A wing 301, 401 for an aircraft, the wing having a passive variable aeroelastic geometry for accommodating efficient flight at multiple aircraft speeds, comprises a wing skin 303, 407 having a composite structure comprising a lamination of multiple layers deposited according to a predetermined lamination profile. One of the layers comprises a continuous non-linear deposition of material 305, 411, the wing skin comprising a stiffness distribution profile defined by the lamination profile. A method of fabricating a component of the aircraft wing comprising depositing a non-linear tow of a first material, wherein this material is deposited as part of a lamination of multiple layers. A composite structure, for a component of an aircraft wing, comprising a lamination of multiple layers having at least one layer with a non-linear continuous tow of a first material. The tow defining a track having a bend radius of curvature within a range 40-100mm. At least one of the layers comprises carbon fibre. The continuous track of material may be formed by way of continuous tow shearing of material.
Aircraft wings
23.11.2022
Patent
Elektronische Ressource
Englisch
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