Bending-torsional flutter of wings with an attached mass subjected to a follower force

Fazelzadeh, S. Ahmad; Mazidi, Abbas; Kalantari, H.

doi:10.1016/j.jsv.2009.01.002

Cited by 65 publications

(39 citation statements)

References 15 publications

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“…For both of the aerodynamic models, the flutter frequency increases as the engine slides from the leading edge to the trailing edge. Indeed, similar behaviour was obtained in [21] and [22], where in the former it was pointed out that moving the engine from trailing edge to the leading edge in chord-wise direction makes the wing more stable. …”

Section: Validationsupporting

confidence: 71%

“…References [19] and [20] examined the effects of a transverse follower force on stability regions of HALE wing; however, they did not account for the inertia properties of the engine and considered only one location along the wing. The dynamic stability of wings carrying external stores and subjected to a lateral follower force was examined by [21]. The study observed that the engine mass, thrust, and location are of great influence on the dynamic stability of the aircraft wing.…”

Section: Introductionmentioning

confidence: 99%

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Effect of engine location on flutter speed and frequency of a tapered viscoelastic wing

Matter

Darabseh

Mourad

2018

IOP Conf. Ser.: Mater. Sci. Eng.

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Abstract. The flutter of a tapered viscoelastic wing carrying an engine and subjected to a follower thrust force is investigated. The wing is considered as a cantilever tapered EulerBernoulli beam, made of a linear viscoelastic material where Kelvin-Voigt model is assumed to represent the viscoelastic behaviour of the material. In addition, quasi-steady and unsteady aerodynamic forces models are introduced along with the follower thrust force. The mass and inertia of the engine are modelled in order to achieve more realistic behaviour of the engine upon flutter characteristics of the system. Moreover, the governing equations of motion are derived through the Extended Hamilton's Principle. The generalized function theory is used to more accurately consider the contribution of the mass and its follower force in the governing equations. The resulting partial differential equations are solved by Galerkin method along with the classical flutter investigation approach. Parametric studies highlighting the sensitivity of the chord-wise engine location, the span-wise engine location, and the vertical engine location on the flutter speed and flutter frequency are reported. It is found that the location of the engine in the three directions play an important role in the dynamic stability of the wing. IntroductionAeroelasticity is the term used to denote the field of study concerned with the interaction among aerodynamics, elasticity, inertia forces, and the phenomena that can result. Aeroelastic phenomena are usually classified as being either static (as the divergence) or dynamic (as the flutter). Divergence is a phenomenon that occurs when the moments resulting from aerodynamic forces overcome the elastic restoring forces due to structural stiffness. The flutter is defined as a dynamic lack of stability that occurs in a flexible structure subjected to aerodynamic loads at certain speed and frequency -called the flutter speed and the flutter frequency -which cause the structure to undergo divergent oscillations. Bending-torsion aeroelastic instabilities have been investigated by many authors. References [1] and [2] studied the flutter phenomenon of a uniform wing by analysing a set of partial differential equations governing the motion of the wing. The use of quasi-steady aerodynamic theory for aeroelastic analysis of the lifting surfaces is a good approximation in the field of aeroelasticity as found in [3][4][5][6], and others. In Reference [7], a systematic approach based on Galerkin method was developed to investigate the flutter speed and frequency for a wing subjected to quasi-steady aerodynamic forces. The quasi-steady aerodynamic model can be used for low frequencies with acceptable results as investigated in [8]. However, Reference [9] observed that the quasi-steady

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Section: Validationsupporting

confidence: 71%

Section: Introductionmentioning

confidence: 99%

Effect of engine location on flutter speed and frequency of a tapered viscoelastic wing

Matter

Darabseh

Mourad

2018

IOP Conf. Ser.: Mater. Sci. Eng.

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“…In this framework classical examples can be found mainly in aerospace engineering, for example, when the flutter behavior of a wing, immersed in a gas flow, namely, under nonconservative and velocity-dependent loads, is considered [5,36]. Other examples, when configuration-dependent loads act, can be found in [37], where the flutter instability of a cantilever beam containing a tip mass, subjected to a transverse follower force at the tip, and in the presence of airflow, is addressed; in [38], where the lateral-torsional stability of deep cantilever beams loaded by a transverse follower force at the tip, is studied; in [39], where the lateral stability of a slender beam, under a transverse follower force is addressed; in [21], where the flexural-torsional bifurcations of a cantilever beam under the simultaneous action of a nonconservative follower force and a conservative couple at the free end, have been analyzed; and finally in [40], where the bending-torsional flutter analysis of a cantilever, containing an arbitrarily placed mass, under a follower force and airflow, is analyzed. Remarkably, in the greatest part of the previous papers, a foil beam, namely, a beam for which one of the two inertia moments is much larger than the other, is considered as the mathematical model of aircraft's wing.…”

Section: Mathematical Problems In Engineeringmentioning

confidence: 99%

Flexural-Torsional Flutter and Buckling of Braced Foil Beams under a Follower Force

Ferretti

D’Annibale

Luongo

2017

Mathematical Problems in Engineering

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The flutter and buckling behavior of a cantilever foil beam, loaded at the tip by a follower force, are addressed in this paper. The beam is internally and externally damped and braced at the tip by a linear spring-damper device, which is located in an eccentric position with respect to beam axis, thus coupling the flexural and torsional behaviors. An exact linear stability analysis is carried out, and the linear stability diagram of the trivial rectilinear configuration is built up in the space of the follower load and spring's stiffness parameters. The effects of the flexural-torsional coupling, as well as of the damping, on the flutter and buckling critical loads are discussed.

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“…Also, Edwards and Wieseman 8 studied the flutter and divergence of three check cases that include unrestrained airfoils and wing models. The bending-torsional flutter characteristics of an aircraft wing containing an arbitrarily placed mass under a follower force have been studied by Fazelzadeh et al 9 They showed the important influence of the location and magnitude of the store mass and the follower force on the flutter speed and frequency of the wing. Also, Mazidi and Fazelzadeh 10 investigated the flutter of an aircraft wing with a powered engine.…”

Section: Introductionmentioning

confidence: 99%

Aeroelastic Analysis of Unrestrained Aircraft Wing with External Stores Under Roll Maneuver

Fazelzadeh¹,

Ghasemi²,

Mazidi³

2016

IJAV

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This paper discusses our study on the flutter of an unrestrained aircraft wing carrying a fuselage at its semispan and arbitrary placed external stores under roll maneuver. Maneuver terms are combined in the governing equations which are obtained using the Hamilton's principle. The wing is represented by a classical beam and incorporates bending-torsion flexibility. Theodorsen unsteady aerodynamic pressure loadings are considered to simulate the aeroelastic loads. The Galerkin method is subsequently applied to convert the partial differential equations into a set of ordinary differential equations. Numerical simulations are validated against several previous published results and good agreement is observed. In addition, simulation results are presented to show the effects of the roll angular velocity, fuselage mass, external stores mass, and their locations on the wing flutter of an aircraft in free-flight condition. Parametric studies show that the predicted flutter boundaries are very sensitive to the aircraft rigid body roll angular velocity, fuselage mass and external stores mass and locations.

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Bending-torsional flutter of wings with an attached mass subjected to a follower force

Cited by 65 publications

References 15 publications

Effect of engine location on flutter speed and frequency of a tapered viscoelastic wing

Effect of engine location on flutter speed and frequency of a tapered viscoelastic wing

Flexural-Torsional Flutter and Buckling of Braced Foil Beams under a Follower Force

Aeroelastic Analysis of Unrestrained Aircraft Wing with External Stores Under Roll Maneuver

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