Patent ID: 7967243

Claim:
A configuration of engines ( 3 ) for aircraft located in a rear part of a fuselage ( 2 ) of said aircraft, the engines ( 3 ) being attached in a fixed manner by suspension pylons ( 5 ) to a structure of the aircraft, said structure comprising a torsion box ( 14 ) which traverses the fuselage ( 2 ) and is used to attach the suspension pylons ( 5 ), wherein said fuselage ( 2 ) comprises an opening ( 4 ) allowing passage of the suspension pylons ( 5 ) for the engines ( 3 ), said configuration further comprising a pivoting area ( 8 ), an actuator ( 7 ), and a fitting ( 6 ) through which the actuator ( 7 ) is attached to the suspension pylons ( 5 ) and to the torsion box ( 14 ) of said aircraft, such that an assembly formed by the actuator ( 7 ) and the fitting ( 6 ) allow balancing of the suspension pylon ( 5 ) and the engine ( 3 ) assembly of the aircraft through the pivoting area ( 8 ), thereby achieving controllable and optimal thrust vectoring of said aircraft for each flight phase.