Aircraft having a reduced environmental impact
View Patent ↗An aircraft having a propeller engine mounted at the rear of the aircraft, on the back thereof, such that the axis of the engine is parallel to the longitudinal axis of the aircraft. The aircraft has a cell, the rear part of which comprises a horizontal empennage and two vertical empennages, positioned one at each end of said horizontal empennage. The propeller is positioned vertically in line with the rear part of the cell, and the rear part of the cell forms a lateral and downward barrier, on each side of a plane of the propeller, that screens an acoustic intensity equal to approximately−5 dB with respect to a maximum acoustic intensity emitted by the engine.
1. A commercial aircraft with reduced environmental impact, having a longitudinal axis and comprising:
a fuselage including a cell at a rear portion of the fuselage;
at least one engine comprising two coaxial contra-rotating propellers, with the at least one engine being mounted at the cell on the fuselage, and the at least one engine having an axis parallel to said longitudinal axis of the aircraft;
a horizontal empennage at a rear part of the cell;
wings mounted on the fuselage, forward of said cell; and
two vertical empennages at the cell, wherein the two vertical empennages comprise control surfaces and are positioned such that each vertical empennage is located at each end of said horizontal empennage, and both of said propellers are positioned vertically in line with said rear part of the cell, wherein the vertical and horizontal empennages are configured to form a lateral and downward noise barrier screen on each side of the at least one engine and inside a channel formed by the horizontal and vertical empennages, which noise barrier screen provides an acoustic intensity at the engine equal to at least −5 dB with respect to a maximum acoustic intensity emitted by said engine.
2. The aircraft as claimed in claim 1 , wherein said propellers are positioned behind said engine and exert thrust on said aircraft.
3. The aircraft as claimed in claim 1 , wherein said propellers do not have any peripheral cowling.
4. The aircraft as claimed in claim 1 , wherein the shortest distance between the end of the propellers and said rear part of the cell is at least equal to 10% of the diameter of said propellers.
5. The aircraft as claimed in claim 1 , further comprising at least two turbine engines, each of the at least two turbine engines being carried symmetrically by the wings.
6. The aircraft as claimed in claim 1 , further comprising two propeller engines mounted on the rear portion of the fuselage, positioned one beside the other, and having parallel axes.
7. The aircraft as claimed in claim 6 , wherein the distance between the ends of the propellers of said engines is at least 60 cm.
8. The aircraft as claimed in claim 6 , wherein the wings do not bear any engine.