Numerical Modal Analysis of an Aircraft Wing Prototype for Sae Aerodesign Competition

Gasparetto, Victor E. L.; Machado, Marcela; Carneiro, Sergio

doi:10.26678/abcm.cobem2019.cob2019-0647

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(3 citation statements)

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“…This section presents the experimental results obtained by GVT. The results of the experimental model presented were compared with the numerical results in [25]. Fig.…”

Section: Resultsmentioning

confidence: 99%

“…The modes identified were similar to the symmetric and fundamental asymmetric modes of bending and twisting. Those modes were also identified in the numerical model presented in [25]. The MAC criterion was used to verify the correlation between the modes obtained by the Line-Fit and Circle-Fit methods.…”

Section: Resultsmentioning

confidence: 99%

“…The main objective of the work is to experimentally determine the modal parameters of the structure of the aircraft wing designed for the SAE BRASIL Aero Design Competition. The numerical study and model calibration are presented in [25]. However, because research studies have demonstrated the application of experimental modal analysis (EMA) in aircraft, the contribution of this paper is its presentation of a comprehensive technical report on the experimental modal analysis of the aircraft wing for the SAE AeroDesign Competition by showing in detail the experimental setup and post-processing technique.…”

Section: Introductionmentioning

confidence: 99%

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Experimental Modal Analysis of an Aircraft Wing Prototype for SAE Aerodesign Competition

Gasparetto

Machado

Carneiro

2020

DYNA

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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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“…This section presents the experimental results obtained by GVT. The results of the experimental model presented were compared with the numerical results in [25]. Fig.…”

Section: Resultsmentioning

confidence: 99%

Section: Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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