Method and apparatus for producing an aircraft structural component

Patent metadata

Field	Value
Publication number	US-11230034-B2
Application number	US-201313887706-A
Country	US
Kind code	B2
Filing date	May 6, 2013
Priority date	Nov 8, 2010
Publication date	Jan 25, 2022
Grant date	Jan 25, 2022

Abstract

A method for producing an aircraft structural component includes the steps of introducing a plurality of semi-finished product layers for producing a component from a fibre-reinforced, thermoplastic plastic material into a compression mould, applying pressure to the stacked semi-finished product layers, the stacked semi-finished product layers being fixed, before pressure is applied, at particular points in their position in the compression mould and/or relative to one another in such a way that, while pressure is being applied to the semi-finished product layers stacked in the compression mould, a sliding movement of the semi-finished product layers relative to one another and/or relative to the compression mould, preventing wrinkling in the semi-finished product layers, takes place, and removing the aircraft structural component from the compression mould.

First claim

The invention claimed is:

1. A method for producing an aircraft structural component comprising the steps of:
(a) clipping together a plurality of semi-finished product layers for producing a component from a fibre-reinforced, thermoplastic plastic material,
(b) introducing the plurality of the semi-finished product layers, clipped together in the step (a), into a first compression mould comprising plane compression plates, such that the plurality of the semi-finished product layers are clipped at particular points in their position in the compression mould,
(c) applying pressure to the plurality of the semi-finished product layers introduced into the first compression mould in the step (b),
(d) enabling, during the applying of the pressure and due to the clipping in at least one of the step (a) and the step (b), a sliding movement of the semi-finished product layers, at least in an area between said particular points, relative to at least one of (i) one another and (ii) the compression mould, and
(e) removing the semi-finished product layers from the compression mould after the applying of the pressure,
wherein said step (c) comprises a first pressure-applying phase, during the first pressure-applying phase a pressure applied to a central region of the stacked semi-finished product layers in said first compression mould is higher than a pressure applied to a marginal region of the stacked semi-finished product layers.

2. The method according to claim 1 ,
wherein the pressure applied to the stacked semi-finished product layers during the first pressure-applying phase decreases continuously or discontinuously from the central region of the stacked semi-finished product layers in the direction of the marginal region of the stacked semi-finished product layers.

3. The method according to claim 1 ,
wherein said step (c) further comprises a second pressure-applying phase following the first pressure-applying phase, during the second pressure-applying phase are introduced into a second compression mould where a pressure applied to the marginal region of the stacked semi-finished product layers is increased in relation to the pressure applied to the marginal region of the stacked semi-finished product layers during the first pressure-applying phase.

4. The method according to claim 3 ,
wherein the pressure applied to the stacked semi-finished product layers during the second pressure-applying phase is increased continuously or discontinuously from the central region of the stacked semi-finished product layers in the direction of the marginal region of the stacked semi-finished product layers.

5. The method according to claim 3 ,
wherein the pressure applied to the marginal region of the stacked semi-finished product layers during the second pressure-applying phase is increased until it corresponds to the pressure applied to the central region of the semi-finished product layers during the first pressure-applying phase.

6. The method according to claim 3 , wherein the second compression mould comprises curved compression plates.

7. The method according to claim 1 ,
wherein the stacked semi-finished product layers are heated to a temperature of 300 to 500° C. while pressure is being applied and/or in that the semi-finished product layers are at least one of pre-fixed, heated, preshaped and preconsolidated before being introduced into the first compression mould.

8. The method according to claim 1 ,
wherein at least one semi-finished product layer for producing a stiffening element from a fibre-reinforced, thermoplastic plastic material is connected to the stacked semi-finished product layers for producing a component from a fibre-reinforced, thermoplastic plastic material.

9. The method according to claim 1 , wherein the stacked semi-finished product layers are clipped, before pressure is applied, relative to one another in at least one of (i) a central region and (ii) a marginal region of the semi-finished product layers.

10. The method according to claim 1 ,
wherein the sliding movement facilitates preventing wrinkling in the semi-finished product layers.

11. A method for producing an aircraft structural component comprising the steps of:
(a) fixing together by a local fusing a plurality of semi-finished product layers for producing a component from a fibre-reinforced, thermoplastic plastic material,
(b) introducing the plurality of the semi-finished product layers, locally fused together in the step (a), into a compression mould comprising plane compression plates, such that the plurality of the semi-finished product layers are locally fused at particular points in their position in the compression mould,
(c) applying pressure to the plurality of the semi-finished product layers introduced into the compression mould in the step (b),
(d) enabling, during the applying of the pressure and due to the fusing in at least one of the step (a) and the step (b), a sliding movement of the semi-finished product layers, at least in an area between said particular points, relative to at least one of (i) one another and (ii) the compression mould, and
(e) removing the semi-finished product layers from the compression mould after the applying of the pressure,
wherein said step (c) comprises a pressure applied to a central region of the stacked semi-finished product layers in said compression mould is higher than a pressure applied to a marginal region of the stacked semi-finished product layers.

12. The method according to claim 11 ,
wherein the sliding movement facilitates preventing wrinkling in the semi-finished product layers.

Assignees

• Airbus Operations Gmbh

Inventors

• Naumann Niko
• Willamowski Michaela

Classifications

• B29C33/12 Primary

  with incorporated means for positioning inserts, e.g. labels {(positioning reinforcements B29C70/541)} · CPC title

• B29C70/46 Primary

  using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs · CPC title

• B32B2305/07

  Parts immersed or impregnated in a matrix · CPC title

• B32B37/203

  One or more of the layers being plastic · CPC title

• B29C43/58

  Measuring, controlling or regulating {(for bank adjustment in calendering B29C43/245)} · CPC title