• Journal of the Korean Society of Manufacturing Technology Engineers
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• v.22 no.3
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• pp.388-393
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• 2013

Carbon fiber reinforced plastic (CFRP) has many desirable qualities, including being lightweight and very strong. These characteristics have led to its use in applications ranging from small consumer products to vehicles. Circular and square CFRP members were fabricated using 8ply unidirectional prepreg sheets stacked at different angles ($[+15^{\circ}/-15^{\circ}]_4$, $[+45^{\circ}/-45^{\circ}]_4$ and $[90]_8$, where $0^{\circ}$ coincides with the axis of the member). Based on the collapse characteristics of a CFRP circular member, the collapse characteristics and energy absorption capability were analyzed. Impact collapse tests were carried out for each section member. In this study, the impact energies at crossheads speeds of 5.52 m/s, 5.14 m/s and 4.57 m/s were 611.52 J, 529.2 J and 419.44 J (circular member) 2.16 m/s, 1.85 m/s and 1.67 m/s are 372.4 J, 274.4 J and 223.44 J (square member). The purpose is to experimentally examine the absorption behavior and evaluation the strength in relation to changes in the stacking configuration when the CFRP circular members with different stacking configurations were exposed to various impact velocities. In addition, the dynamic characteristics were considered.

• Journal of the Korean Society of Manufacturing Technology Engineers
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• v.22 no.6
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• pp.976-981
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• 2013

This aims to examine experimentally the absorption behavior and strength of circular CFRP members with different stacking configurations on exposure to a separate impact velocity. In addition, considered the dynamic characteristics. Circular and square CFRP members were prepared from 8-ply unidirectional prepreg sheets stacked at different angles ($0^{\circ}/90^{\circ}$ and $90^{\circ}/0^{\circ}$, where the $0^{\circ}$ direction coincides with the axis of the member) and interface numbers (2, 4, and 6). Based on the collapse characteristics of the circular CFRP members. In this study, for the circular members, the impact energies at crosshead speeds of 5.52 m/s, 5.14 m/s, and 4.57 m/s are 611.52 J, 529.2 J, and 419.44 J (at circular members), respectively. Likewise, for the square members, the impact energies at crosshead speeds of 2.16 m/s, 1.85 m/s, and 1.67 m/s are 372.4 J, 274.4 J, and 223.44 J (at square members).

• Journal of the Korea institute for structural maintenance and inspection
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• v.12 no.1
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• pp.73-80
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• 2008

Experimental study has been performed in order to construct the standard test methods and appraisal criteria by investigating the influence of specimen types(property, width, layers) and loading rate on the tensile characteristics of FRP used in strengthening RC structures. The FRP composite tested in this study are the unidirectional CFRP sheet/strip and the bidirectional GFRP sheet. Test variables consist of the various width ranging from 10mm to 25mm and number of CFRP sheets plied up to 5 layers. Test results indicated that maximum tensile strength and minimum coefficient of variation are recorded at each different width according to the fiber types and weaving directions. Also, the average tensile strengths of CFRP sheets are decreased as the number of layer of CFRP sheet are increased.

• Journal of the Korean Society of Fisheries and Ocean Technology
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• v.31 no.3
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• pp.272-278
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• 1995

In this paper to investigate mode I and mode II critical energy release rates, G sub(IC) and G sub(IIC), three prepregs which are domestic products are used. Those are used for the unidirectional composites, but only one is used for the cross-ply laminate composites which is molded [0/90] sub(6s), [0/45] sub(6s) and [0/45/90] sub(6s). The value of G sub(IC) is almost same when modified three calculating methods are applied. The highest value of G sub(IC) at crack initiation is obtained at the [0/90] sub(6s) interlaminar and the lowest one is at the [0/45/90] sub(6s) interlaminar.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.41 no.10
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• pp.959-965
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• 2017

In recent years, major airplane manufacturers have been using the laminate failure theory to estimate the strain of composite structures for airplanes. The laminate failure theory uses the failure strain of the laminate to analyze composite structures. This paper describes a procedure for the experimental assessment of laminate tensile failure characteristics. Regression analysis was used as the experimental assessment method. The regression analysis was performed with the response variable being the laminate failure strain and with the regressor variables being two-ply orientation ($0^{\circ}$ and ${\pm}45^{\circ}$) variables. The composite material in this study is a carbon/epoxy unidirectional (UD) tape that was cured as a pre-preg at $177^{\circ}C(350^{\circ}F)$. A total of 149 tension tests were conducted on specimens from 14 distinct laminates that were laid up at standard angle layers ($0^{\circ}$, $45^{\circ}$, $-45^{\circ}$, and $90^{\circ}$). The ASTM-D-3039 standard was used as the test method.