Laboratory Results of a Real-Time SHM Integrated System on a P180 Full-Scale Wing-Box Section
Author:
Ciminello Monica1ORCID, Sikorski Bogdan1, Galasso Bernardino1, Pellone Lorenzo1ORCID, Mercurio Umberto1ORCID, Apuleo Gianvito2, Cirio Daniele2, Bosco Laura2, Cozzolino Aniello2, Kressel Iddo3, Shoham Shay3, Tur Moshe4ORCID, Concilio Antonio1ORCID
Affiliation:
1. Adaptive Structures Division, The Italian Aerospace Research Centre (CIRA), 81043 Capua, Italy 2. Research Division, Piaggio Aerospace Industries, 81043 Capua, Italy 3. Advanced Structural Technologies, Engineering Center, Israel Aerospace Industries (IAI), Ben Gurion International Airport, Tel Aviv 70100, Israel 4. School of Electrical Engineering, Tel Aviv University (TAU), Tel Aviv 69978, Israel
Abstract
The final objective of the study herein reported is the preliminary evaluation of the capability of an original, real-time SHM system applied to a full-scale wing-box section as a significant aircraft component, during an experimental campaign carried out at the Piaggio Lab in Villanova D’Albenga, Italy. In previous works, the authors have shown that such a system could be applied to composite beams, to reveal damage along the bonding line between a longitudinal stiffening element and the cap. Utilizing a suitable scaling process, such work has then been exported to more complex components, in order to confirm the outcomes that were already achieved, and, possibly, expanding the considerations that should drive the project towards an actual implementation of the proposed architecture. Relevant topics dealt with in this publication concern the application of the structural health monitoring system to different temperature ranges, by taking advantage of a climatic room operating at the Piaggio sites, and the contemporary use of several algorithms for real-time elaborations. Besides the real-time characteristics already introduced and discussed previously, such further steps are essential for applying the proposed architecture on board an aircraft, and to increase reliability aspects by accessing the possibility of comparing different information derived from different sources. The activities herein reported have been carried out within the Italian segment of the RESUME project, a joint co-operation between the Ministry of Defense of Israel and the Ministry of Defense of Italy.
Subject
Electrical and Electronic Engineering,Biochemistry,Instrumentation,Atomic and Molecular Physics, and Optics,Analytical Chemistry
Reference29 articles.
1. North Atlantic Treaty Organization (NATO) (2007). STANAG 4671 “UAV Systems Air Worthiness Requirements (USAR) for North Atlantic Treaty Organization (NATO)Military UAV Systems”, North Atlantic Treaty Organization (NATO). [1st ed.]. 2. (2022, March 12). EASA AMC 20–29 Composite Aircraft Structure. Available online: https://www.easa.europa.eu/downloads/1698/en. 3. Ewald, V., Groves, R., and Benedictus, R. (2017, January 12–14). Transducer Placement Option for Ultrasonic Lamb Wave Structural Health Monitoring (SHM) on Damage Tolerant Aircraft Substructure. Proceedings of the 11th International Workshop on Structural Health Monitoring (IWSHM) 2017: Real-Time Material State Awareness and Data-Driven Safety Assurance, Stanford, CA, USA. 4. Suleman, A. (2014). Structural Health Monitoring of Military Vehicles, NATO Science & Technology Organization. STO-EN-AVT-220. STO Educational Notes. 5. Acellent (2023, May 27). Localized (“Hot Spot”) Monitoring. Available online: https://www.acellent.com/applications/localized-monitoring.
|
|