Input data determination for assessment of flutter resistance of small aircraft

Input data determination for assessment of flutter resistance of small aircraft

WoS Article

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.

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.

Aeroelasticity; Finite element analysis; Optimization

Aeroelasticity; Finite element analysis; Optimization

ŠPLÍCHAL, J.; NAVRÁTIL, J.; JURAČKA, J.

18.08.2025

EMERALD GROUP PUBLISHING LTD

Leeds

1748-8842

AIRCRAFT ENGINEERING AND AEROSPACE TECHNOLOGY

97

7

United Kingdom of Great Britain and Northern Ireland

833

844

12

https://doi.org/10.1108/AEAT-12-2024-0347