Ageing of a carbon epoxy composite for aeronautic applications

Bellenger, V.; Decelle, J.; Huet, Nathalie

doi:10.1016/j.compositesb.2004.04.016

Cited by 53 publications

(29 citation statements)

References 14 publications

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“…The oxidation mechanism is limited to superfi cial layers and from a kinetic point of view, in general, it is diffusion-controlled in the parallel direction to fi bres whereas it is controlled by the chemical reaction kinetics in the transverse direction. 59 The presence of carbon fi bres does not promote a specifi c effect on the weight loss induced by oxidation at the ageing temperature under consideration.…”

Section: Modelling Chemical Ageingmentioning

confidence: 99%

“…With particular reference to thermo-oxidative ageing, there are two ways to accelerate the process: 59 increasing temperature and increasing pressure of oxygen. It has been suggested by Tsotsis and Lee 15 that more realistic accelerated ageing results are obtained by the use of high-pressure air ageing at lower temperatures.…”

Section: Accelerated Thermal Degradation and Oxidationmentioning

confidence: 99%

“…As an example, for the case of epoxy matrices, it is possible to simulate the weight loss and the density increase of an epoxy matrix induced by oxidation with a kinetic model of radical chain oxidation coupled with the equation of oxygen diffusion. 59 The reaction can be modelled 59 with a closed-loop radicalic oxidation mechanistic scheme. From this scheme a set of differential equations can be derived (balance of species) which describe the concentration evolution of reactive species.…”

Section: Modelling Chemical Ageingmentioning

confidence: 99%

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Modelling accelerated ageing in polymer composites

Mensitieri

Iannone²

2008

Ageing of Composites

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Section: Modelling Chemical Ageingmentioning

confidence: 99%

Section: Accelerated Thermal Degradation and Oxidationmentioning

confidence: 99%

Section: Modelling Chemical Ageingmentioning

confidence: 99%

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Modelling accelerated ageing in polymer composites

Mensitieri

Iannone²

2008

Ageing of Composites

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“…Many researchers used weight loss models to study the thermo-oxidation of polymer and polymer matrix composites. Bellenger et al [5] studied the weight loss of unidirectional carbon/epoxy composites aged at 150 and 180°C. Weight loss was estimated as the sum of grafted oxygen on the matrix and eliminated water and volatiles by solving a closed-loop mechanistic scheme of reactions.…”

Section: Introductionmentioning

confidence: 99%

Anisotropic oxidation prediction using optimized weight loss behavior of bismaleimide composites

2016

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High-temperature polymer matrix composites are susceptible to thermo-oxidation, which accelerates their degradation and reduces the service life. This work presents the viability of using experimental weight loss for modeling the spatial distribution of oxidation when the oxidized polymer matrix is not discernible due to cracking. The oxidized layer thickness and weight loss were predicted at a microscale level by implementing a volumetric integral in finite element analysis and scaled to a macroscale level by respective area ratios. Weight loss was shown to have a spatial distribution following the three-zone model. The proportionality parameter was optimized by fitting the scaled finite element predictions to the experimental results using artificial neural networks and a generalized pattern search algorithm. Aging experiments have been conducted at the operating temperature range of BMIs, 176.67°C (350°F) and 200°C (392°F). Optical dark field images were acquired to monitor longitudinal and transverse oxidation. Microscale simulations were conducted using representative volume elements utilizing COMSOL Multiphysics. A novel characteristic index for describing the completely oxidized matrix was the weight loss per unit volume that equals 0.44 mg/lm 3 as shown by spatial distribution simulations. The orthotropic diffusivity resulted in a higher degree of anisotropy in the oxidized thickness compared to the weight loss %. At the representative volume element scale, the oxidized layer thickness simulations showed a higher degree of non-linearity at higher temperatures stemming from the cracking effect.

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“…25,26 Among these environment factors, the effect of moisture absorption and hygrothermal condition can deteriorate dynamic properties of CFRP composites such as compressive strength, transverse strength, interlaminar shear strength, fatigue resistance, impact tolerance, and interfacial adhesive. 27-37 Pei 27 and Lee 28 studied the effect of various temperature and cyclic hygrothermal aging on the interlaminar shear strength of CFRP composites.…”

Section: Introductionmentioning

confidence: 99%

Effect of hygrothermal condition on buckling and post-buckling performance of CCF300/5228A aero composite stiffened panel under axial compression

Feng

et al. 2015

Journal of Reinforced Plastics and Composites

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CCF300/5228A aero composite stiffened panels achieved absorbing saturation in hygrothermal condition (70 C distilled water), whose absorbing process followed the Fick law. Many debonding and gaps of matrix to fibers could be observed after hygrothermal exposure by scanning electron microscope (SEM). Compressive experiments were conducted on unaged and aged composite stiffened panels. Failure modes of the two types of specimens are quite similar with several major ways, including the debonding and fracture of stiffeners together with the splitting and ripping of panel. Buckling patterns for both types of specimens are similar and characterized by buckling of panels between stiffeners and buckling of the middle two stiffeners. However, the bending direction of buckling mid-panel for aged specimens is opposite to that of the unaged at same position panel, which shows that hygrothermal condition influences the bending direction of buckling mid-panels seriously. There still exists a post-buckling process for aged specimens under axial compression, whose average buckling load and failure load decrease by 3.1% and 22.2% respectively, comparing to that of unaged specimens.

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Ageing of a carbon epoxy composite for aeronautic applications

Cited by 53 publications

References 14 publications

Modelling accelerated ageing in polymer composites

Modelling accelerated ageing in polymer composites

Anisotropic oxidation prediction using optimized weight loss behavior of bismaleimide composites

Effect of hygrothermal condition on buckling and post-buckling performance of CCF300/5228A aero composite stiffened panel under axial compression

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