DYNAMIC RESPONSE OF A STIFFENED LAMINATED COMPOSITE PLATE SUBJECTED TO BLAST LOAD

1999 ◽  
Vol 221 (3) ◽  
pp. 371-389 ◽  
Author(s):  
H.S. Türkmen ◽  
Z. Mecitoğlu
Keyword(s):  
Dynamic Response ◽  
Composite Plate ◽  
Laminated Composite ◽  
Blast Load ◽  
Laminated Composite Plate

Nonlinear Damped Vibrations of a Laminated Composite Plate Subjected to Blast Load

AIAA Journal ◽  
2006 ◽  
Vol 44 (9) ◽  
pp. 2002-2008 ◽  
Author(s):  
Zafer Kazanci ◽  
Zahit Mecitoglu
Keyword(s):  
Composite Plate ◽  
Laminated Composite ◽  
Blast Load ◽  
Laminated Composite Plate

scholarly journals A cell-based smoothed discrete shear gap method (CS-FEM-DSG3) for dynamic response of laminated composite plate subjected to blast loading

2015 ◽  
Vol 37 (2) ◽  
pp. 81-90 ◽  
Author(s):  
Dang Trung Hau ◽  
Nguyen Thoi My Hanh ◽  
Nguyen Thoi Trung
Keyword(s):  
Dynamic Response ◽  
Composite Plate ◽  
Shear Deformation Theory ◽  
Laminated Composite ◽  
Blast Loading ◽  
Laminated Composite Plate ◽  
A Cell ◽  
Sinusoidal Shape ◽  
Discrete Shear Gap ◽  
Equivalent Layer

The paper investigates the dynamic response of laminated composite plate under the effect of blast loading. The cell-based smoothed discrete shear gap method (CS-FEM-DSG3) based on the first-order shear deformation theory (FSDT) and the equivalent layer theory (ELT) is used to model the behavior of the laminated composite plate. The blast loading is simulated by a time diagram of rectangular, triangular, exponential, or sinusoidal shape. The effects of the number of layers and fiber orientation to the displacement and stress fields of the laminated composite plate are discussed. Numerical results demonstrated the accuracy and reliability of the present method compared with previous published methods.

scholarly journals Nonlinear Damped Vibrations of a Hybrid Laminated Composite Plate Subjected to Blast Load

2014 ◽  
Vol 88 ◽  
pp. 18-25 ◽  
Author(s):  
Süleyman Baştürk ◽  
Haydar Uyanık ◽  
Zafer Kazancı
Keyword(s):  
Composite Plate ◽  
Laminated Composite ◽  
Blast Load ◽  
Laminated Composite Plate

ACTIVE VIBRATION CONTROL OF COMPOSITE PLATE USING AFC ACTUATOR AND PVDF SENSOR

2011 ◽  
Vol 11 (02) ◽  
pp. 237-255 ◽  
Author(s):  
S. B. KERUR ◽  
ANUP GHOSH
Keyword(s):  
Dynamic Response ◽  
Vibration Control ◽  
Composite Plate ◽  
Fiber Composite ◽  
Active Vibration Control ◽  
Time Integration ◽  
Laminated Composite ◽  
Element Formulation ◽  
Laminated Composite Plate ◽  
Active Vibration

A finite element formulation for active vibration control of laminated composite plate integrated with active fiber composite (AFC) layer acting as distributed actuator and PVDF layer as sensor is presented in this paper. An eight noded quadratic isoparametric element with five mechanical degrees of freedom and one electrical degree of freedom per node of the element is considered. Newmark time integration method is used to calculate the dynamic response and negative velocity feedback control algorithm is used to control the dynamic response of the laminated composite plate. The effect of piezoelectric fiber orientation in actuator layer on the control of vibration is studied.

Non-linear response and buckling of imperfect laminated composite plates under in-plane pulse forces

2021 ◽  
pp. 095440622199639
Author(s):  
Rajesh Kumar ◽  
Vishal Singh ◽  
SN Patel ◽  
Tanish Dey
Keyword(s):  
Dynamic Response ◽  
Composite Plate ◽  
Failure Load ◽  
Laminated Composite ◽  
Composite Plates ◽  
Dynamic Buckling ◽  
Laminated Composite Plates ◽  
Laminated Composite Plate ◽  
Non Linear ◽  
Static Failure

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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