Effect of reinforcement and solvent content on moisture absorption in epoxy composite materials

Buehler, Frédéric U.; Seferis, James C.

doi:10.1016/s1359-835x(00)00036-1

Cited by 108 publications

(76 citation statements)

References 13 publications

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“…The disc was analyzed (256 scans) in a Perkin Elmer 2000 FTIR spectrophotometer, in transmission mode using KBr as the background reference. Analysis of wet composite carried out under the same conditions showed significant, but small, water peaks (free and bound) between 3650 and 3450 cm 21 for the initial $ 30-60 scans, but then these were lost by IR heating.…”

Section: Methodsmentioning

confidence: 89%

“…Considerable discussion and disagreement has occurred on the types of molecular environment of adsorbed water (bonded and nonbonded) and the types of absorption kinetics (Fickian or non-Fickian). [21][22][23][24][25][26][27][28][29][30] In contrast, the bulk of the industry testing has relied on the mechanical and fatigue (microcracking) effects on composite samples and has often used quite extreme conditions to accelerate changes. For example, the use of full water immersion at 708C, 908C, or even boiling water is common.…”

Section: Introductionmentioning

confidence: 99%

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Accelerated ageing versus realistic ageing in aerospace composite materials. IV. Hot/wet ageing effects in a low temperature cure epoxy composite

Dao

Hodgkin

Krstina

et al. 2007

J of Applied Polymer Sci

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Samples of an aerospace grade carbon fiber epoxy composite (Hexcel, M20/IM7) were subject to long term (%1 year) hot/wet ageing and thermal spiking under a variety of humidity levels and temperature conditions related to ''in service'' conditions seen by military aircraft. Changes to the chemical and physicochemical structure of the composite were analyzed by a range of different techniques including gravimetric analysis, FTIR, and DMA to compare the effects of the various ageing conditions. The results indicated that the chemical effects of hot/wet and spiking conditions on this incompletely cured type of composite are very complex because of the variations in moisture levels and cure chemistry from the composite surface inwards as the resin ages under the different external environments. Physicochemical changes (such as T g ) and structural effects (such as microcracking) are similarly complex and dependent on composite thickness.

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Section: Methodsmentioning

confidence: 89%

Section: Introductionmentioning

confidence: 99%

Accelerated ageing versus realistic ageing in aerospace composite materials. IV. Hot/wet ageing effects in a low temperature cure epoxy composite

Dao

Hodgkin

Krstina

et al. 2007

J of Applied Polymer Sci

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show abstract

“…Additionally, the composites can be used in other areas like home construction, navy, automotive and sport industries 3,4 . In general, aeronautical polymeric composites are classified as advanced and present continuous fiber reinforcement (for example, carbon, glass or aramide) of high-modulus or high-strength embedded in a thermoset or thermoplastic polymeric matrix.…”

Section: Introductionmentioning

confidence: 99%

Comparison of tensile strength of different carbon fabric reinforced epoxy composites

2006

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Carbon fabric/epoxy composites are materials used in aeronautical industry to manufacture several components as flaps, aileron, landing-gear doors and others. To evaluate these materials become important to know their mechanical properties, for example, the tensile strength. Tensile tests are usually performed in aeronautical industry to determinate tensile property data for material specifications, quality assurance and structural analysis. For this work, it was manufactured four different laminate families (F155/PW, F155/HS, F584/PW and F584/HS) using pre-impregnated materials (prepregs) based on F155 TM and F584 TM epoxy resins reinforced with carbon fiber fabric styles Plain Weave (PW) and Eight Harness Satin (8HS). The matrix F155TM code is an epoxy resin type DGEBA (diglycidil ether of bisphenol A) that contains a curing agent and the F584 TM code is a modified epoxy resin type. The laminates were obtained by handing lay-up process following an appropriate curing cycle in autoclave. The samples were evaluated by tensile tests according to the ASTM D3039. The F584/PW laminates presented the highest values of tensile strength. However, the highest modulus results were determined for the 8HS composite laminates. The correlation of these results emphasizes the importance of the adequate combination of the polymeric matrix and the reinforcement arrangement in the structural composite manufacture. The microscopic analyses of the tested specimens show valid failure modes for composites used in aeronautical industry.

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“…Glass/matrix interface: According to the experiments by Ray [49], the ILSS (interlaminar shear stress) of both carbon and glass /epoxy interfaces are reduced by 1.5 times (while it is 120 for carbon and 27 for glass in dry conditions; the same numbers are mentioned in [68], around 100 and 27 MPa). The authors of [72] noted that the mode I interlaminar fracture toughness decreases "upon water absorption for the glass fiber laminates, while the carbon fiber materials showed an increase in G IC under the same conditions. Mode II interlaminar fracture toughness as well as flexural modulus and flexural strength were observed to decrease upon water absorption, and to recover slightly after water desorption."…”

Section: Changing Materials Properties Under Environmental (Moisture) mentioning

confidence: 99%

Carbon nanotube reinforced hybrid composites: Computational modeling of environmental fatigue and usability for wind blades

Dai

Mishnaevsky

2015

Composites Part B: Engineering

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Effect of reinforcement and solvent content on moisture absorption in epoxy composite materials

Cited by 108 publications

References 13 publications

Accelerated ageing versus realistic ageing in aerospace composite materials. IV. Hot/wet ageing effects in a low temperature cure epoxy composite

Accelerated ageing versus realistic ageing in aerospace composite materials. IV. Hot/wet ageing effects in a low temperature cure epoxy composite

Comparison of tensile strength of different carbon fabric reinforced epoxy composites

Carbon nanotube reinforced hybrid composites: Computational modeling of environmental fatigue and usability for wind blades

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