A New Approach in Finite Element Modeling of Generally Laminated Composite Beams

2006 ◽  
Author(s):  
M. T. Ahmadian ◽  
R. A. Jafari-Talookolaei
Keyword(s):  
Finite Element ◽  
Natural Frequencies ◽  
Laminated Composite ◽  
Element Model ◽  
Quick Response ◽  
New Approach ◽  
Mass Matrices ◽  
Laminated Composite Beam ◽  
Ply Orientation ◽  
Laminated Composite Beams

In this paper, a new finite element model for a generally laminated composite beam (LCB) is presented. Natural frequencies of a generally LCB are derived by developing the stiffness and mass matrices considering the effects of axial force, shear and torsional deformations and rotary inertia. This model includes coupling of bending and torsional modes of deformations which is usually present in LCBs due to ply orientation. The model is designed in such away that it can be used for single and double stepped cross-section. Comparing numerical results for simple cases with analytical solutions and literature indicate high accurate and quick response of the model.

Inflight Deicing of Self-Actuating Aircraft Wing Structures With Piezoelectric Actuators

2002 ◽  
Author(s):  
Y. J. Lin ◽  
Suresh V. Venna
Keyword(s):  
Finite Element ◽  
Natural Frequencies ◽  
Laminated Composite ◽  
Piezoelectric Actuators ◽  
Element Model ◽  
Harmonic Excitation ◽  
Dynamic Responses ◽  
Underlying Structure ◽  
Shear Stresses ◽  
Modeling And Analysis

Self-actuating aircraft wings for in-flight deicing with minimal power requirements are proposed. Lightweight piezoelectric actuators are utilized to excite the wing structure to its natural frequencies to induce shear stresses on the surface of the wing. The shears are generated in such a way that they are sufficient to break the weak bond between the ice layer and the wing surface. A laminated composite cantilever plate is used for the modeling and analysis. Analytical model is developed to predict the natural frequencies and shear stresses on the surface of the plate and finite element modal analysis is carried out to verify the results. In addition, finite element model involving the ice deposited on the underlying structure is built. The dynamic responses of the structure to harmonic excitation to its first five natural frequencies are investigated. It is observed that significant amount of ice de-bonding from the substrate occurs in the third mode, or the second symmetric mode. Moreover, the energy requirements of the piezoelectric actuators to actuate an adaptive composite structure with given weight are evaluated.

scholarly journals Stacking Sequence Effects on Natural Frequency of Laminated Composite Beams

2008 ◽  
Vol 17 (1) ◽  
pp. 096369350801700 ◽  
Author(s):  
Muzaffer Topcu ◽  
Gökmen Atlıhaı ◽  
Hasan Çallıoğlu ◽  
E. Şahin Çonkur
Keyword(s):  
Natural Frequencies ◽  
Laminated Composite ◽  
Stacking Sequence ◽  
Laminated Beams ◽  
Laminated Beam ◽  
Theoretical Approaches ◽  
Package Program ◽  
Sequence Effects ◽  
Laminated Composite Beam ◽  
Laminated Composite Beams

In this study, the natural frequencies of composite laminated beams are considered using experimental and theoretical approaches while the effects of stacking sequences of composite laminated beams on natural frequencies are investigated using theoretical approaches. A theoretical model of the laminated composite beam has been developed. Numeric calculations are carried out by means of a computer package program, ANSYS 7.0 that implements the finite element method (FEM). It has been concluded that in all of the modes considered, natural frequencies in the beam of angle (0°)12 are maximum values, natural frequencies in the beam composed of [(±52°)3]s are the lowest values according to the other stacking sequence and while natural frequencies in the beam of higher angles from [(±52°)3]s are getting higher, they at angle (90°)12 take more higher values. Furthermore, some of the results obtained from these theoretical analyses are compared with the experimental results using the composite laminated beam at [(0°/90°)3]s produced in Izoreel Composite Isolated Materials Company, Izmir, Turkey. Its natural frequencies are calculated both analytically and numerically. It has been concluded that experimental, theoretical and numerical results are very close to each other.

scholarly journals The Effect of Various Fiber Orientations and Boundary Conditions on Natural Frequencies of Laminated Composite Beam

2018 ◽  
Vol 7 (3.11) ◽  
pp. 67 ◽  
Author(s):  
M Arif Mat Norman ◽  
M Amiruddin Zainuddin ◽  
Jamaluddin Mahmud
Keyword(s):  
Boundary Condition ◽  
Finite Element ◽  
Aspect Ratio ◽  
Free Vibration ◽  
Boundary Conditions ◽  
Composite Beam ◽  
Natural Frequencies ◽  
Laminated Composite ◽  
Mode Shapes ◽  
Laminated Composite Beam

