FOAM STIFFENED HOLLOW COMPOSITE STRINGER

• US 20090127393A1
• Filed: 11/08/2007
• Published: 05/21/2009
• Est. Priority Date: 11/08/2007
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Rotter, Daniel M., McCarville, Douglas A., Guzman, Juan C., VanWest, Barry P.
• Granted Patent: US 7,879,276 B2
• Time in Patent Office: Days
• US Class Current: 244/133
• CPC Class Codes: B29C 44/583 for making articles with cavities
• CPC Class Codes: B29C 70/086 and with one or more layers of pure plastics material, e.g. foam layers applying a non-preformed coating, e.g. a gel-coat, B29C37/0025; with foam blocks B29C70/86
• CPC Class Codes: B29C 70/865 completely encapsulated
• CPC Class Codes: B29D 99/0003 Producing profiled members, e.g. beams
• CPC Class Codes: B29K 2715/003 Cellular or porous
• CPC Class Codes: B64C 1/064 Stringers; Longerons
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y10T 428/24744 Longitudinal or transverse tubular cavity or cell

Abstract

A method and apparatus for a composite stringer. A method is used for manufacturing a hollow composite stringer. Foam is formed with a mandrel installed into the foam. A composite material and the foam is laid up onto a tool in a form of a stringer. The composite material and the foam in the form of the stringer is cured to form a cured stringer. The mandrel from the foam is removed to form the hollow composite stringer.

Claims

1. A method for manufacturing a hollow composite stringer, the method comprising:

forming foam with a mandrel installed into the foam;

laying up a composite material and the foam onto a tool in a form of a stringer;

curing the composite material and the foam in the form of the stringer to form a cured stringer;

removing the mandrel from the foam to form the hollow composite stringer.

2. The method of claim 1, wherein the laying up step comprises:

laying up the composite material onto an inside mold line;

placing the foam onto the composite material.

3. The method of claim 2, wherein the laying up step further comprises:

placing a skin ply over the foam and the composite material.

4. The method of claim 1, wherein the laying up step comprises:

placing the foam onto a skin ply; and

placing the composite material over the foam.

5. The method of claim 4, wherein the laying up step is performed using an outside mold line.

6. The method of claim 1, wherein the hollow composite stringer has a shape selected from one of a trapezoid shape and a hat shape.

7. The method of claim 1, wherein the hollow composite stringer is located in an aircraft.

8. A method for manufacturing a hollow composite part, the method comprising:

forming a composite part with a first channel extending from a first end to a second end of the composite part;

forming a foam core within the first channel;

creating a set of channels within the foam core to form the hollow composite part.

9. The method of claim 8, wherein the step of forming the composite part with the first channel extending from the first end to the second end of the composite part and the step of forming the foam core within the first channel comprises:

laying up a composite material and the foam core onto a tool in a form of the composite part; and

curing the composite material and the foam core in the form of the composite part.

10. The method of claim 8, wherein the foam core has a set of mandrels in the set of channels and wherein the creating step comprises:

removing the set of mandrels to form the set of channels.

11. The method of claim 8, wherein the creating step comprises:

removing a portion of the foam core to form the set of channels.

12. The method of claim 9, wherein the laying up step comprises:

laying up the composite material onto an inside mold line;

placing the foam core onto the composite material.

13. The method of claim 9, wherein the laying up step comprises:

placing the foam core onto a skin ply; and

placing the composite material over the foam core.

14. The method of claim 8, wherein the composite part is a composite stringer

15. The method of claim 14, wherein the composite stringer has a shape selected from one of a trapezoid shape and a hat shape.

16. The method of claim 8, wherein the composite part is a stringer.

17. An apparatus comprising:

a composite part having a first channel; and

foam located in the first channel, wherein the foam has a set of channels.

18. The apparatus of claim 17 further comprising:

a set of removable mandrels located in the set of channels in the foam.

19. The apparatus of claim 17, wherein the composite part is a composite stringer.

20. The apparatus of claim 19 further comprising:

an aircraft, wherein the composite stringer is located in the aircraft.