DE102008001416A1 - External skin arrangement for air- or spacecraft, comprises a first lightening conductor layer for conducting of light energy, and a fiber reinforced composite layer, which carries the first lightening conductor layer - Google Patents

Abstract

The external skin arrangement (1) comprises a first light conductor layer for conducting of light energy, and a fiber reinforced composite layer (2), which carries the first lightening conductor layer (4). A first electric connection (7, 8) is intended for a connection of first electric component (9, 10) with the first lightening conducting layer. An insulation layer and a second lightening conducting layer are intended between the first lightening conducting layer and the fiber reinforced composite layer. The external skin arrangement (1) comprises a first light conductor layer for conducting of light energy, and a fiber reinforced composite layer (2), which carries the first lightening conductor layer (4). A first electric connection (7, 8) is intended for a connection of first electric component (9, 10) with the first lightening conducting layer. An insulation layer and a second lightening conducting layer are intended between the first lightening conducting layer and the fiber reinforced composite layer in such a way that it form a sequence of first light conducting layers, insulation layers, second light conducting layers and fiber composite material layers. The second electric connection is equipped for a connection of the second lightening conducting layers with second electric components. The first and/or the second lightening conducting layers are arranged in the area of the first and/or the second connection. The first and/or the second lightening conducting layers comprise metallic gauze, a perforated or slotted metal foil and/or a non-woven. The first and/or the second electric connection are formed as ground connection. An independent claim is included for air- or spacecraft.

Description

The The present invention relates to an outer skin assembly for an aircraft or spacecraft, as well as an air or spacecraft Spacecraft with such a skin arrangement.

In particular, aircraft are increasingly being formed with skin assemblies having carbon fiber plastic (CFRP). Because of the low electrical conductivity of CFK compared to metal, such outer skin assemblies must be provided with a lightning arrestor material, such as in the DE 10 2006 046 002 A1 described.

Farther In aircraft there is the requirement of having an on-board connection provided electrical components to ground. This is achieved by the fact that in the aircraft separate, metallic Ladder are introduced and this with the respective ground connections the components are connected.

at This approach has proved to be disadvantageous that the introduced, separate, metallic conductor the weight of the aircraft increase. In addition, the installation effort for this ladder considerably.

task Therefore, the present invention is as described above To fix disadvantages.

These Task is by an outer skin arrangement with the features of claim 1 and / or by an aircraft or spacecraft solved with the features of claim 6.

Accordingly, becomes an outer skin arrangement for an aircraft or spacecraft provided. The outer skin assembly has a first one Lightning conductor layer for a discharge of lightning energy and a fiber composite layer containing the first lightning arrester layer carries on. Furthermore, the outer skin arrangement with a first electrical connection for connection a first, electrical component with the first lightning arrester layer intended.

Further is an aircraft or spacecraft with the inventive Outer skin and a first, electrical component, which with the first, electrical connection of the outer skin arrangement according to the invention connected.

The The idea underlying the present invention is that that the first lightning arrester layer occupies a double function On the one hand, it serves to dissipate lightning energy and, on the other hand serves as a ground connection for electrical components. Characterized in that the lightning arrester layer, for example, substantially the entire hull covers, now only need still comparatively short electrical conductors between the ground connections the components and the mass are provided, resulting in a clear Weight saving leads. In addition, deleted the need to lay long ladders in the plane, thereby continues to reduce assembly costs.

Out the dependent claims are advantageous embodiments and improvements of the invention.

With "components" are in particular electricity consumers and power sources in the present case.

According to one preferred development of the invention Exterior skin assembly is between the first lightning arrester layer and the fiber composite layer an insulation layer and a second lightning arrester layer provided such that the order first lightning conductor layer, insulation layer, second lightning arrester layer, Fiber composite layer results, with a second, electrical Connection for connecting the second lightning arrester layer is provided with a second, electrical component. The first and second lightning arrester layer can thus have two masses form with different electrical potentials. This can favorable for different types of components be.

According to one preferred development has the fiber composite material layer CFK on. Preferably, the CFRP has a matrix system which a high isolation effect compared to the first or second lightning rod has.

According to one preferred development of the invention Exterior skin assembly is the first and / or second lightning arrestor layer locally, in particular in the area of the first or second connection, revealed for improved conductivity.

