Systems and methods for assembling stiffened composite structures

• US 9,199,417 B1
• Filed: 01/02/2013
• Issued: 12/01/2015
• Est. Priority Date: 01/02/2013
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Rotter, Daniel M., Noel, Jennifer Sue, Robins, Brian G., Madden, Kimberlee, Macias, Henry, Coxon, Brad A., Kirchmeier, Stephen K., Anderson, Joseph D., Willden, Kurtis S.
• Primary Examiner(s): Musser, Barbara J
• Application Number:
  US13/732,961
• Time in Patent Office: 1,063 Days
• Field of Search: None
• US Class Current: 1/1
• CPC Class Codes: B29C 70/32 on a rotating mould, former or core
• CPC Class Codes: B29D 99/0014 provided with ridges or ribs, e.g. joined ribs

Abstract

Methods of assembling a stiffened composite structure include loading, with a stiffener loading tool, a respective stiffener from a supply of stiffeners onto an inner mold line layup mandrel; repeating the loading to load a plurality of stiffeners onto the inner mold line layup mandrel; and following the repeating, affixing a respective skin segment from a supply of skin segments to the plurality of stiffeners loaded on the inner mold line layup mandrel to form at least a portion of the stiffened composite structure. Systems for assembling stiffened composite structures include a supply of stiffeners; an inner mold line layup mandrel; and a stiffener loading tool configured to load the respective stiffener onto the inner mold line layup mandrel.

Claims

1. A method of assembling a stiffened composite structure, comprising:

providing a supply of stiffeners;

providing a supply of skin segments;

loading, with a stiffener loading tool, a respective stiffener from the supply of stiffeners onto an inner mold line layup mandrel, wherein the loading includes;

positioning the stiffener loading tool vertically underneath the inner mold line layup mandrel; and

raising the respective stiffener with the stiffener loading tool until the respective stiffener operatively engages the inner mold line layup mandrel;

repeating the loading to load a plurality of stiffeners onto the inner mold line layup mandrel; and

following the repeating the loading, affixing a respective skin segment from the supply of skin segments to the plurality of stiffeners loaded on the inner mold line layup mandrel to form at least a portion of the stiffened composite structure.

2. The method of claim 1, further comprising:

prior to the repeating, rotating the inner mold line layup mandrel to position the inner mold line layup mandrel for subsequent loading of a respective stiffener.

3. The method of claim 1,

wherein the inner mold line layup mandrel includes a plurality of spaced-apart stiffener forms, each stiffener form having an outer surface that corresponds to one side of a respective stiffener;

and

wherein the loading includes loading the respective stiffener onto a respective stiffener form.

4. The method of claim 1, wherein the loading includes:

operatively aligning the stiffener loading tool with the inner mold line layup mandrel, wherein the operatively aligning includes engaging an alignment pin with an alignment bore.

5. The method of claim 1, further comprising:

following the affixing, repeating the repeating the loading and repeating the affixing to form at least a portion of the stiffened composite structure; and

following the repeating the repeating the loading and repeating the affixing, assembling a plurality of formed portions of the stiffened composite structure to form the stiffened composite structure.

6. The method of claim 1, wherein the stiffened composite structure includes one of a barrel section of an aircraft fuselage, an aircraft fuselage, a wing section of an aircraft, a wing of an aircraft, a stabilizer section of an aircraft, a stabilizer of an aircraft, a structural section of an aircraft, and an aircraft.

7. The method of claim 1, wherein the stiffeners and the skin segments are constructed of fiber reinforced composite material.

8. A method of assembling a barrel section of an aircraft fuselage, comprising:

providing a supply of stiffeners constructed of pre-preg fiber reinforced composite material;

providing a supply of skin segments constructed of pre-preg fiber reinforced composite material;

applying an adhesive to one side of a respective stiffener from the supply of stiffeners;

transporting, with a stiffener transporting tool, the respective stiffener;

following the transporting, coupling the stiffener transporting tool to an upper side of a stiffener loading tool;

following the coupling;

positioning the stiffener loading tool vertically underneath an inner mold line layup mandrel; and

following the positioning, raising the stiffener loading tool and the respective stiffener with the stiffener loading tool until the one side of the respective stiffener and the adhesive operatively engage the inner mold line layup mandrel;

following the positioning, decoupling the stiffener transporting tool from the stiffener loading tool;

following the decoupling, vacuum compacting, with the stiffener transporting tool, the respective stiffener on the inner mold line layup mandrel;

following the decoupling, rotating the inner mold line layup mandrel to position the inner mold line layup mandrel for subsequent loading of a respective stiffener;

repeating the transporting, the positioning, the raising, the decoupling, the vacuum compacting, and the rotating to load and compact a plurality of stiffeners onto the inner mold line layup mandrel; and

following the repeating, affixing a respective skin segment from the supply of skin segments to the plurality of stiffeners loaded on the inner mold line layup mandrel to form at least a portion of the barrel section.

9. A method of assembling a stiffened composite structure, comprising:

providing a supply of stiffeners;

providing a supply of skin segments;

transporting, with a stiffener transporting tool, a respective stiffener from the supply of stiffeners;

following the transporting, coupling the stiffener transporting tool to a stiffener loading tool;

loading, with the stiffener transporting tool and the stiffener loading tool, the respective stiffener from the supply of stiffeners onto an inner mold line layup mandrel;

repeating the transporting, the coupling, and the loading to load a plurality of stiffeners onto the inner mold line layup mandrel; and

following the repeating the transporting, the coupling, and the loading, affixing a respective skin segment from the supply of skin segments to the plurality of stiffeners loaded on the inner mold line layup mandrel to form at least a portion of the stiffened composite structure.

