Joint member for a composite wing structure

• US 10,513,325 B2
• Filed: 02/03/2017
• Issued: 12/24/2019
• Est. Priority Date: 02/08/2016
• Status: Active Grant

• Current Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Original Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Inventors: Kooiman, James E., Decker, George R., Hogue, Charles D.
• Primary Examiner(s): Bonzell, Philip J
• Assistant Examiner(s): Abell, Tye William
• Application Number:
  US15/424,338
• Publication Number:
  US 20170225770A1
• Time in Patent Office: 1,054 Days
• CPC Class Codes: B29C 70/302 Details of the edges of fibre composites, e.g. edge finishing or means to avoid delamination
• CPC Class Codes: B29C 70/545 Perforating, cutting or machining during or after moulding
• CPC Class Codes: B29D 99/0014 provided with ridges or ribs, e.g. joined ribs
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage
• CPC Class Codes: B64C 3/18 Spars; Ribs; Stringers
• CPC Class Codes: B64C 3/187 Ribs
• CPC Class Codes: B64C 3/26 Construction, shape, or attachment of separate skins, e.g. panels
• CPC Class Codes: B64F 5/10 Manufacturing or assembling aircraft, e.g. jigs therefor
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

In one aspect, there is a joint member for a composite having a laminate layer including a support member having a first side and a second side; a first flange extending laterally from the first side and having an attachment surface for attachment to a structure; and a second flange extending laterally from the second side and having an attachment surface configured for attachment to the laminate layer. The joint member is configured to provide a load path from the first flange to the second flange. In an embodiment, a joint system for a composite system includes a joint member attached to a first skin and a second skin. In still another embodiment, a joint system for a rib assembly includes a joint member attached to a rib web and rib post.

Claims

1. A joint system for a composite skin assembly, comprising:

a composite skin comprising a first skin, a second skin, and a honeycomb core, disposed between the first skin and second skin, the honeycomb core and the second skin extend in a spanwise direction on the first skin, the honeycomb core having an edge disposed on the first skin, the second skin haying an edge disposed on the honeycomb core; and

a joint member comprising;

a support member having a first side and a second side;

a first flange extending laterally from the first side and having an attachment surface configured for attachment to the first skin; and

a second flange extending laterally from the second side and having an attachment surface configured for attachment to the second skin;

wherein the attachment surface of the first flange is coupled to the first skin and the attachment surface of the second flange is coupled to the second skin;

wherein the joint member secures the second skin to the first skin.

2. The joint system of claim 1, wherein the joint member is “

Z”

shape.

4. The joint system of claim 1, wherein the joint member comprises at least one of a composite material and a metallic material.

5. The joint system of claim 1, wherein the honeycomb core comprises a plurality of honeycomb panels.

6. The joint system of claim 1, wherein the attachment surface of the first flange and the first skin are attached together with at least one of an adhesive material and a fastener.

7. The joint system of claim 1, wherein the attachment surface of the second flange and the second skin are attached together with at least one of an adhesive material and a fastener.

10. The joint system of claim 1, wherein the top surface of the first skin is substantially parallel to the top surface of the second skin.

11. The joint system of claim 1, wherein the edges of the honeycomb core and the second skin are about 90 degrees relative to the top surface of the first skin.

12. The joint system of claim 11, wherein the edges of the honeycomb core and the second skin are aligned.

3. The joint system of 1, wherein the joint member is comprised of a material that is a fluid barrier.

8. The joint system of clam 1, wherein the joint member provides a load path from the first skin to the second skin.

9. The joint system of clam 1, wherein the first skin having a periphery defined by an aft edge, a forward edge, and outboard ends, the second skin having a perimeter within the periphery of the first skin.

13. A method of making a composite skin assembly, comprising:

providing a composite skin having a first skin, a second skin, and a honeycomb core disposed between the first skin and second skin, the first skin having a periphery defined by the aft edges, forward edges, and outboard ends, the second skin and the honeycomb core having a perimeter within the periphery of the first skin;

positioning a plurality of joint members having a “

Z”

configuration at the forward and aft edges of the second skin, each joint member comprising a support member having a first side and a second side, a first flange extending laterally from the first side and having an attachment surface configured for attachment to the first skin, and a second flange extending laterally from the second side and having an attachment surface configured for attachment to the second skin; and

securing the attachment surfaces of first flange of the joint members to the first skin and the attachment surfaces of the second flange of the joint members to the second skin to form a composite skin assembly.

14. The method of claim 13, further comprising:

trimming the composite skin to include a plurality of openings having a perimeter;

positioning a plurality of joint members having a “

Z”

configuration at the perimeter of the openings; and

securing the joint members to the first skin and the second skin.

15. The method of claim 13, wherein the top surface of the first skin is substantially parallel to the top surface of the second skin.