Evaluation of Fretting Wear of Contact Surfaces of Composite Material-Aircraft Alloy in Nominally Stationary Joints of Aircraft Structures.
6 affiliations
- 1Department of Technical Sciences, Ma'an College, Al-Balqa Applied University, Al-Salt 19117, Jordan.
- 2Department of Air Transport, National University «Kyiv Aviation Institute», 03058 Kyiv, Ukraine.
- 3Department of Applied Mechanics and Materials Engineering, National University «Kyiv Aviation Institute», 03058 Kyiv, Ukraine.
- 4Department of Ecology, Chemistry and Chemical Technology, National University «Kyiv Aviation Institute», 03058 Kyiv, Ukraine.
- 5Department of Vibration and Thermostability Studies, Anatolii Pidhornyi Institute of Power Machines and Systems of the National Academy of Sciences of Ukraine, Komunalnykiv Str. 2/10, 61046 Kharkiv, Ukraine.
- 6Department of Materials Science and Engineering of Composite Structures, O.M. Beketov National University of Urban Economy in Kharkiv, Chornohlazivska Str. 17, 61002 Kharkiv, Ukraine.
Abstract
The article examines and analyzes the use of composite materials, such as carbon fiber-reinforced plastic (CFRP) and glass fiber-reinforced plastic (GFRP), in new-generation aircraft. Comparative studies were conducted on these composite materials alongside aviation alloys based on aluminum, titanium, and steel. It was determined that contact interfaces in nominally stationary joints suffer significant damage due to vibrational loads-stemming from aircraft engines and normal operations-a phenomenon classified as fretting corrosion. The study found that Al-CFRP/GFRP contact leads to the catastrophic degradation of friction surfaces caused by the formation of hard Al₂O₃ oxides. Ti-CFRP/GFRP contact is the most common configuration in new-generation aircraft; notably, the wear resistance of the composite materials is 6-20 times higher than that of the titanium alloy, owing to the inherent properties of titanium and its susceptibility to wear. Furthermore, the article analyzes surface processing and protection methods for titanium components aimed at enhancing the durability and wear resistance of these contact pairs.
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BibTeX
@article{alquraan2026evaluation,
title = {{Evaluation of Fretting Wear of Contact Surfaces of Composite Material-Aircraft Alloy in Nominally Stationary Joints of Aircraft Structures.}},
author = {Tareq M A Al-Quraan and Andrii Khimko and Oksana Mikosianchyk and Margaryta Khimko and Rudolf Mnatsakanov and Igor Trofimov and Natalia Smetankina and Andrii Kondratiev},
journal = {Materials (Basel, Switzerland)},
year = {2026},
month = oct,
doi = {10.3390/ma19204336},
url = {https://europepmc.org/article/MED/42941077},
note = {CC BY},
}
RIS
TY - JOUR
TI - Evaluation of Fretting Wear of Contact Surfaces of Composite Material-Aircraft Alloy in Nominally Stationary Joints of Aircraft Structures.
AU - Tareq M A Al-Quraan
AU - Andrii Khimko
AU - Oksana Mikosianchyk
AU - Margaryta Khimko
AU - Rudolf Mnatsakanov
AU - Igor Trofimov
AU - Natalia Smetankina
AU - Andrii Kondratiev
PY - 2026
DA - 2026/10/15
JO - Materials (Basel, Switzerland)
DO - 10.3390/ma19204336
UR - https://europepmc.org/article/MED/42941077
AB - The article examines and analyzes the use of composite materials, such as carbon fiber-reinforced plastic (CFRP) and glass fiber-reinforced plastic (GFRP), in new-generation aircraft. Comparative studies were conducted on these composite materials alongside aviation alloys based on aluminum, titanium, and steel. It was determined that contact interfaces in nominally stationary joints suffer significant damage due to vibrational loads-stemming from aircraft engines and normal operations-a phenomenon classified as fretting corrosion. The study found that Al-CFRP/GFRP contact leads to the catastrophic degradation of friction surfaces caused by the formation of hard Al₂O₃ oxides. Ti-CFRP/GFRP contact is the most common configuration in new-generation aircraft; notably, the wear resistance of the composite materials is 6-20 times higher than that of the titanium alloy, owing to the inherent properties of titanium and its susceptibility to wear. Furthermore, the article analyzes surface processing and protection methods for titanium components aimed at enhancing the durability and wear resistance of these contact pairs.
SN - 1996-1944
ER -