scholarly journals A Study on Thermal Buckling and Mode Jumping of Metallic and Composite Plates

Aerospace ◽  
2021 ◽  
Vol 8 (2) ◽  
pp. 56
Author(s):  
Javier Gutiérrez Álvarez ◽  
Chiara Bisagni
Keyword(s):  
Composite Material ◽  
Thermal Expansion ◽  
Parametric Analysis ◽  
Shape Change ◽  
Composite Plates ◽  
Thermal Buckling ◽  
Test Setup ◽  
Low Thermal Expansion ◽  
Structural Adaptability ◽  
Post Buckling

Composite plates in post-buckling regime can experience mode jumping in their buckling shape, suddenly increasing the number of half-waves. This phenomenon can be advantageous, because the shape change could be used for local morphing or structural adaptability in future aerospace structures. A study of this phenomenon under heating is here presented, combining numerical and experimental techniques. At first, a set of parametric analysis was conducted to identify composite panels that present a mode jump when heated. Three plates were selected, one in aluminum alloy 2024T3, and two in AS4/8552 composite material, with layup [30/−30/5/−5]s and [35/−35/10/−10]s. The plates were tested in a new test setup for thermal buckling based on low thermal expansion fixtures. The mode jumping was successfully obtained experimentally for both composite plates. Numerical simulations predicted the general trends for all plates, and the mode jumps for the composite plates.

scholarly journals Thermal Buckling and Post-Buckling Improvements of Laminated Composite Plates Using Finite Element Method

2011 ◽  
Vol 471-472 ◽  
pp. 536-541 ◽  
Author(s):  
Zainudin A. Rasid ◽  
Ayob Amran ◽  
Rizal Zahari ◽  
Faizal Mustapha ◽  
D.L. Majid ◽  
...  
Keyword(s):  
Finite Element ◽  
Shape Memory Alloy ◽  
Shape Memory ◽  
Laminated Composite ◽  
Composite Plates ◽  
Thermal Buckling ◽  
Element Formulation ◽  
Laminated Composite Plates ◽  
Aerospace Applications ◽  
Post Buckling

Thermal buckling and thermal post-buckling behaviours of laminated composite plates are improved by embedding shape memory alloy wires within laminates of composite plates. The procedure is to use the recovery stress that is induced when the reverse transformation of the shape memory alloy from martensite to austenite phases is constrained. For aerospace applications where the source of the shape memory alloy heating is the high temperature environment itself, a study is conducted to see the effect of shape memory alloy in improving the thermal buckling and post-buckling of composite plates. Due to the temperature dependent nature of the composite matrix and the shape memory alloy, the finite element formulation developed here is in the incremental form. Solving this non-linear model using the developed in-house source code, critical loads are determined and the post-buckling paths of the shape memory alloy composite plates are traced. This study shows that by embedding the shape memory alloy within composite plates, the thermal buckling and post-buckling behaviours of composite plates can be improved substantially.

The Instability Improvement of the Shape Memory Alloy Composite Plates Subjected to In-Plane Parabolic Temperature Distribution

2014 ◽  
Vol 554 ◽  
pp. 32-36 ◽  
Author(s):  
Z.A. Rasid ◽  
R. Zahari ◽  
Amran Bin Ayob
Keyword(s):  
Temperature Field ◽  
Shape Memory Alloy ◽  
Shape Memory ◽  
Composite Plates ◽  
Thermal Buckling ◽  
Recovery Stress ◽  
Uniform Temperature ◽  
Source Codes ◽  
Temperature Distributions ◽  
Post Buckling

The designs of thin structure components of aerospace vehicles require the consideration of thermal buckling and post-buckling problems. Thermal buckling of the structures in the aerospace environment may occur due to non-uniformly distributed temperature field. A finite element method study on the post-buckling of composite plates with embedded shape memory alloy wires was conducted. The plates were subjected to in-plane and through-thickness non-uniform thermal loadings where the non-uniform temperature distributions considered were parabolic in-plane and linearly varying through-thickness thermal loadings that may act separately or in combination. Recovery stress induced by the shape memory alloy was exploited to improve the thermal buckling behaviours of the composite plates. A non-linear finite element model along with its source codes that considered the recovery stress of the shape memory alloy, the non-uniform temperature field, the temperature dependent properties of the SMA and the composite matrix were developed. The post-buckling paths that showed the effect of the shape memory alloy on the thermal post-buckling behaviour of composite plates were generated using the source codes. It was found that the strain energy tuning method of the shape memory alloy greatly improved the post-buckling behaviour of composite plates subjected to the non-uniform temperature distributions.

