Fatigue Response and Modelling of Variable Stress Amplitude and Frequency in AS-4/PEEK Composite Laminates, Part 2: Analysis and Formulation

LEE, C.-H.; Jen, Ming Hwa R.

doi:10.1106/pfej-d1t1-41xk-4fx3

Cited by 7 publications

(12 citation statements)

References 0 publications

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“…Unfortunately the high variation of the data does not allow us to identify a damage curve which could, as a first approximation, be used to generally represent the behaviour described. As already discussed in the Introduction, only the data from Lee and Jen 15,16 and Gamstedt and Sjögren 20 follow an opposite trend with the low‐to‐high sequence less damaging than the high‐to‐low one: it is worth noting, however, that at least in the former case the data are obtained on thermoplastic matrix laminates.…”

Section: Comparison With the Literaturementioning

confidence: 90%

“…25,35 More recently, some other models suitable to account for the cumulative fatigue damage have also been presented, such as those reported in references. 16,19,21,34,41±45…”

Section: U M U L a T I V E D A M A G E M O D E L Smentioning

confidence: 99%

“…For a more exhaustive analysis of the available models we refer the reader to the reviews by Hwang and Han 25,35 . More recently, some other models suitable to account for the cumulative fatigue damage have also been presented, such as those reported in references 16,19 , 21,34 , 41–45 …”

Section: Cumulative Damage Modelsmentioning

confidence: 99%

“…2,4,5,7,8,11,13,14,21±23,28 For many metals, the reverse situation occurs in terms of the sequence of the two-stage fatigue loading. In two cases only, 16,20 a more detrimental effect of the high-to-low sequence has been reported for FRP composite materials.…”

Section: Introductionmentioning

confidence: 95%

“…The situation is much more difficult for the more realistic case of variable amplitude loading, since a structural member is usually subjected to a load spectrum far from the constant amplitude case. Hence there are very limited experimental data, 1–31 some of which 22–31 are on glass reinforced plastics, for the fatigue of FRP composites subject to variable amplitude loading conditions.…”

Section: Introductionmentioning

confidence: 99%

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Two‐stage fatigue loading of woven carbon fibre reinforced laminates

Found

Quaresimin

2002

Fatigue Fract Eng Mat Struct

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A brief review of the models used to predict the cumulative fatigue damage in FRP composites is presented. Two-stage fatigue loading of a [0/90,+/- 45(2),0/90](s) quasi-isotropic woven carbon fibre/epoxy resin laminate was evaluated at stress ratio R=0.05 and the failure mechanisms investigated using x-radiography after each loading stage. The results are presented in terms of fatigue strength and damage growth and are compared with those in the literature. A low-to-high loading sequence is more damaging than a high-to-low one and the Palmgren-Miner linear damage rule may no longer be valid for this kind of material, as previously reported

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Section: Comparison With the Literaturementioning

confidence: 90%

“…25,35 More recently, some other models suitable to account for the cumulative fatigue damage have also been presented, such as those reported in references. 16,19,21,34,41±45…”

Section: U M U L a T I V E D A M A G E M O D E L Smentioning

confidence: 99%

Section: Cumulative Damage Modelsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 95%

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Two‐stage fatigue loading of woven carbon fibre reinforced laminates

Found

Quaresimin

2002

Fatigue Fract Eng Mat Struct

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Effects of Load Sequence and Block Loading on the Fatigue Response of Fiber-Reinforced Composites

Paepegem¹,

Degrieck²

2002

Mechanics of Advanced Materials and Structures

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Mechanical Properties in Notched AS-4/PEEK APC-2 Composite Laminates at Elevated Temperature

Jen

Tseng

Chang

et al. 2006

Journal of Composite Materials

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The response of centrally notched AS-4/PEEK APC-2 composite laminates at elevated temperatures is investigated empirically and systematically. The failure mechanism and mechanical properties in notched cross-ply and quasi-isotropic laminates are perceived. First, the ultimate strength decreases seriously as the hole diameter increases, whereas the longitudinal stiffness changes irregularly. Next, combined with the effect of temperature elevation, the ultimate strength is accelerated to decay while the longitudinal stiffness is reduced slowly. Neglecting the increase in longitudinal stiffness, the worst case of both lay-ups as expected with the largest hole diameter and at the highest temperature still sustains at least 60% of ultimate strength. However, the reduction of strength in cross-ply laminates is more serious than that in quasi-isotropic laminates. Finally, a modified predictive model was proposed and found satisfactorily acceptable. It is also highlighted as a reliable, general, and simple model.

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Fatigue Response and Modelling of Variable Stress Amplitude and Frequency in AS-4/PEEK Composite Laminates, Part 2: Analysis and Formulation

Cited by 7 publications

References 0 publications

Two‐stage fatigue loading of woven carbon fibre reinforced laminates

Two‐stage fatigue loading of woven carbon fibre reinforced laminates

Effects of Load Sequence and Block Loading on the Fatigue Response of Fiber-Reinforced Composites

Mechanical Properties in Notched AS-4/PEEK APC-2 Composite Laminates at Elevated Temperature

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