Method for joining a window frame to a fuselage skin of an aircraft made of a fiber composite material

1 . A method for joining an at least partially curable window frame to an at least partially curable fuselage skin of an aircraft made of a fiber composite material, the method comprising:

providing the at least partially curable window frame,

making a window opening in the at least partially curable fuselage skin,

arranging a curable connecting layer around the window opening,

pressing the window frame onto the connecting layer, and

co-curing the at least partially curable fuselage skin, the curable connecting layer and the at least partially curable window opening to form a composite,

wherein the connecting layer is arranged on a carrier material and is configured to be adhered flat to the window frame or the fuselage skin,

wherein the step of making the window opening is carried out by an ultrasonic method, and

wherein no mechanical connecting elements are inserted through the window frame and the adjoining fuselage skin.

2 . The method according to claim 1 ,

wherein the window frame is at least partially cured before being pressed.

3 . The method according to claim 1 ,

further comprising applying a vacuum film to the fuselage skin and the window frame, and

evacuating an area covered by the vacuum film before the step of curing the composite.

4 . The method according to claim 1 ,

wherein the fuselage skin and/or the window frame is at least partially cured before the composite is cured.

5 . The method according to claim 1 ,

wherein the window frame is connected to the fuselage skin over an entire surface of the window frame.

6 . The method according to claim 1 ,

wherein the curing is carried out by an autoclave process.

7 . The method according to claim 4 ,

wherein a tear-off fabric is attached to the at least partially cured window frame or the at least partially cured fuselage skin, which is removed before pressing on.