Composite structure having an integrated support

Patent metadata

Field	Value
Publication number	US-10830376-B2
Application number	US-201816190732-A
Country	US
Kind code	B2
Filing date	Nov 14, 2018
Priority date	Nov 15, 2017
Publication date	Nov 10, 2020
Grant date	Nov 10, 2020

Abstract

A composite structure ( 1 ) for an aircraft, having at least one insert ( 2 ) for receiving attachment devices, each insert ( 2 ) includes a core ( 3 ) having a major dimension and containing at least one through-hole ( 4 ), and a composite strip arrangement formed by a first section ( 5 ) surrounding the core ( 3 ) and attached to said core ( 3 ) by an adhesive polymeric layer, and a second section ( 6 ) including at least one free end ( 6 a ). The first ( 5 ) and the second portion ( 6 ) of the composite strip arrangement are disposed over a first surface ( 1 a ) of the composite structure ( 1 ), such that the major dimension of the core ( 3 ) is positioned transversal to said first surface ( 1 a). The at least one insert ( 2 ) is co-cured with the composite structure ( 1 ).

First claim

The invention is:

1. A composite structure for an aircraft comprising:
a first surface of the composite structure;
at least one insert configured to receive attachment devices, wherein the at least one insert includes:
a core having a major dimension and including at least one through-hole, and
a composite strip arrangement formed by a first section adjacent the core and attached to the core by an adhesive polymeric layer, and a second section adjacent the core and attached to the first section, wherein the second section includes at least one free end;
wherein at least one part of both the first section and the second section of the composite strip arrangement is disposed on a first surface of the composite structure, and the major dimension of the core is positioned substantially transverse to the first surface of the composite structure;
wherein the at least one insert is co-cured with the composite structure form a single piece of the composite structure and the insert, and
wherein the at least one insert is configured to receive at least one attachment device.

2. The composite structure according to claim 1 , wherein the composite structure has opposite edges, and wherein the second section extends between the opposite edges and is configured to provide support for attachment devices to be attached to the at least one insert.

3. The composite structure according to claim 1 , wherein the core is formed by foam polymer or short-fiber thermoplastic polymer.

4. The composite structure according to claim 1 , wherein the core has a polygonal shape.

5. The composite structure according to claim 1 , wherein the at least one through-hole in the core is positioned at an outermost section of the core and away from the second section.

6. The composite structure according to claim 1 , wherein the insert includes a metal bush received in the through-hole of the core, wherein the metal brush formed of an aluminum alloy, titanium or a steel alloy.

7. An attachable system for an aircraft comprising:
a composite structure including a first surface;
an insert including a composite core plate with a through hole and composite strip sections adjacent edges of the composite core plate, wherein the composite strip sections adhere to the core pate, wherein an exposed surface of at least one of the composite strip sections abuts and is secured to the first surface of the composite structure; and
an attachment device including a clamp and the attachment device fixed to the insert by a fastener in the through hole;
wherein a long edge of the core plate is adjacent the first surface such that one of the composite strip sections is sandwiched between the long edge and the first surface;
wherein a free end of at least one of the composite strip sections extends beyond the core plate and is secured to the first surface.

8. The attachable system according to claim 7 , wherein the attachment device includes a bracket configured to support the clamp, wherein the bracket is partially disposed on the insert and fixed to the insert by the fastener.

9. The attachable system according to claim 8 , wherein the bracket and the clamp are a single body component.

10. The attachable system according to claim 8 , wherein the fastener includes a spacer which elevates the clamp above the insert.

11. The attachable system according to claim 7 , wherein the attachment device further comprises a tubular spacer disposed between the clamp and the through-hole of the core.

12. The attachable system according to claim 7 , wherein the clamp has an annular body and opposing projections, wherein one of the opposing projections has an aperture to receive the fastener, and the other of the opposing projections ends at a tubular spacer on the fastener, wherein the spacer has a threaded end to fix the clamp to the insert.

13. The attachable system according to claim 7 , wherein the clamp is one of a saddle clamp, a P-clamp, and a double P clamp.

14. A method to manufacture a composite structure comprising:
forming providing an insert by applying an adhesive layer on a first composite strip to an outer edge of a core plate having a through hole, wherein a long edge of the core plate is not covered by the first composite strip;
applying the long edge of the core plate to a first side of a second composite strip and applying a portion of the first composite strip to a portion of the second composite strip beyond the core plate, wherein the first and second composite strips entirely cover peripheral edges of the core plate;
attaching a second side of the second composite strip to a first surface of the composite structure, such that the second composite strip is sandwiched between the first surface and the long edge of the core plate and portions of the second side of the second composite strip beyond the core plate extend are attached to the first surface; and
curing the insert and the composite structure together such that the insert with the core plate and first and second composite strips and the composite structure form a single piece composite structure.

15. The method according to claim 14 , further comprising, after the curing, fixing a clamp to the insert by a fastener engaging the clamp and the at least one through-hole of the core plate.

Assignees

• Airbus Operations Sl

Inventors

• Honorato Ruiz Francisco Javier
• Sanchez Franco Diego
• Rodriguez Urbina Luis
• Guinaldo Fernandez Enrique
• Garcia Nieto Carlos

Classifications

• B29C70/74 Primary

  Moulding material on a relatively small portion of the preformed part, e.g. outsert moulding {(B29C70/845 takes precedence)} · CPC title

• F16B9/02

  Detachable connections {(F16B9/05 – F16B9/09 take precedence)} · CPC title

• B29C65/5014

  being fibre-reinforced (B29C65/5028 takes precedence) · CPC title

• B29C65/561

  using screw-threads being integral at least to one of the parts to be joined · CPC title

• B29L2031/737

  Articles provided with holes, e.g. grids, sieves (nets B29L2028/00) · CPC title