Input data determination for assessment of flutter resistance of small aircraft
The result's identifiers
Result code in IS VaVaI
<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00216305%3A26210%2F26%3A0197941" target="_blank" >RIV/00216305:26210/26:0197941 - isvavai.cz</a>
Result on the web
<a href="https://doi.org/10.1108/AEAT-12-2024-0347" target="_blank" >https://doi.org/10.1108/AEAT-12-2024-0347</a>
DOI - Digital Object Identifier
<a href="http://dx.doi.org/10.1108/AEAT-12-2024-0347" target="_blank" >10.1108/AEAT-12-2024-0347</a>
Alternative languages
Result language
angličtina
Original language name
Input data determination for assessment of flutter resistance of small aircraft
Original language description
Purpose - This paper aims to present a comprehensive approach to evaluating aircraft resistance to aeroelastic phenomena, emphasizing the challenges of accurately determining the stiffness of structural components. It focuses on the development and validation of finite element (FE) models, detailing critical steps and addressing uncertainties. This paper concludes by examining the influence of rudder balancing on the occurrence and mitigation of aeroelastic phenomena. Design/methodology/approach - Elastic and aeroelastic FE models were developed using the MSC.Patran/Nastran system. A parametric optimization module was used to adjust stiffness parameters of key components, aligning modal analysis results with ground vibration test data. Extensive measurements and simulations on real aircraft ensured the robustness of the approach. The validated models were applied to assess the resistance of the aircraft to aeroelastic phenomena. Findings - Despite the significant variability in initial stiffness parameters, the models were refined through optimization to achieve high accuracy, reducing the difference between measured and calculated frequencies to below 10%. The analysis highlighted the critical impact of rudder balancing, demonstrating its potential to increase flutter speed and, in some cases, entirely mitigate specific aeroelastic modes. Originality/value - This paper presents a new perspective on the approach to the development and validation of FE models used to assess aircraft resistance to aeroelastic phenomena. It addresses the inherent inaccuracies in the initial input parameters for these models and emphasizes the critical need for model validation. By systematically refining these models through ground vibration testing and optimization, the approach ensures greater reliability in the determination of aeroelastic resistance of the aircraft.
Czech name
—
Czech description
—
Classification
Type
J<sub>imp</sub> - Article in a specialist periodical, which is included in the Web of Science database
CEP classification
—
OECD FORD branch
20300 - Mechanical engineering
Result continuities
Project
—
Continuities
S - Specificky vyzkum na vysokych skolach
Others
Publication year
2025
Confidentiality
S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů
Data specific for result type
Name of the periodical
Aircraft Engineering and Aerospace Technology
ISSN
1748-8842
e-ISSN
1758-4213
Volume of the periodical
97
Issue of the periodical within the volume
7
Country of publishing house
GB - UNITED KINGDOM
Number of pages
12
Pages from-to
833-844
UT code for WoS article
001489441000001
EID of the result in the Scopus database
2-s2.0-105005544926