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
2022-11-23
Patent
Electronic Resource
English
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