Updating of Dynamic Model of Aircraft Structure with Wing Tip-tanks According to Results of Ground Vibration Test

Cecrdle, Jiri

doi:10.2514/6.2019-1529

Cited by 3 publications

References 6 publications

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Active flutter suppression for light sport aircraft by a control surface split

Kratochvíl,

Valenta

2024

CEAS Aeronaut J

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A new method of active flutter suppression is present in the paper and aims at the Light Sport Aircraft category, where it has never been used, designed, or even considered. The novelty of the method lies in splitting the control surface into a part controlled by a pilot with purely mechanical control and into a part controlled by a servo-actuator with a controller. The control law of the actuator is designed to follow the pilot-controlled part of the control surfaces and damp unstable oscillations if they occur. The controller design for flutter suppression is focused on achieving simple solutions. The request for simplicity is important for easy acquisition of airworthiness during a certification process and easy implementation by producers. The contribution of this paper also lies in the analysis of flutter suppression capability based on the varying active control surface span. The results show that it is not necessary to use the entire area of a control surface for active flutter suppression.A mathematical model based on a real aircraft is developed and verified for the simulation of active flutter suppression. In addition, control law design and simulations of the dynamic response are performed. The robustness of the control law and aircraft controllability in the case of active control surface malfunction is investigated.

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Active flutter suppression for light sport aircraft by a control surface split

Kratochvíl,

Valenta

2024

CEAS Aeronaut J

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Finite Element Model Updating for Very Flexible Wings

Sharqi

2023

Journal of Aircraft

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As aircraft wings become more flexible as a result of searching for more fuel efficient and higher performance solutions, structural nonlinearities become more apparent. Geometric nonlinearities make the structure’s modal parameters a function of the deformed shape and therefore of the loading condition. Modal characterization of very flexible structures is challenging due to these nonlinearities and the very low natural frequencies (the fundamental mode is typically below 1 Hz). In traditional, stiffer structures, a single shape is sufficient to characterize the structure through ground vibration testing and finite model updating due to its linear behavior. However, with very flexible structures, different deformed shapes have different modal parameters (frequencies, damping, and mode shapes). This paper investigates the impact of large displacements on the modal parameters (frequency and mode shapes) of very flexible structures and introduces a method to update the corresponding finite element model. Results are presented to discuss the impact of deformed shapes and the development and applicability of the procedure to general very flexible wing structures.

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Finite Element Model Updating for Very Flexible Wings

Sharqi

Cesnik

2022

AIAA SCITECH 2022 Forum

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Updating of Dynamic Model of Aircraft Structure with Wing Tip-tanks According to Results of Ground Vibration Test

Cited by 3 publications

References 6 publications

Active flutter suppression for light sport aircraft by a control surface split

Active flutter suppression for light sport aircraft by a control surface split

Finite Element Model Updating for Very Flexible Wings

Finite Element Model Updating for Very Flexible Wings

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