The Warping Restraint Effect in the Critical and Subcritical Static Aeroelastic Behavior of Swept Forward Composite Wing Structures 891056

An exact approach to the aeroelastic spanwise lift distribution and divergence instability of swept (aft and back) uniform composite wing structures is developed in this paper. The approach based on the Laplace transform technique enables one to solve in a unified manner both aeroelastic problems. The analysis encompasses the cases of free and restrained warping models for the wing twist. Numerical results are finally presented to demonstrate the effects played by the fiber-orientation, ply lay-up, warping restraint and wing geometry both on the subcritical static aeroelastic response and on the divergence instability of composite swept wings.


Subscribers can view annotate, and download all of SAE's content. Learn More »


Members save up to 43% off list price.
Login to see discount.
Special Offer: With TechSelect, you decide what SAE Technical Papers you need, when you need them, and how much you want to pay.