Multiobjective design of laminated cylindrical shells for maximum torsional and axial buckling loads

Walker, Mark; Reiss, T.; Adali, Sarp

doi:10.1016/s0045-7949(96)00189-7

Cited by 30 publications

(13 citation statements)

References 10 publications

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“…The Method of weighted-sum, which is the most common MOO method, belongs to this group. Examples of applications of this method in stacking sequence design of composite materials can be found in [17][18][19][20]. Another common non-generating method is called the ε-constraint method.…”

Section: Optimization Algorithmmentioning

confidence: 99%

Optimum Structural and Manufacturing Design of a Braided Hollow Composite Part

et al. 2009

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Simultaneous material consolidation and shaping, as performed in manufacturing of composite materials, causes a strong interconnection between structural and manufacturing parameters which makes the design process complicated. In this paper, the design of a carbon fiber bicycle stem is examined through the application of a multi-objective optimization method to illustrate the interconnection between structural and manufacturing objectives. To demonstrate the proposed method, a test case dealing with the design of composite part with complex geometry, small size and hollow structure is described. Bladder-assisted Resin Transfer Molding is chosen as the manufacturing method. A finite element model of the stem is created to evaluate the objectives of the structural design, while a simplified 2D model is used to simulate the flow inside the preform during the injection process. Both models are formulated to take into account the variation of fiber orientation, thickness and fiber volume fraction as a function of braid diameters, injection pressure and bladder pressure. Finally, a multiobjective optimization method, called Normalized Normal Constraint Method, is used to find a set of solutions that simultaneously optimizes weight, filling time and strength. The solution to the problem is a set of optimum designs which represent the Pareto frontier of the problem. Pareto frontier helps to gain insight into the trade-off among objectives, whose presence and importance is confirmed by the numerical results presented in this paper.

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Section: Optimization Algorithmmentioning

confidence: 99%

Optimum Structural and Manufacturing Design of a Braided Hollow Composite Part

et al. 2009

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“…Multi-objective design of laminate composite cylindrical shells is carried out by Sun and Hansen [18] and Tennyson and Hansen [19] considering torsional, axial, external and internal pressure loadings. Walker et al [20] have determined the best layup to optimize the multi-objective design of laminated cylindrical shells for a weighted combination of maximum axial and torsional buckling loads. Smerdov [21,22] have dealt with different formulations of optimization problems on buckling of multi-layered composite cylindrical shells under axial compression and external pressure as well as the effects of variations in the dimensions and materials of the shell on buckling strength.…”

Section: Previous Workmentioning

confidence: 99%

Development of a hybrid meta-heuristic algorithm for combinatorial optimisation and its application for optimal design of laminated composite cylindrical skirt

Rao

Shyju

2008

Computers & Structures

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“…A typical example might be the minimization of weight of a laminate subject to a speci®c stiffn ess. H owever, if there is also a need to trade weight with cost, strength and various buckling constraints, analytical methods become more dif®cultÐthough attempts have been made with multiple objectives [9].…”

Section: Description Of Databasementioning

confidence: 99%

“…Even by restrictin g the choice of angles to four allows a huge number of possible lay-ups to be chosen. F or an n-layer laminate there are 4 n potentially different laminates; thus for a 16-layer laminate which may have a plate thickness of as little as 2 mm there are in excess of 4610 9 permutationsÐa staggeringly high number. In practice, designers restrict the actual number of viable alternatives, typically by eliminating undesirable coupling responses and so making the laminate balanced and symmetrical.…”

Section: Introductionmentioning

confidence: 99%

Designing composite structures: Lay-up selection

Weaver

2002

Proceedings of the Institution of Mechanical Engineers, Part G:

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The use of high-performance composite materials of the sort used in the aerospace and F ormula 1 industries is becoming more widespread. On one level they are exciting to work with because they give scope for designing the`material' in addition to a`structure' through judicious placement of the ply orientation. Layers are stiff and strong in the ®bre direction while weak and compliant in the transverse direction. It is this ability to tailor material properties layer by layer that gives designers huge potential in design. One possible explanation for the prevalent use of quasiisotropic (`black aluminium') carbon composites in structures is the lack of available design tools. Analysis packages exist that will predict performance, but only for a given choice of ®bre orientation. H ere a design tool is presented that aids selection of ®bre orientations. Optimization of laminate ®bre angles is dif®cult for multiple-load cases and objectives since there are many local minima to assess. The alternative approach that is presented here, for¯at plates and cylindrical shells, circumvents the need (in the early stages of design) for conventional optimization strategies that often prove dif®cult and complicated to implement. The basic idea is to build a database that stores appropriate properties of all permutations of lay-up angles for a laminate. R ather than access these properties by a question and answer, black-box technique, a graphical method is proposed. The designer can select viable laminates by ®rst plotting a succession of two-dimensional charts containing relevant properties. Then, using simple on-screen techniques, the number of potential laminates is visually reduced by selecting those with desirable properties. Two case studies are presented to illustrate the selection method. The ®rst concerns the optimization of a spar web, typically found in an aircraft wing structure, while the second concerns the optimization of a cylindrical shell, subject to axial compression, that undergoes simultaneous Euler-type buckling and local buckling.

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Multiobjective design of laminated cylindrical shells for maximum torsional and axial buckling loads

Cited by 30 publications

References 10 publications

Optimum Structural and Manufacturing Design of a Braided Hollow Composite Part

Optimum Structural and Manufacturing Design of a Braided Hollow Composite Part

Development of a hybrid meta-heuristic algorithm for combinatorial optimisation and its application for optimal design of laminated composite cylindrical skirt

Designing composite structures: Lay-up selection

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