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Experimental Modal Analysis of an Aircraft Wing Prototype for SAE Aerodesign Competition
Análisis modal experimental de un prototipo de ala de avión para la competencia SAE Aerodesign
DOI:
https://doi.org/10.15446/dyna.v87n214.85833Palabras clave:
Experimental modal analysis, Ground Vibration Testing, SAE Aerodesign, Modal Assurance Criterion (en)Análisis modal experimental, Prueba de vibración del suelo, SAE Aerodesign, Criterio de garantía modal (es)
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This work presents an experimental modal analysis of an aircraft wing prototype, designed by the Aerodesign team of the University of Brasilia, and performs a ground vibration testing of the prototype. The dynamic response data were acquired using the software LabVIEW, and the modal parameters were identified through the EasyMod toolbox. The modal parameters are characterised for the first seven vibration modes of the structure, with the firsts two being suspension modes of vibration. The effect of small changes in the experimental procedure on the identified modal parameters is discussed. It was observed that the use of an excitation signal as a logarithmic sine sweep and with a frequency range of excitation between 2 to 150 Hz resulted in less noise and more accurate measurement of the structure’s response. Results for different modal identification methods were verified using the Modal Assurance Criterion (MAC), and good correlation was achieved.
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CrossRef Cited-by
1. Rafael A. Márquez, Miguel A. Martínez, Manuel J. Martínez. (2021). Control surface design for radio-controlled aircraft. Case: SAE Aero Design Micro-class prototype. Revista Facultad de Ingeniería Universidad de Antioquia, https://doi.org/10.17533/udea.redin.20210740.
2. Thomas Kletschkowski. (2025). Analysis of a Vibrating Beam Structure in the Context of Hands-On Teaching in Structural Dynamics. Journal of Experimental and Theoretical Analyses, 3(4), p.31. https://doi.org/10.3390/jeta3040031.
3. Bi Ying, Ying Zhuolin, Zhu Zijian, Zhu Chen. (2024). Ground Servoelasticity Test and Analysis of UAVs With Large Aspect Ratio and Joined-Wing Layout. IEEE Access, 12, p.105370. https://doi.org/10.1109/ACCESS.2024.3426088.
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