System and a method for fastening aircraft components in the case of a CFK-metal hybrid construction
The present invention relates to the use of connecting elements for fastening CFK components and metal components in an aircraft or spacecraft, wherein a CFK component and a metal component can be connected to each other via at least one connecting element. The connecting element in this case is produced from an electrically non-conducting material, or has a shank and is produced from an electrically conducting or non-conducting material, wherein the shank is provided with a sleeve consisting of an electrically non-conducting material.
1. A method for fastening a skin panel of an aircraft fuselage, clips and stringers, which are carbon fibre reinforced plastic components and frames which are metal components, comprising:
providing the skin panel, the clip and the stringer, each of which is at least partially produced from a carbon fibre reinforced plastic material, and the frame which is produced from a metal material,
providing a separating layer between the skin panel and the frame,
providing a separating layer between the clip and the frame, wherein each separating layer comprises a layer comprising an aramide fibre reinforced plastic material,
connecting the skin panel and the frame via a connecting section of a connecting element,
connecting the skin panel and the stringer via a connecting section of a connecting element,
connecting the stringer and the frame with the clip, wherein the clip is connected to the stringer and the frame, respectively, via the connecting section of a connecting element,
wherein each connecting element is a rivet,
wherein each connecting element comprising the connecting section is produced from one of a glass fibre reinforced plastic, aramide fibre reinforced plastic, titanium and a titanium alloy, and wherein the connecting section of the connecting element connecting the skin panel and the frame extends through the skin panel, the frame and the separating layer therebetween and wherein the connecting section of the connecting element connecting the clip and the frame extends through the clip, the frame and the separating layer therebetween.
2. The method according to claim 1 , wherein the metal material is a metal or a metal alloy.
3. An aircraft fuselage comprising a skin panel, clips and stringers which are at least partially produced from a carbon fibre reinforced plastic material and frames, which are metal components, wherein a separating layer is provided between the skin panel and the frame and a separating layer is provided between the frame and the clip, wherein each separating layer comprises a layer comprising an aramide fibre reinforced plastic material, or a tedlar film, wherein the skin panel and the frame are connected via a connecting section of a connecting element, wherein the skin panel and the stringer are connected via a connecting section of a connecting element, wherein the frame and the stringer are connected with the clip, wherein the clip is connected to the stringer and the frame, respectively, via the connecting section of a connecting element, wherein each connecting element comprises a rivet, wherein each connecting element comprising the connecting section is produced from a glass fibre reinforced plastic, aramide fibre reinforced plastic, titanium or a titanium alloy, and wherein the connecting section of the connecting element connecting the skin panel and the frame extends through the skin panel, the frame and the separating layer therebetween and wherein the connecting element connecting the clip and the frame extends through the clip, the frame and the separating layer therebetween.
4. A method for fastening, a skin panel of an aircraft fuselage, clips and stingers, which are carbon fibre reinforced plastic components, and frames which are metal components, comprising:
providing the skin panel, the clip and the stringer, each of which is at least partially produced from a carbon fibre reinforced plastic material, and the frame which is produced from a metal material,
providing a separating layer between the skin panel and the frame,
providing a separating layer between the clip and the frame, wherein each separating layer comprises a layer comprising a tedlar film,
connecting the skin panel and the frame via a connecting section of a connecting element,
connecting the skin panel and the stringer via a connecting section of a connecting element,
connecting the stringer and the frame with the clip, wherein the dip is connected to the stringer and the frame, respectively via the connecting section of a connecting element, wherein each connecting element is a rivet, and
wherein each connecting element comprising the connecting section is produced from one of a glass fibre reinforced plastic, aramide fibre reinforced plastic, titanium and a titanium alloy, and wherein the connecting section of the connecting element connecting the skin panel and the frame extends through the skin panel, the frame and the separating layer therebetween and wherein the connecting section of the connecting element connecting the clip and the frame extends through the clip, the frame and the separating layer therebetween.
5. The method according to claim 4 , wherein the metal material is a metal or a metal alloy.
6. An aircraft fuselage comprising as skin panel, clips and frames which are at least partially produced from a carbon fibre reinforced plastic material and stringer, which are metal components, wherein a separating layer is provided between the skin panel and the stringer and a separating layer is provided between the stringer and the clip, wherein each separating layer comprises a layer comprising an aramide fibre reinforced plastic material, or a tedlar film, wherein the skin panel and the stringer are connected via a connecting section of a connecting element, wherein the skin panel and the frame are connected via a connecting section of as connecting element, wherein the frame and the stringer are connected with the clip, wherein the clip is connected to the stringer and the frame, respectively, via the connecting section of a connecting element, wherein each connecting element comprises a rivet and wherein each connecting element comprising the connecting section is produced from a glass fibre reinforced plastic, aramide fibre reinforced plastic, titanium or a titanium alloy, and wherein the connecting section of the connecting element connecting the skin panel and the stringer extends through the skin panel, the stringer and the separating layer therebetween and wherein the connecting element connecting the clip and the stringer extends through the clip, the stringer and the separating layer therebetween.
7. The aircraft fuselage according to claim 6 , wherein the metal component is made of metal or a metal alloy.
8. A method for fastening a skin panel of an aircraft fuselage, clips and frames, which are carbon fibre reinforced plastic components, and stringer which are metal components, comprising:
providing the skin panel, the clip and the frames, each of which is at least partially produced from a carbon fibre reinforced plastic material, and the stringer which is produced from a metal material,
providing a separating layer between the skin panel and the stringer,
providing a separating layer between the clip and the stringer, wherein each separating layer comprises a layer comprising an aramide fibre reinforced plastic material, or to tedlar film,
connecting the skin panel and the stringer via a connecting section of a connecting element,
connecting the skin panel and the frame via a connecting section of a connecting element,
connecting the stringer and the frame with the clip, wherein the clip is connected to the stringer and the frame, respectively, via the connecting section of a connecting element, wherein each connecting element is a rivet,
wherein each connecting element comprising the connecting section is produced from one of a glass fibre reinforced plastic, aramide fibre reinforced plastic, titanium and a titanium alloy, and wherein the connecting section of the connecting element connecting the skin panel and the stringer extends through the skin panel, the stringer and the separating layer therebetween and wherein the connecting section of the connecting element connecting the clip and the stringer extends through the clip, the stringer and the separating layer therebetween.
9. The method according to claim 8 , wherein the metal material is a metal or a metal alloy.