Thermoplastic titanium honeycomb panel

• US 6,039,832 A
• Filed: 02/27/1998
• Issued: 03/21/2000
• Est. Priority Date: 02/27/1998
• Status: Expired due to Fees

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: McCarville, Douglas A.
• Primary Examiner(s): Ball, Michael W.
• Assistant Examiner(s): MUSSER, BARBARA J
• Application Number:
  US09/032,227
• Time in Patent Office: 753 Days
• Field of Search: 428/116, 428/118, 156/292, 156/308.2, 156/308.6, 156/309.6, 156/324.4
• US Class Current: 156/292
• CPC Class Codes: B32B 2305/024 Honeycomb
• CPC Class Codes: B32B 2307/308 Heat stability dimensional stability B32B2307/734
• CPC Class Codes: B32B 2309/68 Vacuum
• CPC Class Codes: B32B 2311/18 Titanium
• CPC Class Codes: B32B 2398/20 Thermoplastics
• CPC Class Codes: B32B 2607/00 Walls, panels
• CPC Class Codes: B32B 3/12 characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
• CPC Class Codes: B32B 37/146 whereby one or more of the layers is a honeycomb structure

Abstract

The present invention discloses a structural panel sequentially comprising a first face sheet having an outward facing thermoplastic surface and an inward facing bonding surface, a first thermoplastic bonding layer, a titanium honeycomb core, a second thermoplastic bonding layer, and a second face sheet having an outward facing thermoplastic surface and an inward facing bonding surface. The face sheet is formed by thermally consolidating a thermoplastic laminate composite and a bonding layer. The face sheet bonding surface and intermediate bonding layer are made from thermoplastic resinous materials having comparable melt temperatures that are lower than that of the thermoplastic materials of the laminate composite. The present invention also provides a method for fabricating a structural panel having thermoplastic face sheets and a titanium honeycomb core that includes the steps of forming a first and second thermoplastic face sheet; preparing a titanium honeycomb core for bonding to the face sheets; and thermally consolidating a panel assembly sequentially having a first face sheet having an outward facing thermoplastic surface and an inward facing bonding surface, a first thermoplastic bonding layer, a titanium honeycomb core prepared for bonding to the face sheets, a second thermoplastic bonding layer, and a second face sheet having an outward facing thermoplastic surface and an inward facing bonding surface.

Claims

1. A structural panel sequentially comprising:

(a) a first face sheet having an outward facing surface and an inward facing bonding surface, wherein the outward facing surface comprises a first resinous material and the inward facing bonding surface comprises a second resinous material, wherein the melt temperature of the first resinous material is greater than the melt temperature of the second resinous material;

(b) a first bonding layer, comprising a third resinous material having a melt temperature comparable to the melt temperature of the second resinous material;

(c) a titanium honeycomb core, comprising resin fillets;

(d) a second bonding layers comprising a third resinous material having a melt temperature comparable to the melt temperature of the second resinous material; and

(e) a second face sheet having an outward facing surface and an inward facing bonding surface, wherein the outward facing surface comprises a first resinous material and the inward facing bonding surface comprises a second resinous material, wherein the melt temperature of the first resinous material is greater than the melt temperature of the second resinous material.

2. The panel of claim 1 wherein each face sheet comprises a thermoplastic laminate composite.

3. The panel of claim 2 wherein the laminate composite comprises a multi-ply laminate.

4. The panel of claim 3 wherein the multi-ply laminate comprises plies of preimpregnated resin and graphite.

5. The panel of claim 2 wherein the multi-ply laminate comprises oriented plies.

6. The panel of claim 2 wherein the laminate composite comprises a wet thermoplastic resin system.

7. The panel of claim 6 wherein the wet thermoplastic system comprises an aromatic polyimide resinous material.

8. The panel of claim 2 wherein the laminate composite comprises a dry thermoplastic resin system.

9. The panel of claim 8 wherein the dry thermoplastic system comprises a resinous material selected from the group selected from a polyetherimide and a polyether ether ketone resinous material.

