Flutter of wings involving a locally distributed flexible control surface

Mozaffari-Jovin, S.; Firouz-Abadi, R. D.; Roshanian, Jafar

doi:10.1016/j.jsv.2015.03.044

Cited by 26 publications

(12 citation statements)

References 29 publications

(42 reference statements)

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“…A lot of efforts have been made to employ the scientific and rigorous research methods and technologies for investigating the flight mechanism of insect in recent years. For example, the trajectory of wing tip was captured [41] and the unsteady flow of wings caused by wing's flutter was investigated [42] . These findings can be used to explain the special phenomena of the high lift force generation of a flying beetle.…”

Section: Discussionmentioning

confidence: 99%

A simulation of the flight characteristics of the deployable hindwings of beetle

Sun

Liu

et al. 2017

J Bionic Eng

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Section: Discussionmentioning

confidence: 99%

A simulation of the flight characteristics of the deployable hindwings of beetle

Sun

Liu

et al. 2017

J Bionic Eng

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“…( 2)). The design flow is run by predefined GA, the OF value is approximated and compared with the result of the 3D FEM simulation [23][24][25][26][27][28][29][30][31][32][33] and then ANN database is updated accordingly (Fig. 8).…”

Section: Effect Of Aileron On Fluttermentioning

confidence: 99%

“…Shi [26] represented the gust loads FEM form formulation to study the wing instability behavior. Based on the model, the other studies and designing development were conducted to assess flutter clearance of the wing with the control surfaces [27].…”

Section: Introductionmentioning

confidence: 99%

Aeroelastic Optimization of the High Aspect Ratio Wing with Aileron

Ghalandari¹,

Mahariq²,

Ghadak³

et al. 2022

Computers, Materials &Amp; Continua

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In aircraft wings, aileron mass parameter presents a tremendous effect on the velocity and frequency of the flutter problem. For that purpose, we present the optimization of a composite design wing with an aileron, using machine-learning approach. Mass properties and its distribution have a great influence on the multi-variate optimization procedure, based on speed and frequency of flutter. First, flutter speed was obtained to estimate aileron impact. Additionally mass-equilibrated and other features were investigated. It can deduced that changing the position and mass properties of the aileron are tangible following the speed and frequency of the wing flutter. Based on the proposed optimization method, the best position of the aileron is determined for the composite wing to postpone flutter instability and decrease the existed stress. The represented coupled aero-structural model is emerged from subsonic aerodynamics model, which has been developed using the panel method in multidimensional space. The structural modeling has been conducted by finite element method, using the p-k method. The fluid -structure equations are solved and the results are extracted.

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“…The Euler–Lagrange governing differential equations of the wing are obtained Meirovitch and Silverberg (1984), Banerjee et al (2008) and Mozaffari-Jovin et al (2015)…”

Section: Formulationmentioning

confidence: 99%

Delamination effects on the unsteady aero-elastic behavior of composite wing by modal analysis

Torabi

Shams

Narab

et al. 2021

Journal of Vibration and Control

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This article deals with the investigation of delamination effects on the flutter behavior of a composite wing subjected to unsteady aerodynamic loads by providing an integrated procedure using exact methods. For this purpose, an undamaged wing structure is modeled as a cantilevered Bernoulli–Euler beam with coupled bending–torsion and delaminated wing structure is modeled as three interconnected intact beams. The modal analysis of the intact and delaminated beams is performed and mode shapes are obtained based on the development of the dynamic stiffness matrix, a computer code and an iterative method. The fundamental modes of the intact and delaminated beam derived from the free vibration analysis are used in Galerkin’s method and the flutter and divergence speeds are obtained with aerodynamic forces applied. In fact, modified shape functions were developed to reflect the delamination effect in the aeroelastic analysis. Also, for the unsteady aeroelastic analysis, an iterative algorithm is developed. It was found that the delamination location and its length can have a positive or a negative influence on the flutter behavior of the wing which depends on the fiber angle.

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Flutter of wings involving a locally distributed flexible control surface

Cited by 26 publications

References 29 publications

A simulation of the flight characteristics of the deployable hindwings of beetle

A simulation of the flight characteristics of the deployable hindwings of beetle

Aeroelastic Optimization of the High Aspect Ratio Wing with Aileron

Delamination effects on the unsteady aero-elastic behavior of composite wing by modal analysis

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