AEROELASTIC ANALYSIS OF A THIN-WALLED COMPOSITE AIRCRAFT WING WITH AN EXTERNAL STORE SUBJECTED TO A FOLLOWER FORCE


Aksongur A. K. , Eken S., Kaya M. O.

ASME International Mechanical Engineering Congress and Exposition (IMECE), Montreal, Canada, 14 - 20 November 2014 identifier

  • Publication Type: Conference Paper / Full Text
  • City: Montreal
  • Country: Canada

Abstract

This study reports dynamic aeroelastic analyses of an aircraft wing with an attached mass subjected a lateral follower force in an incompressible flow. A swept thin-walled composite beam with a biconvex cross-section is used as the structural model that incorporates a number of non-classical effects such as material anisotropy, transverse shear deformation and warping restraint. A symmetric lay-up configuration i.e. circumferentially asymmetric stiffness (CAS) is further adapted to this model to generate the coupled motion of flapwise bending-torsion transverse shear. For this beam model, the unsteady aerodynamic loads are expressed using Wagners function in the time domain as well as using Theodorsen function in the frequency domain. The flutter speeds are evaluated for several ply angles and the effects of follower force, transverse shear, fiber orientation and sweep angle on the aeroelastic instabilities are further discussed.