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 for plates are developed using first order shear deformation
theory to carry out exact free vibration analysis of plate assemblies. The analysis has been …

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 …

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 …

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 …

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 …

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 …

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 …

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 …

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 …