Aircraft comprising a propulsion assembly including a pair of propellers at the rear of the fuselage
The present invention relates to an aircraft comprising a fuselage ( 1 ), a propulsion unit ( 7 ) at the rear tip of the fuselage and at least two engines ( 3, 5 ) each driving an engine shaft ( 32, 52 ), the propulsion unit including at least one propeller ( 71, 73 ) driven mechanically by the engine shafts ( 32, 52 ), characterized in that the propulsion unit ( 7 ) includes two propellers ( 71, 73 ), each of the propellers being driven by a propeller shaft ( 72, 74 ), the two propeller shafts being driven by the engine shafts ( 32, 52 ) via a first differential epicyclic gear train ( 40 ). Specifically, the input of the first differential gear train ( 40 ) is connected to the output of a second differential epicyclic gear train ( 60 ), the second differential gear train ( 60 ) including two inputs ( 61 c 2, 62 c 2 ), each of said two inputs being connected mechanically to one of said engine shafts ( 32, 52 ).
1. Aircraft comprising:
a fuselage, a propulsion assembly at a tail cone of the fuselage and at least two motors each driving a motor shaft,
the propulsion assembly comprising at least one propeller driven mechanically by the motor shafts,
wherein the propulsion assembly comprises a first, propeller and a second propeller,
each of the first and second propellers being driven respectively by a first propeller shaft and a second propeller shaft,
said first and second propeller shafts being driven by the motor shafts by a transmission mechanism comprising a first differential epicyclic gear train and a second differential epicyclic gear train,
the first differential epicyclic gear train comprising a first input which is connected to an output of the second differential epicyclic gear train and the second differential epicyclic gear train comprising two inputs, each of said two inputs of said second differential epicyclic gear train being mechanically connected to one of said motor shafts.
2. The aircraft according to claim 1 , wherein the first differential epicyclic gear train comprises the first input and two outputs, the first input being mechanically connected to the two motor shafts and each of said two outputs driving one of the first and second propeller shafts.
3. The aircraft according to claim 1 , wherein the axis of rotation of the first input of the first differential epicyclic gear train is coaxial with an axis of rotation of an output of the second differential epicyclic gear train.
4. The aircraft according claim 1 , wherein the second differential epicyclic gear train comprises a planet carrier forming an output of the second differential epicyclic gear train, planet gears of the planet carrier meshing on two opposite rings which are coaxial with the planet carrier, the two rings each being driven by one of the motor shafts.
5. The aircraft according to claim 1 , wherein the motor shafts are arranged radially with respect to an axis of rotation of the planet carrier.
6. The aircraft according to claim 1 , wherein the motors are motors with each having an air input ducts spaced apart from the fuselage.
7. The aircraft according to claim 2 , wherein the first differential epicyclic gear train comprises a sun gear at the first input, and a ring and a planet carrier at said two outputs.
8. The aircraft according to claim 5 , wherein the planet gears of the second differential epicyclic gear train have a radial axis of rotation with respect to an axis of rotation of the planet carrier.
9. The aircraft according to claim 6 , wherein the motors are configured to propel the aircraft in the event of failure of the propulsion assembly.