Flutter Mechanism of a Thin Plate Considering Attack Angles DOI Creative Commons

Chengjun Yan,

Qi Wang, Bo Wu

et al.

Applied Sciences, Journal Year: 2024, Volume and Issue: 14(20), P. 9380 - 9380

Published: Oct. 15, 2024

It is well known that the flutter performance of a section sensitive to changing wind angles attack. Exploring thin plate’s mechanism under different attack excellent, which helps understand inner characteristics and ensures structural safety. This study investigated derivatives plate with an aspect ratio 40 via forced vibration technique. The otherness aerodynamic damping phase lag angles, in understanding mechanism, are analyzed using bimodal-coupled method. shown coupled vertical–torsional dominated modality 0° 3° critical velocity dramatically decreased increasing attributed negative induced by self-excited forces decreasing positive uncoupled forces. Moreover, vertical motion lags behind torsional 7° angle attack, was totally contrary other Major works this reveal weakened plates large provide reference for analysis plates.

Language: Английский

A novel FSI model of composite blisk with blades-disk coupling and ROM-based for flutter analysis DOI
Qian Xu, Lei Hou,

Lixian Hou

et al.

Aerospace Science and Technology, Journal Year: 2025, Volume and Issue: unknown, P. 109961 - 109961

Published: Jan. 1, 2025

Language: Английский

Citations

0
An efficient dynamics frame of flexible C/SiC composite blisk with FSI for vibration response analysis DOI
Qian Xu, Lei Hou,

Lixian Hou

et al.

European Journal of Mechanics - A/Solids, Journal Year: 2025, Volume and Issue: unknown, P. 105659 - 105659

Published: April 1, 2025

Language: Английский

Citations

0
Dynamic Behavior and Stability Analysis of Composite Panels under Nonlinear Aeroelastic Conditions DOI

Kangjie Wang,

Junli Wang, Yang Zhou

et al.

Journal of Vibration Engineering & Technologies, Journal Year: 2025, Volume and Issue: 13(5)

Published: May 8, 2025

Language: Английский

Citations

0
Active aero-visco-elastic flutter control and layerwise modelling of supersonic smart sandwich panels with variable stiffness composites DOI Creative Commons
J.A. Moreira, F. Moleiro, A.L. Araújo

et al.

Aerospace Science and Technology, Journal Year: 2024, Volume and Issue: 157, P. 109847 - 109847

Published: Dec. 9, 2024

Language: Английский

Citations

2
A novel tensor-based modal decomposition method for reduced order modeling and optimal sparse sensor placement DOI
Zhirong Zhong, Xuanhao Hua, Zhi Zhai

et al.

Aerospace Science and Technology, Journal Year: 2024, Volume and Issue: 155, P. 109530 - 109530

Published: Aug. 30, 2024

Language: Английский

Citations

1
Single-mode flutter analysis of drag reduction spike by parameterized eigenvalue method and energy method DOI
Chengde Huang, Xiangyan Chen, Xueyuan Nie

et al.

Aerospace Science and Technology, Journal Year: 2024, Volume and Issue: 155, P. 109736 - 109736

Published: Nov. 14, 2024

Language: Английский

Citations

1
Optimization flutter response of laminated smart nanocomposite truncated conical shell under supersonic aerodynamic pressure using hybrid IGWO-DQHFEM DOI
L. Shan,

M. Furjan,

Reza Kolahchi

et al.

Aerospace Science and Technology, Journal Year: 2024, Volume and Issue: unknown, P. 109766 - 109766

Published: Nov. 1, 2024

Language: Английский

Citations

1
Flutter Mechanism of a Thin Plate Considering Attack Angles DOI Creative Commons

Chengjun Yan,

Qi Wang, Bo Wu

et al.

Applied Sciences, Journal Year: 2024, Volume and Issue: 14(20), P. 9380 - 9380

Published: Oct. 15, 2024

It is well known that the flutter performance of a section sensitive to changing wind angles attack. Exploring thin plate’s mechanism under different attack excellent, which helps understand inner characteristics and ensures structural safety. This study investigated derivatives plate with an aspect ratio 40 via forced vibration technique. The otherness aerodynamic damping phase lag angles, in understanding mechanism, are analyzed using bimodal-coupled method. shown coupled vertical–torsional dominated modality 0° 3° critical velocity dramatically decreased increasing attributed negative induced by self-excited forces decreasing positive uncoupled forces. Moreover, vertical motion lags behind torsional 7° angle attack, was totally contrary other Major works this reveal weakened plates large provide reference for analysis plates.

Language: Английский

Citations

0