Buckling load prediction of laminated composite stiffened panels subjected to in-plane shear using artificial neural networks

UK Mallela, A Upadhyay - Thin-Walled Structures, 2016 - Elsevier
Stiffened panels are basic building blocks of weight sensitive structures. Design of laminated
composite stiffened panels is more involved and requires the use of an optimization …

Dynamic stiffness elements and their applications for plates using first order shear deformation theory

M Boscolo, JR Banerjee - Computers & structures, 2011 - Elsevier
Dynamic stiffness elements for plates are developed using first order shear deformation
theory to carry out exact free vibration analysis of plate assemblies. The analysis has been …

Dynamic stiffness formulation for composite Mindlin plates for exact modal analysis of structures. Part I: Theory

M Boscolo, JR Banerjee - Computers & Structures, 2012 - Elsevier
The dynamic stiffness formulation for both inplane and bending free vibration based on the
first order shear deformation theory for composite plates is presented. The explicit terms of …

[HTML][HTML] Compressive strength of composite laminates with delamination-induced interaction of panel and sublaminate buckling modes

AT Rhead, R Butler, GW Hunt - Composite Structures, 2017 - Elsevier
Abstract Compression After Impact (CAI) strength is critical to the safety and weight of carbon
fibre aircraft. In this paper, the standard aerospace industry practice of using separate …

Buckling and post-buckling analysis of cracked stiffened panels via an X-Ritz method

V Gulizzi, V Oliveri, A Milazzo - Aerospace Science and Technology, 2019 - Elsevier
A multi-domain eXtended Ritz formulation, called X-Ritz, for the analysis of buckling and
post-buckling of stiffened panels with cracks is presented. The theoretical framework is …

Free vibration analysis of a twisted beam using the dynamic stiffness method

JR Banerjee - International Journal of Solids and Structures, 2001 - Elsevier
An exact dynamics stiffness matrix is developed and subsequently used for free vibration
analysis of a twisted beam whose flexural displacements are coupled in two planes. First the …

Buckling and postbuckling of stiffened composite panels with cracks and delaminations by Ritz approach

A Milazzo, V Oliveri - AIAA Journal, 2017 - arc.aiaa.org
A Ritz approach for the analysis of buckling and postbuckling of stiffened composite panels
with through-the-thickness cracks and/or delaminations is presented. The structure is …

Layer-wise dynamic stiffness solution for free vibration analysis of laminated composite plates

M Boscolo, JR Banerjee - Journal of Sound and Vibration, 2014 - Elsevier
The dynamic stiffness method has been developed by using a sophisticated layer-wise
theory which complies with the C z 0 requirements and delivers high accuracy for the …

Compressive strength of delaminated aerospace composites

R Butler, AT Rhead, W Liu… - … Transactions of the …, 2012 - royalsocietypublishing.org
An efficient analytical model is described which predicts the value of compressive strain
below which buckle-driven propagation of delaminations in aerospace composites will not …

Optimum design of aircraft panels based on adaptive dynamic harmony search

B Keshtegar, P Hao, Y Wang, Y Li - Thin-Walled Structures, 2017 - Elsevier
Aiming at the optimization of aircraft panels, a modified version of harmony search (HS)
algorithm is proposed based on the information of the harmony memory (a memory location …