Patent ID: 8196861
Filing Date: 2012-06-12
Classification: B64D

Abstract:
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.