The effect of cure cycle heating rate on the fibre/matrix interface

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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Title	The effect of cure cycle heating rate on the fibre/matrix interface
Author(s)	Coenen, Victoria Walker, Andrew Day, Richard Nesbitt, Alan Zhang, Jin Fox, Bronwyn
Conference name	Riso International Symposium on Materials Science (28th: 2007: Roskilde, Denmark)
Conference location	Roskilde, Denmark
Conference dates	3-6 September 2007
Title of proceedings	Proceedings of the 28th Risø International Symposium on Materials Science: Interface Design of the Polymer Matrix Composites - Mechanics, Chemistry, Modelling and Manufacturing
Editor(s)	Sorensen. B.F. Mikkelsen, L.P. Lilholt, H. Goutianos, S. Abdul-Mahdi, F.S.
Publication date	2007
Conference series	Riso International Symposium on Materials Science
Start page	157
End page	164
Publisher	Riso National Laboratory
Place of publication	Roskilde, Denmark
Summary	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.
Notes	Every reasonable effort has been made to ensure that permission has been obtained for items included in Deakin Research Online. If you believe that your rights have been infringed by this repository, please contact drosupport@deakin.edu.au
ISBN	8755036260 9788755036260
Language	eng
Field of Research	090199 Aerospace Engineering not elsewhere classified
HERDC Research category	E1 Full written paper - refereed
Persistent URL	http://hdl.handle.net/10536/DRO/DU:30008077

Document type:	Conference Paper
Collections:	Centre for Material and Fibre Innovation Open Access Collection

Every reasonable effort has been made to ensure that permission has been obtained for items included in DRO. If you believe that your rights have been infringed by this repository, please contact drosupport@deakin.edu.au.

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The effect of cure cycle heating rate on the fibre/matrix interface

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