Modal Parameters of Light Aircraft Wing

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Abstract
The main aim of this work is to extract modal parameters of a light aircraft wing. Modal parameters like modal frequency, modal damping and mode shapes characterise the dynamic response of a particular structure and can be used for determining an excess wing flexure as well as the long-term effect of fatigue. For the experimental part the response of the Piper Warrior II was recorded during ground runs. A set of temporarily attached accelerometers was used to record the response of the wing and the signals were recorded. Subsequently a Frequency Response Function was generated in the post-processing stage, which resulted in determining the first and second bending modes as well as the first twisting mode. A Finite Elements Model was applied to validate the results. Due to the limitations of the taxiing speed the method cannot excite higher frequency modes; however the findings can find numerous applications in real time in-flight flexure monitoring.
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Author(s)
Vulovic, Zoran
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Publication Year
2005
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Conference Paper
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UNSW Faculty
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download Published version.pdf 104.95 KB Adobe Portable Document Format
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