Method and system for co-consolidation of thermoplastic composite material parts

Patent metadata

Field	Value
Publication number	US-11279092-B2
Application number	US-201916358578-A
Country	US
Kind code	B2
Filing date	Mar 19, 2019
Priority date	Mar 19, 2019
Publication date	Mar 22, 2022
Grant date	Mar 22, 2022

Abstract

A co-consolidation tool, including a heating assembly to receive one or more thermoplastic parts and to apply a consolidation temperature to the one or more thermoplastic parts, a pressure bladder to apply a consolidation pressure to the one or more thermoplastic parts, and a support insert shaped and configured to support and at least partially surround at least one of the one or more thermoplastic parts, wherein at least one of heating assembly and the pressure bladder is shaped to receive and support the support insert.

First claim

What is claimed is:

1. A co-consolidation tool to form a thermoplastic fuselage skin with integrally formed thermoplastic stiffening elements, comprising:
a heating assembly, comprising one or more heating surfaces, to receive and apply a consolidation temperature to a thermoplastic fuselage skin and one or more thermoplastic stiffening elements;
a pressure bladder, disposed within the heating assembly, to apply a consolidation pressure to the thermoplastic fuselage skin and the one or more thermoplastic stiffening elements; and
a plurality of support inserts, disposed within the heating assembly, to support and at least partially surround the one or more thermoplastic stiffening elements,
wherein the pressure bladder and the plurality of support inserts are thermally conductive.

2. The co-consolidation tool of claim 1 ,
wherein the pressure bladder is configured to press the thermoplastic fuselage skin and the one or more thermoplastic stiffening elements together when the pressure bladder is pressurized, and
wherein the pressure bladder is configured to press the thermoplastic fuselage skin and the one or more thermoplastic stiffening elements in contact with at least one of the one or more heating surfaces when the pressure bladder is pressurized.

3. The co-consolidation tool of claim 2 , wherein the plurality of support inserts apply a compaction pressure to one of the one or more thermoplastic stiffening elements within the support inserts when the pressure bladder is pressurized.

4. The co-consolidation tool of claim 2 ,
wherein the pressure bladder comprises a plurality of cavities shaped to receive and support the plurality of support inserts, and
wherein, when the pressure bladder is pressurized, the plurality of support inserts apply a compaction pressure to one of the one or more thermoplastic stiffening elements contained therewithin in response to the consolidation pressure applied by the pressurized pressure bladder and physical constraints of said plurality of cavities.

5. The co-consolidation tool of claim 4 ,
wherein, when placed within the heating assembly, the pressure bladder, the plurality of thermally conductive support inserts, and the one or more thermoplastic stiffening elements, define a support surface configured to support the thermoplastic fuselage skin within the heating assembly.

6. The co-consolidation tool of claim 3 ,
wherein at least one of the one or more heating surfaces comprises a plurality of cavities shaped to receive and support the plurality of support inserts, and
wherein, when the pressure bladder is pressurized, the plurality of support inserts apply a compaction pressure to one of the one or more thermoplastic stiffening elements contained therewithin in response to the consolidation pressure applied by the pressurized pressure bladder and physical constraints of said plurality of cavities.

7. The co-consolidation tool of claim 6 ,
when placed within the heating assembly, the plurality of thermally conductive support inserts and the one or more thermoplastic stiffening elements together with a top surface of the at least one of the one or more heating surfaces comprising a plurality of cavities define a support surface configured to support the thermoplastic fuselage skin within the heating assembly.

8. The co-consolidation tool of claim 3 , further comprising a rotating mandrel,
wherein at least one of the one or more heating surfaces is supported by the rotating mandrel.

9. The co-consolidation tool of claim 1 , wherein the heating assembly comprises one or more heating bodies.

10. The co-consolidation tool of claim 9 , wherein the one or more heating bodies are configured to generate a magnetic field for induction heating.

11. The co-consolidation tool of claim 10 , wherein the one or more heating bodies comprise a plurality of induction coils and coolant channels.

12. The co-consolidation tool of claim 11 , wherein at least one of the one or more heating bodies comprises a contoured surface configured to accommodate at least one of the plurality of thermally conductive support inserts.

13. The co-consolidation tool of claim 10 , wherein at least one of the one or more heating surfaces comprises a smart susceptor to generate heat according to the magnetic field generated by the one or more heating bodies.

14. The co-consolidation tool of claim 1 , wherein at least one of the one or more heating surfaces comprises a contoured surface configured to accommodate at least one of the plurality of thermally conductive support inserts.

15. The co-consolidation tool of claim 1 , wherein each of the plurality of support inserts comprises one or more complementary support inserts.

16. The co-consolidation tool of claim 1 , wherein the pressure bladder is a pneumatic pressure bladder.

17. The co-consolidation tool of claim 1 , wherein the pressure bladder applies a consolidation pressure of up to 300 psi.

18. The co-consolidation tool of claim 1 , wherein the pressure bladder is thermally stable up to 750° F.

19. The co-consolidation tool of claim 1 , wherein the pressure bladder is a metallic pressure bladder comprising one or more metallic sheets.

20. The co-consolidation tool of claim 1 , wherein the pressure bladder comprises at least one of aluminum or an aluminum alloy.

Assignees

• Boeing Co

Inventors

• Koehn Joshua P
• Matsen Marc R
• Malmquist Kirk J
• Gideon David E

Classifications

• B29K2307/00

  Use of elements other than metals as reinforcement · CPC title

• B29C66/1122

  Single lap to lap joints, i.e. overlap joints (B29C66/45, B29C66/472, B29C66/52272 take precedence) · CPC title

• B29C66/91951

  in explicit relation to time, e.g. temperature-time diagrams · CPC title

• B29C2035/0811

  using induction · CPC title

• B29C66/131

  Single flanged joints, i.e. one of the parts to be joined being rigid and flanged in the joint area · CPC title