Connector to connect a center wing box to a bulkhead of an aircraft

Patent metadata

Field	Value
Publication number	US-11999464-B2
Application number	US-202217577863-A
Country	US
Kind code	B2
Filing date	Jan 18, 2022
Priority date	Jan 27, 2021
Publication date	Jun 4, 2024
Grant date	Jun 4, 2024

Abstract

A connector to connect a center wing box to a bulkhead of an aircraft. The connector includes a panel with a first edge positioned at the center wing box, an opposing second edge positioned at the bulkhead, and a central section. A first flexible seal extends across the panel and provides for relative movement between the first edge and the central section. A second flexible seal extends across the panel and provides for relative movement between the second edge and the central section.

First claim

What is claimed is:

1. A connector to connect a center wing box to a bulkhead of an aircraft, the connector comprising:
a panel comprising a first edge positioned at the center wing box, an opposing second edge positioned at the bulkhead, and a central section;
a first flexible seal that extends across the panel and that provides for relative movement between the first edge and the central section;
a second flexible seal that extends across the panel and that provides for relative movement between the second edge and the central section;
a first support mounted to the center wing box to support a first section of the panel;
a second support mounted to the bulkhead to support a second section of the panel; and
wherein the panel is positioned at a downward sloping angle between the first edge and the second edge with the first flexible seal positioned vertically above the second flexible seal.

2. The connector of claim 1 , wherein the first flexible seal is spaced apart on the panel from the second flexible seal.

3. The connector of claim 1 , wherein each of the first flexible seal and the second flexible seal are constructed from a flexible membrane material.

4. The connector of claim 1 , wherein the panel comprises:
a first flange that comprises the first edge and an opposing inner edge with the inner edge connected to the first flexible seal;
a second flange that comprises the second edge and an opposing inner edge with the inner edge connected to the second flexible seal; and
the central section connected to inner edges of each of the first flexible seal and the second flexible seal.

5. The connector of claim 1 , further comprising:
the first support comprising a plurality of first stiffener arms attached to the center wing box and the central section, the first stiffener arms configured to prevent interference with the first flexible seal; and
the second support comprising a plurality of second stiffener arms attached to the bulkhead and the central section, the second stiffener arms configured to prevent interference with the second flexible seal.

6. The connector of claim 5 , wherein the first and second stiffener arms are aligned in pairs along a length of the panel with the first and second stiffener arms of each of the pairs positioned in an overlapping configuration on opposing sides of the panel.

7. The connector of claim 5 , further comprising lug and clevis joints with pins that pivotally connect the first stiffener arms to the center wing box and that pivotally connect the second stiffener arms to the bulkhead.

8. The connector of claim 7 , wherein the lug and clevis joints provide for movement of the first stiffener arms relative to the center wing box and the second stiffener arms relative to the bulkhead.

9. The connector of claim 1 , further comprising closeout panels positioned on lateral sides of the panel and against the fuselage, the closeout panels comprising pressure panels to structurally connect the panel to the fuselage.

10. A connector to connect a center wing box to a bulkhead of an aircraft, the connector comprising:
a panel sized to extend across a gap formed between the center wing box and the bulkhead, the panel comprising:
a central section sized to extend across the gap, the central section comprising a first edge and an opposing second edge;
a first flange pivotally connected to the first edge at a first flexible seal, the first flange configured to be connected to the center wing box;
a second flange pivotally connected to the second edge at a second flexible seal, the second flange configured to be connected to the bulkhead;

a first support mounted to the center wing box and to a first side of the central section; and
a second support mounted to the bulkhead and to a second side of the central section.

11. The connector of claim 10 , wherein each of the first flexible seal and the second flexible seal extend across an entire width of the panel.

12. The connector of claim 11 , wherein the first support comprises a plurality of stiffener arms spaced apart across the width of the panel, each of the stiffener arms comprising a first end configured to be connected to the center wing box and an opposing second end positioned at and connected to the central section.

13. The connector of claim 10 , wherein the first support is configured to prevent interference with the first flexible seal and the second support is configured to prevent interference with the second flexible seal.

14. The connector of claim 10 , wherein each of the first flexible seal and the second flexible seal are straight and are aligned parallel.

15. A method of connecting a center wing box to a bulkhead of an aircraft, the method comprising:
attaching a first flange of a panel to the center wing box;
attaching a second flange of the panel to the bulkhead;
positioning a central section of the panel along a gap formed between the center wing box and the bulkhead;
aligning a first flexible seal that connects the first flange to the central section along the center wing box;
aligning a second flexible seal that connects the second flange to the central section along the bulkhead;
attaching a plurality of first stiffener arms across a width of the panel with each of the first stiffener arms mounted to the center wing box and the central section; and
attaching a plurality of second stiffener arms across the width of the panel with each of the second stiffener arms mounted to the bulkhead and the central section.

16. The method of claim 15 , further comprising aligning the central section at a downward angle with the first flange positioned vertically above second flange.

17. The method of claim 15 , further comprising attaching the first stiffener arms to a first side of the panel and the second stiffener arms to an opposing second side of the panel.

18. The method of claim 15 , wherein attaching the second flange of the panel to the bulkhead comprises attaching the second flange to an upper chord of the bulkhead.

19. The method of claim 15 , further comprising attaching the first flange to an upper panel of the center wing box.

20. The connector of claim 10 , wherein the central section of the panel is positioned at a downward sloping angle with the first flange being vertically higher than the second flange.

Assignees

• Boeing Co

Inventors

• Young Jenny
• Cox Daniel
• Ingham Steven David
• Johnson Kyle Alexander
• Mclaughlin Mark Ronald
• Lai Paul Hungwai

Classifications

• B64C1/069

  Joining arrangements therefor · CPC title

• B64C1/26 Primary

  Attaching the wing or tail units or stabilising surfaces · CPC title

• B64C1/10

  Bulkheads · CPC title