Abstract:
The aerodynamic performance and flying safety of HALE (High Altitude and Long Endurance) UAVs are largely affected by the aeroelastic distortion of its large aspect ratio wing. Large aspect ratio wing of UAV is bended and twisted by the air load during flight and thus is not to be treated as a traditional rigid wing. The effect of static aeroelastic distortion to the aeroelasticity is analyzed for a large aspect ratio composite wing under different angle of attack statuses and the anisotropy of composite. The integrated design method combining aerodynamics with structural dynamics is adopted by computational fluid dynamics (CFD) program Fluent and computational structural dynamics (CSD) program ABAQUS. The results show that a lift coefficient? and lift drag ratio drop, but with the increase of angle of attack, the lift coefficient of the elastic wing increases faster, even more than the rigid body wing. The aerodynamic characteristics are obviously changed by adjusting the carbon fiber ply angle at the wing skin. When the ply angle is ±45°, the torsional rigidity of the wing reaches the maximum, and the lift coefficient and lift drag ratio are the largest.