Maximization of Fundamental Frequencies of Axially Compressed Laminated Plates Against Fiber Orientation

AIAA Journal ◽  
2009 ◽  
Vol 47 (4) ◽  
pp. 916-922 ◽  
Author(s):  
Hsuan-Teh Hu ◽  
Wen-Kwai Tsai
Keyword(s):  
Fiber Orientation ◽  
Laminated Plates ◽  
Fundamental Frequencies

Fiber Orientation Angles Optimization for Maximum Fundamental Frequency of Laminated Composite Plates by the Genetic Algorithm and Meshless Method

2014 ◽  
Vol 709 ◽  
pp. 130-134
Author(s):  
Feng Wang ◽  
Wei Ping Zhao ◽  
Song Xiang
Keyword(s):  
Genetic Algorithm ◽  
Fundamental Frequency ◽  
Fiber Orientation ◽  
Meshless Method ◽  
Laminated Composite ◽  
Composite Plates ◽  
Laminated Plates ◽  
Laminated Composite Plates ◽  
Fundamental Frequencies ◽  
Design Variables

Fiber orientation angles optimization is carried out for maximum fundamental frequency of clamped laminated composite plates using the genetic algorithm. The meshless method is utilized to calculate the fundamental frequency of clamped laminated composite plates. In the present paper, the maximum fundamental frequency is an objective function; design variables are a set of fiber orientation angles in the layers. The examples of square laminated plates are considered. The results for the optimal fiber orientation angles and the maximum fundamental frequencies of the 2-layer plates are presented.

Effect of Fiber Orientation on the Critical Buckling Load of Symmetric Composite Laminated Plates

2012 ◽  
Vol 629 ◽  
pp. 95-99 ◽  
Author(s):  
N. Hamani ◽  
D. Ouinas ◽  
N. Taghezout ◽  
M. Sahnoun ◽  
J. Viña
Keyword(s):  
Fiber Orientation ◽  
Composite Plates ◽  
Laminated Plates ◽  
Buckling Load ◽  
The Finite Element Method ◽  
Notch Radius ◽  
Critical Buckling Load ◽  
Buckling Strength ◽  
Degree Of Anisotropy ◽  
Circular Notch

In this study, a buckling analysis is performed on rectangular composite plates with single and double circular notch using the finite element method. Laminated plates of carbon/bismaleimde (IM7/5250-4) are ordered symmetrically as follows [(θ/-θ)2]S. The buckling strength of symmetric laminated plates subjected to uniaxial compression is highlighted as a function of the fibers orientations. The results show that whatever the notch radius, the buckling load is almost stable. Increasing the degree of anisotropy significantly improves critical buckling load.

Effect of Fiber Orientation on Vibration Characteristic of Composite Laminated Plates

2014 ◽  
Vol 670-671 ◽  
pp. 158-163 ◽  
Author(s):  
Hui Fen Peng ◽  
Cheng Wang ◽  
Peng Wang
Keyword(s):  
Fiber Orientation ◽  
Natural Frequencies ◽  
Structure Design ◽  
Laminated Plates ◽  
Mode Shapes ◽  
Vibration Characteristic ◽  
Composite Laminated Plates ◽  
Practical Engineering ◽  
Lamination Theory ◽  
Theoretical Results

To describe vibration characteristic of composite laminated plates with various fiber orientations, a composite laminated finite element, which follows classical lamination theory, was constructed. In each ply of rectangular composite laminated plates, the fiber orientation changes with respect to the horizontal coordinate. Natural frequencies and mode shapes of composite laminated plates were studied. The first six natural frequencies and mode shapes of composite laminated plates with various fiber orientations are obtained. The accuracy of this composite laminated element is verified by comparing numerical and theoretical results. The results show that the changes of fiber orientation bring a greater degree of flexibility for structure design of composite laminated plates, which can be used to adjust frequencies and mode shapes of composite laminated plates according to practical engineering need.

Maximizing Buckling Strength of Perforated Composite Laminates by Optimizing Fiber Orientation Using Genetic Algorithm

2006 ◽  
Author(s):  
H. K. Cho ◽  
R. E. Rowlands
Keyword(s):  
Genetic Algorithm ◽  
Fiber Orientation ◽  
Composite Laminates ◽  
Shell Theory ◽  
Layered Composite ◽  
Laminated Plates ◽  
Genetic Optimization ◽  
Subspace Iteration ◽  
Plate Geometry ◽  
Genetic Optimization Algorithm

This paper demonstrates ability to significantly increase buckling loads of perforated composite laminated plates by synergizing FEM and a genetic optimization algorithm (GA). Plate geometry is discretized into specially-developed 3D degenerated eight-node shell isoparametric layered composite elements. General shell theory, involving incremental nonlinear finite element equilibrium equation, is employed. Fiber orientation within individual plies of each element is controlled independently by the genetic algorithm. Eigen buckling analysis is performed using the subspace iteration method. Available results demonstrate the approach is superior to more conventional methodologies such as modifying ply thickness or the stacking sequence of individual rectilinear plies having common fiber orientation through the plate.

Panel flutter of curvilinear composite laminated plates in the presence of delamination

2018 ◽  
Vol 52 (20) ◽  
pp. 2789-2801 ◽  
Author(s):  
Jamshid Fazilati
Keyword(s):  
Fiber Orientation ◽  
Shear Deformation Theory ◽  
Laminated Composite ◽  
Axial Direction ◽  
Laminated Plates ◽  
Fiber Placement ◽  
Aerodynamic Pressure ◽  
Finite Strip Method ◽  
Loading Effects ◽  
Stiffness Characteristics

The effect of variable fiber placement angle on the supersonic linear flutter of rectangular composite panels containing square delamination zone is investigated using an enhanced spline version of finite strip method (FSM). The location dependent stiffness characteristics and mass matrices due to variable fiber orientation angles within every ply are extracted. The structural formulation is based on the higher-order shear deformation theory while the first-order piston theory is utilized to predict the loading effects of the supersonic airflow. Laminated composite material with varying fiber orientation angles along the axial direction is considered. The effect of aerodynamic damping is overlooked. The flutter coalescence of vibration modes is then traced using a standard eigenvalue procedure. Some representative results are provided to show the accuracy and capability of the developed formulation. The effects of material layup as well as geometry on the flutter behavior of laminated panels are then studied and the variation of critical aerodynamic pressure considering different delamination size, delamination depth, and boundary conditions are examined.

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