Fatigue Response and Modelling of Variable Stress Amplitude and Frequency in AS-4/PEEK Composite Laminates, Part 1: Experiments

Lee, C. H.; Jen, Ming Hwa R.

doi:10.1177/002199830003401101

Cited by 31 publications

(14 citation statements)

References 22 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 Sjo È gren 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: O M P a R I S O N W I T H T H E L I T E R A T U R Ementioning

confidence: 89%

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: O M P a R I S O N W I T H T H E L I T E R A T U R Ementioning

confidence: 89%

Two‐stage fatigue loading of woven carbon fibre reinforced laminates

Found

Quaresimin

2002

Fatigue Fract Eng Mat Struct

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“…The glass-rubber transition temperature (T g ) of PEEK is 143 C and melting point temperature (T m ) is 343 C. The temperature, pressure, cooling rate and annealing were found significantly effective on the morphology and degree of crystallinity and results in the change of mechanical properties of composites sensitively. Hence a modified diaphragm curing process was developed as shown in Figure 1 [20,21]. The received optimal degree of crystallinity was 30-33%.…”

Section: Methodsmentioning

confidence: 99%

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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“…The basic mechanical properties of various layups at elevated temperatures were determined at the authors' laboratory in an earlier study and used as the baseline properties. 18,20 In this study, the tensile strength of the cross-ply laminates with and without notches at elevated temperature were determined and the pooled data presented in Table 1. The schematic failure modes and mechanisms of the layups with a central hole have been presented elsewhere, 18 along with other mechanical properties.…”

Section: Experimental Studiesmentioning

confidence: 99%

Determination of residual strength in notched APC-2 cross-ply composite laminates at elevated temperature

Jen

Sung

2011

Journal of Composite Materials

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The residual strength of notched AS-4/polyetheretherketone (PEEK) composite (APC-2) laminates with a central hole at elevated temperature was systematically investigated by both analytical and empirical methods. First, APC-2 cross-ply [0/ 90] 4s panels were fabricated and cut into samples. A circular hole with one of five diameters was drilled in the center of each sample. The samples were subjected to quasi-static tensile tests at elevated temperatures to measure their mechanical properties -strength and longitudinal stiffness. Stress concentration and high temperature were found to remarkably affect the residual strength of composite. Point stress criterion (PSC) above was found to be unsatisfactory in predicting the residual strength. A modified PSC combined with the equation of thermal degradation was able to predict the characteristic length at elevated temperature. The residual strengths predicted by the extended modified PSC model were in very close agreement with the empirical data.

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Fatigue Response and Modelling of Variable Stress Amplitude and Frequency in AS-4/PEEK Composite Laminates, Part 1: Experiments

Cited by 31 publications

References 22 publications

Two‐stage fatigue loading of woven carbon fibre reinforced laminates

Two‐stage fatigue loading of woven carbon fibre reinforced laminates

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

Determination of residual strength in notched APC-2 cross-ply composite laminates at elevated temperature

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