Effect of Thermal and External Load on Mechanical Behaviour on CFRP/Aluminium Hybrid Joints

• Autorzy: Okada Takao , Takeda Tomo , Kumazawa Hisashi , Kasahara Toshiyuki , Miyashita Sho , Yamada Koichi , Nagao Kasumi , Aoki Yuichiro

Identyfikatory

DOI

10.2478/fas-2024-0002

• Języki publikacji: EN

Abstrakty

EN

JAXA has been conducted the research to evaluate the fatigue life up to form a certain size of fatigue crack in a CFRP/Aluminum hybrid joint. Thermal stress occurs in the hybrid joints during operation due to the difference of coefficient of thermal expansion between Aluminum and CFRP. In ICAF2023, we presented the experimental and numerical results for the hybrid joint under thermal cycles. In this study, the mechanically fastened hybrid joint specimens composed of two Aluminum plates and two CFRP plates are prepared. Most of the dimensions of the hybrid joint such as thickness, width of the plates and types and pitch of the fasteners and etc. are same as those evaluated in the previous research. The cyclic thermal and external loads are simultaneously applied to the hybrid joint and stress and strain on the Aluminum plate are evaluated experimentally and numerically. From the behavior of the elastic strain, which is the total strain minus the thermal strain, it is shown that when thermal load and external load are coupled, the hysteresis loop becomes larger than when only the external load is repeatedly applied. In addition, it is shown that the strain and stress around the fastener holes in the top row through the load direction are high, and this could be a critical area for fatigue failure.

Słowa kluczowe

EN

hybrid joints; thermal load; external load; hysteresis loop; fatigue fracture; finite element analysis

• Wydawca: Wydawnictwa Naukowe Sieci Badawczej Łukasiewicz - Instytutu Lotnictwa
• Czasopismo: Fatigue of Aircraft Structures
• Rocznik: 2024
• Tom: Iss.16
• Strony: 16--28
• Opis fizyczny: Bibliogr. 13 poz., fot., rys., tab., wykr.

Twórcy

autor

Okada Takao

• Japan Aerospace Exploration Agency, 7-44-1 Jindaiji Higashi-machi, Chofu-shi, Tokyo 182-8522, Japan

• https://orcid.org/0000-0002-2782-1955

autor

Takeda Tomo

• Japan Aerospace Exploration Agency, 7-44-1 Jindaiji Higashi-machi, Chofu-shi, Tokyo 182-8522, Japan

• https://orcid.org/0000-0002-2295-1590

autor

Kumazawa Hisashi

• Japan Aerospace Exploration Agency, 7-44-1 Jindaiji Higashi-machi, Chofu-shi, Tokyo 182-8522, Japan

• https://orcid.org/0009-0000-2838-135X

autor

Kasahara Toshiyuki

• Adecco Group Japan, 3-7-2 Sekitoukyuu Bld., Kasumigaseki, Chiyoda-ku, Tokyo, 100-0013, Japan

• https://orcid.org/0009-0008-5239-1564

autor

Miyashita Sho

• Former Japan Aerospace Exploration Agency

• https://orcid.org/0009-0008-4860-6569

autor

Yamada Koichi

• Former Japan Aerospace Exploration Agency

• https://orcid.org/0009-0007-7459-9158

autor

Nagao Kasumi

• Former Japan Aerospace Exploration Agency

• https://orcid.org/0009-0002-8688-8444

autor

Aoki Yuichiro

• Former Japan Aerospace Exploration Agency

• https://orcid.org/0000-0002-6174-9520

Bibliografia

• Bakuckas, J. J. (2002). Full-Scale testing and analysis of fuselage structure containing multiple cracks, final report (DOT/FAA/AR-01/46). Federal Aviation Administration.
• Battelle Memorial Institute (Red.). (2015). Metallic materials properties development and standardization MMPDS-10. Federal Aviation Administration.
• Boller, C., & Seeger, T. (2013). Materials data for cyclic loading, part D: Aluminium and titanium alloys (C. Laird, Red.). Elsevier.
• Eastin, R. (2009). ‘WFD’ - What is it and what’s ‘LOV’ got to do with it? International Journal of Fatigue, 31(6), 1012-1016. https://doi.org/10.1016/j.ijfatigue.2008.04.003
• Federal Aviation Administration. (2010). Aging Airplane Program: Widespread Fatigue Damage. Federal Register, 75(219). https://www.govinfo.gov/content/pkg/FR-2010-11-15/pdf/2010-28363.pdf
• Federal Aviation Administration. (2011). Establishing and implementing limit of validity to prevent widespread fatigue damage (AC 120-104).
• Li, G., Renaud, G., Liao, M., Okada, T., & Machida, S. (2017). A methodology for assessing fatigue life of a countersunk riveted lap joint. Advances in Aircraft and Spacecraft Science, 4(1), 1-19.
• Morimoto, T., Sugimoto, S., Kato, H., Hara, E., Yasuoka, T., Iwahori, Y., Ogasawara, T., & Ito, S. (2018). JAXA advanced composites database (in Japanese). JAXA Research and Development Memorandum, JAXA-RM-17-004, 1-230.
• Muller, R. P. G. (1995). An experimental and analytical investigation on the fatigue behaviour of fuselage riveted lap joints. Delft University of Technology.
• Okada, T., Kumazawa, H., Toyosawa, T., Takeda, T., Kasahara, T., Yamada, Y., Nagao, K., Aoki, Y., & Shoji, H. (2023). Research for thermal load and procedure to predict fatigue life up to form a fatigue crack on CFRP/Aluminum hybrid joints. Proceedings of the 31st ICAF Symposium. https://www.icaf.aero/icaf2023/proceedings/documents/118.pdf
• Seki, S., Arai, T., Fukushima, S., & Hosoi, A. (2017). Evaluation of fatigue life of thick CFRP laminates with toughened interlaminar layers in out-of-plane and in-plane transverse directions (in Japanese). Transaction of the JSME, 83(851), 16-00571. https://doi.org/10.1299/transjsme.16-00571
• Terada, H., Okada, T., & Dybskiy, P. (2001). Effect of load components on fatigue like of fuselage model structure. Proceedings of the International Committee on Aeronautical Fatigue 2001, 1, 263-272.
• Transport Airplane Metallic and Composite Structures Working Group. (2018). Transport Airplane Metallic and Composite Structures Working Group Recommendation Report. https://www.faa.gov/regulations_policies/rulemaking/committees/documents/media/TAMCSWG%20Recommendation%20Report.pdf

Uwagi

This article was presented at the 32nd Symposium of ICAF https://www.icaf2025.com/