TY - GEN
T1 - High Strain-Rate Compressive Properties of Carbon/Epoxy Laminated Composites-Effects of loading direction and temperature
AU - Nakai, Kenji
AU - Fukushima, Tsubasa
AU - Yokoyama, Takashi
AU - Arakawa, Kazuo
N1 - Publisher Copyright:
© 2018 The Authors, published by EDP Sciences.
PY - 2018/9/7
Y1 - 2018/9/7
N2 - The high strain-rate compressive characteristics of a cross-ply carbon/epoxy laminated composite in the three principal material directions or fibre (1-), in-plane transverse (2-) and throughthickness (3-) directions are investigated on the conventional split Hopkinson pressure bar (SHPB) over a range of temperatures between 20 and 80 °C. A nearly 10 mm thick cross-ply carbon/epoxy composite laminate fabricated using vacuum assisted resin transfer molding (VaRTM) was tested. Cylindrical specimens with a slenderness ratio (= length/diameter) of 0.5 are used in high strain-rate tests, and those with the slenderness ratios of 1.0 and 1.5 are used in low and intermediate strain-rate tests. The uniaxial compressive stress-strain curves up to failure at quasi-static and intermediate strain rates are measured on an Instron testing machine at elevated temperatures. A pair of steel rings is attached to both ends of the cylindrical specimens to prevent premature end crushing in the 1-and 2-direction tests on the Instron testing machine. It is shown that the ultimate compressive strength (or failure stress) exhibits positive strainrate effects and negative temperature ones over a strain-rate range of 10-3 to 103/s and a temperature range of 20 to 80 °C in the three principal material directions.
AB - The high strain-rate compressive characteristics of a cross-ply carbon/epoxy laminated composite in the three principal material directions or fibre (1-), in-plane transverse (2-) and throughthickness (3-) directions are investigated on the conventional split Hopkinson pressure bar (SHPB) over a range of temperatures between 20 and 80 °C. A nearly 10 mm thick cross-ply carbon/epoxy composite laminate fabricated using vacuum assisted resin transfer molding (VaRTM) was tested. Cylindrical specimens with a slenderness ratio (= length/diameter) of 0.5 are used in high strain-rate tests, and those with the slenderness ratios of 1.0 and 1.5 are used in low and intermediate strain-rate tests. The uniaxial compressive stress-strain curves up to failure at quasi-static and intermediate strain rates are measured on an Instron testing machine at elevated temperatures. A pair of steel rings is attached to both ends of the cylindrical specimens to prevent premature end crushing in the 1-and 2-direction tests on the Instron testing machine. It is shown that the ultimate compressive strength (or failure stress) exhibits positive strainrate effects and negative temperature ones over a strain-rate range of 10-3 to 103/s and a temperature range of 20 to 80 °C in the three principal material directions.
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U2 - 10.1051/epjconf/201818302011
DO - 10.1051/epjconf/201818302011
M3 - Conference contribution
AN - SCOPUS:85053678496
SN - 9782759890538
T3 - EPJ Web of Conferences
BT - DYMAT 2018 - 12th International Conference on the Mechanical and Physical Behaviour of Materials under Dynamic Loading
A2 - Cosculluela, Antonio
A2 - Cadoni, Ezio
A2 - Buzaud, Eric
A2 - Couque, Herve
PB - EDP Sciences
T2 - 12th International Conference on the Mechanical and Physical Behaviour of Materials under Dynamic Loading, DYMAT 2018
Y2 - 9 September 2018 through 14 September 2018
ER -