Smart structure application for the Challenger aircraft

L. Grenier; Franz A. Blaha

doi:10.1117/12.184845

13 September 1994 Smart structure application for the Challenger aircraft

L. Grenier, Franz A. Blaha

Proceedings Volume 2361, Second European Conference on Smart Structures and Materials; (1994) https://doi.org/10.1117/12.184845
Event: Smart Structures and Materials: Second European Conference, 1994, Glasgow, United Kingdom

Abstract

The Challenger aircraft fleet of the Canadian Forces will fly demanding missions, requiring the implementation of a fatigue management program based on the monitoring of in-flight aircraft load conditions. Conventional sensing techniques experience problems arising from severe electromagnetic interference (EMI). This paper describes the development of an EMI- insensitive smart-structure sensing concept for loads monitoring. Fiber-optic strain sensors, incorporated at critical structural locations, are used to monitor the fatigue life of the aircraft wing, fuselage, and empennage. A fiber-optic accelerometer is also incorporated in the system. A long-term plan is presented for the development of an advanced smart-structure concept which can support the continuous monitoring of fatigue-prone components, and provide the aircraft with near real-time damage location and assessment.

Citation Download Citation

L. Grenier and Franz A. Blaha "Smart structure application for the Challenger aircraft", Proc. SPIE 2361, Second European Conference on Smart Structures and Materials, (13 September 1994); https://doi.org/10.1117/12.184845

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