A crash load distribution structure of a fuselage, includes a floor frame defining a fuselage floor, a skid member fastened to the lower portion of the floor frame, and a crash box coupled to the skid member and extending to the lower portion of the floor frame, and configured to selectively deform in a crash load direction when an oblique crash occurs thereto.
CRASH LOAD DISTRIBUTION STRUCTURE OF FUSELAGE
2024-09-19
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |