METHOD FOR PRODUCING A SANDWICH COMPONENT HAVING A HONEYCOMB CORE

1 . A method for producing composite components having a honeycomb core ( 2 ), comprising:

preforming a first skin ( 3 ) and a second skin ( 4 );

impregnating the first skin ( 3 ) and the second skin ( 4 );

Forming the first skin ( 3 ) and the second skin ( 4 ) to a three-dimensional curved shape;

bringing together one of the skins ( 3 ) of the first skin ( 3 ) or the second skin ( 4 ) with the honeycomb core ( 2 ), so that the base surfaces of the walls of the honeycomb core ( 2 ) contact the not yet hardened surface of this one skin ( 3 );

bringing together the other of the skins ( 4 ) of the first skin ( 3 ) or the second skin ( 4 ) with the honeycomb core ( 2 ), so that abutments of the walls of the honeycomb core ( 2 ) touch the not yet hardened surface of this one skin ( 4 );

and jointly hardening first skin ( 3 ), second skin ( 4 ) and honeycomb core ( 2 ), so that the one skin ( 3 ) of the first skin ( 3 ) or the second skin ( 4 ) forms a compound with the base surfaces of the walls of the honeycomb core ( 2 ) and the other one of the skins ( 4 ) of the first skin ( 3 ) or the second skin ( 4 ) forms a compound with the abutments of the walls of the honeycomb core ( 2 ).

2 . The method according to claim 1 , characterised in that the preform ( 3 , 4 ) is partially hardened.

3 . The method according to claim 1 , characterised by:

creating the preform ( 3 , 4 ) whilst providing the preform ( 3 , 4 ) with a matrix.

4 . The method according to claim 3 , characterised in that the matrix is highly viscous.

5 . The method according to claim 4 ,

characterised in that creating the preform ( 4 ) comprises:

impregnating a cover with the matrix and

then draping the cover.

6 . The method according to claim 5 , characterised by accomplishing the draping of the preform ( 4 ) manually.

7 . Method according to claim 1 ,

characterised by:

fine moulding of the partially hardened preform ( 4 ) on the honeycomb core ( 2 ).

8 . The method according to claim 1 ,

characterised by:

ending the partial hardening of the preform ( 3 , 4 ) before the preform ( 3 , 4 ) is hardened on one surface of the preform ( 3 , 4 ).

9 . The method according to claim 1 ,

characterised by:

compacting the preform ( 3 , 4 ) to a predefined thickness before ending the partial hardening of the preform ( 3 , 4 ).

10 . The method according to claim 1 ,

characterised by:

connecting the preform ( 3 , 4 ) to the honeycomb core ( 2 ) during the joint hardening.

11 . A composite component ( 1 ) having a honeycomb core ( 2 ) and a cover ( 3 , 4 ) which covers at least one section of the honeycomb core ( 2 ),

characterised by an absence of an adhesive film between the cover and the section of the honeycomb core covered by the cover.

12 . The composite component,

produced using the process steps according to claim 1 .

13 . A helicopter cell characterised by a composite component ( 1 ) according to claim 11 .

14 . A vehicle, in particular an aircraft,

characterised by a composite component ( 1 ) according to claim 11 .

15 . The method according to claim 2 ,

characterised by:

creating the preform ( 3 , 4 ) whilst providing the preform ( 3 , 4 ) with a matrix.