Skin-stiffened composite panel

Patent metadata

Field	Value
Publication number	US-9302446-B2
Application number	US-201414515805-A
Country	US
Kind code	B2
Filing date	Oct 16, 2014
Priority date	Oct 28, 2013
Publication date	Apr 5, 2016
Grant date	Apr 5, 2016

Abstract

A skin-stiffened composite panel ( 1 ) comprising at least two essentially longitudinal stiffeners ( 3 ) arranged distant to each other in a plane with a skin ( 2 ) of a planar outer continuous composite layer ( 9 ) and an inner continuous composite layer ( 10 ). The at least two essentially longitudinal stiffeners ( 3 ) have a height “a” perpendicular to the skin ( 2 ). At least two sandwich assemblies ( 4 ) in said plane are along each one of the at least two essentially longitudinal stiffeners ( 3 ), said at least two sandwich assemblies ( 4 ) comprising each the planar outer and the inner continuous composite layers ( 9, 10 ) and a grid-type foam module ( 8 ) with openings and with a height “b”, with the foam modules ( 8 ) on the same side of the planar outer continuous composite layer ( 9 ) as the essentially longitudinal stiffeners ( 3 ) between the inner continuous composite layer ( 10 ) and the planar outer continuous layer ( 9 ).

First claim

What is claimed is:

1. A skin-stiffened composite panel extending essentially along a common plane, said panel comprising:
at least two essentially longitudinal stiffeners arranged distant to each other in said plane, said at least two essentially longitudinal stiffeners having each at least one base flange;
a skin of a planar outer continuous composite layer and an inner continuous composite layer, the at least two essentially longitudinal stiffeners being each bonded unilaterally by means of said at least one base flange to one side of the inner continuous composite layer of the skin, wherein the at least two essentially longitudinal stiffeners have a height a perpendicular to the skin;
at least two sandwich assemblies in said common plane along each one of the at least two essentially longitudinal stiffeners, said at least two sandwich assemblies comprising each the planar outer and the inner continuous composite layers and a foam module, with the foam modules on the same side of the planar outer continuous composite layer as the essentially longitudinal stiffeners between the inner continuous composite layer and the planar outer continuous layer and the foam modules each having a height b less than 3.5 mm, perpendicular to the planar outer continuous composite layer, the foam module having a grid-type structure with openings and flat ribs along first and second angled directions in said plane, the width c of the flat ribs being at least 5 times larger than the height b of the foam modules, the inner continuous composite layer and the planar outer continuous layer being connected to each other within the openings of the foam module and along at least two interstices between the at least two sandwich assemblies for the at least two essentially longitudinal stiffeners.

2. The panel according to claim 1 , wherein the essentially longitudinal stiffeners are parallel to each other.

3. The panel according to claim 1 , wherein the essentially longitudinal stiffeners are adhesively or cohesively bonded to the inner continuous composite layer.

4. The panel according to claim 1 , wherein the inner continuous composite layer and the planar outer continuous layer are respectively composed of tows of a plurality of either preimpregnated or dry composite unidirectional plies.

5. The panel according to claim 1 , wherein the flat ribs are oriented at 0° or 90° or 45° with respect to the essentially longitudinal stiffeners.

6. The panel according to claim 1 , wherein the inner continuous composite layer and the planar outer continuous layer are directly connected to the foam modules and to each other without any additional adhesive layer.

7. A method for manufacturing a panel according to claim 1 , with the following steps:
a) providing of at least one machined foam module having a grid type structure and at least one uncured, essentially longitudinal stiffener preform with a supporting mold;
b) providing a planar outer continuous composite layer by means of automatic fiber placement processes;
c) unilateral placement of the foam modules on the laid-up planar outer continuous composite layer with an essentially longitudinal interstice between for the stiffener preform;
d) automatic lay-up of the inner continuous composite layer by means of automatic fiber placement processes on top of both: the planar outer continuous composite layer and the foam modules;
e) placement of the at least one uncured, essentially longitudinal stiffener preforms and its supporting mold on top of the inner continuous composite layer to a preliminary panel; and
f) bagging and curing of the panel.

Assignees

• Airbus Helicopters Deutschland GmbH

Inventors

• Fink Axel

Classifications

• B32B2605/18

  Aircraft · CPC title

• B32B5/18 Primary

  characterised by features of a layer {of} foamed material · CPC title

• B32B37/18

  involving the assembly of discrete sheets or panels only · CPC title

• B29D99/0014 Primary

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

• Y10T428/233

  Foamed or expanded material encased · CPC title