10. The method of claim 9, wherein the transporting includes suctioning the respective stiffener to the stiffener transporting tool.

11. The method of claim 9,

wherein the coupling includes coupling the stiffener transporting tool to an upper side of the stiffener loading tool;

and

wherein the loading includes;

positioning the stiffener loading tool vertically underneath the inner mold line layup mandrel; and

raising the stiffener loading tool and the respective stiffener with the stiffener loading tool until the respective stiffener operatively engages the inner mold line layup mandrel.

12. The method of claim 9,

wherein the transporting includes transporting the respective stiffener with a respective stiffener transporting tool from a plurality of stiffener transporting tools;

and

wherein the coupling includes coupling the respective stiffener transporting tool to a respective stiffener loading tool from a plurality of stiffener loading tools, resulting in more than one combination of a respective stiffener transporting tool and a respective stiffener loading tool being ready for loading a respective stiffener onto the inner mold line layup mandrel.

13. The method of claim 9, further comprising:

following the loading, vacuum compacting, with the stiffener transporting tool, the respective stiffener on the inner mold line layup mandrel;

wherein the repeating includes repeating the vacuum compacting to compact the plurality of stiffeners onto the inner mold line layup mandrel.

14. The method of claim 13, further comprising:

following the loading and prior to the vacuum compacting, decoupling the stiffener transporting tool from the stiffener loading tool.

15. The method of claim 9, further comprising:

prior to the loading, applying an adhesive to one side of the respective stiffener, optionally wherein the adhesive includes one or more adhesive strips;

wherein the loading includes adhering the respective stiffener to the inner mold line layup mandrel with the adhesive.

16. The method of claim 9, wherein the loading includes:

positioning the stiffener loading tool vertically underneath the inner mold line layup mandrel; and

raising the respective stiffener with the stiffener loading tool until the respective stiffener operatively engages the inner mold line layup mandrel.

17. The method of claim 9, further comprising:

prior to the repeating, rotating the inner mold line layup mandrel to position the inner mold line layup mandrel for subsequent loading of a respective stiffener.

18. The method of claim 9,

wherein the inner mold line layup mandrel includes a plurality of spaced-apart stiffener forms, each stiffener form having an outer surface that corresponds to one side of a respective stiffener;

and

wherein the loading includes loading the respective stiffener onto a respective stiffener form.

19. The method of claim 9, wherein the providing the supply of stiffeners includes forming the stiffeners, including:

providing a supply of composite stiffener plies;

forming a respective stiffener from a respective subset of composite stiffener plies from the supply of composite stiffener plies; and

repeating the forming a respective stiffener to form multiple stiffeners.

20. The method of claim 19, wherein the forming the stiffeners is performed simultaneously with the loading and the affixing to have multiple stiffeners ready for loading onto the inner mold line layup mandrel.

21. The method of claim 9, wherein the providing the supply of skin segments includes forming the skin segments, including:

providing a supply of composite skin plies; and

forming a respective skin segment from a respective subset of composite skin plies from the supply of composite skin plies; and

repeating the forming a respective skin segment to create the supply of skin segments.

22. The method of claim 21, wherein the forming the skin segments is performed simultaneously with the loading and the affixing to have multiple skin segments ready for loading onto the inner mold line layup mandrel.

23. The method of claim 9, further comprising:

following the affixing, repeating the repeating the loading and repeating the affixing to form at least a portion of the stiffened composite structure; and

following the repeating the repeating the loading and repeating the affixing, assembling a plurality of formed portions of the stiffened composite structure to form the stiffened composite structure.

24. The method of claim 9, wherein the stiffened composite structure includes one of a barrel section of an aircraft fuselage, an aircraft fuselage, a wing section of an aircraft, a wing of an aircraft, a stabilizer section of an aircraft, a stabilizer of an aircraft, a structural section of an aircraft, and an aircraft.

25. The method of claim 9, wherein the stiffeners and the skin segments are constructed of fiber reinforced composite material.

26. A system for assembling stiffened composite structures, comprising:

a supply of stiffeners;

a supply of skin segments;

an inner mold line layup mandrel;

a stiffener transporting tool configured to transport a respective stiffener from the supply of stiffeners, wherein the stiffener transporting tool includes a compaction structure that is configured to vacuum compact the respective stiffener on the inner mold line layup mandrel;

a stiffener loading tool configured to operatively receive the stiffener transporting tool with the respective stiffener and with the stiffener transporting tool to operatively load the respective stiffener onto the inner mold line layup mandrel; and

a skin segment loading tool configured to load a respective skin segment from the supply of skin segments onto the inner mold line layup mandrel and onto a plurality of stiffeners loaded on the inner mold line layup mandrel.

27. The system of claim 26, further comprising:

a stiffener forming tool configured to form the supply of stiffeners; and

a supply of composite stiffener plies;

wherein the stiffener forming tool is configured to form a respective stiffener from a subset of composite stiffener plies from the supply of composite stiffener plies.

28. The system of claim 26, wherein the inner mold line layup mandrel is configured to rotate after each loading of a respective stiffener onto the inner mold line layup mandrel.