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 a strut, comprising a thrust resistance device ( 20 ) comprising a spreader beam ( 28 ) provided with two lateral lower ends ( 32 a ) placed such that a horizontal plane passes through them and through a longitudinal axis of the engine. Moreover, the device ( 20 ) is also fitted with two fittings ( 44 ) each comprising a forward end ( 44 a ) through which the said horizontal plane also passes and fixed to a forward part of a central casing ( 22 ), and an aft end ( 44 b ) connected to one of the ends ( 32 a ). Furthermore, the spreader beam is connected to the forward mount and to the rigid structure through its upper end ( 30 b ).
1. Mounting system ( 1 ) inserted between an aircraft engine ( 2 ) and a rigid structure ( 4 ) of an attachment strut ( 6 ) fixed under a wing ( 8 ) of an aircraft, the system including a forward mount ( 16 ), an aft mount ( 18 ), and a device ( 20 ) for resisting thrusts generated by the engine ( 2 ), characterized in that the said thrust resistance device ( 20 ) comprises a spreader beam ( 28 ) provided with an upper arm ( 30 ) and two lateral lower arms ( 32 ), the upper and lateral lower arms ( 30 , 32 ) being fixed and fitted with an upper end ( 30 b ) and two lateral lower ends ( 32 a ) of the spreader beam ( 28 ), the two lateral lower ends ( 32 a ) being placed such that a horizontal plane passes through them and through a longitudinal axis ( 5 ) of the engine ( 2 ), the thrust resistance device ( 20 ) also being fitted with two fittings ( 44 ) on each side of the engine ( 2 ) and each comprising a forward end ( 44 a ) through which the horizontal plane passing through the longitudinal axis ( 5 ) of the engine ( 2 ) also passes, and fixed to a forward part of a central casing ( 22 ) of the engine, and an aft end ( 44 b ) connected to one of the two lateral lower ends ( 32 a ) of the spreader beam ( 28 ), and in that the said spreader beam ( 28 ) is also connected to the forward mount ( 16 ) of the mounting system, and to the rigid structure ( 4 ) of the attachment strut ( 6 ) through its upper end ( 30 b ).
2. Mounting system ( 1 ) according to claim 1 , characterized in that the said spreader beam ( 28 ) is connected to the forward mount ( 16 ) through at least one swivel pin ( 34 ) oriented along a transverse direction (Y) of the aircraft.
3. Mounting system ( 1 ) according to claim 2 , characterized in that each swivel pin ( 34 ) passes through a double headed end ( 17 a ) of a forward mount body ( 17 ), and a lower end ( 30 a ) of the upper arm ( 30 ) of the said spreader beam ( 28 ).
4. Mounting system ( 1 ) according to any one of the above claims, characterized in that the upper end ( 30 b ) of the upper arm ( 30 ) is connected to the rigid structure ( 4 ) of the attachment strut ( 6 ) through a connecting rod ( 36 ).
5. Mounting system ( 1 ) according to claim 4 , characterized in that the said connecting rod ( 36 ) is oriented approximately along a longitudinal direction (X) of the aircraft, and in that an aft end ( 36 b ) of the said connecting rod ( 36 ) cooperates with a forward part of an upper stringer ( 10 ) of the rigid structure ( 4 ) of the attachment strut ( 6 ).
6. Mounting system ( 1 ) according to claim 5 , characterized in that the upper end ( 30 b ) of the upper arm ( 30 ) is connected to a forward end ( 36 a ) of the said connecting rod ( 36 ) through at least one swivel pin ( 38 ) oriented along a transverse direction (Y) of the aircraft, and in that a fitting ( 40 ) fixed to the forward part of the upper stringer ( 10 ) of the rigid structure ( 4 ) of the attachment strut ( 6 ) is connected to the aft end ( 36 b ) of the said connecting rod ( 36 ) through at least one swivel pin ( 42 ) oriented along this same transverse direction (Y) of the aircraft.
7. Mounting system ( 1 ) according to claim 6 , characterized in that the upper end ( 30 b ) of the upper arm ( 30 ) and the said fitting ( 40 ) are double headed.
8. Mounting system ( 1 ) according to claim 1 , characterized in that each aft end ( 44 b ) of the two fittings ( 44 ) fixed to the forward part of the central casing ( 22 ) of the engine ( 2 ) is connected to one of the two lateral lower ends ( 32 a ) of the spreader beam ( 28 ) using a connecting rod ( 46 ).
9. Mounting system ( 1 ) according to claim 1 , characterized in that the upper arm ( 30 ) of the spreader beam ( 28 ) is straight and is oriented along a vertical direction (Z) of the aircraft, and in that the two lateral lower arms ( 32 ) combined form an approximate half-ring.
10. Mounting system ( 1 ) according to claim 1 , characterized in that the said system comprises a forward mount ( 16 ) fixed to the forward part of the central casing ( 22 ) of the engine ( 2 ) and a forward end of a pyramid ( 14 ) forming a forward part of the rigid structure ( 4 ) of the strut ( 6 ), and in that the said system also comprises an aft mount ( 18 ) fixed to an aft part of the central casing ( 22 ) of the engine ( 2 ) and the rigid structure ( 4 ) of the strut ( 6 ).
11. Mounting system ( 1 ) according to claim 10 , characterized in that the upper arm ( 30 ) of the spreader beam ( 28 ) is arranged so as to pass through the said pyramid ( 14 ) of the rigid structure ( 4 ) of the strut ( 6 ).
12. Attachment strut ( 6 ) of an aircraft engine ( 2 ) under a wing ( 8 ) of an aircraft, the said strut being provided with a mounting system ( 1 ) inserted between the said engine ( 2 ) and a rigid structure ( 4 ) of this strut, characterized in that the said mounting system ( 1 ) is a system according to claim 1 .