According to one further preferred embodiment of the invention Exterior skin assembly includes the first and / or second lightning arrestor layer Metal mesh, a metal foil, in particular a perforated or Slotted metal foil and / or a flow on.

According to a further preferred development of the aircraft or spacecraft according to the invention, a second, electrical component is provided see, which is connected to the second, electrical connection of the outer skin assembly. The resulting advantages in this context have already been explained above.

According to one further preferred embodiment of the invention Aircraft or spacecraft is the first and / or second lightning arrester layer on the outside with respect to the fiber composite material layer and the first and / or second component inside arranged the fiber composite material layer. Thus protect the first and second lightning arrester layer effectively both the fiber composite layer as well as the components from lightning.

The Invention will be described below with reference to exemplary embodiments explained in more detail with reference to the accompanying figures.

From show the figures:

1 schematically a section of an aircraft or spacecraft according to an embodiment of the present invention;

2 schematically a section of an aircraft or spacecraft according to another embodiment of the invention.

In the same reference numerals designate the same or functionally identical Components, unless stated otherwise.

1 schematically shows a section of an aircraft or spacecraft according to an embodiment of the present invention.

1 shows an outer skin arrangement 1 , in particular a fuselage of an aircraft. The outer skin arrangement 1 has a fiber composite layer 2 which essentially forms a supporting structure of the aircraft or spacecraft. The fiber composite layer 2 bears on an interior 3 of the aircraft or spacecraft on the outside a first lightning arrester layer 4 , The lightning arrester layer 4 is preferably with respect to a schematically indicated environment 5 by means of a lacquer layer 6 protected provided.

From the interior 3 Two connections are sufficient 7 and 8th through the fiber composite layer 2 therethrough. The connections 7 . 8th are each at one end with the first lightning arrester layer 4 connected. In this case, the lightning arrester layer 4 , such as for the connection 8th shown locally thickened for improved conductivity. The thickening is denoted by the reference numeral 6a Mistake. Alternatively or additionally, this can be done with the first lightning arrester layer 4 connected end of the connection 8th For example, be formed flat to improved conductivity between the terminal 8th and the lightning arrester layer 4 to ensure.

Of course, the connections should 7 and 8th opposite the layer 2 provided electrically insulated.

The connection 7 is at the other end with a consumer 9 , For example, a light source, electrically connected. In the figures, electrical lines are represented by a double-crossed line.

The consumer 9 is in turn by means of an electrical line with a power source 10 , For example, a generator connected. The power source 10 is in turn with the other end of the connector 8th electrically connected.

Thus, as in 1 shown, a closed circuit 10a , wherein the first lightning arrester layer 4 acts as a mass or the first lightning arrester layer 4 a section of the circuit 10a formed.

2 schematically shows a section of an aircraft or spacecraft according to another embodiment of the present invention.

The embodiment according to 2 is based on the embodiment according to 1 , In this respect, only the differences between the exemplary embodiments will be discussed below.

The embodiment according to 2 points opposite to the 1 furthermore an insulation layer 11 and a second lightning arrester layer 12 between the first lightning arrester layer 4 and the fiber composite layer 2 on.

The second lightning arrester layer 12 forms a section of a second circuit 17 out. The second circuit 17 is made up of connections 13 and 14 a consumer 15 and a power source 16 together and is in accordance with the already related 1 explained circuit constructed.

The circuits 10a and 17 can be operated electrically isolated from each other. In particular, it can be provided that the reference potential of the masses 4 and 12 is provided differently. In particular, an influence on the circuits 10a and 17 each other is thus avoided.

Of course, in should 2 the connections 7 and 8th opposite the layers 2 . 12 and 11 provided electrically insulated. Also the connections 13 and 14 should of course be opposite the layer 2 provided electrically insulated. This can be achieved, for example, by forming the CFRP with an insulating matrix system.

Of course, any number of consumers 9 respectively 15 and power sources 10 respectively 16 in the embodiments according to 1 or according to 2 to get integrated.

Preferably, the fiber composite material layer 2 a CFK on. Preferably, the first and second lightning arrester layers 4 . 12 formed from a metal fabric or a metal foil.

The lightning arrester layers 4 . 12 in the present case do not necessarily have to with the mass connections of the components 9 . 10 . 15 . 16 get connected. Rather, they can also form a reference potential for other electrical connections of the components.

