Open Access

ARTICLE

Aeroelasticity analysis of folding wing with structural nonlinearity using modified DLM

Yingge Ni¹, Peicheng Li², Hui Zhao¹, Shengjun Qiao¹

1 School of Aircraft Engineering, Xi’an Aeronautical University, China
2 School of Aeronautics, Northwestern Polytechnical University, China

* Corresponding Author: Yingge Ni ()

Revista Internacional de Métodos Numéricos para Cálculo y Diseño en Ingeniería 2024, 40(3), 1-15. https://doi.org/10.23967/j.rimni.2024.06.004

Received 04 March 2024; Accepted 16 June 2024; Issue published 12 July 2024

Abstract

The structural nonlinear aeroelastic analysis of folding wings is conducted by integrating the modified Doublet Lattice Method in this paper. Firstly, a modified Doublet Lattice Method is investigated to relax the aspect ratio limitation of aerodynamic elements, and its correctness is verified through numerical examples. Secondly, the rational function approximation method is discussed, and the modified Doublet Lattice Method is approximated using the minimum state method to obtain the unsteady aerodynamic forces in the time domain. Finally, the aeroelastic characteristics of a folding wing with free-play and friction nonlinearity are studied by integrating time-domain unsteady aerodynamics with the nonlinear structural dynamics model. The results show that the modified Doublet Lattice Method, which relaxes the aspect ratio limitation of aerodynamic grid elements, is feasible and effective; Friction can suppress the influence of free-play nonlinearity on aeroelastic response.

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Keywords

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