| 摘要 |
This invention relates to a mounting system ( 1 ) inserted between an aircraft engine and a rigid structure of an attachment strut, the system particularly comprising a thrust resistance device ( 20 ). The thrust resistance device ( 20 ) comprises two lateral actuators ( 30 ) each provided with a rod ( 34 ) in which a forward end ( 34 b) is a piston located inside a chamber ( 38 ) of a central casing ( 22 ) of the engine, the chamber ( 38 ) comprising a forward compartment ( 40 ) and an aft compartment ( 42 ). Moreover, the thrust resistance device ( 20 ) comprises a device ( 32 ) including a piston ( 48 ) fixed to the forward mount ( 16 ) and located inside a chamber ( 50 ) fixed to the central casing, the chamber ( 50 ) comprising a forward compartment ( 52 ) and an aft compartment ( 54 ), the forward compartment ( 52 ) of the chamber ( 50 ) being hydraulically connected to the aft compartments ( 42 ) of the actuators ( 30 ).
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