Finite Element Analysis of Functionally Graded Mindlin–Reissner Plates for Aircraft Tapered and Interpolated Wing Defluxion and Modal Analysis

Ali Hajjia (), Mohammed Berrada Gouzi, Bilal Harras, Ahmed El Khalfi (), Sorin Vlase and Maria Luminita
Additional contact information
Ali Hajjia: Al Idrissi Research Laboratory in Science and Engineering, Faculty of Science and Technology, Sidi Mohamed Ben Abdellah University, Fez 30000, Morocco
Mohammed Berrada Gouzi: Al Idrissi Research Laboratory in Science and Engineering, Faculty of Science and Technology, Sidi Mohamed Ben Abdellah University, Fez 30000, Morocco
Bilal Harras: Al Idrissi Research Laboratory in Science and Engineering, Faculty of Science and Technology, Sidi Mohamed Ben Abdellah University, Fez 30000, Morocco
Ahmed El Khalfi: Al Idrissi Research Laboratory in Science and Engineering, Faculty of Science and Technology, Sidi Mohamed Ben Abdellah University, Fez 30000, Morocco
Sorin Vlase: Department of Mechanical Engineering, Faculty of Mechanical Engineering, Transylvania University of Brasov, B-dul Eroilor 29, 500036 Brasov, Romania
Maria Luminita: Department of Mechanical Engineering, Faculty of Mechanical Engineering, Transylvania University of Brasov, B-dul Eroilor 29, 500036 Brasov, Romania

Mathematics, 2025, vol. 13, issue 4, 1-23

Abstract: This paper explores and discusses how wing structures vibrate by using the Mindlin–Reissner plate theory, which takes into consideration the effects of transverse shear deformation and rotary inertia. This theory works well for thicker structures, like aircraft wings, where it gives accuracy by detecting shear and rotation effects. FGMs, or functionally graded materials, are used in aviation to enhance structural patterns and reduce stress points by gradually changing material properties along the wing thickness based on the volume fraction index. Finite element method (FEM) simulations were conducted to compare the natural frequencies and mode shapes of tapered and interpolated wing geometries. The results indicate that interpolated meshes exhibit higher natural frequencies due to increased stiffness, whereas tapered meshes show lower frequencies due to their flexibility. Validation through ANSYS simulations confirms the accuracy of the FEM results, highlighting the influence of geometry and material gradation on vibrational behavior. The findings offer valuable insights for aerospace applications, supporting the development of lightweight and efficient wing designs.

Keywords: functionally graded materials; Mindlin–Reissner theory; finite element analysis; modal analysis; aircraft wings; interpolated mesh; tapered mesh (search for similar items in EconPapers)
JEL-codes: C (search for similar items in EconPapers)
Date: 2025
References: View complete reference list from CitEc
Citations:

Downloads: (external link)
https://www.mdpi.com/2227-7390/13/4/620/pdf (application/pdf)
https://www.mdpi.com/2227-7390/13/4/620/ (text/html)

Related works:
This item may be available elsewhere in EconPapers: Search for items with the same title.

Export reference: BibTeX RIS (EndNote, ProCite, RefMan) HTML/Text

Persistent link: https://EconPapers.repec.org/RePEc:gam:jmathe:v:13:y:2025:i:4:p:620-:d:1590838

Access Statistics for this article

Mathematics is currently edited by Ms. Emma He

More articles in Mathematics from MDPI
Bibliographic data for series maintained by MDPI Indexing Manager ().