Dynamic response of laminated composite plates under initial stress

This study presents a semi-analytical solution of the non-linear dynamic response, shock spectrum, and dynamic buckling of an imperfect angle-ply laminated composite plate under various types of in-plane pulse forces. The laminated composite plate is modeled using a higher-order shear deformation theory and von-Kármán geometric nonlinearity. The non-linear governing partial differential equations (PDEs) of imperfect laminated composite plates are derived via Hamilton’s principle. Using Galerkin’s method, the non-linear PDEs are transformed into non-linear algebraic equations for the static stability problems and non-linear ordinary differential equations for the dynamic problem such as dynamic response, shock spectrum, and dynamic buckling. The buckling load of the plate is obtained through the associated eigenvalue problem. The static failure load of the composite plate is evaluated using the post-buckling analysis based on the Tsai-Wu failure criterion. The dynamic response and shock spectrum of the composite plate are determined via Newmark’s method. The dynamic failure load of the plate is evaluated using Newmark’s method based on the Tsai-Wu failure criterion. Dynamic buckling is to be characterized by dynamic load factor (DLF), which is represented as the ratio of the dynamic failure load to the static failure load. Based on the pulse/shock duration time, the pulse forces are divided into three loading regimes known as impulsive, dynamic, and quasi-static. The study revealed that the DLF values are > 1, < 1, and [Formula: see text]1 respectively for the case of impulsive, dynamic, and quasi-static loading regimes of pulse force. The influences of various types of in-plane pulse forces, amplitude and time duration of pulse forces, and amplitude of initial geometric imperfections on the non-linear dynamic response, shock spectrum, and dynamic buckling behavior of the laminated composite plate are addressed in detail. The results will help in the appropriate design of the laminated composite plate against dynamic buckling.

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Dynamic response of laminated composite plates fitted with piezoelectric actuators

New Materials in Civil Engineering ◽

10.1016/b978-0-12-818961-0.00010-7 ◽

2020 ◽

pp. 375-394

Author(s):

S.K. Sahu ◽

A. Gupta ◽

E.V. Prasad

Keyword(s):

Dynamic Response ◽

Laminated Composite ◽

Piezoelectric Actuators ◽

Composite Plates ◽

Laminated Composite Plates

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On the Low Velocity Impact Response of Laminated Composite Plates using the P-Version Ritz Method

Advanced Composites Letters ◽

10.1177/096369350301200501 ◽

2003 ◽

Vol 12 (5) ◽

pp. 096369350301200 ◽

Cited By ~ 1

Author(s):

Y.P. Markopoulos ◽

V. Kostopoulos

Keyword(s):

Dynamic Response ◽

Laminated Composite ◽

Composite Plates ◽

Low Velocity Impact ◽

Loading Path ◽

Contact Boundary ◽

Laminated Composite Plates ◽

Low Velocity ◽

Velocity Impact ◽

The Impact

Low energy impact in composite laminates is often a crucial and destructive loading condition since it leads to significant internal damage, undetectable by visual inspection. Low velocity impact upon a laminated plate imposes a complex stress state mainly due to the structural heterogeneity resulting by the ply orientation of the constituent laminae and the contact boundary conditions, which lead to a loading path that varies with the impact energy and the properties of the impactor-impacted plate system. The present work deals with the development of a numerical scheme for the calculation of the dynamic response of any type of laminated composite plates under low-velocity impact. The governing non-linear, second order differential equations are derived using p-Ritz admissible polynomial functions and the elastoplastic version of the Hertzian contact law. The dynamic response of fully clamped, cross ply and angle ply composite plates are investigated.

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