10. The panel of claim 3 wherein the laminate composite comprises a reinforcement material.

11. The panel of claim 10 wherein the reinforcement material is selected from the group consisting of graphite tape and glass fabric.

12. The panel of claim 1 wherein each bonding surface comprises a resinous material selected from the group consisting of an aromatic polyimide resinous material and a polyetherimide resinous material.

13. The panel of claim 1 wherein each face sheet has a thickness of from about 0.02 to about 0.08 inch.

14. The panel of claim 1 wherein each face sheet is thermally stable at temperatures between about 350°

F. to about 400°

F.

15. The panel of claim 2 wherein the laminate composite comprises a first thermoplastic resinous material having a melt temperature in the range of from about 600°

F. to about 650°

F.

16. The panel of claim 1 wherein each bonding layer comprises a resinous material selected from the group consisting of an aromatic polyimide resinous material and a polyetherimide resinous material.

17. The panel of claim 1 wherein the titanium core has a density of from about 2.7 to about 6.0 lb/ft³.

18. The panel of claim 1 wherein the titanium core has a foil thickness of from about 0.002 to about 0.0025 inch.

19. The panel of claim 1 wherein the titanium core has a cell size of from about 1/4 to about 3/8 inch.

20. The panel of claim 1 wherein the resin fillets comprise a resinous material selected from the group consisting of an aromatic polyimide resinous material and a polyetherimide resinous material.

21. The panel of claim 1 wherein the titanium honeycomb core is a multicore panel.

22. The panel of claim 21 wherein the multicore panel further comprises a core splice.

23. The panel of claim 22 wherein the core splice comprises a foaming adhesive.

24. A method for fabricating a structural panel having thermoplastic face sheets and a titanium honeycomb core, comprising the steps of:

(a) forming a first and second thermoplastic face sheet, wherein each face sheet comprises an outward facing surface and an inward facing bonding surface, the outward facing surface comprising a first resinous material and the inward facing bonding surface comprising a second resinous material, wherein the melt temperature of the first resinous material is greater than the melt temperature of the second resinous material;

(b) preparing a titanium honeycomb core having resin fillets for bonding to the face sheets;

(c) preparing a panel assembly sequentially comprising a first face sheet, a first thermoplastic bonding layer, a titaniurn honeycomb core, a second thermoplastic bonding layer, and a second face sheet, wherein each bonding layer comprises a third resinous material having a melt temperature comparable to the melt temperature of the second resinous material; and

(d) thermally consolidating the panel assembly.

25. The method of claim 24 wherein forming a thermoplastic face sheet comprises thermally consolidating a laminate composite and a bonding layer, wherein the laminate composite comprises one or more plies of a first thermoplastic resinous material and the bonding layer comprises a second thermoplastic material having a melt temperature lower than the melt temperature of the first thermoplastic material.

26. The method of claim 25 wherein thermally consolidating the laminate composite and the bonding layer comprises heating to about 655°

F. at a pressure of about 185 psi and holding at that temperature and pressure for about one hour.

27. The method of claim 24 wherein preparing a titanium honeycomb core for bonding to the face sheets comprises the steps of:

(a) etching the titanium core to provide a chemically active surface;

(b) optionally, priming the etched core to preserve the chemically active surface;

(c) infusing a thermoplastic resinous material into the core to form resin fillets on the chemically active surface and

(d) heating the core to bond the resin fillets to the core.

28. The method of claim 24 wherein thermally consolidating the panel assembly comprises heating to about 525°

F. at a pressure of about 35 psi and holding at that temperature and pressure for about 30 minutes.

29. The method of claim 24 wherein thermally consolidating the panel assembly comprises effectively bonding the face sheets to the titanium honeycomb core through a thermoplastic resinous material having a melt temperature below the consolidation temperature.