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.


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    Title :

    Smart structure application for the Challenger aircraft


    Contributors:

    Conference:

    Second European Conference on Smart Structures and Materials ; 1994 ; Glasgow,United Kingdom


    Published in:

    Publication date :

    1994-09-13





    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



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