The effect of cure cycle heating rate on the fibre/matrix interface
Coenen, Victoria, Walker, Andrew, Day, Richard, Nesbitt, Alan, Zhang, Jin and Fox, Bronwyn 2007, The effect of cure cycle heating rate on the fibre/matrix interface, in Proceedings of the 28th Risø International Symposium on Materials Science: Interface Design of the Polymer Matrix Composites - Mechanics, Chemistry, Modelling and Manufacturing, Riso National Laboratory, Roskilde, Denmark, pp. 157-164.
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Proceedings of the 28th Risø International Symposium on Materials Science: Interface Design of the Polymer Matrix Composites - Mechanics, Chemistry, Modelling and Manufacturing
Sorensen. B.F. Mikkelsen, L.P. Lilholt, H. Goutianos, S. Abdul-Mahdi, F.S.
Riso International Symposium on Materials Science
Riso National Laboratory
Place of publication
Development of civil aerospace composites is key to future “greener” aircraft. Aircraft manufacturers must improve efficiency of their product and manufacturing processes to remain viable. The aerospace industry is undergoing a materials revolution in the design and manufacture of composite airframes. The Airbus A350 and Boeing 787 (both due to enter service in the latter part of this decade) will push utilisation levels of composite materials beyond 50% of the total airframe by weight. This change requires massive investment in materials technology, manufacturing capability and skills development. The Quickstep process provides the ability to rapidly cure aerospace standard composite materials whilst providing enhanced mechanical properties. Utilising fluid to transfer heat to the composite component during the curing process allows far higher heat rates than with conventional cure techniques. The rapid heat-up rates reduce the viscosity of the resin system greatly to provide a longer processing window introducing greater flexibility and removing the need for high pressure during cure. Interlaminar fracture toughness (Mode I) and Interfacial Shear Strength of aerospace standard materials cured using Quickstep have been compared to autoclave cured laminates. Results suggest an improvement in fibre-matrix adhesion.
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Field of Research
090199 Aerospace Engineering not elsewhere classified
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