A fuselage structure splice (106) may include a panel (111) having an edge (113) and a strap (120) connected to the first panel along the panel edge (113). A strap surface (123) not in contact with the panel tapers toward the panel with distance from the panel edge. A stringer (114) is mounted on the panel and extends away from the edge of the panel and has a flange (126) mounted to the panel. A fitting (100) has a stringer base portion (132) and a strap base portion (131). The stringer base portion is connected to the stringer flange and extends along a first line (146) extending in a plane (P1) normal to the panel edge. The strap base portion of the fitting is mounted on the strap surface and extends along a second line (147) in the plane (P1). The second line is transverse to the first line and the strap base portion of the fitting has a constant thickness along the second line.
FUSELAGE STRUCTURE SPLICE
RUMPFSTRUKTURSPLEISS
ÉPISSURE DE STRUCTURE DE FUSELAGE
2024-05-15
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |