Nonlinear aeroelastic stability analysis of in-plane functionally graded metal nanocomposite thin panels in supersonic flow

Hussein, Omar S.; Mulani, Sameer B.

doi:10.1016/j.tws.2019.03.016

Cited by 18 publications

(7 citation statements)

References 72 publications

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“…Therefore, only appropriate spatial discretization methods can be used to discretize the partial differential equations into finite dimensional ordinary‐differential equations for the solution. At present, the most commonly used discrete methods are the Galerkin method, 8,31,40,110 Rayleigh‐Ritz method 16,46,94,114 and FEM 6,10,24,38,111 …”

Section: Contents and Methods Of Aeroelastic Analysismentioning

confidence: 99%

“…After flutter occurs, the vibration amplitude of the structure in- are the Galerkin method, 8,31,40,110 Rayleigh-Ritz method 16,46,94,114 and FEM. 6,10,24,38,111 (1) Galerkin method: The Galerkin method is one of the earliest methods used in panel flutter analysis.…”

Section: Nonlinear Flutter Response Analysismentioning

confidence: 99%

“…Functionally graded materials (FGM) combine the excellent mechanical properties of metal materials and the heat‐resistance properties of ceramic materials. Therefore, the aerothermoelastic behaviors of FGM structures have attracted attention from many scholars 29–31 . In addition, as a new type of lightweight structures, the lattice sandwich structures have been proved to possess strong energy absorption, 32,33 heat insulation 34,35 and noise reduction characteristics 36,37 .…”

Section: Introductionmentioning

confidence: 99%

“…Therefore, the aerothermoelastic behaviors of FGM structures have attracted attention from many scholars. [29][30][31] In addition, as a new type of lightweight structures, the lattice sandwich structures have been proved to possess strong energy absorption, 32,33 heat insulation 34,35 and noise reduction characteristics. 36,37 Therefore, the lattice sandwich structures have a wide range of application prospects in the aerospace field.…”

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confidence: 99%

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Aeroelastic analysis and flutter control of wings and panels: A review

Chai

Gao

Ankay

et al. 2021

Int Journal of Mech Sys Dyn

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Flutter is a self-excited vibration under the interaction of the inertial force, aerodynamic force, and elastic force of the structure. After the flutter occurs, the aircraft structures will exhibit limit cycle oscillation, which will cause catastrophic accidents or fatigue damage to the structures. Therefore, it is of great theoretical and practical significance to study the aeroelastic characteristics and flutter control for improving the aeroelastic stability of aircraft structures. This paper reviews the recent advances in aeroelastic analysis and flutter control of wings and panel structures. The mechanism of aeroelastic flutter of wings and panels is presented. The research methods of aeroelastic flutter for different structures developed in recent years are briefly summarized. Various control strategies including the linear and nonlinear control algorithms as well as the active flutter control results of wings and panels are presented. Finally, the paper ends with conclusions, which highlight challenges of the development in aeroelastic analysis and flutter control, and provide a brief outlook on the future investigations. This study aims to present a comprehensive understanding of aeroelastic analysis and flutter control. It can also provide guidance on the design of new wings and panel structures for improving their aeroelastic stability.

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Section: Contents and Methods Of Aeroelastic Analysismentioning

confidence: 99%

Section: Nonlinear Flutter Response Analysismentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

mentioning

confidence: 99%

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Aeroelastic analysis and flutter control of wings and panels: A review

Chai

Gao

Ankay

et al. 2021

Int Journal of Mech Sys Dyn

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“…(1) 𝐷 ( 𝜕 4 𝑤 𝜕𝑥 4 + 2 𝜕 4 𝑤 𝜕𝑥 2 𝜕𝑦 2 + 𝜕 4 𝑤 𝜕𝑦 4 ) + 𝜌ℎ 𝜕 2 𝑤 𝜕𝑡 2 = 𝑝(𝑥, 𝑦, 𝑡) Boundary conditions for x=0 or x=Lx in different support modes are defined as follows: In this study, the first order piston theory is used. In this study, it is assumed that the flow only passes through the sheet and on the other side of the sheet there is only static air pressure.…”

Section: Figure1 View Of Rectangular Sheet In Supersonic Air Flowmentioning

confidence: 99%

Aerodynamic modeling and calculating the flutter speed of a rectangular plate in supersonic air flow

nazemizadeh,

Samadi Foroushan,

mohammadi ghanaghestani

2023

MASM

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The presented paper investigates the flutter phenomenon in a rectangular-shaped plate in supersonic air flow. First, the phenomenon of flutter and its identification method based on the analysis of eigenvalues are presented. Then, using the assumptions of Kirchhoff plate, the plate motion equation is derived and coupled with the first-order piston aerodynamic model. Next, the coupled structure-fluid equation is solved in matrix form using the differential quadrature method (DQM). Using the DQM numerical method in matrix form provides advantages such as high accuracy for solving the flutter problem. The obtained results show that the first phenomenon of flutter in an aluminum plate with a length and width of 1 meter and a thickness of 5 mm with clamped-free-clamped-free boundary conditions occurs in dimensionless dynamic pressure 617 (equivalent to Mach 3.395). The presented formulation can be used as a benchmark for solving and calculating the flutter speed of various objects in the supersonic air flow.

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