Method for curing shell components

Patent metadata

Field	Value
Publication number	US-9592640-B2
Application number	US-201414522786-A
Country	US
Kind code	B2
Filing date	Oct 24, 2014
Priority date	Oct 30, 2013
Publication date	Mar 14, 2017
Grant date	Mar 14, 2017

Abstract

A curing tool for a shell component, includes a first tool component, which is a polyhedron and has a wedge-shaped bevel forming a first sheared edge on a first side edge, and a second tool component, which is a polyhedron, has a wedge-shaped bevel forming a second sheared edge on a first side edge and has a first corner bevel on a second side edge diagonally opposite the first side edge. The wedge angles of the first and the second sheared edge are equal.

First claim

The invention claimed is:

1. A method for curing a shell component, comprising:
placing a fibre-reinforced stringer prepreg comprising a stringer foot and a stringer web pointing away from a skin portion on the skin portion;
arranging a first tool component having a cross-section having four or five sides and a wedge-shaped bevel forming a first sheared edge on a first side edge, on the skin portion, so that the first sheared edge points away from the skin portion;
arranging a second tool component having a cross-section having five sides, a wedge-shaped bevel forming a second sheared edge on a first side edge, the wedge angle of the first and the second sheared edge being equal, and a first corner bevel on a second side edge diagonally opposite the first side edge, on the skin portion and at least part of the stringer foot, so that the second sheared edge rests on the first sheared edge and a flange portion of the stringer prepreg projects over the first corner bevel of the second tool component at a flange angle relative to the stringer foot; and
composite-curing the stringer prepreg using the first and second tool components to form a composite together with the skin portion.

2. The method according to claim 1 , wherein the wedge angle is between 10° and 35°.

3. The method according to claim 2 , wherein the flange angle is greater than the wedge angle.

4. The method according to claim 3 , wherein the flange angle is greater than the wedge angle by less than 3°.

5. The method according to claim 1 , further comprising:
removing the second tool component after the composite-curing by moving the second tool component away from the skin portion along the first sheared edge of the first tool component.

6. The method according to claim 1 , wherein the skin portion is curved.

7. A method for curing a shell component, the method comprising:
arranging a first tool component having a cross-section having four or five sides and a wedge-shaped bevel forming a first sheared edge on a first side edge, on a portion of a stringer foot of a first fibre-reinforced stringer prepreg comprising a stringer foot and a stringer web, so that the first sheared edge points away from the stringer foot;
arranging a second tool component having a cross-section having five sides, a wedge-shaped bevel forming a second sheared edge on a first side edge, the wedge angle of the first and the second sheared edge being equal, and a first corner bevel on a second side edge diagonally opposite the first side edge, on a portion of a stringer foot of a second fibre-reinforced stringer prepreg comprising a stringer foot and a stringer web, so that the second sheared edge rests on the first sheared edge and a flange portion of the second stringer prepreg projects over the first corner bevel of the second tool component at a flange angle relative to the stringer foot;
placing the assembly made up of the first stringer prepreg, the second stringer prepreg, the first tool component and the second tool component on a skin portion of the shell component; and
composite-curing the first and second stringer prepreg using the first and second tool components to form a composite together with the skin portion.

8. The method according to claim 7 , wherein the wedge angle is between 10° and 35°.

9. The method according to claim 8 , wherein the flange angle is greater than the wedge angle.

10. Method according to claim 9 , wherein the flange angle is greater than the wedge angle by less than 3°.

11. The method according to claim 7 , further comprising:
removing the second tool component after the composite-curing by moving the second tool component away from the skin portion along the first sheared edge of the first tool component.

12. The method according to claim 7 , wherein the skin portion is curved.

Assignees

• Airbus Operations Gmbh

Inventors

• Hoffmeister Thomas
• Mueller Markus
• Zuardy M Ichwan

Classifications

• B29C70/345

  using matched moulds · CPC title

• B29L2031/3082

  Fuselages · CPC title

• B29D99/0003 Primary

  Producing profiled members, e.g. beams · CPC title

• B29C33/02

  with incorporated heating or cooling means · CPC title

• B29C33/48

  with means for collapsing or disassembling · CPC title