A Parametric Study on the Aeroelasticity of Flared Hinge Folding Wingtips

Aerospace

Erick I. Saavedra Flores¹  Rafic M. Ajaj²  Mohammadreza Amoozgar³  Jonathan E. Cooper⁴ 

[1] Departamento de Ingeniería en Obras Civiles, Universidad de Santiago de Chile, Av. Ecuador, Santiago 3659, Chile;Department of Aerospace Engineering, Khalifa University of Science and Technology, Abu Dhabi 127788, United Arab Emirates;Department of Mechanical, Materials and Manufacturing Engineering, University of Nottingham, Nottingham NG7 2RD, UK;Dynamics and Control Group, Department of Aerospace Engineering, University of Bristol, Bristol BS8 1TR, UK;

关键词: folding wingtips;    flared hinge;    finite element method;    aeroelasticity;    structural nonlinearities;   

DOI  :  10.3390/aerospace8080221

来源: DOAJ

【 摘 要 】

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

【 授权许可】

Unknown