A Parametric Study on the Aeroelasticity of Flared Hinge Folding Wingtips

This paper presents a parametric study on the aeroelasticity of cantilever wings equipped with Flared Hinge Folding Wingtips (FHFWTs). The finite element method is utilized to develop computational, low-fidelity aeroelastic model. wing structure modelled using Euler–Bernoulli beam elements, and unsteady Theodorsen’s aerodynamic strip Theory used for load predictions. PK estimate boundaries. model validated three rectangular, whose properties are available in literature. Then, effect folding wingtips response stability Two scenarios considered analysis. In first scenario, baseline, rectangular split into inboard outboard segments connected by flared hinge that allows segment fold. second wingtip added baseline wing. For both scenarios, influence fold angle, hinge-line angle (flare angle), stiffness, tip mass geometry assessed. addition, alleviation capability FHFWT evaluated when encounters discrete (1-cosine) gusts. Finally, assumed exhibit cubic nonlinear behavior torsion, nonlinearity assessed analyzed different cases.