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Mechanics of Composite Materials
Erschienen in: Mechanics of Composite Materials 4/2023

04.09.2023

An Analytical-Numerical Coupled Model for an Aeroelastic Analysis of Tail Flutter Based on Bending–Torsional Coupling

verfasst von: H. Nejatbakhsh, A. R. Ghasemi, A. Gharaei, H. R. Najafabadi

Erschienen in: Mechanics of Composite Materials | Ausgabe 4/2023

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Abstract

The aeroelastic instability is the mutual interaction of aerodynamic, structural, and inertial forces that can cause the flutter in aircraft structures. In this research, applying the coupling of a flutter with two degrees of freedom and the finite-element method, to a symmetric airfoil section of an aircraft tail, the flutter speed is investigated. The geometry and thickness of tail skin and isotropic and layups of composite materials are effective parameters of the torsional and bending stiffnesses of the airfoil section studied using the finite-element method. Lagrange’s equation is used to analyze the aeroelastic instability of the tail. Finally, the impact of the effective parameters on the flutter speed and instability of tail are discussed. The results obtained show that, at the same thickness, the flutter speed of angle-ply layups is higher than of quasi-isotropic composite laminates.
Vorheriger Artikel Influence of Polyethersulfone on the Fracture Toughness of Epoxy Matrices and Reinforced Plastics on Their Basis
Nächster Artikel Coil-Processing of CFRP Bandages for Rotors of High-Speed Synchronous Electric Machines with Permanent Magnets

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Metadaten
Titel
An Analytical-Numerical Coupled Model for an Aeroelastic Analysis of Tail Flutter Based on Bending–Torsional Coupling
verfasst von
H. Nejatbakhsh
A. R. Ghasemi
A. Gharaei
H. R. Najafabadi
Publikationsdatum
04.09.2023
Verlag
Springer US
Erschienen in
Mechanics of Composite Materials / Ausgabe 4/2023
Print ISSN: 0191-5665
Elektronische ISSN: 1573-8922
DOI
https://doi.org/10.1007/s11029-023-10129-3

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