Patent ID: 8844868
Filing Date: 2014-09-30
Classification: B64C,F16B,Y10T

Abstract:
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.