Login
Register
Open Access
ARTICLE
Aeroelasticity analysis of folding wing with structural nonlinearity using modified DLM
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
Download PDFAbstract
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.Keywords
Folding Wing; Modified Doublet Lattice Method; Rational Function Approximation; Structural Nonlinearity
Cite This Article
APA Style
Ni, Y., Li, P., Zhao, H., Qiao, S. (2024). Aeroelasticity analysis of folding wing with structural nonlinearity using modified DLM. Revista Internacional de Métodos Numéricos para Cálculo y Diseño en Ingeniería, 40(3), 1-15. https://doi.org/10.23967/j.rimni.2024.06.004
Vancouver Style
Ni Y, Li P, Zhao H, Qiao S. Aeroelasticity analysis of folding wing with structural nonlinearity using modified DLM. Rev int métodos numér cálc diseño ing. 2024;40(3):1-15 https://doi.org/10.23967/j.rimni.2024.06.004
IEEE Style
Y. Ni, P. Li, H. Zhao, and S. Qiao, “Aeroelasticity analysis of folding wing with structural nonlinearity using modified DLM,” Rev. int. métodos numér. cálc. diseño ing., vol. 40, no. 3, pp. 1-15, 2024. https://doi.org/10.23967/j.rimni.2024.06.004
Copyright © 2024 The Author(s). Published by Tech Science Press.This work is licensed under a Creative Commons Attribution 4.0 International License , which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
Downloads
Citation Tools
