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• W1880243208 abstract "The objective of the present work is to develop mathematical/finite element basedoptimization techniques for fibre reinforced polymer (FRP) laminated composite structuressubjected to buckling. Many issues arise when a laminated FRP composite structuresubjected to compressive load and ultimately fail under buckling. Issues such asunderstanding FRP composite materials, buckling and post-buckling behaviour of thestructure, delamination and detection of the crack front need attention. Hence, in thepresent research works were carried out in each of these areas.Various experimental studies were carried out to study material characterisation, thedelamination fracture toughness in mode I, mode II and mixed-mode l/ll using DCB, ENF andMMB tests and buckling of FRP composite plates. From these series of test GIC, GIIC andfracture envelope under different mode mixity ratio were determined. Also the bucklingtests of the plates with optimum and non-optimum stacking sequence were performed toverify the optimisation results. The effect of damage on buckling load was studied by testson buckling of plates with pre-existing centrally located delamination patch at the plate mid-plane and on plate with a hole at the centre of the plate to investigate the effect of cut-outand damage on buckling load. Finally, IR thermography and CT-Scan non-destructive tests(NDT) were used for plates with pre-existing centrally located delamination patch to studythe direction and the extent of delamination crack propagation after the buckling tests.In the case of plates with pre-existing centrally located delamination patch with diameterless than 32mm, the critical buckling load has not changed. But when the delaminationpatch diameter reached to 48mm (at around 60% of plate width), there was significantreduction in the critical buckling load. in the case for plate with cut-out a noticeablereduction on the critical buckling load was observed when the diameter of the hole wasmore than 25% of the plate width.IR thermography and CT-Scan images analysis of the plates after buckling tests showed thatin plates with pre-existing centrally located delamination patch with a diameter of D=16mm, the plate failure occurs near the loading edge. In the case of plates with delaminationpatch of D=32mm, some plates failed near the loading edge and in some plates crack propagated along the i45° fibre direction around delamination patch. However, for plateswith delamination patch with diameter of D=48mm, in all samples the delaminated areapropagated along the fibre direction around the delaminated area and no failure observednear the loading edge.Inherent to the use of FRP composite materials is the inclusion of ply angles and stackingsequence as design variables. These design variables are discrete in nature. The optimizationof these models is typically difficult due to their combinatorial nature and potentialexistence of multiple local minima in the search space.In this research bottom-up enumeration search optimisation approach was developed foroptimum design of stacking sequence of laminated composite structure for maximumcritical buckling load above the required target load using MATLAB software. The optimisedresults were verified by buckling experiments and FE simulations. The developedprogramme is flexible to use for other loading condition. For the case of uniaxialcompressive loading with preselected target buckling load, the optimum number of layersand orientation for 0/90 biaxial fabrics and unidirectional plies were determined. Thepercentage of difference between analytical buckling load and FEA eigen solution withexperiments are about -13.1% and -3.2%, respectively.Depending on the properties and arrangement of the skin and stiffener, different bucklingmodes and failure loads can occur in a stiffened plate. For shape optimisation of blade-stiffened plate subjected to buckling, Sequential Quadratic Programming (SQP), GeneticAlgorithms (GA) and Simulated Annealing (SA) techniques were used in MATLABoptimisation programme in conjunction with ANSYS finite element software. The developedtechniques are tested for minimum weight of a blade-stiffened plated with predefinedstacking sequence of stiffener and the plate where the geometry parameters were designvariables. In this work, the size of the stiffener height and the distance between the stiffenerfor a required target buckling load and optimum weight were determined." @default.
• W1880243208 created "2016-06-24" @default.
• W1880243208 creator A5047896476 @default.
• W1880243208 date "2014-05-01" @default.
• W1880243208 modified "2023-09-27" @default.
• W1880243208 title "Optimisation of stacking sequence of fibre reinforced plastic laminated composite structures subjected to buckling" @default.
• W1880243208 hasPublicationYear "2014" @default.
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