Rear propulsion system with lateral air inlets for an aircraft with such system

1. An auxiliary propulsive system for an aircraft, integrated within a tail cone of a fuselage, said propulsive system comprising an auxiliary jet engine and a device for supplying external air to said engine, said air supplying device including a lateral air intake on each one of the two sides of the fuselage ahead, along the displacement direction of the flying aircraft, of the auxiliary jet engine, in which air supplying device:

each lateral air intake is provided with closure means comprising a first position, called a closed position, where a continuity of an external surface of the fuselage is ensured, and at least a second position, called an opened position, where the auxiliary jet engine may be fed with air;

each lateral air intake is continued by an aerodynamic channel for supplying the auxiliary engine;

wherein the aerodynamic channels of the air intakes join to form a common channel behind, along the displacement direction of the flying aircraft, the lateral air intakes and in front of the auxiliary jet engine;

and wherein at least one flap, movable about a substantially vertical axis and substantially on the centerline of the fuselage is arranged in the common channel in a confluence area of the aerodynamic channels of the air intakes.

2. The propulsive system according to claim 1 , wherein the closure means are adjustable in order to take, for each lateral air intake, more or less opened positions during the operation of the auxiliary jet engine, and wherein each of said lateral air intake comprises a sufficiently opened position of the closure means to allow the auxiliary jet engine to be fed with air, to ensure the operation of said auxiliary jet engine in a propulsive engine operating mode, by one air intake in an opened position when the other air intake is in a closed position.

3. The propulsive system according to claim 1 wherein a management system for the auxiliary jet engine adjusts by means of actuators the positions of the closure means of the air intakes and the position of the at least one flap according to at least one of operating parameters of the auxiliary jet engine, operating parameters of the closure means, and aircraft flying conditions.

4. Propulsive system according to claim 1 wherein each lateral air intake includes a closure means shaped as a scoop, said scoop being movable between a closed position where the air intake is masked on the external surface of the fuselage and at least an opened position where external air is directed towards the aerodynamic channel associated with said air intake.

5. The propulsive system according to claim 4 , wherein the common channel is interdependent in a rear part of said common channel of a rear frame located within the tail cone ahead of the auxiliary jet engine.

6. An aircraft comprising a propulsive system according claim 1 .

7. The propulsive system according to claim 3 wherein the aircraft flying conditions includes non-symmetrical conditions of the aerodynamic flow along the fuselage.