Simplified methods for the buckling analysis of composite multi-spar wing boxes

Aston, G. H.; Williams, F.W.

doi:10.1016/0263-8223(94)90050-7

Cited by 7 publications

(6 citation statements)

References 3 publications

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“…A literature review has revealed that investigation on multispar wing structures is rare [1][2][3], while studies on the possible advantages of composite multispar wing configurations have not performed so far. Most researchers are focusing their studies on other specific problems of composite wing design, such as aeroelasticity, flutter, and local optimization of panels or areas with cut-outs, etc.…”

Section: Introductionmentioning

confidence: 99%

Investigation on a multispar composite wing

Stamatelos

Labeas

2011

Proceedings of the Institution of Mechanical Engineers, Part G:

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The potential advantages of an airliner composite wing are investigated by considering a multispar configuration. An efficient initial sizing methodology, suitable for large-scale composite components, such as the studied aircraft main wing, is applied for the preliminary design of a multispar wing. The methodology comprises three basic modules, i.e. the computational stress analysis of the structure, the comparison of the stress–strain results to design allowable, and a suitable resizing procedure in order to satisfy all design requirements. A detailed comparison between optimized designs of conventional (2-spar) and three alternative wing configurations, which comprise 4-, 5-, and 6-spars for the wing construction is performed. In order to understand the effect of different material properties, as well as the variation of maximum strain level allowed the total wing mass, parametric analyses are performed for all configurations considered. Comparing the conventional and the multispar arrangements, it arises that under certain conditions, the multispar configuration demonstrates significant advantages over the conventional design. In addition, for all the configurations investigated, i.e. the 2-, 4-, 5- and 6-spar designs, the mass breakdown in the wing subcomponents is presented, such that the maximum mass saving potentials are identified for each multispar configuration.

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Section: Introductionmentioning

confidence: 99%

Investigation on a multispar composite wing

Stamatelos

Labeas

2011

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…It is a variation on the dimensions of a wing box which was obtained from British Aerospace Defence (Military Aircraft) for an earlier [17] demonstration of a structure splitting method for analysis, as opposed to the present design application. Tables 2 and 3 show the lay-ups and loading of the structure.…”

Section: Details Of the Examplementioning

confidence: 99%

“…This value of =0.5 was applied to the loads and stiffnesses in the hatched portions of the spars, but not to their thicknesses, which retained their values for the original box. A lower bound answer is guaranteed for analysis [17,25], which implies that an upper bound must be obtained when designing by this splitting method. Hence the design which results must overestimate the optimum design mass and must have a reserve of strength, i.e.…”

Section: Details Of the Examplementioning

confidence: 99%

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Design of structures by a splitting method

Watson

Kennedy²,

Williams³

1999

Computers & Structures

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-A simplified method for the design of multi-spar wing boxes is presented.In typical multi-spar wing boxes the spars divide the boxes into cells. In the method presented these are analyzed individually, with adjacent cells taking their share of the stiffnesses of the common spar wall. This splitting method yields a design method that is computationally much quicker than designing a complete wing box, because each cell is considered separately from the others, except for linking between their design variables. The critical buckling load factor of the assembled structure when designed in this way will usually exceed the design load factor and otherwise will be equal to it, i.e. the design is guaranteed to be conservative.

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“…A study carried out by Watson et al [22] investigates a multispar configuration by considering only the buckling of skin, with semi-analytical methods, as a constraint, while for the rest of the members no additional failure criteria are adopted. Aston et al in [23] developed a methodology for conservatively designing a multispar wing, and the focus of this work is to achieve fast design results rather than obtaining optimized member sizing. Herbeck developed a design methodology for sizing a wing structure by having as design criteria the buckling of skin and ribs, as well as bolted joints behavior [24].…”

Section: Introductionmentioning

confidence: 99%

Towards the Design of a Multispar Composite Wing

Stamatelos

Labeas

2020

Computation

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In the pursuit of a lighter composite wing design, fast and effective methodologies for sizing and validating the wing members (e.g., spar, ribs, skins, etc.) are required. In the present paper, the preliminary design methodology of an airliner main composite wing, which has an innovative multispar configuration instead of the conventional two-spar design, is investigated. The investigated aircraft wing is a large-scale composite component, requiring an efficient analysis methodology; for this purpose, the initial wing sizing is mostly based on simplified Finite Element (FE) stress analysis combined to analytically formulated design criteria. The proposed methodology comprises three basic modules, namely, computational stress analysis of the wing structure, comparison of the stress–strain results to specific design allowable and a suitable resizing procedure, until all design requirements are satisfied. The design constraints include strain allowable for the entire wing structure, stability constraints for the upper skin and spar webs, as well as bearing bypass analysis of the riveted/bolted joints of the spar flanges/skins connection. A comparison between a conventional (2-spar) and an innovative 4-spar wing configuration is presented. It arises from the comparison between the conventional and the 4-spar wing arrangement, that under certain conditions the multispar configuration has significant advantages over the conventional design.

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Simplified methods for the buckling analysis of composite multi-spar wing boxes

Cited by 7 publications

References 3 publications

Investigation on a multispar composite wing

Investigation on a multispar composite wing

Design of structures by a splitting method

Towards the Design of a Multispar Composite Wing

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