Aircraft wing composite ribs having electrical grounding paths

Patent metadata

Field	Value
Publication number	US-11038334-B2
Application number	US-201916247201-A
Country	US
Kind code	B2
Filing date	Jan 14, 2019
Priority date	Jan 14, 2019
Publication date	Jun 15, 2021
Grant date	Jun 15, 2021

Abstract

Aircraft wing composite ribs having electrical grounding paths are described. An example composite rib includes a carbon fiber reinforced plastic (CFRP) panel, a metallic rib post, a metallic fitting, and a metallic grounding member. The metallic rib post is coupled to the CFRP panel and configured to be coupled to a spar of an aircraft wing, the spar being coupled to a current return network (CRN) cable. The metallic fitting is coupled to the CFRP panel and configured to be coupled to a skin panel of the aircraft wing. The metallic grounding member is positioned between the CFRP panel and the metallic fitting. The metallic grounding member provides an electrical grounding path extending from the metallic fitting to the metallic rib post.

First claim

What is claimed is:

1. A composite rib, comprising:
a carbon fiber reinforced plastic (CFRP) panel;
a metallic rib post coupled to the CFRP panel and configured to be coupled to a spar of an aircraft wing, the spar coupled to a current return network (CRN) cable;
a metallic fitting coupled to the CFRP panel and configured to be coupled to a skin panel of the aircraft wing; and
a metallic grounding member positioned between the CFRP panel and the metallic fitting, the metallic grounding member providing an electrical grounding path extending from the metallic fitting to the metallic rib post.

2. The composite rib of claim 1 , wherein the electrical grounding path is configured to carry lightning current from the metallic fitting to the metallic rib post, the lightning current to be received at the metallic fitting from the skin panel, to pass through the electrical grounding path, and to pass from the metallic rib post through the spar to the CRN cable.

3. The composite rib of claim 1 , wherein the electrical grounding path is configured to carry electrostatic charge from the metallic fitting to the metallic rib post, the electrostatic charge to be received at the metallic fitting from the skin panel, to pass through the electrical grounding path, and to pass from the metallic rib post through the spar to the CRN cable.

4. The composite rib of claim 1 , wherein the metallic grounding member is a non-structural member.

5. The composite rib of claim 1 , wherein the metallic fitting is a first metallic fitting, the skin panel is an upper skin panel, and the electrical grounding path is a first electrical grounding path, wherein the composite rib further comprises a second metallic fitting coupled to the CFRP panel and configured to be coupled to a lower skin panel of the aircraft wing, and wherein the metallic grounding member is further positioned between the CFRP panel and the second metallic fitting, the metallic grounding member providing a second electrical grounding path extending from the second metallic fitting to the metallic rib post.

6. The composite rib of claim 5 , wherein the metallic grounding member is a metallic grounding plate.

7. The composite rib of claim 6 , wherein the metallic grounding plate includes a border and an opening surrounded by the border, the opening being located between the first and second metallic fittings, the first and second metallic fittings contacting the border, the border connecting the first and second electrical grounding paths.

8. The composite rib of claim 6 , wherein the metallic grounding plate includes a first surface and a second surface located opposite the first surface, the first surface contacting the CFRP panel, the second surface contacting the first and second metallic fittings.

9. The composite rib of claim 6 , further comprising a hat stiffener coupled to the CFRP panel.

10. The composite rib of claim 6 , wherein the first metallic fitting is a first upper metallic fitting and the second metallic fitting is a first lower metallic fitting, the composite rib further comprising:
a second upper metallic fitting coupled to the CFRP panel and configured to be coupled to the upper skin panel, the second upper metallic fitting being spaced apart from the first upper metallic fitting;
a second lower metallic fitting coupled to the CFRP panel and configured to be coupled to the lower skin panel, the second lower metallic fitting being spaced apart from the first lower metallic fitting;
a first shear tie coupled to the metallic grounding plate at a location between the first and second upper metallic fittings; and
a second shear tie coupled to the metallic grounding plate at a location between the first and second lower metallic fittings.

11. The composite rib of claim 9 , wherein the CFRP panel includes a first surface and a second surface located opposite the first surface, the hat stiffener contacting the first surface of the CFRP panel, the metallic grounding plate contacting the second surface of the CFRP panel.

12. The composite rib of claim 11 , wherein the hat stiffener is bonded to the first surface of the CFRP panel, and the metallic grounding plate is bonded to the second surface of the CFRP panel.

13. The composite rib of claim 11 , wherein the CFRP panel further includes a central segment defining a plane, a first flange extending away from the central segment at a first angle relative to the plane, and a second flange extending away from the central segment at a second angle relative to the plane, and wherein the hat stiffener is located between the first flange and the second flange.

14. The composite rib of claim 11 , further comprising:
a first fastener extending through the first metallic fitting, the metallic grounding plate, the CFRP panel, and the hat stiffener; and
a second fastener extending through the second metallic fitting, the metallic grounding plate, the CFRP panel, and the hat stiffener.

15. A method for assembling a composite rib, the method comprising:
coupling a metallic grounding member to a carbon fiber reinforced plastic (CFRP) panel;
coupling a metallic rib post to the CFRP panel, the metallic rib post configured to be coupled to a spar of an aircraft wing, the spar coupled to a current return network (CRN) cable; and
coupling a metallic fitting to the CFRP panel, the metallic fitting configured to be coupled to a skin panel of the aircraft wing;
wherein the metallic grounding member is positioned between the CFRP panel and the metallic fitting, the metallic grounding member providing an electrical grounding path extending from the metallic fitting to the metallic rib post.

16. The method of claim 15 , wherein the metallic fitting is a first metallic fitting, the skin panel is an upper skin panel, and the electrical grounding path is a first electrical grounding path, wherein the method further comprises coupling a second metallic fitting to the CFRP panel, the second metallic fitting configured to be coupled to a lower skin panel of the aircraft wing, and wherein the metallic grounding member is further positioned between the CFRP panel and the second metallic fitting, the metallic grounding member providing a second electrical grounding path extending from the second metallic fitting to the metallic rib post.

17. The method of claim 16 , wherein the metallic grounding member is a metallic grounding plate.

18. The method of claim 17 , wherein the metallic grounding plate includes a border and an opening surrounded by the border, the opening being located between the first and second metallic fittings, the first and second metallic fittings contacting the border, the border connecting the first and second electrical grounding paths.

19. The method of claim 17 , further comprising coupling a hat stiffener to the CFRP panel.

20. The method of claim 19 , wherein the CFRP panel includes a first surface and a second surface located opposite the first surface, the hat stiffener contacting the first surface of the CFRP panel, the metallic grounding plate contacting the second surface of the CFRP panel.

21. The method of claim 20 , wherein the coupling the hat stiffener to the CFRP panel includes bonding the hat stiffener to the first surface of the CFRP panel, and wherein the coupling the metallic grounding plate to the CFRP panel includes bonding the metallic grounding plate to the second surface of the CFRP panel.

22. The method of claim 20 , wherein the coupling the first metallic fitting to

Assignees

• Boeing Co

Inventors

• Walker Steven Paul

Classifications

• B64C2001/0072

  from composite materials · CPC title

• B64D45/02

  Lightning protectors; Static dischargers · CPC title

• B64C3/187 Primary

  Ribs · CPC title

• B64C3/26

  Construction, shape, or attachment of separate skins, e.g. panels · CPC title

• H02G13/80 Primary

  Discharge by conduction or dissipation, e.g. rods, arresters, spark gaps · CPC title