Method for manufacturing an integrated composite trailing edge and integrated composite trailing edge

Patent metadata

Field	Value
Publication number	US-9522504-B2
Application number	US-201414551589-A
Country	US
Kind code	B2
Filing date	Nov 24, 2014
Priority date	Nov 28, 2013
Publication date	Dec 20, 2016
Grant date	Dec 20, 2016

Abstract

An integrated composite trailing edge and its method of manufacturing. The trailing edge comprises an integrated main structure having an upper cover, lower flanges, and a set of ribs extending between the upper cover and the lower flanges, with a set of sandwich type lower panels attachable to the lower flanges of the integrated main structure. The method comprises the steps of providing a set of prepreg laminated preforms over a set of tool modules having a hollow so that each laminated configures a double C-shaped laminated preform having an upper section with a recess, two primary and secondary flanges, the upper section partly forming the upper cover, the two primary flanges partly forming the ribs and the two secondary flanges forming the lower flanges.

First claim

The invention claimed is:

1. A method for manufacturing an integrated composite trailing edge of an aircraft, the trailing edge comprising:
an integrated main structure comprising:
an upper cover,
lower flanges, and
a set of ribs extending between the upper cover and the lower flanges, and

a set of sandwich type lower panels attachable to the lower flanges of the integrated main structure,
the method comprising the following steps:
a) providing a set of prepreg laminated preforms of composite material over a set of tool modules, said tool modules having a hollow located at their upper part for receiving a sandwich core, the tool modules being configured so that each prepreg laminated perform configures a double C-shaped laminated preform having an upper section with a recess corresponding with the hollow, two primary flanges and two secondary flanges, the upper section configured for partly forming a segment of the upper cover of the integrated main structure, the two primary flanges configured for partly forming the ribs and the two secondary flanges configured for forming the lower flanges of the integrated main structure,
b) providing a set of sandwich cores into the recesses of the double C-shaped laminated preforms,
c) aligning the set of tool modules so that adjacent primary flanges are located together,
d) providing rovings to fill up the space in the radii between adjacent primary flanges,
e) providing a prepreg laminate on top of the aligned set of tool modules,
f) providing lower prepreg laminates against two consecutive secondary flanges, and
g) applying a curing process to co-cure said laminated preforms so that the integrated main structure of the trailing edge is formed,
wherein, during the forming process, a membrane is located over the tool module being pressed against the tool module by means of the vacuum provided by a general air port, while a male tool presses the flat prepreg laminate against the hollow of the tool module for forming the recess of the C-shaped laminated preform,
wherein, during the forming process, a membrane is located over the tool module, the membrane being pressed against the tool module for forming the recess of the C-shaped laminated preform by means of a vacuum provided by at least two air ports located in the proximity of the hollow.

2. The method according to claim 1 , wherein, during the forming process, a membrane is located over the tool module being pressed against the tool module by means of the vacuum provided by a general air port, while a male tool presses the flat prepreg laminate against the hollow of the tool module for forming the recess of the C-shaped laminated preform.

3. The method according to claim 1 , wherein the two air ports are located in the proximity of each of the inner corners of the hollow.

4. The method according to claim 1 , wherein
wherein the double C-shaped laminated preform is formed by lying up a flat prepreg laminate onto the upper section of the tool module by an automatic tape laying machine to obtain a flat laminate with the shape of the recess and then applying a forming process in order to achieve the double C shape.

5. The method according to claim 1 , wherein the double C-shaped prepreg laminated preform and its recess are formed by directly laying up a laminate over the tool module by means of a fiber placement machine.

6. A method for manufacturing an integrated composite trailing edge of an aircraft, the trailing edge comprising:
an integrated main structure comprising:
an upper cover,
lower flanges, and
a set of ribs extending between the upper cover and the lower flanges, and

a set of sandwich type lower panels attachable to the lower flanges of the integrated main structure,
the method comprising the following steps:
a) providing a set of prepreg laminated preforms of composite material over a set of tool modules, said tool modules having a hollow located at their upper part for receiving a sandwich core, the tool modules being configured so that each prepreg laminated perform configures a double C-shaped laminated preform having an upper section with a recess corresponding with the hollow, two primary flanges and two secondary flanges, the upper section configured for partly forming a segment of the upper cover of the integrated main structure, the two primary flanges configured for partly forming the ribs and the two secondary flanges configured for forming the lower flanges of the integrated main structure,
b) providing a set of sandwich cores into the recesses of the double C-shaped laminated preforms,
c) aligning the set of tool modules so that adjacent primary flanges are located together,
d) providing rovings to fill up the space in the radii between adjacent primary flanges,
e) providing a prepreg laminate on top of the aligned set of tool modules,
f) providing lower prepreg laminates against two consecutive secondary flanges, and
g) applying a curing process to co-cure said laminated preforms so that the integrated main structure of the trailing edge is formed,
wherein the double C-shaped laminated preform is formed by lying up a flat prepreg laminate onto the upper section of the tool module by an automatic tape laying machine to obtain a flat laminate with the shape of the recess and then applying a forming process in order to achieve the double C shape,
wherein, during the forming process, the recess is finished by positioning a membrane over the tool module, the membrane being pressed against the tool module by means of the vacuum provided by at least two air ports located in a proximity of the hollow.

7. The method according to claim 6 , wherein the double C-shaped laminated preform is formed by providing a flat prepreg laminate over the tool module followed by a forming process of said flat laminate over the tool module for forming the double C shape and the recess.

8. The method according to claim 6 , wherein the two air ports are located in the proximity of each of the inner corners of the hollow.

9. The method according to claim 6 , wherein, during the forming process, the recess is finished by positioning a membrane over the tool module, the membrane being pressed against the tool module by means of the vacuum provided by an air port and by pressing a male tool against the hollow of the tool module.

10. The method according to claim 6 , wherein the double C-shaped prepreg laminated preform and its recess are formed by directly laying up a laminate over the tool module by means of a fiber placement machine.

Assignees

• Airbus Operations Sl

Inventors

• Garcia Martin Diego
• Nunez Delgado Julio
• Barroso Fernandez Lara

Classifications

• B29L2031/3085

  Wings · CPC title

• B29C70/865

  completely encapsulated · CPC title

• B29C70/088

  and with one or more layers of non-plastics material or non-specified material, e.g. supports · CPC title

• B29D99/0014

  provided with ridges or ribs, e.g. joined ribs · CPC title

• B32B37/1018

  using only vacuum · CPC title