite laminates is improved because of the other layers.
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页码:157 / 168
页数:12
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