Patent ID: 8152095
Filing Date: 2012-04-10
Classification: B64C,B64D,Y02T

Abstract:
1. An aircraft, having: a fuselage, a wing structure fixed to the fuselage, at least one horizontal stabilizer rearward of the wing, at least two vertical stabilizers, substantially vertical, fixed to the fuselage rearward of the wing, and at least two propulsion jet engines, wherein: the fuselage has a cylindrical fuselage section followed rearward by a fuselage section, the cross section of which is progressively flattened to have a low thickness fuselage rear end and the width of which is substantially those of the cylindrical section; the wing is fixed to the fuselage on the top of said fuselage; the at least two propulsion jet engines are mounted side by side on top of the fuselage, rearward of the wing, inside a cowling structure extended longitudinally above the fuselage between, in front, air inlet openings located above the fuselage at the location of wing root chords, and, on the rear, exhaust nozzle outlets located above the fuselage and forwardly of the fuselage rear end, the width of said fuselage being at least the width of said cowling structure; the cowling structure has lateral walls, substantially vertical, one on each outer side of the cowling structure, which are substantially in aerodynamic continuity with two vertical stabilizers of the at least two vertical stabilizers, and has a substantially flat horizontal wall joining the lateral walls extending longitudinally between the air inlet openings and the exhaust nozzle outlets, said exhaust nozzle outlets being located between said two vertical stabilizers and located forward of the trailing edges of said two vertical stabilizers and aft of the leading edges of said two vertical stabilizers.