Automated structural design and analysis of advanced composite wing models

Mccullers, L. A.; Naberhaus, J.D.

doi:10.1016/0045-7949(73)90067-9

Cited by 6 publications

(4 citation statements)

References 1 publication

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“…Regarding the detailed design of a composite wing, the majority of research works are focused on local structural problems, e.g. buckling issues or lay-up optimization for obtaining lighter designs [7][8][9][10][11][12]. The first work referring to the analysis of a multispar concept was published in 1932 by Sunger [13] and presents the static analysis of a metallic multispar wing structure.…”

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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“…Bolt Load πd 2 / 4 ≤ Allowabe shear o f bolt (11) In Equation 11, the Bolt Load for a double row of bolts is calculated with the use of Equation (12).…”

Section: Shear Stress =mentioning

confidence: 99%

“…Furthermore, topology optimization is frequently employed to determine the optimum location of certain structural components under static and aeroelastic loads [8,9]. Additionally, a lot of work has been accomplished for the solution of local structural problems, e.g., buckling issues or lay-up optimization [10][11][12][13][14][15][16][17], aeroelasticity, flutter [18], local optimization of panels or areas with cut-outs [19][20][21] for obtaining lighter designs. The aforementioned studies refer to a 2-spar arrangement only and to some specific structural problems, while the advantages that can be obtained by accommodating additional spar (more than two) in the wingbox as well as the design methodology that has to be followed is not exhaustively covered.…”

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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“…The strength criterion required the model wings to be stronger than their full-scale counterparts. Previous experience with a high-strength aeroelastic model 1 ' 15 suggested the use of a hybrid laminate of unidirectional glassepoxy and graphite-epoxy to provide sufficient strength without excessive stiffness. Glass-epoxy and graphite-epoxy tape with cured ply thicknesses of 0.0023 and 0.0018 in., respectively, were used to preserve the stiffness distribution of the full-scale wings.…”

Section: Model Designmentioning

confidence: 99%

Design, analyses, and model tests of an aeroelastically tailored lifting surface

Rogers

Braymen

Shirk

1983

Journal of Aircraft

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Aeroelastic tailoring provides a measure of control over the interaction of aerodynamic loading and structural response during the design of composite lifting surfaces. A recent investigation involving the design, fabrication, and test of an aeroelastically tailored fighter wing was conducted to provide data for validating the design methodology. Three sets of composite wings with different design objectives were tested in addition to a set of rigid steel wings. The static aeroelastic tests featured the measurement of model forces, pressure distributions, and deflected shapes in the transonic regime. Test results are compared with analytical predictions and show significant aeroelastic benefits.

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Automated structural design and analysis of advanced composite wing models

Cited by 6 publications

References 1 publication

Investigation on a multispar composite wing

Investigation on a multispar composite wing

Towards the Design of a Multispar Composite Wing

Design, analyses, and model tests of an aeroelastically tailored lifting surface

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