Design and Testing of Aeroelastically Tailored Wings Under Maneuver Loading

Werter, Noud; Sodja, Jurij; Breuker, Roeland De

doi:10.2514/1.j054965

Cited by 8 publications

(6 citation statements)

References 34 publications

(31 reference statements)

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“…These experiments have been performed on platelike structures; hence, they are unsuitable for validation of aeroelastic design frameworks dealing with wing structures having a closed-cell cross-section. Wind tunnel experiments involving such tailored composite wings with a closed-cell cross-section have been presented only recently by Werter et al [41] and Sodja et al [42].…”

Section: Subscriptsmentioning

confidence: 99%

Aeroelastic Demonstrator Wing Design for Maneuver Load Alleviation Under Cruise Shape Constraint

Sodja

Werter

Breuker

2021

Journal of Aircraft

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Section: Subscriptsmentioning

confidence: 99%

Aeroelastic Demonstrator Wing Design for Maneuver Load Alleviation Under Cruise Shape Constraint

Sodja

Werter

Breuker

2021

Journal of Aircraft

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“…This framework is based on gradient-based optimization in the lamination parameter domain employing a geometrically nonlinear beam model with variable thickness and stiffness. Its application to the design of a rectangular unswept composite wing with tailored skins was presented in [12]. The designed wing employed constant thickness and stiffness along the span, so that a manufacturable stacking sequence could be found by a simple sweep over ply angles.…”

Section: Introductionmentioning

confidence: 99%

“…Although the wings designed and manufactured in the mentioned works [9,10,12] employ tailored composite skins, they all feature foam as internal structure in place of spars and ribs. Therefore, on one hand those wings represent a step closer to industrial practice with respect to plate structures, but on the other hand they are not entirely representative of a realistic wing as they miss the typical wingbox structure.…”

Section: Introductionmentioning

confidence: 99%

Multi-Fidelity Design of an Aeroelastically Tailored Composite Wing for Dynamic Wind-Tunnel Testing

Mitrotta

Rajpal²,

Sodja³

et al. 2020

AIAA Scitech 2020 Forum

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Aeroelastic tailoring offers an effective way to exploit the anisotropic properties of the composite materials used in lightweight aerospace structures. This paper presents a design methodology for experimental wings that employ a typical wingbox structure. The proposed methodology combines three different analysis tools: P , a low-fidelity aeroelastic framework with tailoring capabilities, O BLESS, an open-source toolbox for optimization of blended stacking sequences and MSC N , a commercial software commonly used in industry for aeroelastic analyses. An experimental wing is designed using the proposed framework. The developed design is manufactured using carbon fibre pre-preg and hand layup technique. Finally, the manufactured wing is tested in the wind-tunnel at speeds up to 25 m/s. Both static and dynamic tests are performed, where for the latter a gust generator is used. The experimental results provide a source of comparison for the numerical models used in the proposed design methodology.

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“…Furthermore, considering the reliance on computer software and the critical choices that must be made during early design phases, the development of accurate, yet rapid, structural analysis methods is of paramount importance for aerospace applications [4]. Finite element (FE) beam models, which are known to be reliable at predicting global structural behaviours with relatively few degrees of freedom (DoFs), have consequently become widely used approximations for the preliminary design and aeroelastic tailoring of aerospace structures [5,6].…”

Section: Introductionmentioning

confidence: 99%

Corotational Finite Element Formulation for Static Nonlinear Analyses with Enriched Beam Elements

et al. 2020

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The increasing reliance of aerospace structures on numerical analyses encourages the development of accurate, yet computationally efficient, models. Finite element (FE) beam models have, in particular, become widely-used approximations during preliminary design stages and to investigate novel concepts, e.g. aeroelastic tailoring. Over the last 50 years, developments in hp-FE methods based on elements of variable size (h) and polynomial degree (p) have helped reduce the computational cost of numerical analyses. Concurrently, many structures, including aircraft wings and wind turbine blades, have gradually increased in length, slenderness, and complexity. As a result, modern blades and wings regularly operate beyond the range of linear deformation, requiring non-linear analyses for which hp-FE methods are often not readily applicable. The aim of this paper is, therefore, to derive a co-rotational finite element formulation for enriched 3-, 4-and 5-noded beam elements, suitable for non-linear hp-FE refinement. To this end, we derive the mathematical formulation to incorporate enriched elements within the co-rotational FE beam framework. The proposed formulation is then validated against multiple non-linear benchmark problems and an experimental case study.

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Design and Testing of Aeroelastically Tailored Wings Under Maneuver Loading

Cited by 8 publications

References 34 publications

Aeroelastic Demonstrator Wing Design for Maneuver Load Alleviation Under Cruise Shape Constraint

Aeroelastic Demonstrator Wing Design for Maneuver Load Alleviation Under Cruise Shape Constraint

Multi-Fidelity Design of an Aeroelastically Tailored Composite Wing for Dynamic Wind-Tunnel Testing

Corotational Finite Element Formulation for Static Nonlinear Analyses with Enriched Beam Elements

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