Even though the present invention with reference to preferred embodiments described above, it is not limited thereto but modifiable in many ways.

The The present invention provides an outer skin assembly as well an aircraft or spacecraft with such an outer skin arrangement. The outer skin assembly has a first lightning arrester layer for a dissipation of flash energy and a fiber composite layer, which carries the first lightning arrester layer on. Further the outer skin assembly has a first electrical Connection for connecting a first, electrical component with the first lightning arrester layer on. The inventively resulting The advantage is that the lightning arrester layer has a dual function fulfilled: on the one hand, it serves to dissipate lightning energy and on the other hand it forms a section of a circuit to Operating the first electrical component. With it reduced the need for electrical wiring in the aircraft, which in turn in a weight reduction for the aircraft or spacecraft results.

1

Shell arrangement

2

Fiber composite material layer

3

inner space

4

first lightning conductor layer

5

environment

6

paint layer

6a

thickening

7

connection

8th

connection

9

consumer

10

power source

10a

circuit

11

insulating

12

second lightning conductor layer

13

connection

14

connection

15

consumer

16

power source

17

circuit

QUOTES INCLUDE IN THE DESCRIPTION

This list The documents listed by the applicant have been automated generated and is solely for better information recorded by the reader. The list is not part of the German Patent or utility model application. The DPMA takes over no liability for any errors or omissions.

Cited patent literature

• - DE 102006046002 A1 [0002]

Claims (10)

Outer skin arrangement ( 1 ) for an aircraft or spacecraft, comprising: a first lightning arrester layer ( 4 for a derivative of flash energy; and a fiber composite layer ( 2 ), which the first lightning arrester layer ( 4 ) wearing; characterized in that a first electrical connection ( 7 . 8th ) for connecting a first, electrical component ( 9 . 10 ) with the first lightning arrester layer ( 4 ) is provided. Exterior skin arrangement according to claim 1, characterized in that between the first lightning conductor layer ( 4 ) and the fiber composite layer ( 2 ) an insulation layer ( 11 ) and a second lightning arrester layer ( 12 ) is provided such that the order of the first lightning arrester layer ( 4 ), Insulation layer ( 11 ), second lightning arrester layer ( 12 ), Fiber composite layer ( 2 ), wherein a second, electrical connection ( 13 . 14 ) for connecting the second lightning arrester layer ( 12 ) with a second, electrical component ( 15 . 16 ) is provided. Exterior skin arrangement according to claim 1 or 2, characterized in that the first and / or second lightning conductor layer ( 4 . 12 ) in the region of the first and / or second connection ( 7 . 8th . 13 . 14 ) is formed thickened. Exterior skin arrangement according to at least one of the preceding claims, characterized in that the first and / or second lightning conductor layer ( 4 . 12 ) has a metal fabric, a metal foil, in particular a perforated or slotted metal foil and / or a nonwoven. Exterior skin arrangement according to at least one of the preceding claims, characterized in that the first and / or second electrical connection ( 7 . 8th ; 13 . 14 ) is designed as a ground terminal. An aircraft or spacecraft, comprising: an outer skin assembly according to any one of the preceding claims; and a first, electrical component ( 9 . 10 ) connected to the first electrical connection ( 7 . 8th ) of the outer skin arrangement ( 1 ) connected is. Aerial or spacecraft according to claim 6, characterized in that a second, electrical component ( 15 . 16 ) provided with the second, electrical connection ( 13 . 14 ) connected is. Aerospace vehicle according to claim 6 or 7, characterized in that the first and / or second lightning arrester layer ( 4 . 12 ) on the outside with respect to the fiber composite material layer ( 2 ) and the first and / or second component ( 15 . 16 ) on the inside with respect to the fiber composite material layer ( 2 ) is arranged. Aerospace vehicle according to claim 6 to 8, characterized in that the first, electrical component ( 9 . 10 ) with its ground connection to the first, electrical connection ( 7 . 8th ) and / or the second, electrical component ( 15 . 16 ) with its ground connection to the second, electrical connection ( 13 . 14 ) connected is. Aerospace vehicle according to claim 6 to 9, characterized in that the first, electrical component ( 9 . 10 ) with the first lightning arrester layer ( 4 ) a first circuit ( 10a ) and / or the second electrical component ( 15 . 16 ) with the second lightning arrester layer ( 12 ) a second circuit ( 17 ).