Abstract: A method for producing a composite component including a bottom layer, cover layer and honeycomb structure, including applying the honeycomb structure to the bottom layer wherein honeycomb chambers are formed. Honeycomb chambers are filled in a reinforcement region with a granular material and granular material is removed from other honeycomb chambers wherein each honeycomb chamber is filled up to a granular-material filling height and honeycomb chambers outside the reinforcement region are free of granular material. The cover layer is applied to the honeycomb structure wherein the honeycomb chambers are closed. The composite component is heated so the granular material in the honeycomb chambers expands to fill it with granular material and the cover layer, the bottom layer, the honeycomb structure and the expanded granular material harden, the density of the expanded granular material in the honeycomb chambers filled with granular material being dependent on the granular-material filling height.

Abstract: A method for producing a composite component including a bottom layer, cover layer and honeycomb structure, including applying the honeycomb structure to the bottom layer wherein honeycomb chambers are formed. Honeycomb chambers are filled in a reinforcement region with a granular material and granular material is removed from other honeycomb chambers wherein each honeycomb chamber is filled up to a granular-material filling height and honeycomb chambers outside the reinforcement region are free of granular material. The cover layer is applied to the honeycomb structure wherein the honeycomb chambers are closed. The composite component is heated so the granular material in the honeycomb chambers expands to fill it with granular material and the cover layer, the bottom layer, the honeycomb structure and the expanded granular material harden, the density of the expanded granular material in the honeycomb chambers filled with granular material being dependent on the granular-material filling height.

Abstract: A decompression-element fastening system releasably fastens a trim component serving as a decompression element to a supporting structure in an aircraft internal region. The decompression fastening system includes at least one bolt, a screw for pressing the trim component in the direction of the supporting structure, and at least one detent element configured for resilient support on the supporting structure. The bolt has a bolt axis and on a first end at least one detent recess and on a second end a first thread. The screw is connected by a second thread to the bolt. The detent element upon approach of the bolt may slide over the first end thereof and come into engagement with the detent recess. If a predetermined tensile force acting in the direction of the bolt axis is exceeded, the detent element disengages from the detent recess.

Abstract: A decompression-element fastening system (10) is provided for releasably fastening a trim component (12) serving as a decompression element to a supporting structure (14) in an aircraft internal region. The decompression fastening system (10) comprises at least one bolt (20), a screw (44) configured for pressing the trim component (12) in the direction of the supporting structure (14), and at least one to detent element (22) configured for resilient support on the supporting structure (14). The bolt (20) has a bolt axis (21) and on a first end at least one detent recess (26) and on a second end (28) a first thread (40). The screw (44) is connected by a second thread (42) to the bolt (20). The detent element (22) upon approach of the bolt (20) may slide over the first end (28) thereof and come into engagement with the detent recess (26). If predetermined tensile force acting in the direction of the bolt axis (21) is exceeded, the detent element (22) disengages from the detent recess (26).