scholarly journals A Parametric Study on the Elliptical hole Effects of Laminate Composite Plates under Thermal Buckling Load

2020 ◽  
Vol 27 (1) ◽  
pp. 196-203
Author(s):  
Buntheng Chhorn ◽  
WooYoung Jung
Keyword(s):  
Thermal Expansion ◽  
Thermal Expansion Coefficient ◽  
Expansion Coefficient ◽  
Laminate Composite ◽  
Laminate Plate ◽  
Elliptical Hole ◽  
Composite Plates ◽  
Thermal Buckling ◽  
The Finite Element Method ◽  
Square Plate

AbstractIn this study, a thermal buckling analysis of laminate composite square plate was performed with elliptical hole cutout using the finite element method. Graphite/Epoxy laminate plate used in this study is symmetrical stacking sequence plate [(0/90)2]s. This laminate square plate was subjected to temperature loading with clamped support on all edges. Moreover, the parameters considered were fiber orientation (θ), a/b ratio (elliptical hole), elliptical hole inclination (φ), thermal expansion coefficient ratio (α1/α2), and thickness of plates (t). The results showed that as the thermal expansion coefficient ratio changes, the elliptical hole ratio and the elliptical hole inclination have inconsequential effects on the performance of the resistance of laminate composite plates. The maximum values of thermal buckling amplification factor were obtained when the ratio a/b = 1.0, which is a circle cutout,while the minimum values were obtained when the ratio a/b = 0.5, regardless of the thickness of plates. Moreover, the plate with elliptical or circle cutout hole provides about 4% to 9% higher buckling resistance than that of the plate without hole cutout, because when subjected to temperature loading the plate with hole can release stress better than the plate without hole.

Thermal Post-Buckling Analysis of Functionally Graded Composite Plates with Nonlinear Aerodynamic Forces

2010 ◽  
Vol 123-125 ◽  
pp. 280-283
Author(s):  
Chang Yull Lee ◽  
Ji Hwan Kim
Keyword(s):  
Material Properties ◽  
Numerical Solutions ◽  
Virtual Work ◽  
Shear Deformation Theory ◽  
Composite Plates ◽  
Buckling Analysis ◽  
Functionally Graded ◽  
Governing Equations ◽  
Functionally Graded Composite ◽  
Post Buckling

The post-buckling of the functionally graded composite plate under thermal environment with aerodynamic loading is studied. The structural model has three layers with ceramic, FGM and metal, respectively. The outer layers of the sandwich plate are different homogeneous and isotropic material properties for ceramic and metal. Whereas the core is FGM layer, material properties vary continuously from one interface to the other in the thickness direction according to a simple power law distribution in terms of the volume fractions. Governing equations are derived by using the principle of virtual work and numerical solutions are solved through a finite element method. The first-order shear deformation theory and von-Karman strain-displacement relations are based to derive governing equations of the plate. Aerodynamic effects are dealt by adopting nonlinear third-order piston theory for structural and aerodynamic nonlinearity. The Newton-Raphson iterative method applied for solving the nonlinear equations of the thermal post-buckling analysis

Synthesis of low thermal expansion ceramics based on CaZr4(PO4)6–Li2O system

2001 ◽  
Vol 79 (1) ◽  
pp. 6-10 ◽  
Author(s):  
Chong S. Yoon ◽  
Jae H. Kim ◽  
Chang K. Kim ◽  
K.S. Hong
Keyword(s):  
Thermal Expansion ◽  
Low Thermal Expansion

Material and application study for low thermal expansion glass-ceramic CLEARCERAM series

2005 ◽  
Author(s):  
Kousuke Nakajima ◽  
Toshihide Nakajima ◽  
Nobuo Kawasaki ◽  
Yoshiyuki Owari
Keyword(s):  
Thermal Expansion ◽  
Glass Ceramic ◽  
Application Study ◽  
Low Thermal Expansion
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