Aeroelastic instability of a composite wing with a powered-engine

Amoozgar, Mohammadreza; Irani, Saied; Vio, Gareth A.

doi:10.1016/j.jfluidstructs.2012.10.007

Cited by 29 publications

(18 citation statements)

References 16 publications

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“…For the quasi-steady model, the flutter speed slightly decreases as the engine moves from the wing root to around 25% of the span (x e = 0.25), further sliding towards the wing tip increases the flutter speed. These results show agreement with those in [22]. The flutter frequency decreases by moving the engine towards the wing tip for the two aerodynamic models.…”

Section: Validationsupporting

confidence: 89%

“…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: 72%

“…The study observed that the engine mass, thrust, and location are of great influence on the dynamic stability of the aircraft wing. The dynamic instability of a cantilever composite wing with an attached mass subjected to follower force representing the thrust of the engine was studied in [22]. Therein, it was reported that the ply angle, engine location, the magnitude of engine mass and thrust have significant effects on the aeroelastic stability of the composite wings.…”

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: 89%

Section: Validationsupporting

confidence: 72%

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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“…Furthermore, based on the trajectory optimization, we ignores the influence of temperature and establish the equation of wing flutter carrying with the propulsion system. Therefore, compared with (Amoozgar, 2013;Mardanpour et al, 2014;Mazidi et al, 2013) previous studies, our research is of great significance. (ii) In order to reveal the negative effect of the conventional control on the stability of aeroelastic system (Cassaro & Battipede, 2015;Huang et al, 2015;Singh, 2015;Wang et al, 2012;Zhang et al, 2013;Zhao, 2009Zhao, , 2011 and consider the influence of faults, time delay, input saturation, time-varying parameter uncertainties and external disturbances, this paper focuses on the design of finite-time H 1 adaptive fault-tolerant controller for flutter of wing with propulsion system.…”

Section: Introductionmentioning

confidence: 85%

“…Flutter instability of elastic systems subjected to non-conservative forces have been studied by many authors (Amoozgar, 2013;Mardanpour, Richards, Nabipour, & Hodges, 2014;Mazidi, Kalantari, & Fazelzadeh, 2013). Amoozgar (2013) investigated the aeroelastic instability of a wing model, which behaves as an orthotropic composite beam with a concentrated mass subjected to the engine thrust; Wagner function is used to model the unsteady aerodynamic loads, while the engine thrust is modeled as a follower force and a concentrated mass is used to model the engine mass. Mardanpour et al (2014) using the code NATASHA (Nonlinear Aeroelastic Trim And Stability of HALE Aircraft) investigated the effects of multiple engine placement on flutter characteristics of a backswept flying wing.…”

Section: Introductionmentioning

confidence: 99%