Composite rib assembly

• US 10,513,324 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: Carlson, David G., McCullough, John R., Oldroyd, Paul K., May, Carl A., Kooiman, James E.
• Primary Examiner(s): Bonzell, Philip J
• Assistant Examiner(s): Abell, Tye William
• Application Number:
  US15/424,095
• Publication Number:
  US 20170225766A1
• 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 rib assembly for an aircraft wing including a rib web having a top and a bottom, the rib web includes a first laminate, a second laminate, and a honeycomb panel having an array of large cells disposed between the first laminate and the second laminate, each cell having a width of at least 1 cm; and a plurality of skin flanges for fixedly attaching the rib web to a skin of the wing, each skin flange has a base member having a first portion and a second portion and a vertical member extending from the base member. The plurality of skin flanges can be attached to the top and the bottom of the rib web such that the second portion of the base member and the vertical member are attached to the rib web.

Claims

1. A rib assembly for an aircraft wing comprising:

a rib web having a top, a bottom, a forward edge, and an aft edge;

the rib web comprised of a first laminate, a second laminate, and a honeycomb panel having an array of large cells disposed between the first laminate and the second laminate, each cell having a width of at least 1 cm;

a plurality of skin flanges for fixedly attaching the top and bottom of the rib web to a skin of the wing, each skin flange has a base member having a first portion and a second portion and a vertical member extending from the base member;

a first “

Z”

shaped joint member disposed on the forward edge of the rib web for fixedly attaching the forward edge of the rib web to a forward rib post; and

a second “

Z”

shaped joint member disposed on the aft edge of the rib web for fixedly attaching the aft edge of the rib web to an aft rib post;

wherein the first and second “

Z”

shaped joint member each comprise;

a first flange extending laterally from a first side of the joint member and having an attachment surface that overlaps and is secured to a rib post; and

a second flange extending laterally from a second side of the joint member and having an attachment surface that overlaps and is secured to the second laminate;

wherein the plurality of skin flanges is attached to the top and the bottom of the rib web such that the vertical members are attached to the rib web;

wherein each of the first joint member and the second joint member provide a load path from the second laminate to the respective rib post;

wherein each of the skin flanges further comprises a rounded portion with an opening in the vertical member, the opening corresponds with an aperture in the rib web configured to receive a fuel line, and the rib web and the opening in each of the plurality of skin flanges provides a width sufficient to prevent kinks in the fuel line.

2. The rib assembly according to claim 1, wherein each of the skin flanges is constructed from a composite material.

3. The rib assembly according to claim 1, wherein the width of the first portion in the base member is larger than the width of the second portion of the base member.

4. The rib assembly according to claim 1, wherein the second portion of the base member and the vertical member are attached to the rib web with an adhesive.

5. The rib assembly according to claim 1, wherein the second portion of the base member and the vertical member are structurally bonded to the rib web.

6. The rib assembly according to claim 1, wherein the second portion of the base member and the vertical member are structurally bonded to the rib web with a fastener.

7. The rib assembly according to claim 1, wherein the rib web has a substantially smooth surface.

8. The rib assembly according to claim 1, wherein the “

Z”

shaped joint member is a composite material.

9. The rib assembly according to claim 1, wherein each of the first laminate and the second laminate are a pre-cured laminate.

10. The rib assembly according to claim 9, wherein each of the first laminate and the second laminate are comprised of a total number of plies from 4 plies to 12 plies.

11. The rib assembly according to claim 1, wherein the rib web further comprises at least two apertures.

12. The rib assembly according to claim 11, wherein the at least two apertures are configured to each receive a fuel line.