Optimized configuration of engines for aircraft

Details Optimized configuration of engines for aircraft Optimized configuration of engines for aircraft

B - Operations, Transporting

64

D

B64D 27/14 (2006.01) B64C 15/12 (2006.01)

Patent

CA 2710065

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

La présente invention porte sur une configuration de moteurs (3) pour avion située dans la partie arrière du fuselage (2) dudit avion, les moteurs (3) étant fixés d'une manière fixe par des pylônes (5) à la structure de l'avion, ladite structure comprenant un caisson de torsion (14) qui traverse le fuselage (2) et est utilisé pour fixer les pylônes (5), le fuselage (2) comprenant une ouverture (4) permettant le passage des pylônes de suspension (5) pour les moteurs (3), ladite configuration comprenant en outre une zone de pivotement (8), un actionneur (7) et une fixation (6) grâce à laquelle l'actionneur (7) est fixé aux pylônes de suspension (5) et au caisson de torsion (14) de l'avion, de telle sorte que l'ensemble formé par l'actionneur (7) et la fixation (6) permet le balancement de l'ensemble pylône (5) et moteur (3) de l'avion dans la zone de pivotement (8), ce qui permet ainsi d'obtenir une orientation de poussée contrôlable et optimale de l'avion pour chaque phase de vol.

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