The invention concerns a propulsion system (100) comprising a turbojet (102) with a fan casing (102a) and a central casing (102b), a pylon (104) with an upper spar (106b), a front wall (106d) and on either side of a vertical median plane (P), a fitting (172) rigidly fixed to the rigid structure (106), a cylindrical pin (174) as one with the fan casing (102a) and inserted in a hole of the upper spar (106b), a shackle (200a) with at the vertical median plane (P), an upper articulation (202) between the shackle (200a) and the front wall (106d) and on either side of the vertical median plane (P), a lower articulation (204a-b) between the shackle (200a) and the central casing (102b), and two reaction rods (170a) disposed on either side of the median plane (P), where each rod (170a) is articulated, at a front end, on the central casing (102b), and, at rear end, on the fitting (172).With such an arrangement, it is not necessary to have a rear attachment.
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
2025-02-12
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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