Version 1
: Received: 21 June 2023 / Approved: 21 June 2023 / Online: 25 June 2023 (04:35:14 CEST)
How to cite:
Marano, A.D.; Guida, M.; Polito, T.; Marulo, F. Comparison of Aeroelastic Problems Calculation Methods Based on Numerical and Experimental Results. Preprints2023, 2023061585. https://doi.org/10.20944/preprints202306.1585.v1
Marano, A.D.; Guida, M.; Polito, T.; Marulo, F. Comparison of Aeroelastic Problems Calculation Methods Based on Numerical and Experimental Results. Preprints 2023, 2023061585. https://doi.org/10.20944/preprints202306.1585.v1
Marano, A.D.; Guida, M.; Polito, T.; Marulo, F. Comparison of Aeroelastic Problems Calculation Methods Based on Numerical and Experimental Results. Preprints2023, 2023061585. https://doi.org/10.20944/preprints202306.1585.v1
APA Style
Marano, A.D., Guida, M., Polito, T., & Marulo, F. (2023). Comparison of Aeroelastic Problems Calculation Methods Based on Numerical and Experimental Results. Preprints. https://doi.org/10.20944/preprints202306.1585.v1
Chicago/Turabian Style
Marano, A.D., Tiziano Polito and Francesco Marulo. 2023 "Comparison of Aeroelastic Problems Calculation Methods Based on Numerical and Experimental Results" Preprints. https://doi.org/10.20944/preprints202306.1585.v1
Abstract
The current design process of a new aircraft includes several mod- eling and testing steps.The main purpose of the Ground Vibration Testing is to achieve experimental vibration data of the whole aircraft structure, in terms of frequencies, damping factors, and mode shapes to ensure that the aircraft will be free from any aeroelastic instability and safe to fly in the desired flight envelope. GVT results are also mainly used for validating and eventually im- proving FEM models of the aircraft examined. On the other hand, structural dynamic models are used to predict the flutter behavior and carefully plan the in-flight flutter tests, and lead to mitigation of the risks related to them. This paper aims to compare different aeroelastic methods outcomes achieved using two diverse commercial software: the widely used NASTRAN™ and the most recently developed Zonatech ZAERO. The flutter computation results are obtained by means of P-K, K, and G methods. The first case presented is the aeroelastic analysis of a forward-swept wing whereas the second case concerns the stabilator of a two-seater ultralight aircraft, for which an experimental campaign of vibrations test is also carried out. The structural mode shapes at each generated frequency mode are also visually presented.
Copyright:
This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
