A structural assembly for an aircraft comprises: a frame structure comprising a plurality of structural members each having a longitudinal axis; at least one skin arranged on the frame structure; and at least one connecting element. The at least one connecting element comprises: a first portion configured to conformably interface with at least a portion of the at least one skin; and a second portion configured to rotationally receive at least a portion of one of said structural members, such that said connecting element is rotationally movable relative to said structural member about the longitudinal axis thereof. A method of manufacturing a structural component for an aircraft comprises providing said structural assembly; arranging the at least one connecting element on said structural member; rotationally adjusting the at least one connecting element relative to said structural member; arranging the at least one skin on the first portion of the at least one connecting element; attaching the at least one connecting element to said structural member; and attaching the at least one skin on the first portion of the at least one connecting element.
STRUCTURAL ASSEMBLIES FOR AIRCRAFT
STRUKTURANORDNUNGEN FÜR FLUGZEUGE
ENSEMBLES STRUCTURELS POUR AERONEF
2025-08-13
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |