Prediction of residual stresses and distortion in carbon fiber‐epoxy composite parts due to curing process using finite element analysis

Tavakol, Behrouz; Roozbehjavan, Pooneh; Ahmed, Ashraf Uddin; Das, Rony; Joven, Ronald; Koushyar, Hoda; Rodriguez, Alejandro J.; Minaie, Bob

doi:10.1002/app.38075

Cited by 33 publications

(23 citation statements)

References 24 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Whereas, shrinkage is dependent on the physical properties of the components and their reactions, the creation of residual stresses within a composite are ultimately a function of the duration and temperature of the curing cycle [67,62]. The correlation between the appearance of high levels of residual stresses and the fatigue performance of composites (CFRPs) has been reported by many [86,87,68,88,89]. These researchers have found that the fatigue lifetime of CFRP decreases with a higher presence of residual strains within the composite.…”

Section: Effect Of Processing/manufacturing Defects On the Fatigue Prmentioning

confidence: 99%

The fatigue of carbon fibre reinforced plastics - A review

Alam

Mamalis

Robert

et al. 2019

Composites Part B: Engineering

275

View full text Add to dashboard Cite

Engineering structures are often subjected to the conditions of cyclic-loading, which onsets material fatigue, detrimentally affecting the service-life and damage tolerance of components and joints. Carbon fibre reinforced plastics (CFRP) are high-strength, lowweight composites that are gaining ubiquity in place of metals and glass fibre reinforced plastics (GFRP) not only due to their outstanding strength-to-weight properties, but also because carbon fibres are relatively inert to environmental degradation and as such, show potential as corrosion resistant materials. The effects of cyclic loading on the fatigue of CFRP are detailed in several papers. As such, collating research on CFRP fatigue into a single document is a worthwhile exercise, as it will benefit the engineering-readership interested in designing fatigue resistant structures and components using CFRP. This review article aims to provide the most relevant and up-to-date information on the fatigue of CFRP. The review focuses in particular on defining fatigue and the mechanics of cyclically-loaded composites, elucidating the fatigue response and fatigue properties of CFRP in different forms, discussing the importance of environmental factors on the fatigue performance and service-life, and summarising the different approaches taken to modelling fatigue in CFRP.

show abstract

Section: Effect Of Processing/manufacturing Defects On the Fatigue Prmentioning

confidence: 99%

The fatigue of carbon fibre reinforced plastics - A review

Alam

Mamalis

Robert

et al. 2019

Composites Part B: Engineering

275

View full text Add to dashboard Cite

show abstract

“…Figure 18. Algorithm of the model developed by Rabearison et al [28] A methodology was introduced in the literature [61] to estimate dimensional distortion of a carbon fiber-epoxy composite part upon being removed from the tool. Different phenomena were taken into consideration in this estimation, including cure shrinkage, cure kinetics, tool-part interaction, thermal strains, and improvement of the mechanical properties during cure.…”

Section: Numerical Modelsmentioning

confidence: 99%

“…Simulation results were compared with the experimental data subsequently and a good agreement was observed. As explained before, the methodology was introduced in the previous study for flat panels [61] . Several…”

Section: Numerical Studymentioning

confidence: 99%

See 1 more Smart Citation

Experimental and numerical study of distortion in flat, L‐shaped, and U‐shaped carbon fiber–epoxy composite parts

Roozbehjavan

Tavakol

Ahmed

et al. 2014

J of Applied Polymer Sci

Self Cite

View full text Add to dashboard Cite

In this study, flat composite panels were fabricated to find the effect of different manufacturing parameters, including stacking sequence, part thickness, and tooling material, on distortion of carbon fiber‐epoxy composite parts. L‐shaped and U‐shaped panels were also made to investigate the effect of stacking sequence on spring‐in angle and warpage of the curved panels. Results showed that distortion of the flat panels caused by asymmetry in the stacking sequence was an order of magnitude greater than distortion of the panels with an unbalanced stacking sequence; whereas in the curved panels, the panel with an asymmetric stacking sequence showed the least spring‐in angle, and the largest angle was observed in the symmetric panel. MSC Marc was used to predict distortion of the panels, and the simulation results were compared with the experimental results for several stacking sequences of the flat and the L‐shaped panels. © 2014 Wiley Periodicals, Inc. J. Appl. Polym. Sci. 2014, 131, 40439.

