Method for manufacturing a plurality of preforms for reinforcing members

Patent metadata

Field	Value
Publication number	US-9802366-B2
Application number	US-201414480829-A
Country	US
Kind code	B2
Filing date	Sep 9, 2014
Priority date	Mar 12, 2012
Publication date	Oct 31, 2017
Grant date	Oct 31, 2017

Abstract

A method of manufacturing a plurality of reinforcing element preforms, involving the steps of: positioning reinforcing elements on the external surface of a die; assembling the reinforcing elements thus positioned with one another so as to form a textile sleeve with a longitudinal axis and surrounding the die; moving the sleeve longitudinally toward a multi-cavity mandrel having an elongate overall shape, the multi-cavity mandrel having on its external surface a plurality of longitudinal cavities which are distributed, when viewed in cross section, around the periphery of the external surface; forming the sleeve on the plurality of peripheral cavities so that the sleeve conforms to the shape of the multi-cavity mandrel and thus adopts the shape of a set of reinforcing element preforms.

First claim

The invention claimed is:

1. A method for manufacturing a plurality of preforms for reinforcing members, comprising the steps:
positioning strengthening elements on the outside surface of a die,
assembling together the strengthening elements so positioned in order to form a textile sleeve having a longitudinal axis and surrounding the die,
moving said sleeve longitudinally towards a multi-cavity mandrel of elongate general shape, the multi-cavity mandrel comprising on the outside surface of said mandrel a plurality of longitudinal cavities which are distributed, as viewed in cross-section, around the periphery of the outside surface, and
forming the sleeve on the plurality of peripheral cavities of the multi-cavity mandrel in order for said sleeve to conform to the multi-cavity shape of said mandrel and thus take the shape of an assembly of preforms for reinforcing members.

2. The method according to claim 1 , wherein the textile sleeve is moved longitudinally of the die on a mandrel of longitudinal general shape with a cross-section changing along its length before continuing its movement towards the multi-cavity mandrel, the mandrel having, at an upstream end, a cross-section disposed immediately downstream of the die and of the same cross-section as that of said die and, at an opposite downstream end, a multi-cavity cross-section.

3. The method according to claim 2 , further comprising a step of heating the textile sleeve.

4. The method according to claim 1 , further comprising a step of adjusting the thicknesses and the geometry of the cross-section of the assembly of the preforms for reinforcing members carried by the multi-cavity mandrel, between the multi-cavity mandrel and an outside mold of shape complementary to that of said mandrel.

5. The method according to claim 1 , further comprising a step of drawing the assembly of the preforms for reinforcing members.

6. The method according to claim 1 , further comprising a step of cooling the assembly of the preforms for reinforcing members.

7. The method according to claim 1 , wherein the strengthening elements are one of strands and layers.

8. The method according to claim 1 , wherein the die has an elongate general shape and the strengthening elements are positioned along the outside surface of the die with several angular orientations.

9. The method according to claim 8 , wherein the strengthening elements are positioned on the die both with an angular orientation of 0° corresponding to the longitudinal direction of the die and with at least one different angular orientation.

10. The method according to claim 9 , wherein the distribution of the strengthening elements at 0° is not uniform.

11. The method according to claim 9 , wherein said at least one different angular orientation comprises an angle of 90° and angles of +θ and −θ relative to the longitudinal direction of the die.

12. The method according to claim 1 , further comprising a step of longitudinal cutting up of the assembly of the preforms for reinforcing members in order to longitudinally separate each preform from the adjacent preforms.

13. The method according to claim 1 , wherein each preform is of one of Omega-, T-, U-, C- and I-shaped general cross-section.

14. The method according to claim 1 , wherein at least some of the preforms of the assembly of the preforms for reinforcing members have a thickness in cross-section which varies from one preform to another and/or at least one preform has a thickness in cross-section which varies between two members constituting said at least one preform.

15. The method according to claim 1 , wherein the reinforcing members are aircraft fuselage stiffeners.

Assignees

• Airbus Operations Sas
• Carbone Forge
• Airbus Operations Sas

Inventors

• Legrand Xavier
• Blot Philippe
• Vinot Pascal
• Marchand Christope
• Cavet Alain

Classifications

• D10B2505/12

  Vehicles (D10B2505/08 takes precedence) · CPC title

• B29C70/545

  Perforating, cutting or machining during or after moulding · CPC title

• B29C70/24

  oriented in at least three directions forming a three-dimensional [3D] structure · CPC title

• D03D3/02

  Tubular fabrics · CPC title

• D10B2505/02

  Reinforcing materials; Prepregs · CPC title