Design of variable stiffness composite panels for maximum fundamental frequency using lamination parameters

2007 ◽  
Vol 81 (2) ◽  
pp. 283-291 ◽  
Author(s):  
Mostafa M. Abdalla ◽  
Shahriar Setoodeh ◽  
Zafer Gürdal
Keyword(s):  
Fundamental Frequency ◽  
Variable Stiffness ◽  
Composite Panels ◽  
Lamination Parameters

Design of Variable Stiffness Cylinder with Holes Under Bending for Maximum Buckling Load Using Lamination Parameters

2019 ◽  
Author(s):  
Mazen Albazzan ◽  
Brian Tatting ◽  
Ramy Harik ◽  
Zafer Gürdal ◽  
Adriana Blom-Schieber ◽  
...  
Keyword(s):  
Variable Stiffness ◽  
Buckling Load ◽  
Lamination Parameters

Thermomechanical Response of Variable Stiffness Composite Panels

2008 ◽  
Vol 32 (1-2) ◽  
pp. 187-208 ◽  
Author(s):  
M. M. Abdalla ◽  
Z. Gürdal ◽  
G. F. Abdelal
Keyword(s):  
Variable Stiffness ◽  
Composite Panels ◽  
Thermomechanical Response

Adaptive gradient-enhanced kriging model for variable-stiffness composite panels using Isogeometric analysis

2018 ◽  
Vol 58 (1) ◽  
pp. 1-16 ◽  
Author(s):  
Peng Hao ◽  
Shaojun Feng ◽  
Ke Zhang ◽  
Zheng Li ◽  
Bo Wang ◽  
...  
Keyword(s):  
Isogeometric Analysis ◽  
Variable Stiffness ◽  
Kriging Model ◽  
Composite Panels

Optimization of Variable-Stiffness Panels for Maximum Buckling Load Using Lamination Parameters

AIAA Journal ◽  
2010 ◽  
Vol 48 (1) ◽  
pp. 134-143 ◽  
Author(s):  
Samuel T. IJsselmuiden ◽  
Mostafa M. Abdalla ◽  
Zafer Gurdal
Keyword(s):  
Variable Stiffness ◽  
Buckling Load ◽  
Lamination Parameters

Dynamic analysis of doubly curved composite panels using lamination parameters and spectral-Tchebychev method

2020 ◽  
Vol 239 ◽  
pp. 106294 ◽  
Author(s):  
Gokhan Serhat ◽  
Mirmeysam Rafiei Anamagh ◽  
Bekir Bediz ◽  
Ipek Basdogan
Keyword(s):  
Dynamic Analysis ◽  
Composite Panels ◽  
Lamination Parameters ◽  
Doubly Curved

Aeroelastic analysis of pre-stressed variable stiffness composite panels

2019 ◽  
Vol 26 (9-10) ◽  
pp. 724-734 ◽  
Author(s):  
Mehnaz Rasool ◽  
Maloy K Singha
Keyword(s):  
Dynamic Pressure ◽  
Variable Stiffness ◽  
Limit Cycle Oscillation ◽  
Composite Panels ◽  
Constant Stiffness ◽  
Aerodynamic Pressure ◽  
Aeroelastic Analysis ◽  
Divergence Type ◽  
Cycle Oscillation ◽  
The Stability

The effect of in-plane stresses on the stability behaviors of constant stiffness and variable stiffness composite panels, exposed to aerodynamic pressure, is studied using the finite element method. The dynamic pressure from the high velocity airflow is evaluated from the first-order piston theory, and the eigenvalue analysis is performed to investigate the flutter or divergence type of instabilities in such composite panels under combined mechanical and aerodynamic loads. Attempt is made to understand the effect of the lamination parameter on the stability characteristics of edge-supported and cantilever composite trapezoidal panels. Finally, the limit cycle oscillation of variable stiffness plates subjected to aerodynamic pressure is investigated.

Aeroelastic Tailoring of Blended Composite Panels with Lamination Parameters

2013 ◽  
Vol 401-403 ◽  
pp. 571-577
Author(s):  
Peng Jin ◽  
Bi Feng Song ◽  
Xiao Ping Zhong
Keyword(s):  
Performance Improvement ◽  
Optimization Method ◽  
Composite Panel ◽  
Composite Panels ◽  
Parallel Genetic Algorithm ◽  
Lamination Parameters ◽  
Aeroelastic Tailoring ◽  
Region Division ◽  
Design Variables ◽  
Composite Wing

An optimization method for blended composite panels with aeroelastic constraint is presented in this paper. On the basis of composite panel sub-region division, the lamination parameters of a guide laminate and length indicator of each ply of the guide laminate are introduced as design variables using parallel genetic algorithm (GA) for optimization. For each individual, the inverse problem of obtaining laminate configuration to target the lamination parameters is solved by another GA. The method of defining design variables can reduce the number of design variables obviously compared with previous work. And the numerical results indicate that the present method is capable of producing fully blended designs of composite wing with aeroelastic performance improvement and weight reduction.

Tailoring the Fundamental Frequency of Laminated Composite Panels Using Material Properties

2014 ◽  
Vol 709 ◽  
pp. 157-161
Author(s):  
Li Guo Zhang ◽  
Kang Yang ◽  
Wei Ping Zhao ◽  
Song Xiang
Keyword(s):  
Fundamental Frequency ◽  
Material Properties ◽  
Present Method ◽  
Optimization Problem ◽  
Laminated Composite ◽  
Composite Panels ◽  
Fundamental Frequencies ◽  
Laminated Panels ◽  
Frequency Optimization ◽  
Optimal Material

Optimization of material properties is performed to maximize the fundamental frequency of the laminated composite panels by means of the genetic algorithm. The global radial basis function collocation method is used to calculate the fundamental frequency of clamped laminated composite panels. In this paper, the objective function of optimization problem is the maximum fundamental frequency; optimization variables are material properties of laminated panels. The results for the optimal material properties and the maximum fundamental frequencies of the 2-layer plates are presented to verify the validity of present method.

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