show abstract

“…Residual thermal stresses (thermal forces and moments) arise in the fabrication of laminated and filament wound composites due to differences in CTE in matrix-dominated and fiber-dominated directions, however these affects are beyond the scope of the present investigation [49]. As residual stresses are not to be assessed, the nature of the fibre-matrix interface and the resulting thermal mismatch will not be assessed.…”

Section: High Temperature Effectsmentioning

confidence: 97%

Carbon-carbon combustor for prolonged hypersonic flight: Developing and validating predictive manufacturing and design methods for ultra-high temperature composite assemblies

Papinczak¹

View full text Add to dashboard Cite

A thesis submitted in partial fulfilment of the requirements of the Bachelor of Engineering and Master of Engineering (BE/ME) degree in Mechanical and Materials Engineering To my family, thank you for all the times you reminded me to eat, told me to sleep or listened to me vent my frustrations. ACKNOWLEDGEMENTS "Keep moving forward…" (Walt Disney)i ABSTRACTWith modern developments in hypersonic flight vehicles and the associated improvements to overall space access and payload launch capability, cost effective methods for manufacturing ultra-high temperature composite assemblies is a topic of great interest. Utilising high temperature composite assemblies in-lieu of actively or passively cooled metallic assemblies has the potential to reduce total flight platform weight, allow for higher maximum flight speeds and improve payload mass fractions, albeit at the requirement of complex manufacturing and structural analysis methods. Filament winding, a process of winding unidirectional filament over a mandrel, is considered as a possible alternate and cost-effective manufacturing route for composite scramjet combustors, assuming sufficiently accurate design and analysis tools are developed to account for higher order and intrinsic manufacturing effects. In light of this, a series of coded modules and analysis tools were developed to account for unique filament winding effects. A virtual environment was developed to generate filament winding patterns, fibre trajectories, visualise 'checkerboard' mosaic patterns and provide manufacturing G-Code.Modified shell analysis methods were developed to quantify the characteristic in-plane fibre waviness, out-of-plane fibre undulation and alternating antisymmetric laminate arrangement in filament wound composite assemblies. Due to the dependence of analysis techniques on the fibre-matrix interface, constituent lamina properties and manufacturing processes, Toray T700s + Araldite GY191/Aradur 2961 carbon fibre cylinders were manufactured in order to validate the developed models in manufacturing of a high-temperature composite preform.Manufactured cylinders showed strong agreement with theoretical winding trajectories, however exhibited increasing non-uniformity and defect frequency with increasing filament winding pattern. This variability was validated by microscopy of composite sample interior planes that indicated a reduction in fibre volume fraction, increase in void-rich regions with higher order filament winding patterns and corresponding reduction in load-bearing capacity (in uniaxial compression). The developed combined out-of-plane undulation and mosaic model showed far better agreement with digital image correlation derived experimental moduli than unmodified classical lamination theory (26% versus 47%). The developed capabilities, including a graphical user interface (GUI), were utilised in a simplified design and analysis of a scramjet combustor to demonstrate the potential for ultra-high temperature composite assembly design assuming necessary modifications to models...

show abstract

Prediction of residual stresses and distortion in carbon fiber‐epoxy composite parts due to curing process using finite element analysis

Cited by 33 publications

References 24 publications

The fatigue of carbon fibre reinforced plastics - A review

The fatigue of carbon fibre reinforced plastics - A review

Experimental and numerical study of distortion in flat, L‐shaped, and U‐shaped carbon fiber–epoxy composite parts

Carbon-carbon combustor for prolonged hypersonic flight: Developing and validating predictive manufacturing and design methods for ultra-high temperature composite assemblies

Contact Info

Product

Resources

About