STRUCTURAL OPTIMIZATION OF AN AEROELASTICALLY TAILORING COMPOSITE FLAT PLATE MADE OF WOVEN FIBREGLASS/EPOXY
Keywords:
Aeroetasuc tailoring.flutter, optimization, Doublet-lattice Method.Abstract
Effects of aspect ratio, sweep angle. and stacking sequence of laminated composites were
studied to find the optimized configuration of on aeroelastically tailored composite wing
idealized as a flat plate in terms of flutter speed The aeroelastic analysis has been carried
out in frequency-domain. The 2D finite element analysis in conjunction with Doubletlattice
Method (DLM) has been opted for structural and unsteady aerodynamic analysis.
respectively. The interpolation between aerodynamic boxes and structural nodes has been
done using surface spline To study the effect of stacking sequence the classical Iamination
theory (CLT) has been chosen. All the analyses have been implemented in
MSC.NASTRAN/PATRAN. The parametric studies showed the effective ply orientation
angle to be somewhere between 15 and 30 degree, while the plates with lower aspect ratio
seems to have higher flutter speed Forward swept configurations show higher flutter
speed. yet imposed by divergence constraint.
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