journal article·2013-04Open access

Block loading fatigue of adhesively bonded pultruded GFRP joints

Roohollah Sarfaraz, Anastasios P. Vassilopoulos, Thomas Keller

Abstract

The effect of loading sequence on the fatigue behavior of adhesively-bonded pultruded GFRP double-lap joints was experimentally investigated by applying different tensile and compressive block loading patterns. The observed failure modes were consistent with failure modes under constant amplitude loading. A significant load sequence effect was observed for both tensile and compressive loading. Under tensile loading the transition from low to high load cycles in a two-block loading was more damaging than the high to low sequence. The inverse was observed for compression loading. This behavior was associated with the crack propagation rates and their dependence on loading type. The effect of the number of load transitions in a multi-block loading spectrum was also studied by using different loading sequences. The influence of this loading parameter was found to be more dominant than the sequence effect, which is diminished by increasing the number of transitions. © 2012 Elsevier Ltd. All rights reserved.
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Research context

OpenAlex topics: Mechanical Behavior of Composites · Structural Behavior of Reinforced Concrete · Fatigue and fracture mechanics

SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.

References (35)

Show source-provided references
1. A new theory to predict cumulative fatigue damage in fibre–glass reinforced plastics
2. Effect of load sequence on the statistical fatigue of composite10.2514/3.50912 ↗
3. Load sequence effects on graphite/epoxy [±35]2s laminates
4. Fatigue damage in a centrally notched composite laminate due to two-step spectrum loading10.1016/0142-1123(94)90003-5 ↗
5. The influence of two-stage loading on the longitudinal splitting of unidirectional carbon-epoxy laminates10.1111/j.1460-2695.1996.tb00932.x ↗
6. Fatigue life prediction of composite under two-step loading10.1023/A:1018560423889 ↗
7. Damage accumulation in quasi isotropic graphite/epoxy laminates under constant-amplitude fatigue and block loading10.1016/S0266-3538(97)00214-5 ↗
8. Wahl NW, Mandell JF, Samborsky DD. Spectrum fatigue lifetime and residual strength for fiberglass laminates in tension, ASME Wind Energy Symposium, AIAA-2001-0025, ASME/AIAA, 2001.10.2514/6.2001-25 ↗
9. Effects of load sequence and block loading on the fatigue response of fibre-reinforced composites10.1080/153764902317224851 ↗
10. Fatigue characteristic of quasi-isotropic CFRP laminates subjected to variable amplitude cyclic loading of two-stage10.1016/j.ijfatigue.2006.02.039 ↗
11. Fatigue life scattering of RP/C
12. Statistical study of strength and fatigue life of composite materials10.1016/0010-4361(87)90007-3 ↗
13. Hwang W, Han KS. Fatigue of composite materials – Damage model and life prediction. Compos Mater Fatigue Fract, ASTM STP 1012, 2nd volume, Philadelphia:American Society for Testing and Materials; 1989. p. 87–102.10.1520/STP10410S ↗
14. Fatigue response and modelling of variable stress amplitude and frequency in AS-4/PEEK composite laminates, Part 1: experiments10.1177/002199830003401101 ↗
15. Fatigue response and modelling of variable stress amplitude and frequency in AS-4/PEEK composite laminates, Part 2: Analysis and formulation10.1177/002199830003401102 ↗
16. An experimental investigation of the sequence effect in block amplitude loading of cross-ply laminates10.1016/S0142-1123(01)00099-8 ↗
17. Life prediction for fatigue of T800/5425 carbon-fibre composites: II, variable amplitude loading10.1016/0142-1123(94)90479-0 ↗
18. Fatigue of carbon–fibre reinforced plastics under block-loading conditions10.1016/S1359-835X(96)00131-5 ↗
19. Cumulative damage of fiber-reinforced elastomer composites under fatigue loading10.1177/002199839402801306 ↗
20. Bonnee WJA. NLR investigation of polyester composite materials, C.W. Kensche, Editor, Fatigue of materials and components for wind turbine rotor blades. German Aerospace Establishment, European Commission-EUR 16684; 1996. p. 39–70.
21. Two-stage fatigue loading of woven carbon fibre reinforced laminates10.1046/j.1460-2695.2003.00583.x ↗
22. Damage evolution in a [±45]2S CFRP laminate under block loading conditions10.1016/j.ijfatigue.2009.02.020 ↗
23. Life prediction methodology for composite structures. Part I. Constant amplitude and two-step level fatigue10.1177/002199839703100202 ↗
24. Life prediction methodology for composite structures Part II – spectrum fatigue10.1177/002199839703100203 ↗
25. Classical fatigue analysis and load cycle mix-event damage accumulation in fibre reinforced laminates10.1016/j.ijfatigue.2003.10.013 ↗
26. A study of adhesively bonded joints subjected to constant and variable amplitude fatigue10.1016/j.ijfatigue.2004.03.011 ↗
27. Fatigue crack growth acceleration due to intermittent overstressing in adhesively bonded CFRP joints10.1016/j.compositesa.2004.03.002 ↗
28. A simple model to predict crack growth in bonded joints and laminates under variable-amplitude fatigue10.1243/0309324042379239 ↗
29. Experimental investigation of the fatigue behavior of adhesively-bonded pultruded GFRP joints under different load ratios10.1016/j.ijfatigue.2011.05.012 ↗
30. Experimental investigation and modeling of mean load effect on fatigue behavior of adhesively-bonded pultruded GFRP joints10.1016/j.ijfatigue.2012.04.021 ↗
31. Zhang Y. Fracture and fatigue of adhesively-bonded fiber-reinforced polymer structural joints. PhD thesis, Swiss federal institute of technology Lausanne (EPFL); 2010.
32. Suresh · 1998
33. A phenomenological analysis of mode I fracture of adhesively-bonded pultruded GFRP joints10.1016/j.engfracmech.2011.04.007 ↗
34. Mode I interlaminar fracture of carbon/epoxy multidirectional laminates10.1016/j.compscitech.2004.03.001 ↗
35. Modeling the variable amplitude fatigue of composite materials: a review and evaluation of the state of the art for spectrum loading10.1016/j.ijfatigue.2008.07.002 ↗