Fibre reinforced composite aerofoil structures

Patent metadata

Field	Value
Publication number	US-11091245-B2
Application number	US-201815956913-A
Country	US
Kind code	B2
Filing date	Apr 19, 2018
Priority date	Apr 25, 2017
Publication date	Aug 17, 2021
Grant date	Aug 17, 2021

Abstract

A composite component adapted to be formed into an aerofoil, a method of forming an aerofoil, an aerofoil, an aircraft wing and a forming jig. The method involves forming a flat layup sheet of plies (1) to be folded about a central leading edge region (6) of the layup into an aerofoil shape, applying to the flat layup (1) one or more layups of plies (9, 10) shaped as spars, partially curing the layup (1) with the spars attached, folding the resulting partially cured composite component (30) about the leading edge region (6) in a forming jig (19) so that opposing edges (4, 5) of the sheet meet as a trailing edge (36) of the aerofoil (35), clamping the jig (19) closed, and curing the composite component (30) and adhesive in the forming jig (19) to form the finished aerofoil (35).

First claim

The invention claimed is:

1. A method of forming a composite component, wherein the method includes:
forming a first layup of plies of fiber reinforced plastics composite material into a flat sheet having a middle section and side sections on opposite edges of the middle section, wherein the flat sheet has a length in a spanwise direction of the airfoil and a width in a chordwise direction of the airfoil, and the flat sheet has an outer surface configured to form an aerodynamic surface and an opposing reverse surface,
forming on the opposing reverse surface of the side sections a second layup of plies to be formed into a spar extending in a spanwise direction of the flat sheet,
supporting the second layup of plies against the reverse surface,
partially curing the first and second layups of plies together to form the composite component;
folding the composite component to form an aerofoil including a leading edge region form, at least in part, by the middle section of the first layup of plies and the aerofoil further including a trailing edge region formed, at least in part, by edges of the side sections, wherein the side sections overlap each other due to the folding, and wherein the folding of the first layup of plies positions the spar forward of the trailing edge region and positions the spar between the side sections such that the spar abuts both side sections,
supporting the folded composite component in an aerofoil shape, and
applying heat and pressure to fully cure the composite component in the aerofoil shape.

2. The method according to claim 1 , in which the steps of folding the composite component and supporting the folded composite component comprise placing the composite component in a forming jig shaped to form the composite component into the aerofoil shape and folding the composite component in the jig about the leading edge region until edges of the first and second surface regions meet.

3. The method according to claim 1 , in which the second layup of plies is formed as a second flat sheet before being supported in the shape of the spar against the opposing reverse surface.

4. The method according to claim 1 , in which the second layup of plies is formed into a C shape when being supported in the shape of the spar against the opposing reverse surface.

5. A method to form an aerofoil structure comprising:
forming into a sheet a first layup of plies of fiber reinforcing material, wherein the sheet includes an outer surface and an inner surface opposite to the outer surface, and the sheet has a central leading edge section, a first panel section adjacent a first side of the central leading edge section and a second panel section adjacent a second side of the central leading edge section which is opposite to the first panel section, and the central leading edge section and the first and second panel sections each have lengths corresponding to a length of the aerofoil structure;
forming on the inner surface of the first panel section a second layup of plies of fiber reinforcing materials to be formed into a first spar, wherein the second layup of plies is spaced a first distance from a first edge of the sheet;
forming on the inner surface of the second panel section a third layup of plies of fiber reinforcing material to be formed into a second spar, wherein the third layup of plies is spaced a second distance from a second edge of the sheet opposite to the first edge, and the second distance is different than the first distance;
at least partially curing together the first, second and third layups to form a composite component that includes the sheet, the first spar and the second spar;
folding the composite component about the leading edge region until the first edge is proximate to the second edge to form the aerofoil shape, wherein upon the folding the first spar abuts the inner surface of the second panel section and the second spar abuts the inner surface of the first panel section, and
applying heat and pressure to the folded composite component to form and cure the folded composite component in the aerofoil shape.

6. The method of claim 5 , wherein the sheet is flat.

7. The method of claim 5 , wherein the first edge meets the second edge to form a trailing edge of the airfoil shape during the folding step.

8. The method of claim 5 , wherein the first spar is parallel to the second spar and the first and second spars extend in a spanwise direction of the aerofoil shape.

Assignees

• Airbus Operations Ltd

Inventors

• Lage Paulo Jorge Teixeira

Classifications

• B64F5/10

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title

• B29C70/384

  Fiber placement heads, e.g. component parts, details or accessories · CPC title

• B29C53/04 Primary

  of plates or sheets {(B29C63/04 takes precedence; bending or folding paper B31F1/0003; folding films B65H45/00)} · CPC title

• B64C9/02

  Mounting or supporting thereof · CPC title

• B29C33/26 Primary

  by pivotal movement · CPC title