### Abstract

Language | English |
---|---|

Pages | 1-16 |

Number of pages | 16 |

Journal | Journal of Aeroelasticity and Structural Dynamics |

Volume | 5 |

Issue number | 1 |

Publication status | Published - 31 Jan 2017 |

Externally published | Yes |

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### Cite this

*Journal of Aeroelasticity and Structural Dynamics*,

*5*(1), 1-16.

}

*Journal of Aeroelasticity and Structural Dynamics*, vol. 5, no. 1, pp. 1-16.

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

Research output: Contribution to journal › Article

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 -