On analysis of structural response of ship panels subjected to air blast loading

The aim of this work is to present active vibration control of stiffened plates. A stiffened plate finite element with piezoelectric effects is formulated. The characteristic feature of the stiffener is that it can have any shape in plan and need not pass through the nodal lines of the finite element mesh. The coupling between the direct and the converse piezoelectric effects is neglected for simplicity. A velocity feedback algorithm is employed in the active control. Numerical examples for vibration control of isotropic and orthotropic stiffened plates have been presented.

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“…Houlston et al [12] have experimentally investigated the structural response of a clamped plate under air blast (Fig. 3).…”

Section: Numerical Examplesmentioning

confidence: 99%

Active vibration control of piezolaminated stiffened plates

Mukherjee

Joshi

Ganguli

2002

Composite Structures

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“…The response of marine sandwich panels to explosion loading has been addressed in [Hayman 1996], [Makinen 1999], [Shin and Geers 1994], [Jiang and Olson 1994] (underwater explosion) and [Houlston et al 1985] (in air explosion). Studies of the response of aircraft composite panels under impulsive loading include [Cheng and Benveniste 1968;Crocker and Hudson 1969;Rajamani and Prabhakaran 1980;Dobyns 1981;Birman and Bert 1987;Cederbaum et al 1988;1989;Librescu and Nosier 1990;Librescu and Na 1998;Song et al 1998;Librescu et al 2004;Hause and Librescu 2005;2007;Xue and Hutchinson 2004].…”

Section: Introductionmentioning

confidence: 99%

Untitled

2009

J. Mech. Solids Struct.

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“…Studies concerning a blast loading on a panel were carried out by Houlston et al [2], Houlston and DesRochers [3], Gupta et al [4], Redekop and Azar [5]. Recently, Tiirkmen and MecitogIu [6] carried out a numerical study on the dynamic behavior of laminated composite plates subjected to shock loading.…”

Section: Introductionmentioning

confidence: 99%

Nonlinear Structural Response of Laminated Composite Panels Subjected to Blast Loadings

Türkmen

Mecitoğlu

Borat

1996

MCA

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'This paper presents a theoretical analysis and correlation with numerical results of the displacement time histories of laminated composite panels exposed to normal blast shock waves. Nonlinear dynamic equations of the cylindrically curved laminated panels are derived by the use of the Lagrange equations in the frame of Love's theory of thin shells. The governing equations of the laminated curved panel are solved by Runge-Kutta method. In addition, ANSYS finite element software is used to obtain displacement time history numerically. The effect ofloading conditions and geometrical properties is examined on the dynamic behavior.

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On analysis of structural response of ship panels subjected to air blast loading

Cited by 76 publications

References 2 publications

Active vibration control of piezolaminated stiffened plates

Active vibration control of piezolaminated stiffened plates

Untitled

Nonlinear Structural Response of Laminated Composite Panels Subjected to Blast Loadings

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