Aeroelastic analysis of cantilever plates using Peters’ aerodynamic model, and the influence of choosing beam or plate theories as the structural model

Modaress-Aval, Amir Hossein; Bakhtiari-Nejad, Firooz; Dowell, Earl H.; Shahverdi, Hossein; Rostami, Hamidreza; Peters, David A.

doi:10.1016/j.jfluidstructs.2020.103010

Cited by 5 publications

(3 citation statements)

References 26 publications

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“…This model is based on the assumption of incompressible potential flow, and consequently, the effects of viscosity have been neglected. 35 The aerodynamic moment and force can be written as 36 where a is referred to the aerodynamic reference axis, b is the semi-chord, and ρ is the air density. Also, λ is a column matrix which includes inflow states, and [Ainflow], {binflow}, {cinflow} are constant matrices derived in Peters and Karunamoorthy 34 work.…”

Section: Governing Equationsmentioning

confidence: 99%

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Nonlinear aeroelastic stability analysis of a two-stage axially moving telescopic wing by using fully intrinsic equations

Barzani

Shahverdi

Amoozgar

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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During the process of span extension for an aircraft wing equipped with a telescopic morphing mechanism, the wing aspect ratio increases, and hence, the geometrical nonlinearities might become more significant. In this regard, this paper aims to investigate the effect of structural nonlinearity on the aeroelasticity of span morphing wings using the exact fully intrinsic equations for the first time. Furthermore, the effects of various parameters such as thrust force, engine location, chord size, flight altitude, initial angle of attack, and overlapping mass on the aeroelasticity of the wing are studied. The applied aerodynamic loads in an incompressible flow regime are determined using Peters’ unsteady aerodynamic model. In order to check the stability of the system, first the resulting nonlinear partial differential equations are discretized by using the central finite difference method and then linearized about the static equilibrium. Finally, by obtaining the eigenvalues of the linearized system, the stability of the wing is evaluated. It is observed that by using the fully intrinsic equations, the instability of the axially moving telescopic wing can be determined more accurately. Moreover, the results show that the morphing length and overlapping mass have significant effects on the aeroelastic stability of the telescopic wing.

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Section: Governing Equationsmentioning

confidence: 99%

Section: Governing Equationsmentioning

confidence: 99%

Nonlinear aeroelastic stability analysis of a two-stage axially moving telescopic wing by using fully intrinsic equations

Barzani

Shahverdi

Amoozgar

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…CT, also known as Bernoulli-Euler theory, was proposed by Euler [5] and Bernoulli [6] about 280 years ago and provides good enough predictions of mechanical behavior when the beam is thin. Boley [7] can be given as an example of the early usage of CT, and Modaress-Aval et al [8] can be given as an example of the resent usage of this theory. FSDT, developed by Timoshenko [9] and also named after him, takes into account rotational inertia and first-order shear effects.…”

Section: Introductionmentioning

confidence: 99%

Stress Analysis of Laminated HSDT Beams Considering Bending Extension Coupling

BAB

Kutlu

2023

Turkish Journal of Civil Engineering

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This study demonstrates a mixed finite element formulation procedure for the bending and stress analyses of laminated composite beams. The finite element method is based on the Hellinger-Reissner variational principle, while the beam assumptions are based on the Higher Order Shear Deformation Theory (HSDT). Reddy’s shear function is employed for the beam theory where the beam is discretized by two-noded linear elements. The displacements and stress resultants are obtained directly at the nodes according to the proposed mixed formulation. The validation of current study is performed by comparison and convergence analyzes for various lamination cases under different boundary conditions.

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Parametric Flutter Analysis of Camber Morphing Wing Using Beam-Plate Coupled Model

Huang,

Zhang,

Wang

2024

Lecture Notes in Mechanical Engineering

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Aeroelastic analysis of cantilever plates using Peters’ aerodynamic model, and the influence of choosing beam or plate theories as the structural model

Cited by 5 publications

References 26 publications

Nonlinear aeroelastic stability analysis of a two-stage axially moving telescopic wing by using fully intrinsic equations

Nonlinear aeroelastic stability analysis of a two-stage axially moving telescopic wing by using fully intrinsic equations

Stress Analysis of Laminated HSDT Beams Considering Bending Extension Coupling

Parametric Flutter Analysis of Camber Morphing Wing Using Beam-Plate Coupled Model

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