Method of manufacturing duct stringer

Patent metadata

Field	Value
Publication number	US-11141934-B2
Application number	US-201916454394-A
Country	US
Kind code	B2
Filing date	Jun 27, 2019
Priority date	Jun 29, 2018
Publication date	Oct 12, 2021
Grant date	Oct 12, 2021

Abstract

A duct stringer is disclosed including a structural member with a hat-shaped cross-section. The structural member has a crown, a pair of webs and a pair of feet. A channel member with a U-shaped cross-section has a base and a pair of flanges. The flanges of the channel member are co-cured to opposed inner faces of the webs of the structural member. The structural member and the channel member together provide a duct with a closed cross-section which is adapted to transport fluid, for instance in an aircraft wing to provide a vent function in an aircraft fuel system.

First claim

The invention claimed is:

1. A method of manufacturing a duct stringer, the method comprising:
a. providing a structural member with a hat-shaped cross-section, the structural member comprising a crown, a pair of webs and a pair of feet;
b. providing a channel member with a U-shaped cross-section, the channel member comprising a base and a pair of flanges; and
c. adhering the flanges of the channel member to opposed inner faces of the webs of the structural member so that the structural member and the channel member together provide a duct with a closed cross-section which is adapted to transport fluid.

2. A method according to claim 1 , wherein the step of adhering the flanges comprises inserting the channel member carried by a mandrel between the opposed inner faces of the webs of the structural member, and then expanding the mandrel so that the mandrel presses the flanges of the channel member against the opposed inner faces of the webs of the structural member.

3. A method according to claim 2 , wherein the mandrel comprises: a support core having a waisted cross-sectional shape with a pair of concave sides, and a bladder surrounding the core;
wherein a vacuum is applied so that the bladder is sucked by the vacuum into the concave sides of the support core, and the vacuum continues to be applied as the mandrel is inserted between the opposed inner faces of the webs; and
wherein after insertion, the mandrel is expanded by releasing the vacuum or applying a positive pressure so that the bladder is pushed away from the concave sides of the support core.

4. A method according to claim 3 , wherein the application of the vacuum causes the support core to contract.

5. A method according to claim 4 wherein the support core is made of a compressible or resilient material.

6. A method according to claim 3 , wherein the bladder is made of an elastomeric material.

7. A method according to claim 3 , wherein the channel member is formed over the mandrel in a flange forming stage, and the vacuum is applied before the flange forming stage and continues to be applied during the flange forming stage.

8. A method according to claim 1 , wherein the flanges of the channel member are adhered to the opposed inner faces of the webs of the structural member by a co-bonded, co-cured or secondary-bonded joint.

9. A method according to claim 1 , wherein the flanges of the channel member are adhered to the opposed inner faces of the webs of the structural member by co-curing them to form co-cured joints.

10. A method according to claim 1 , wherein the channel member and the structural member are assembled as dry-fibre preforms and then co-infused with a matrix material.

11. A method according to claim 1 , wherein the flanges of the channel member are adhered to the opposed inner faces of the webs of the structural member by a co-infusion process in which the channel member and the structural member are assembled as dry-fibre preforms and then co-infused with a matrix material.

12. A method according to claim 1 , wherein the base and flanges of the channel member are made of a composite material.

13. A method of manufacturing a structure, the method comprising: manufacturing a duct stringer by the method of claim 1 ; and adhering the duct stringer assembly to a skin.

14. A method according to claim 13 , wherein the feet of the structural member are adhered to the skin.

15. A method according to claim 13 , wherein the duct stringer assembly is adhered to the skin by a co-bonded, co-cured or secondary-bonded joint.

16. A method according to claim 13 , wherein the skin is an aircraft wing skin.

Assignees

• Airbus Operations Ltd

Inventors

• Douglas Paul
• Bryant Anthony
• Peachey Daniel

Classifications

• B29D99/0003

  Producing profiled members, e.g. beams · CPC title

• B29C70/02 Primary

  comprising combinations of reinforcements, {e.g. non-specified reinforcements, fibrous reinforcing inserts} and fillers, {e.g. particulate fillers}, incorporated in matrix material, forming one or more layers and with or without non-reinforced or non-filled layers {(combinations of fibrous reinforcement only B29C70/04; combinations of fillers only B29C70/58; combinations with non reinforcing inserts, e.g. foam blocks, B29C70/68)} · CPC title

• B29C70/549

  Details of caul plates, e.g. materials or shape · CPC title

• B64C3/182 Primary

  Stringers, longerons · CPC title

• B29C33/50

  elastic {or flexible (for isostatic pressing B29C43/3642)} · CPC title