Stringer-less fuselage structures and associated methods of manufacturing are disclosed. In some embodiments, a fuselage structure includes a composite fuselage skin (24) including a plurality of tear straps (32) formed in the composite fuselage skin where each tear strap extends generally along a longitudinal axis of the composite fuselage skin. The fuselage structure also includes a plurality of frames (28) supporting an interior of the composite fuselage skin where the frames are spaced apart along the longitudinal axis of the composite fuselage skin.
STRINGER-LESS FUSELAGE STRUCTURE AND METHOD OF MANUFACTURE
2018-10-18
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
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