Quasi-static tensile CFRP AP-PLY data

Published: 17 August 2022| Version 1 | DOI: 10.17632/4wnzrfvgkc.1
Contributor:
Rutger Kok

Description

Quasi-static tensile test data from experiments conducted on carbon fiber epoxy AP-PLY composites, as presented in: https://doi.org/10.1016/j.compositesa.2022.106989. RESEARCH AIMS Quasi-isotropic [0, 45, 90, -45]S and cross-ply [0, 90]2S laminates with conventional or AP-PLY configurations were tested to failure under quasi-static tensile loading, to investigate the effect of the AP-PLY architecture on the in-plane mechanical properties of the laminates (specifically longitudinal modulus and strength). TESTING PROCEDURE Laminates were manufactured using SHD Composites VTC401 unidirectional prepregs (VTC401-UD300-T700-24K-36%RW-600P SHD1579-600P). Laminates were laid up by hand, and subsequently cured in a hot press at 110 degrees centigrade at a pressure of 4 bar. Specimens were extracted using a water cooled saw. Glass fiber end tabs were adhered to the specimens using SHD Composites VTFA400 epoxy adhesive film. Conventional (non AP-PLY) specimens were 25 mm wide, 250 mm long (50 mm end tabs on either end) and approximately 1.6 mm thick. To account for the large representative volume element size of the AP-PLY composites, their dimensions were 40 mm x 250 mm (again 50 mm end tabs on either end) x 1.6 mm. Testing was conducted according to ISO 527-4. Six to ten specimens were tested for each configuration. Specimens were loaded to failure at a rate of 2 mm/min on an MTS 300kN Universal Testing Machine. Strains were recorded using a 2D digital image correlation system. Forces were provided by the loadcell in the testing machine. DATA FORMAT Data is provided in .csv format. "QI" is used to indicate a quasi-isotropic laminate with 0, 45, 90, and -45 degree fiber orientations. "XP" denotes cross-ply laminates containing only 0 and 90 degree plies. Filenames containing "_AP_PLY" refer to specimens with an AP-PLY quasi-woven internal architecture. Filenames containing "_BASE" refer to baseline, non AP-PLY specimens. Column headings are: crosshead displacement [mm], force [kN], time [s], strain_1 [-] (along loading direction), strain_2 [-] (orthogonal to loading direction), cross-sectional area [mm2], and stress [MPa].

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Institutions

The University of Edinburgh

Categories

Composite Material, Carbon Fiber

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