A platform for research: civil engineering, architecture and urbanism
A platform for research: civil engineering, architecture and urbanism
Experimental Studies of Failure in L-Shaped Carbon Fiber-Reinforced Polymer Composite Under Pullout and Four-Point Bending
https://orcid.org/http://orcid.org/0000-0002-0760-1672
Composite materials are used in place of conventional metals to create complex, homogeneous structures that are lightweight and extremely durable. It has been observed that the curved section of a complex structure is the weakest, with the greatest stress concentration occurring in the L-shaped curved section with uniform thickness. In this work, L-shaped woven carbon fiber-reinforced plastic (CFRP) laminates were fabricated by hand layup method with a stacking sequence of [90°/0°/45°/−45°/90°/0°/45°/−45°]S. The fabricated laminates were experimentally tested under pullout and 4-point bending loads according to ASTM D6415 and modified ASTMD6415, respectively. The average load capacity of the specimen for the pullout test was 496.4 N. For the 4-point bending test, the average load capacity was 857.4 N. A Nikon DSLR camera was used to record the onset and progression of damage. In these tests, matrix cracking occurs mainly before and after the 90° lamina, while delamination occurs mainly at the 0°/45°, 90°/0°, and 45°/0° interfaces. This is due to the fact that in the 4-point bending test, the maximum compressive stresses occur in the contact area and the stresses are transmitted through the matrix to the fiber. An optical microscope was used to examine the microstructures of the specimens before and after the experimental tests. It was found that the failure was caused by cracks in the matrix leading to delamination failure. Other failures such as fiber breakage, cracks in the matrix, fiber splitting, and delamination were also observed with the optical microscope.
Experimental Studies of Failure in L-Shaped Carbon Fiber-Reinforced Polymer Composite Under Pullout and Four-Point Bending
https://orcid.org/http://orcid.org/0000-0002-0760-1672
Composite materials are used in place of conventional metals to create complex, homogeneous structures that are lightweight and extremely durable. It has been observed that the curved section of a complex structure is the weakest, with the greatest stress concentration occurring in the L-shaped curved section with uniform thickness. In this work, L-shaped woven carbon fiber-reinforced plastic (CFRP) laminates were fabricated by hand layup method with a stacking sequence of [90°/0°/45°/−45°/90°/0°/45°/−45°]S. The fabricated laminates were experimentally tested under pullout and 4-point bending loads according to ASTM D6415 and modified ASTMD6415, respectively. The average load capacity of the specimen for the pullout test was 496.4 N. For the 4-point bending test, the average load capacity was 857.4 N. A Nikon DSLR camera was used to record the onset and progression of damage. In these tests, matrix cracking occurs mainly before and after the 90° lamina, while delamination occurs mainly at the 0°/45°, 90°/0°, and 45°/0° interfaces. This is due to the fact that in the 4-point bending test, the maximum compressive stresses occur in the contact area and the stresses are transmitted through the matrix to the fiber. An optical microscope was used to examine the microstructures of the specimens before and after the experimental tests. It was found that the failure was caused by cracks in the matrix leading to delamination failure. Other failures such as fiber breakage, cracks in the matrix, fiber splitting, and delamination were also observed with the optical microscope.
Experimental Studies of Failure in L-Shaped Carbon Fiber-Reinforced Polymer Composite Under Pullout and Four-Point Bending
https://orcid.org/http://orcid.org/0000-0002-0760-1672
Composite materials are used in place of conventional metals to create complex, homogeneous structures that are lightweight and extremely durable. It has been observed that the curved section of a complex structure is the weakest, with the greatest stress concentration occurring in the L-shaped curved section with uniform thickness. In this work, L-shaped woven carbon fiber-reinforced plastic (CFRP) laminates were fabricated by hand layup method with a stacking sequence of [90°/0°/45°/−45°/90°/0°/45°/−45°]S. The fabricated laminates were experimentally tested under pullout and 4-point bending loads according to ASTM D6415 and modified ASTMD6415, respectively. The average load capacity of the specimen for the pullout test was 496.4 N. For the 4-point bending test, the average load capacity was 857.4 N. A Nikon DSLR camera was used to record the onset and progression of damage. In these tests, matrix cracking occurs mainly before and after the 90° lamina, while delamination occurs mainly at the 0°/45°, 90°/0°, and 45°/0° interfaces. This is due to the fact that in the 4-point bending test, the maximum compressive stresses occur in the contact area and the stresses are transmitted through the matrix to the fiber. An optical microscope was used to examine the microstructures of the specimens before and after the experimental tests. It was found that the failure was caused by cracks in the matrix leading to delamination failure. Other failures such as fiber breakage, cracks in the matrix, fiber splitting, and delamination were also observed with the optical microscope.
Experimental Studies of Failure in L-Shaped Carbon Fiber-Reinforced Polymer Composite Under Pullout and Four-Point Bending
J. Inst. Eng. India Ser. D
Chaurasia, Bipin Kumar (author) / Kumar, Deepak (author) / Paswan, Mani Kant (author)
Journal of The Institution of Engineers (India): Series D ; 104 ; 569-579
2023-12-01
11 pages
Article (Journal)
Electronic Resource
English
| British Library Online Contents | 2011
Bond Behavior of Fiber Reinforced Polymer Bars under Direct Pullout Conditions
| British Library Online Contents | 2004
Bond Behavior of Fiber Reinforced Polymer Bars under Direct Pullout Conditions
| Online Contents | 2004
Bond behavior of fiber reinforced polymer bars under direct pullout conditions
| Tema Archive | 2004