Expandable tooling systems and methods

Patent metadata

Field	Value
Publication number	US-11046027-B2
Application number	US-201816053733-A
Country	US
Kind code	B2
Filing date	Aug 2, 2018
Priority date	Aug 2, 2018
Publication date	Jun 29, 2021
Grant date	Jun 29, 2021

Abstract

Prior to curing a composite workpiece assembly, an expandable element can be inserted into a cavity of the workpiece assembly. The expandable element is configured to expand when a predetermined change is produced in an attribute of the element. The attribute can be a temperature of the element. The element is expanded by producing the predetermined change, and the workpiece assembly is cured while the expanded element is in the cavity, so that the expanded element applies positive pressure to inner surfaces of the cavity during curing. The expanded element can be removed from the cavity after curing. The expanded element can comprise a plurality of expandable pellets.

First claim

What is claimed is:

1. A method of manufacturing a first composite workpiece, the method comprising:
inserting a plurality of unexpanded pellets into a cavity of an uncured composite workpiece assembly including at least the first composite workpiece, the plurality of unexpanded pellets being configured to expand when a predetermined change is produced in an attribute of the plurality of unexpanded pellets;
expanding the plurality of unexpanded pellets in the cavity by producing the predetermined change in the attribute of the plurality of unexpanded pellets;
curing the composite workpiece assembly while the plurality of expanded pellets remain discrete from one another in the cavity; and
removing the plurality of expanded pellets from the cavity of the cured workpiece assembly.

2. The method of claim 1 , wherein curing the composite workpiece assembly includes producing the predetermined change in the attribute of the plurality of unexpanded pellets.

3. The method of claim 1 , wherein the attribute of the plurality of unexpanded pellets is a temperature of the plurality of unexpanded pellets, and wherein producing the predetermined change in the attribute of the plurality of unexpanded pellets includes heating the plurality of unexpanded pellets to at least a predetermined first temperature.

4. The method of claim 1 , further comprising:
inserting a contractible element into the cavity along with the plurality of unexpanded pellets, the contractible element being configured to shrink when cooled from a heated curing temperature to a lower temperature;
shrinking the contractible element by cooling the contractible element from the heated curing temperature toward the lower temperature; and
removing the shrunken contractible element from the cavity.

5. The method of claim 4 , wherein the contractible element includes a resilient bladder.

6. The method of claim 1 , the method further comprising:
positioning the uncured composite workpiece assembly within a mold such that an outer surface of the workpiece assembly is placed against the mold;
wherein expanding the plurality of unexpanded pellets includes applying a positive pressure to an inner surface of the workpiece assembly forming the cavity by heating the plurality of unexpanded pellets from a first temperature to a second temperature higher than the first temperature to expand the plurality of unexpanded pellets to produce a predetermined pressure against the inner surface of the workpiece assembly.

7. The method of claim 6 , wherein heating the plurality of unexpanded pellets includes changing a temperature of the plurality of unexpanded pellets according to a predetermined temperature-time profile.

8. The method of claim 7 , wherein the temperature-time profile includes one or a combination of two or more of a starting temperature, one or more heating rates, one or more dwelling time at a predetermined temperature, one or more cooling rates, and an ending temperature.

9. The method of claim 6 , wherein removing includes removing the plurality of expanded pellets from the cavity of the cured workpiece assembly after applying the positive pressure to the inner surface of the workpiece assembly.

10. The method of claim 6 , further comprising inserting a plurality of magnetically attractable beads into the cavity prior to heating the plurality of unexpanded pellets, and removing the magnetically attractable beads with a complementary magnetically attractable element after applying the positive pressure to the inner surface of the workpiece assembly.

11. The method of claim 1 , wherein individual pellets of the plurality of unexpanded pellets have a maximum dimension that is less than 1/10 of a maximum cross-sectional dimension of the cavity.

12. The method of claim 1 , wherein the cavity has an opening on a cavity face, the opening having dimensions smaller than a maximum dimension of the cavity face, the method further comprising retaining the plurality of unexpanded pellets within the cavity during expanding the plurality of unexpanded pellets by closing the opening.

13. The method of claim 1 , wherein the uncured composite workpiece assembly includes an aircraft stiffener and an aircraft skin, and wherein curing the composite workpiece assembly bonds the aircraft stiffener to the aircraft skin.

14. The method of claim 1 , wherein inserting the plurality of unexpanded pellets includes inserting a flexible bag containing the plurality of unexpanded pellets into the cavity.

15. The method of claim 14 , wherein the cavity has an opening on a cavity face, and the method further comprises, after inserting the bag into the cavity, positioning a portion of the bag against the opening sufficient to cover at least a portion of the opening.

16. A method of manufacturing a first composite workpiece, the method comprising:
inserting an unexpanded expandable first element into a cavity of an uncured composite workpiece assembly including at least the first composite workpiece, the unexpanded first element being configured to expand when a predetermined change is produced in an attribute of the unexpanded first element;
inserting a contractible second element into the cavity, the contractible second element being configured to shrink when cooled from a heated curing temperature to a lower temperature;
expanding the unexpanded first element by producing the predetermined change in the attribute of the unexpanded first element;
curing the composite workpiece assembly at a heated curing temperature while the expanded first element is in the cavity;
shrinking the contractible second element by cooling the contractible second element from the heated curing temperature toward the lower temperature; and
removing the shrunken second element from the cavity.

17. The method of claim 16 , wherein the contractible second element includes a resilient bladder.

18. The method of claim 16 , further comprising removing the expanded first element from the cavity of the cured workpiece assembly.

19. The method of claim 18 , wherein removing the shrunken second element from the cavity is performed prior to removing the expanded first element from the cavity to facilitate removal of the expanded first element.

20. The method of claim 16 , wherein the expandable first element includes a plurality of unexpanded pellets, and wherein individual pellets of the plurality of unexpanded pellets have a maximum dimension that is less than 1/10 of a maximum cross-sectional dimension of the cavity.

Assignees

• Boeing Co

Inventors

• Wang Xiaoxi
• Georgeson Gary

Classifications

• B64C1/064

  Stringers; Longerons · CPC title

• Y02T50/40

  Weight reduction · CPC title

• Y02P70/50

  Manufacturing or production processes characterised by the final manufactured product · CPC title

• B29C43/32

  Component parts, details or accessories; Auxiliary operations · CPC title

• B29L2031/3085

  Wings · CPC title