Burhan Cetinkaya
Current Organizations / Institutes
The organizations/institutes from the scholar's latest article
Previous Organizations / Institutes
The organizations / institutes from the scholar's other articles in the past ten years
Research Subjects
Research Interests
Burhan Cetinkaya has a total of 6 co-authors. Here are the top co-authors by number of shared publications:
- Erdem Yilmaz
Metallurgy and Materials Engineering, Yıldız Technical University, Istanbul 34220, Türkiye
1 shared publication - Ibrahim Ozkol
Department of Aeronautics and Astronautics, Istanbul Technical University, Istanbul 34469, Türkiye
1 shared publication - İlhan Şen
Turkish Aerospace Industries, Ankara 06980, Türkiye
1 shared publication - Kazım TEKKANAT
Türk Havacılık ve Uzay Sanayii A.Ş.
1 shared publication - Orhan Gülcan
General Electric Aviation
1 shared publication - Tamer Saraçyakupoğlu
Turkish Aerospace Industries
1 shared publication
Latest Publications
- Open Access
- 23 June 2025
- Published by MDPI AG in Journal of Composites Science
- Vol. 9 (7) , 322
Development of Structural Model of Fiber Metal Laminate Subjected to Low-Velocity Impact and Validation by Tests
In today’s aviation industry, research and studies are carried out to manufacture and design lightweight, high-performance materials. One of the materials developed in line with this goal is glass laminate aluminum-reinforced epoxy (GLARE), which consists of thin aluminum sheets and S2-glass/epoxy layers. Because of its high impact resistance and excellent fatigue and damage tolerance properties, GLARE is used in different aircraft parts, such as the wing, fuselage, empennage skins, and cargo floors. In this study, a survey was carried out and a low-velocity impact model for GLARE materials was developed using the ABAQUS (2014) version V6.14 software and compared with the results of low-velocity impact tests performed according to the American Society for Testing and Materials (ASTM) D7136 standard. This article introduces a novel integrated approach that combines detailed numerical modeling with experimental validation of GLARE 4A FMLs under low-velocity impact. Leveraging ABAQUS, a robust FEM featuring explicit analysis, cohesive resin interfaces, and custom VUMAT subroutines was developed to accurately simulate energy absorption, dent depth, and delamination. The precise model’s predictions align well with test results performed according to ASTM D7136 standards, exhibiting less than a 0.1% deviation in the displacement (dent depth)–time response, along with deviations of 4.3% in impact energy–time and 5.2% in velocity–time trends at 5.5 ms.
- 23 June 2025
- Published by MDPI AG in Journal of Composites Science
- Vol. 9 (7) , 322
Open AccessDevelopment of Structural Model of Fiber Metal Laminate Subjected to Low-Velocity Impact and Validation by Tests
In today’s aviation industry, research and studies are carried out to manufacture and design lightweight, high-performance materials. One of the materials developed in line with this goal is glass laminate aluminum-reinforced epoxy (GLARE), which consists of thin aluminum sheets and S2-glass/epoxy layers. Because of its high impact resistance and excellent fatigue and damage tolerance properties, GLARE is used in different aircraft parts, such as the wing, fuselage, empennage skins, and cargo floors. In this study, a survey was carried out and a low-velocity impact model for GLARE materials was developed using the ABAQUS (2014) version V6.14 software and compared with the results of low-velocity impact tests performed according to the American Society for Testing and Materials (ASTM) D7136 standard. This article introduces a novel integrated approach that combines detailed numerical modeling with experimental validation of GLARE 4A FMLs under low-velocity impact. Leveraging ABAQUS, a robust FEM featuring explicit analysis, cohesive resin interfaces, and custom VUMAT subroutines was developed to accurately simulate energy absorption, dent depth, and delamination. The precise model’s predictions align well with test results performed according to ASTM D7136 standards, exhibiting less than a 0.1% deviation in the displacement (dent depth)–time response, along with deviations of 4.3% in impact energy–time and 5.2% in velocity–time trends at 5.5 ms.
- 27 December 2019
- Published by Makina Muhendisleri Odasi (Chamber of Mechanical Engineering) in Mühendis ve Makina
- Vol. 60 (697) , 262-288
A Review on Fiber Metal Laminates and Their Usage in Aerospace Industry
In todays competitive aerospace environment, it is very important to design and produce aircrafts with high performance and lightweights and in this context, to find new production processes and new production materials. Forth is reason, Fiber metal laminates (FML) developed by Delft University, are special composite materials that can be used as an alternative to the conventional aluminium materials used in aircrafts for their high fatigue resistance. The aim of this study is to provide a broad literature review about the history of FML, their usage areas, variants and properties (static, fatigue, impact, corrosion and thermal resistance) and to suggest research areas in the future.
- 27 December 2019
- Published by Makina Muhendisleri Odasi (Chamber of Mechanical Engineering) in Mühendis ve Makina
- Vol. 60 (697) , 262-288
A Review on Fiber Metal Laminates and Their Usage in Aerospace Industry
In todays competitive aerospace environment, it is very important to design and produce aircrafts with high performance and lightweights and in this context, to find new production processes and new production materials. Forth is reason, Fiber metal laminates (FML) developed by Delft University, are special composite materials that can be used as an alternative to the conventional aluminium materials used in aircrafts for their high fatigue resistance. The aim of this study is to provide a broad literature review about the history of FML, their usage areas, variants and properties (static, fatigue, impact, corrosion and thermal resistance) and to suggest research areas in the future.