Nonlinear Response of Functionally Graded Panels with stiffeners in Supersonic Flow

Mohammadreza Amoozgar, Hossein Shahverdi, Hamidreza Ovesy

Research output: Contribution to journalArticle

Abstract

This paper aims to study the nonlinear response of a stiffened functionally graded plate in supersonic flow. To model the geometrically nonlinear behavior of the stiffened panel, the von Karman large deflection plate theory is employed and the stiffener which is placed on the plate in different positions is modeled by using the Euler-Bernoulli beam theory. These two structural models are coupled to each other via a pair of action reaction forces. The plate is in the supersonic regime and the quasi-steady first order piston theory is utilized to estimate the aerodynamic pressure induced by the supersonic flow. By using the Hamilton’s principle the nonlinear partial differential equations of the stiffened panel are obtained. These partial differential equations are converted to ordinary differential equations by using the Galerkin’s method which then solved by numerical integration. It is found that by using the stiffeners, the onset of flutter and also the limit cycle oscillation amplitude of the system changes dramatically and the rate of this change extremely depends on the volume fraction index of the plate made of functionally graded materials and the plate aspect ratio. Moreover, the effect of number of stiffeners on the aeroelastic behavior of FG panel is studied and it is clarified that by increasing the number of stiffeners, the flutter boundary increases.
LanguageEnglish
Pages1-16
Number of pages16
JournalJournal of Aeroelasticity and Structural Dynamics
Volume5
Issue number1
Publication statusPublished - 31 Jan 2017
Externally publishedYes

Fingerprint

Supersonic flow
Partial differential equations
Functionally graded materials
Galerkin methods
Ordinary differential equations
Pistons
Aspect ratio
Volume fraction
Aerodynamics

Cite this

@article{027fea13822a45be8eb08a8cfc330799,
title = "Nonlinear Response of Functionally Graded Panels with stiffeners in Supersonic Flow",
abstract = "This paper aims to study the nonlinear response of a stiffened functionally graded plate in supersonic flow. To model the geometrically nonlinear behavior of the stiffened panel, the von Karman large deflection plate theory is employed and the stiffener which is placed on the plate in different positions is modeled by using the Euler-Bernoulli beam theory. These two structural models are coupled to each other via a pair of action reaction forces. The plate is in the supersonic regime and the quasi-steady first order piston theory is utilized to estimate the aerodynamic pressure induced by the supersonic flow. By using the Hamilton’s principle the nonlinear partial differential equations of the stiffened panel are obtained. These partial differential equations are converted to ordinary differential equations by using the Galerkin’s method which then solved by numerical integration. It is found that by using the stiffeners, the onset of flutter and also the limit cycle oscillation amplitude of the system changes dramatically and the rate of this change extremely depends on the volume fraction index of the plate made of functionally graded materials and the plate aspect ratio. Moreover, the effect of number of stiffeners on the aeroelastic behavior of FG panel is studied and it is clarified that by increasing the number of stiffeners, the flutter boundary increases.",
author = "Mohammadreza Amoozgar and Hossein Shahverdi and Hamidreza Ovesy",
year = "2017",
month = "1",
day = "31",
language = "English",
volume = "5",
pages = "1--16",
journal = "Journal of Aeroelasticity and Structural Dynamics",
issn = "1974-5117",
number = "1",

}

Nonlinear Response of Functionally Graded Panels with stiffeners in Supersonic Flow. / Amoozgar, Mohammadreza; Shahverdi, Hossein; Ovesy, Hamidreza.

In: Journal of Aeroelasticity and Structural Dynamics, Vol. 5, No. 1, 31.01.2017, p. 1-16.

Research output: Contribution to journalArticle

TY - JOUR

T1 - Nonlinear Response of Functionally Graded Panels with stiffeners in Supersonic Flow

AU - Amoozgar, Mohammadreza

AU - Shahverdi, Hossein

AU - Ovesy, Hamidreza

PY - 2017/1/31

Y1 - 2017/1/31

N2 - This paper aims to study the nonlinear response of a stiffened functionally graded plate in supersonic flow. To model the geometrically nonlinear behavior of the stiffened panel, the von Karman large deflection plate theory is employed and the stiffener which is placed on the plate in different positions is modeled by using the Euler-Bernoulli beam theory. These two structural models are coupled to each other via a pair of action reaction forces. The plate is in the supersonic regime and the quasi-steady first order piston theory is utilized to estimate the aerodynamic pressure induced by the supersonic flow. By using the Hamilton’s principle the nonlinear partial differential equations of the stiffened panel are obtained. These partial differential equations are converted to ordinary differential equations by using the Galerkin’s method which then solved by numerical integration. It is found that by using the stiffeners, the onset of flutter and also the limit cycle oscillation amplitude of the system changes dramatically and the rate of this change extremely depends on the volume fraction index of the plate made of functionally graded materials and the plate aspect ratio. Moreover, the effect of number of stiffeners on the aeroelastic behavior of FG panel is studied and it is clarified that by increasing the number of stiffeners, the flutter boundary increases.

AB - This paper aims to study the nonlinear response of a stiffened functionally graded plate in supersonic flow. To model the geometrically nonlinear behavior of the stiffened panel, the von Karman large deflection plate theory is employed and the stiffener which is placed on the plate in different positions is modeled by using the Euler-Bernoulli beam theory. These two structural models are coupled to each other via a pair of action reaction forces. The plate is in the supersonic regime and the quasi-steady first order piston theory is utilized to estimate the aerodynamic pressure induced by the supersonic flow. By using the Hamilton’s principle the nonlinear partial differential equations of the stiffened panel are obtained. These partial differential equations are converted to ordinary differential equations by using the Galerkin’s method which then solved by numerical integration. It is found that by using the stiffeners, the onset of flutter and also the limit cycle oscillation amplitude of the system changes dramatically and the rate of this change extremely depends on the volume fraction index of the plate made of functionally graded materials and the plate aspect ratio. Moreover, the effect of number of stiffeners on the aeroelastic behavior of FG panel is studied and it is clarified that by increasing the number of stiffeners, the flutter boundary increases.

M3 - Article

VL - 5

SP - 1

EP - 16

JO - Journal of Aeroelasticity and Structural Dynamics

T2 - Journal of Aeroelasticity and Structural Dynamics

JF - Journal of Aeroelasticity and Structural Dynamics

SN - 1974-5117

IS - 1

ER -