Method for forming inner mold line tooling without a part model

• US 5,876,546 A
• Filed: 09/25/1997
• Issued: 03/02/1999
• Est. Priority Date: 09/25/1997
• Status: Expired due to Fees

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Cloud, David J.
• Primary Examiner(s): Ball, Michael W.
• Assistant Examiner(s): Musser, Barbara J.
• Application Number:
  US08/937,855
• Time in Patent Office: 523 Days
• Field of Search: 156/212, 156/245, 264/220
• US Class Current: 156/212
• CPC Class Codes: B29C 2791/001 Shaping in several steps
• CPC Class Codes: B29C 35/02 Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mouldcold vulcanisation B29C35/18 ; vulcanising tyres, presses therefor B29D30/0601
• CPC Class Codes: B29C 43/3642 Bags, bleeder sheets or cauls for isostatic pressing
• 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 70/44 using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
• CPC Class Codes: B29C 70/549 Details of caul plates, e.g. materials or shape
• CPC Class Codes: B29K 2105/24 crosslinked or vulcanised
• CPC Class Codes: B29K 2105/243 Partially cured
• CPC Class Codes: Y10T 156/1028 by bending, drawing or stretch forming sheet to assume shape of configured lamina while in contact therewith

Abstract

A method of forming a caul plate (14) for use in producing a composite honeycomb core sandwich panel (27). The uncured honeycomb core sandwich panel (27) is laid-up on a lay-up mandrel (20). An inner bagging film (28) is then extended over the uncured honeycomb core sandwich panel (27). Tooling prepreg sheets (34) are extended over the inner bagging film (28), and a outer bagging film (40) is extended over the tooling prepreg sheets (34). Reduced vacuum is applied to the inner bagging film (28), and full vacuum is applied to the outer bagging film (40). The tooling prepreg sheets (34) are then partially cured so that they harden into the shape of the inner mold line of the honeycomb core sandwich panel (27). The partially cured tooling prepreg sheets (34) are then final cured to form the caul plate (14). The caul plate (14) can then be used for inner mold line tooling for the honeycomb core sandwich panel (27) or parts having the same inner mold line shape.

Claims

1. A method of forming a caul plate for aligning against the inner mold line of a composite part, comprising:

laying-up a first uncured composite material on a lay-up mandrel, the first uncured composite material having a first primary curing temperature;

extending a nonporous film over an inner mold line of the first uncured composite material;

arranging a second composite material over the nonporous film so as to form an assembly, the second composite material having a second primary curing temperature that is lower than the first primary curing temperature; and

curing the assembly at a curing temperature that is at least as high as the second primary curing temperature but is less than the first primary curing temperature such that the second composite material is made substantially rigid, whereby the cured, second composite material can be used as a caul plate for the inner mold line of the first uncured composite material.

2. The method of claim 1, wherein curing the second composite material at the curing temperature results in partial curing of the second composite material, and further comprising removing the cured, second composite material from the nonporous film and final curing the second composite material.

3. The method of claim 2, further comprising arranging the final-cured second composite material against the inner mold line of the first uncured composite material and curing the first uncured composite material.

4. The method of claim 1, further comprising vacuum bagging the second composite material in a first chamber prior to curing the second composite material, and applying vacuum to the first chamber during curing.

5. The method of claim 4, further comprising vacuum bagging the first composite material in a second chamber prior to curing the second composite material, and applying vacuum to the second chamber during curing, the second chamber being separate from the first chamber.

6. The method of claim 1, further comprising vacuum bagging the first composite material in a chamber prior to curing the second composite material, and applying vacuum to the chamber during curing.

7. The method of claim 6, wherein the first uncured composite material comprises a honeycomb core sandwich panel having a honeycomb core, the nonporous film comprises one side of the chamber, and wherein the vacuum applied to the chamber during curing is sufficient to draw the nonporous film into contact with the honeycomb core sandwich panel, but is not sufficient to crush the honeycomb core.

8. The method of claim 7, wherein the vacuum applied to the chamber is less than ten inches of mercury.

9. The method of claim 1, wherein the first uncured composite material is an uncured honeycomb core sandwich panel.

10. The method of claim 1, further comprising arranging the second composite material against the inner mold line of the first uncured composite material and curing the first uncured composite material.

11. The method of claim 1, wherein the second composite material extends substantially over the first uncured composite material.

12. A method of forming a caul plate for aligning against the inner mold line of a composite honeycomb core sandwich panel, comprising:

laying-up an uncured composite honeycomb core sandwich panel having a honeycomb core on a lay-up mandrel, the uncured composite honeycomb core sandwich panel having a first primary curing temperature;

extending a nonporous film over an inner mold line of the uncured composite honeycomb core sandwich panel;

arranging a second composite material over the nonporous film so as to form an assembly, the second composite material having a second primary curing temperature that is lower than the first primary curing temperature; and

curing the assembly at a curing temperature that is at least as high as the second primary curing temperature but is less than the first primary curing temperature such that the second composite material is made substantially rigid, whereby the cured, second composite material can be used as a caul plate for the inner mold line of the uncured composite honeycomb core sandwich panel.

13. The method of claim 12, wherein curing the second composite material at the curing temperature results in partial curing of the second composite material, and further comprising removing the cured, second composite material from the nonporous film and final curing the second composite material.

14. The method of claim 13, further comprising arranging the final-cured second composite material against the inner mold line of the uncured composite honeycomb core sandwich panel and curing the uncured composite honeycomb core sandwich panel.

15. The method of claim 12, further comprising vacuum bagging the second composite material in a first chamber prior to curing the second composite material, and applying vacuum to the first chamber during curing.

16. The method of claim 15, further comprising vacuum bagging the uncured composite honeycomb core sandwich panel in a second chamber prior to curing the second composite material, and applying vacuum to the second chamber during curing, the second chamber being separate from the first chamber.

17. The method of claim 12, further comprising vacuum bagging the uncured composite honeycomb core sandwich panel in a chamber prior to curing the second composite material, and applying vacuum to the chamber during curing.

18. The method of claim 17, wherein the nonporous film comprises one side of the chamber, and wherein the vacuum applied to the chamber during curing is sufficient to draw the nonporous film into contact with the uncured composite honeycomb core sandwich panel, but is not sufficient to crush the honeycomb core.

19. The method of claim 12, further comprising arranging the second composite material against the inner mold line of the uncured composite honeycomb core sandwich panel and curing the uncured composite honeycomb core sandwich panel.

20. The method of claim 12, wherein the second composite material extends substantially over the uncured composite honeycomb core sandwich panel.