This paper investigates the free vibration characteristics of laminate composite beam for various lamination schemes and under various boundary conditions. A beam model with the aspect ratio (length to thickness) of 25 to 150 made of carbon/ epoxy laminates under free vibration were constructed using a commercially available finite element software (ANSYS). The varied parameters are the lamination schemes (cross ply, angle ply and unidirectional ply) and boundary conditions (Clamp-Free (C-F), Clamp-Clamp (C-C), Clamp-Hanger (C-H), Free-Free (F-F) and Hanger-Hanger (H-H) ). For each case, finite element simulations were performed and the natural frequencies were determined. Mode shapes were also analyzed to observe the beam’s deformation behavior. Results showed that increasing aspect ratio will decrease natural frequencies for the first seven mode shapes. In terms of lamination scheme, the unidirectional ply produced the highest frequency (34.26 Hz), followed by cross ply (34.05 Hz) and angle ply (13.60 Hz) at the aspect ratio of 25. In terms of boundary conditions, the Hanger-Hanger boundary condition produced the highest natural frequency (2272.52  Hz) at the aspect ratio of 25, while Clamped-Free boundary condition produced the lowest frequency (2.28 Hz) at the aspect ratio of 150. In general, it can be concluded that the current study is useful and has contributed significant knowledge to better understand of effect of various fiber orientations and boundary conditions on the natural frequencies of laminated composite beam. 

scholarly journals Vibration Analysis of Carbon Fiber Reinforced Laminated Composite Skin with Glass Honeycomb Sandwich Beam Using HSDT

2017 ◽  
Vol 61 (3) ◽  
pp. 213 ◽  
Author(s):  
Mageshwaran Subramani ◽  
Ananda Babu Arumugam ◽  
Manoharan Ramamoorthy
Keyword(s):  
Finite Element ◽  
Aspect Ratio ◽  
Vibration Analysis ◽  
Natural Frequencies ◽  
Sandwich Beam ◽  
Laminated Composite ◽  
Element Model ◽  
Composite Sandwich ◽  
The Core ◽  
Core Thickness

In this paper, the vibration analysis of uniform laminated composite sandwich beam with a viscoelastic core was studied. The governing equation of motion of the laminated composite sandwich beam has been derived based on higher order shear deformation theory (HSDT) in finite element model (FEM). The developed finite element model has been validated in terms of natural frequencies with the experimental values and the available literature. Various parametric studies have been performed to examine the impact of the core thickness, ply orientation and aspect ratio of the uniform laminated composite sandwich beam in response to free vibration for various boundary conditions. From the results it was concluded that that natural frequencies could be increased with increasing the core thickness and decreased with increasing the aspect ratio.

scholarly journals Free Vibration and Buckling Analysis of the Laminated Composite Beams by Using GDQM

2009 ◽  
Vol 18 (2) ◽  
pp. 096369350901800
Author(s):  
Gökmen Atlıhan ◽  
Ersin Demir ◽  
Zekeriya Girgin ◽  
Hasan Çallıoğlu
Keyword(s):  
Free Vibration ◽  
Natural Frequencies ◽  
Differential Quadrature Method ◽  
Laminated Composite ◽  
Mode Shapes ◽  
Load Carrying Capacity ◽  
Load Carrying ◽  
Generalized Differential ◽  
Laminated Composite Beam ◽  
Laminated Composite Beams

In this study, effects of stacking sequences of composite laminated beams on natural frequencies and buckling behaviour have been analyzed by Generalized Differential Quadrature Method (GDQM) and Finite Element Method (FEM). Mode shapes were also investigated for one mode of buckling and three modes of free vibration analyses. In addition, variations of mode shapes for different boundary conditions were presented in details. Numerical results show that the effective stiffness of the laminated composite beam can be altered through an adjustment in the stacking sequence. Thus, such an adjustment in stacking sequences allows operations in desired natural frequencies and load carrying capacity without changing its geometry drastically or without changing its weight.

Buckling Analysis of Laminated Composite Beams by Using an Improved First Order Formulation

2021 ◽  
Vol 1033 ◽  
pp. 156-160
Author(s):  
Shammely Ayala ◽  
Augusto Vallejos ◽  
Roman Arciniega
Keyword(s):  
Finite Element ◽  
Finite Element Model ◽  
Virtual Work ◽  
Three Dimensional ◽  
Laminated Composite ◽  
Element Model ◽  
Composite Beams ◽  
Lagrange Polynomials ◽  
First Order ◽  
Laminated Composite Beams

In this work, a finite element model based on an improved first-order formulation (IFSDT) is developed to analyze buckling phenomenon in laminated composite beams. The formulation has five independent variables and takes into account thickness stretching. Three-dimensional constitutive equations are employed to define the material properties. The Trefftz criterion is used for the stability analysis. The finite element model is derived from the principle of virtual work with high-order Lagrange polynomials to interpolate the field variables and to prevent shear locking. Numerical results are compared and validated with those available in literature. Furthermore, a parametric study is presented.

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