Mechanical analysis of hybrid structured aircraft wing ribs with different geometric gaps

Tümay Battal Akdoğan; İsmail Yasin Sülü

doi:10.1515/mt-2024-0033

Article

Mechanical analysis of hybrid structured aircraft wing ribs with different geometric gaps

Tümay Battal Akdoğan
Tümay Battal Akdoğan graduated with a BSc degree from the Mechanical Engineering Department, Engineering Faculty, İnönü University, Malatya, Turkey. He started his MSc in the Mechanical Engineering Department, Institute of Natural and Applied Sciences, İnönü University, Malatya, Turkey. During his MSc degree, he studied at Kielce University of Technology in Kielce, Poland for 5 months under the Erasmus+ program. Currently, he is working as a Hydraulic Workshop Engineer at Turkish Techic. His study areas are mechanics of composites and hybrid composites.
and İsmail Yasin Sülü
Associate Prof. İsmail Yasin Sülü graduated with a BSc degree from the Mechanical Engineering Department, Engineering Faculty, İnönü University, Malatya, Turkey. He finished his MSc in the Mechanical Engineering Department, Institute of Natural and Applied Sciences, Çukurova University, Adana, Turkey. Then, he received his PhD from the Mechanical Engineering Department, Institute of Natural Sciences, İnönü University. Currently, he is Associate Professor in the Mechanical Engineering Department, Engineering Faculty, İnönü University. His study areas are mechanics of composites, solid mechanics and mechanics of adhesives.

Published/Copyright: July 12, 2024

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From the journal Materials Testing Volume 66 Issue 8

Abstract

Wing ribs, which play a critical role in aviation, are an important design element, especially for unmanned aerial vehicles. Aircraft wing ribs are structural elements that generally extend from the wing root to the tip, used to maintain the shape of the wing, provide aerodynamic stability and add durability to the wing surface. In this study, the wing root rib of the MQ-1B Predator unmanned aerial vehicle were modeled with cavities with different geometric structures and its mechanical behavior were examined. Wing rib structures were created from circular, elliptical, slot and beam geometry gaps. The hybrid structure was created by considering the combined use of Carbon–Kevlar–Aramid. In the hybrid structure, the thickness of each fiber layer was taken into account as 0.25 mm and the wing rib consisted of six layers. The effects of different fiber angles in hybrid composite structures were also examined. As a result of the analyses, equivalent stress (von-Mises stress) and total deformation results were examined.

Keywords: composite material; aircraft wing; finite element method; stress; deformation

Corresponding author: İsmail Yasin Sülü, Mechanical Engineering, İnönü Üniversitesi, Malatya, Türkiye, E-mail: ismail.sulu@inonu.edu.tr

About the authors

Tümay Battal Akdoğan

Tümay Battal Akdoğan graduated with a BSc degree from the Mechanical Engineering Department, Engineering Faculty, İnönü University, Malatya, Turkey. He started his MSc in the Mechanical Engineering Department, Institute of Natural and Applied Sciences, İnönü University, Malatya, Turkey. During his MSc degree, he studied at Kielce University of Technology in Kielce, Poland for 5 months under the Erasmus+ program. Currently, he is working as a Hydraulic Workshop Engineer at Turkish Techic. His study areas are mechanics of composites and hybrid composites.

İsmail Yasin Sülü

Associate Prof. İsmail Yasin Sülü graduated with a BSc degree from the Mechanical Engineering Department, Engineering Faculty, İnönü University, Malatya, Turkey. He finished his MSc in the Mechanical Engineering Department, Institute of Natural and Applied Sciences, Çukurova University, Adana, Turkey. Then, he received his PhD from the Mechanical Engineering Department, Institute of Natural Sciences, İnönü University. Currently, he is Associate Professor in the Mechanical Engineering Department, Engineering Faculty, İnönü University. His study areas are mechanics of composites, solid mechanics and mechanics of adhesives.

Research ethics: Not applicable.
Author contributions: The authors have accepted responsibility for the entire content of this manuscript and approved its submission.
Competing interests: The authors state no conflict of interest.
Research funding: None declared.
Data availability: Not applicable.

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Published Online: 2024-07-12

Published in Print: 2024-08-27

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Articles in the same Issue

https://doi.org/10.1515/mt-2024-0033

Keywords for this article

composite material; aircraft wing; finite element method; stress; deformation