Thermal buckling and vibration analysis of laminated composite curved shell panel

Abstract

Purpose -The purpose of this paper is to develop a general mathematical model for laminated curved structure of different geometries using higher-order shear deformation theory to evaluate in-plane and out of plane shear stress and strains correctly. Subsequently, the model has to be validated by comparing the responses with developed simulation model (ANSYS) as well as available published literature. It is also proposed to analyse thermal buckling load parameter of laminated structures using Green-Lagrange type non-linear strains for excess thermal distortion under uniform temperature loading. Design/methodology/approach -Laminated structures known for their flexibility as compared to conventional material and the deformation behaviour are greatly affected due to combined thermal/aerodynamic environment. The vibration/buckling behaviour of shell structures are very different than that of the plate structures due to their curvature effect. To model the exact behaviour of laminated structures mathematically, a general mathematical model is developed for laminated shell geometries. The responses are evaluated numerically using a finite element model-based computer code developed in MATLAB environment. Subsequently, a simulation model has been developed in ANSYS using ANSYS parametric design language code to evaluate the responses. Findings -Vibration and thermal buckling responses of laminated composite curved panels have been obtained based on proposed model through a customised computer code in MATLAB environment and ANSYS simulation model using ANSYS parametric design language code. The convergence behaviour are tested and compared with those available in published literature and ANSYS results. Finally, the investigation has been extended to examine the effect of different parameters (thickness ratios, curvature ratios, modular ratios, number of layers and support conditions) on the free vibration and thermal buckling responses of laminated curved structures. Practical implications -The present paper intends to give sufficient amount of numerical experimentation, which may lead to help in designing of finished product made up of laminated composites. Most of the aerospace, space research and defence organisation intend to develop low cost and high durable products for real hazard conditions by taking combined loading and environmental conditions. Further, case studies might lead to a lighter design of the laminated composite panels used in high-performance systems, where the weight reduction is the major parameter, such as aerospace, space craft and missile structures. Originality/value -In this analysis, the geometrical distortion due to temperature is being introduced through Green-Lagrange sense in the framework of higher-order shear deformation theory for different types of laminated shells (cylindrical/spherical/hyperboloid/elliptical). A simulation-based model is developed using ANSYS parametric design language in ANSYS environment for different geometries and loading condition and compared with the numeri...

Prediction of nonlinear eigenfrequency of laminated curved sandwich structure using higher-order equivalent single-layer theory

“…cylindrical ( R x = R and R y = ∞), spherical ( R x = R and R y = R ), elliptical ( R x = R and R y = 2 R ), hyperbolical ( R x = R and R y = − R ) and flat ( R x = ∞ and R y = ∞). The displacement field of sandwich composite shell panel considered as equation (1) based on higher-order ESL mid-plane kinematics [39] where u , v and w are the displacement of any point within the panel along x , y and z directions, respectively. u 0 , v 0 and w 0 are the mid-plane displacement of any point within the panel along x , y and z directions, respectively.…”

“…In addition to that, for an accurate prediction of the nonlinear nature of the vibration of sandwich composite structures, the transverse shear deformation, and geometric nonlinearity is considered as Green–Lagrange type of nonlinearity instead of von-Karman type of nonlinearity. Subsequently, an effort has been made in the recent past to investigate the geometrical nonlinear frequency and dynamic responses of the curved layered structure using Green–Lagrange strain including all of the nonlinear higher-order terms in the framework of the HSDT kinematics [35–40]. Further, the nonlinear vibration responses of carbon nanotubes (CNTs) conveying viscous fluid is examined based on the nonlocal and the modified couple stress theories with the help of method of multiple scale (MMS) and Galerkin approach and differential quadrature method (DQM) by considering the geometrical nonlinearity in von-Karman sense [41,42].…”

Effects of aluminum foam filling on the low-velocity impact response of sandwich panels with corrugated cores

“…Structures applied as primary load carrying component subjected to both the quasi-static and impact load require high specific strength and energy absorption as well as low density [1–3]. Lightweight sandwich structures with metallic lattice cores such as honeycombs [4–6], corrugated cores [7–9], pyramidal cores [10–12], as well as laminated sandwich panels [13–16] are proposed to have such features compared with acoustic damping, thermal insulation, and other multifunctional properties. For the laminated sandwich composite panel, the delamination is also very important, and efforts have been down to study and improve its mechanical [3], vibration [13,14], and thermal buckling [15,16] properties.…”

Experimental study of ballistic resistance of sandwich targets with aluminum face-sheet and graded foam core

“…In recent decades, analysis of sandwich panels and laminated composite, taking into account the load and boundary conditions, was highly regarded. For example, analysis of the nonlinear termo-elasticity, frequency analysis, stability, vibration and static responses, thermal buckling, and ballistic resistance of these structures were studied by researchers [18][19][20][21][22].…”