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...
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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.
Composite structures need structural monitoring systems to improve maintenance and design processes. Maintenance may be supported by prompt detection of damage insurgence, moving towards condition-based rather than sc...
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ISBN:
(纸本)9781510625990;9781510626003
Composite structures need structural monitoring systems to improve maintenance and design processes. Maintenance may be supported by prompt detection of damage insurgence, moving towards condition-based rather than scheduled approaches. Design can attain adequate safety levels with lighter structures, in force of a continuous knowledge of their status. Required practices and systems are dependent on damage type, each with its own particularity;therefore, complex systems are necessary to respond to such a necessity. Among the many, bonding defects are particularly important. They can be classified as bonding deficiency, as adhesive misses in some parts, or de-bonding, as attachment collapses. Moving from activities performed within OPTICOMS, a project funded within the European flagship Clean Sky 2 JTI, the present work focuses on the preliminary characterization of bonding imperfections effect on selected composite aircraft components. In detail, how local adhesive absence influences static structural response and how this flaw type can be detected through a proprietary algorithm is investigated. A multi-element beam is referred, representing a main spar of the primary structure. A large numerical campaign is conducted on a tuned FE model, implementing different defect layouts, for size and location. Numerical structural response is computed through a representation of a distributed strain sensing system. Supported by a basic theoretical discussion, results are processed and commented, to individuate specific parameters that can describe applied failures. Finally, an in-house code verifies preliminarily its capabilities in exposing presence and size of the applied imperfections, correlating numerical outcomes with performed estimations.
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