A collision load distribution structure of a fuselage includes a front unit configured to be located at front ends relative to wings attached to the fuselage, a rear unit configured to be located at rear ends relative to the wings attached to the fuselage, a support unit configured to be located between the front unit and the rear unit, and a wing unit. The support unit is configured to transfer loads applied to the fuselage in case of a crash of the fuselage. The wing unit is configured to be located in the support unit, and connected to the support unit so as to transfer the loads in case of the crash of the fuselage. Loads in a length direction of the fuselage are passed through to the front unit, and are distributed to the wing unit through the support unit.
Collision Load Distribution Structure of Fuselage
01.08.2024
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
Collision load distribution structure of the fuselage
Europäisches Patentamt | 2024
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