Method for manufacturing composite components

• US 7,748,119 B2
• Filed: 06/03/2005
• Issued: 07/06/2010
• Est. Priority Date: 06/03/2005
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Kismarton, Max U.
• Primary Examiner(s): Cozart; Jermie E
• Application Number:
  US11/144,146
• Publication Number:
  US 20060272143A1
• Time in Patent Office: 1,859 Days
• Field of Search: 298/97, 298/972, 298/973.4, 294/191, 294/23, 294/64, 295/251.3, 292/811, 428/615, 428/297.4, 249/57, 244/2, 244/99.1, 244/133, 244/123.1, 269/289.R, 269/909, 264/155, 264/163, 409/219
• US Class Current: 29/897.2
• CPC Class Codes: B29C 37/00 Component parts, details, accessories or auxiliary operations, not covered by group B29C33/00 or B29C35/00
• CPC Class Codes: B29C 70/202 arranged in parallel planes or structures of fibres crossing at substantial angles, e.g. cross-moulding compound [XMC] B29C70/207 takes precedence
• CPC Class Codes: B29C 70/34 and shaping or impregnating by compression , i.e. combined with compressing after the lay-up operation
• CPC Class Codes: B29C 70/865 completely encapsulated
• CPC Class Codes: Y10T 29/49622 Vehicular structural member making
• CPC Class Codes: Y10T 29/49801 Shaping fiber or fibered material
• CPC Class Codes: Y10T 29/49885 with coating before or during assembling
• CPC Class Codes: Y10T 29/49895 Associating parts by use of aligning means [e.g., use of a drift pin or a "fixture"]
• CPC Class Codes: Y10T 29/49966 with supplemental joining
• CPC Class Codes: Y10T 29/4998 Combined manufacture including applying or shaping of fluent material
• CPC Class Codes: Y10T 409/30868 Work support
• CPC Class Codes: Y10T 428/12493 Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]

Abstract

Methods and systems for manufacturing composite components, including asymmetric composite components, are disclosed. In one embodiment, a method of forming a composite component includes providing a forming tool having a base portion and at least one retaining portion; forming an uncured composite component on the forming tool; curing the composite component; performing a manufacturing operation on the cured composite component engaged with the forming tool; and after performing the manufacturing operation on the cured composite component, removing the cured composite component from the forming tool. In further embodiments, the forming tool may have a plurality of reference apertures disposed therethrough for performing drilling operations on the cured composite component.

Claims

1. A method comprising forming a composite component using an assembly including a forming tool having a plurality of apertures for drilling fastener holes in the composite component after curing on the tool but before the cured composite component is removed from the tool, the assembly further including a metallic layer insertable in the uncured composite component for supporting fasteners that are subsequently installed in the drilled holes,

the method including:

laying out the composite component while uncured on the forming tool and the metallic layer in the uncured composite component;

curing the composite component;

using the apertures in the forming tool to drill fastener holes into the cured composite component; and

removing the drilled composite component from the forming tool.

2. The method of claim 1, wherein the uncured composite component is asymmetric.

3. The method of claim 1, further comprising inserting fasteners into the drilled holes and the metallic layer after the drilled component has been removed from the tool, the metallic layer distributing fastener load and preventing composite material from being crushed.

4. The method of claim 1, wherein a bead of resinous material is formed along an interface between a base portion and a retaining portion of the forming tool.

5. The method of claim 4, wherein removing the cured composite component from the forming tool includes disengaging the cured composite component from the bead of resinous material.

6. The method of claim 1, wherein curing the composite component includes applying at least one of an elevated temperature and an elevated pressure to the composite component.

7. A method of manufacturing an aircraft, comprising forming a composite aircraft component of the aircraft using an assembly including a forming tool having a plurality of apertures for drilling fastener holes in the composite component after curing on the tool but before the cured composite component is removed from the tool, the assembly further including a metallic layer insertable in the uncured composite component for supporting fasteners that are subsequently installed in the drilled holes, the method including:

forming an uncured composite component on the forming tool with the metallic layer inserted in the composite component;

curing the composite component;

using the apertures in the forming tool to drill fastener holes into the cured component while the cured component is still on the forming tool;

removing the cured composite component from the forming tool; and

inserting fasteners into the drilled holes to fasten the composite aircraft component to at least one of a frame assembly and a second component.

8. The method of claim 7, wherein forming an uncured composite component on the forming tool includes forming an asymmetric composite component on the forming tool.

9. The method of claim 7, wherein a bead of resinous material is formed along an interface between a base portion and a retaining portion of the forming tool.

10. The method of claim 9, wherein removing the cured composite component from the forming tool includes disengaging the cured composite component from the bead of resinous material.