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2025 | OriginalPaper | Chapter

Detection of Impact Damages on Full Scale Wing Using Distributed Fiber Optics Sensors Network

Authors : M. Ciminello, L. Pellone, F. Romano

Published in: Dynamic Response and Failure of Composite Materials

Publisher: Springer Nature Switzerland

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Abstract

The aviation industry aims to reduce costs in aircraft design, manufacturing, and maintenance. Structural Health Monitoring (SHM) is a key technique for monitoring the health of aircraft structures, providing valuable data throughout their operational life. This data can enhance design techniques, production control, real-time structural health evaluations, and maintenance plans, improving reliability and safety.

This study examines the effectiveness of distributed fiber optic sensors in detecting impact damage on a full-scale composite wing. The sensors track changes in strain distribution caused by controlled impacts at predefined locations. A specific algorithm developed by CIRA identifies the position and size of the damage without relying on reference systems of the undamaged structure. Through structural tests under load, the SHM system’s accuracy in detecting damage was experimentally validated.

Funded by the Clean Sky 2 Joint Undertaking under the EU Horizon 2020 program, this research advances SHM techniques for aeronautical applications and presents an alternative to traditional Non-Destructive Inspection (NDI) methods.

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previous chapter Mesh and Homogenization Effects of Simulated High Strain Rate Delamination in CFRP Using VCCT

next chapter Evolution of Unstable Skin-Stringer Debonding Propagation in Composite Aircraft Structures: Implications on Damage Tolerant Design

FAA – AC 20–107B: Composite Aircraft Structure (2010)

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Monica Murthy, N., Desai Kakade, P.: Review on strain monitoring of aircraft using optical fiber sensor. Int. J. Electron. Telecommun. 68(3), 625–634 (2022). https://doi.org/10.24425/ijet.2022.141282CrossRef

De Martin, A., Sorli, M., Jacazio, G.: Integrated health monitoring for robust actuation system of UAV primary flight controls. Int. J. Mech. Control. 91–104 (2019)

Ciminello, M., et al.: Cross-correlation based algorithm for SHM de-bonding analysis of typical aeronautical structures via OFDR. In: Rizzo, P., Milazzo, A. (eds.) European Workshop on Structural Health Monitoring: EWSHM 2022 - Volume 1, pp. 254–263. Springer International Publishing, Cham (2023). https://doi.org/10.1007/978-3-031-07254-3_25CrossRef

Concilio A., Ciminello M., Apuleo G., Kressel I., Shoham S., Bardenstein D.: Preliminary Characterization of Bonding Defects in Multi-Element Spars. In: SPIE Smart Structures and NDE Conference 2019, Denver (CO-USA), 3–7 Marzo 2019. https://doi.org/10.1117/12.2514297

Concilio, A., et al.: De-bonding numerical characterization and detection in aeronautic multi-element spars. Sensors 22(11), 4152 (2022). https://doi.org/10.3390/s22114152CrossRefPubMedPubMedCentral

Title: Detection of Impact Damages on Full Scale Wing Using Distributed Fiber Optics Sensors Network
Authors: M. Ciminello
L. Pellone
F. Romano
Publisher: Springer Nature Switzerland
Book: Dynamic Response and Failure of Composite Materials
Print ISBN: 978-3-031-77696-0

Electronic ISBN: 978-3-031-77697-7

Copyright Year: 2025
DOI: https://doi.org/10.1007/978-3-031-77697-7_2