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RESEARCH PAPERS

Creep Rupture of Multidirectional Polymer Composite Laminates — Influence of Time-Dependent Damage

[+] Author and Article Information
A. Birur, A. Gupta

Composite Materials and Structures Research Group, University of Manitoba, Winnipeg, MB R3T 5V6, Canada

J. Raghavan1

Composite Materials and Structures Research Group, University of Manitoba, Winnipeg, MB R3T 5V6, Canadarags@cc.umanitoba.ca

1

Corresponding author. Department of Mechanical & Manufacturing Engineering, University of Manitoba, E2-482, EITC Building, 75B, Chancellor Circle, Winnipeg, MB R3T 5V6, Canada.

J. Eng. Mater. Technol 128(4), 611-617 (Jun 23, 2006) (7 pages) doi:10.1115/1.2345454 History: Received November 06, 2005; Revised June 23, 2006

Evolution of various damage modes with time, in multidirectional laminates of a polymer composite (Hexcel F263-7/T300) subjected to a constant load, was experimentally studied and correlated to experimental creep rupture results to understand the influence of the former on the latter. Influence of various parameters, such as stress, temperature, thickness of inner plies, and outer-ply constraint, on damage evolution was evaluated. Observed damages include transverse (also referred in the literature as matrix cracks) cracking due to in-plane stresses, vertical cracking due to out-of-plane normal stress, delamination due to interlaminar stresses, splitting, and fiber fracture. The sequence of evolution of these damages varied with laminate stacking sequence, stress, and temperature. These damages significantly influenced one another and the creep rupture time.

Copyright © 2006 by American Society of Mechanical Engineers
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Figures

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Figure 1

A schematic of global and principal coordinate system

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Figure 2

Transverse crack density evolution in L1, [0/90/0], during tensile testing

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Figure 3

Transverse crack density evolution in L2, [0∕902]s, during tensile testing

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Figure 4

Transverse crack density evolution in L3, [±45∕902]s, during tensile testing

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Figure 5

Process-induced damage (transverse and vertical cracking) in L2

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Figure 6

Edge of specimen in Fig. 4 after polishing, showing the disappearance of vertical cracking

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Figure 7

Damage in L2 after reaching CDS, showing delamination and splitting of [0] plies

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Figure 8

Damage in L1, showing fiber fracture in [0] plies

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Figure 9

Damage in L3 showing delamination between various layers

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Figure 10

Creep rupture data for three laminates at 80°C

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Figure 11

Creep rupture data for three laminates at 180°C

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Figure 12

Creep rupture data for three laminates at 240°C

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Figure 13

Time-dependent evolution of transverse crack density in L1 at 80°C

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Figure 14

Time-dependent evolution of transverse crack density in L2 at 80°C

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Figure 15

Time-dependent evolution of transverse crack density in L3 at 80°C

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Figure 16

Rate of increase of transverse crack density in L3 at a stress of 75% UTS

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Figure 17

Rate of increase of transverse crack density in L1 at a stress of 85% UTS

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