A fuselage structure splice (101) may include a panel (112a-b) having an edge (113a-b) and a strap (120) connected to the first panel (112a) along the panel edge (113a). A strap surface (123a-b) not in contact with the panel tapers toward the panel 5 (112a-b) with distance from the panel edge (113a-b). A stringer (114, 116) is mounted on the panel (112a-b) and extends away from the edge (113a-b) of the panel (112a-b) and has a flange (126a-b, 127a-b) mounted to the panel (112a-b). A fitting (100a-d) has a stringer base portion (132a-d) and a strap base portion (131a-d). The stringer base portion (132a-d) is connected to the stringer flange (126a-b, 127a-b) and extends along 0 a first line (146) extending in a plane (P1) normal to the panel edge (113a-b). The strap base portion (131a-d) of the fitting (100a-d) is mounted on the strap surface (123a-b) and extends along a second line (147) in the plane (P1). The second line (147) is transverse to the first line (146) and the strap base portion (131a-d) of the fitting (100a-d) has a constant thickness along the second line (147). Co Ca C=>D C-C I C > Zc2 CO> C=> C=> ChiN -- C:2 CD> Ca -C 2
Fuselage structure splice
2021-09-09
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |