An aircraft fuselage assembly (100) comprising: first (112) and second (114) skin sections each further comprising a plurality of plies of composite materials and having a mating edge, with the mating edges (116, 118) disposed in edgewise alignment with each other; anda plurality of tabs (120) each extending longitudinally from the mating edge (116) of the first skin (112) section along an interior surface of the second skin (114) section, each tab (120) including an exterior surface (124) in facing registration with a corresponding portion of the interior surface (132) of the second skin (114) section, each of said tabs (120) further including at least one injection hole (142) formed therethrough for injection of bonding material (140) between said exterior surface (124) and said corresponding portion for attaching the first (112) and second (114) skin sections.
Composite structural panels and aircraft fuselages
Panele aus Verbundstruktur und Luftfahrzeugrümpfe
Panneaux structuraux composites et fuselages d'avion
19.12.2018
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |