Mounting system inserted between an aircraft engine and a rigid structure of an attachment strut fixed under a wing of this aircraft
View Patent ↗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 ).
1. Mounting system inserted between an aircraft engine and a rigid structure of an attachment strut fixed under a wing of this aircraft, the system including a forward mount, an aft mount, and a device for resisting thrusts generated by the engine, wherein: said device comprises two lateral actuators arranged one on each side of the engine, each actuator being provided with a rod in which an aft end is connected to one of said forward and aft mounts and for which one forward end is a piston located inside a chamber fixed to a forward part of a central casing of the engine, said chamber comprising a forward compartment and an aft compartment separated by said piston;
and wherein said thrust resistance device also comprises a hydraulic piston device comprising a piston fixed to the forward mount and located inside a chamber fixed to said forward part of the central casing of the engine, said chamber comprising a forward compartment and an aft compartment separated by said piston, said forward compartment of said chamber of the hydraulic piston device being hydraulically connected to said aft compartments of the lateral actuators.
2. Mounting system according to claim 1 , wherein said aft compartment of said chamber of the hydraulic piston device is hydraulically connected to said forward compartments of the lateral actuators.
3. Mounting system according to claim 1 or 2 , wherein said forward compartments of the two lateral actuators are hydraulically connected, and said aft compartments of these two lateral actuators are also hydraulically connected.
4. Mounting system according to claim 1 , wherein said chambers are formed inside the forward part of the central casing of the engine.
5. Mounting system according to claim 1 , wherein the aft end of each of the two rods is connected to said forward mount.
6. Mounting system according to claim 1 , wherein said system comprises a forward mount fixed to the forward part of the central casing of the engine, and said system also comprises an aft mount fixed to one aft part of the central casing of the engine and to the rigid structure of the strut.
7. Mounting system according to claim 6 , wherein the forward mount comprises a ball joint mounted on a hinge pin oriented along a longitudinal direction (X) of the aircraft, and the piston of the hydraulic piston device is fixed to this hinge pin, and arranged to be approximately perpendicular to this longitudinal direction (X).
8. Mounting system according to claim 1 , wherein the forward compartment of the chamber of the hydraulic piston device is hydraulically connected only to the aft compartments of the lateral actuators.
9. Mounting system according to claim 1 , wherein said forward compartment of the hydraulic piston device is also hydraulically connected to a high pressure hydraulic supply and is provided with at least one leak orifice for which access can be enabled/disabled by a device fixed to said piston, as a function of the hydraulic pressure inside the forward compartment, and as a function of thrust forces generated by the engine.
10. Mounting system according to claim 9 , wherein said aft compartment of the hydraulic piston device is also hydraulically connected to a high pressure hydraulic supply and is provided with at least one leak orifice for which access can be enabled/disabled by a device fixed to said piston, as a function of the hydraulic pressure inside the aft compartment, and as a function of the reverse thrusts generated by the engine.