The invention concerns an aircraft propulsion system (100) comprising a turbojet (102) having a fan casing (103) with a rear face (103a), a pylon (104) with a front part (106a) and a lower spar (106b) with a rear fitting (108) fixed to it, and a front engine attachment (150) fixed between an upper part of the fan casing (103) and the front part (106a), a front arch (152) having two arms (152b-c), each having a first end fixed to the lower spar (106b) and a second end fastened in an articulated manner to the rear face (103a), and two lateral rods (154), each having a first end fastened in an articulated manner to the rear fitting (108) and a second end fastened in an articulated manner to the rear face (103a).With such an arrangement, the forces are transmitted to the rear of the pylon.
PROPULSION SYSTEM FOR AN AIRCRAFT COMPRISING A TURBOJET, A PYLON AND ENGINE ATTACHMENT
ANTRIEBSSYSTEM FÜR EIN FLUGZEUG MIT EINEM STRAHLTRIEBWERK, EINEM PYLON UND EINER MOTORBEFESTIGUNG
SYSTÈME DE PROPULSION POUR AÉRONEF COMPRENANT UN TURBORÉACTEUR, UN MÂT ET UNE ATTACHE MOTEUR
2025-01-08
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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