28th Congress of the International Council of the Aeronautical Sciences, 23 - 28 September 2012, Brisbane, Australia
Paper ICAS 2012-8.9.3

BUCKLING-OPTIMIZED VARIABLE STIFFNESS LAMINATES FOR A COMPOSITE FUSELAGE WINDOW SECTION

W. Van den Brink, W. J. Vankan, R. Maas
NLR, Netherlands

Keywords: variable stiffness laminates, window panel design, optimization, fem, automated fiber placement

In this research a variable stiffness method for optimization of composite laminates is proposed and presented on a realistic aerospace application; a composite fuselage window section including frames and stiffeners which is loaded in shear. Through fibre steering, an increase in buckling resistance and better internal load distribution is achieved.

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