Nacelle for an aircraft engine assembly comprising at least one jointed nacelle cowling at its front end

1. An aircraft comprising at least one aircraft engine assembly, the at least one aircraft engine assembly comprising:

a turbine engine comprising:

an engine housing;

a gas generator; and

a receiver with a pair of open, counter-rotating propellers, wherein the receiver is arranged at a rear of the gas generator; and

a nacelle arranged about the turbine engine, the nacelle comprising:

a fixed nacelle structure;

an air intake located at a front of the nacelle in a direction of a longitudinal axis of the assembly; and

one or more movable cowlings jointed on the fixed nacelle structure and extending, in the direction of the longitudinal axis of the assembly, to cover an entire length, in the direction of the longitudinal axis of the assembly, between the air intake and a front edge of the receiver,

wherein the one or more movable cowlings are jointed at a front end thereof, respectively, on the fixed nacelle structure so that, upon closing one of the one or more movable cowlings, a rear end thereof moves rearwardly and radially inside,

wherein the at least one aircraft engine assembly is mounted on a rear portion of a fuselage of an aircraft.

2. The aircraft according to claim 1 , wherein the one or more movable cowlings are arranged to occupy an entire aerodynamic surface between the air intake and the receiver.

3. The aircraft according to claim 1 , wherein the one or more movable cowlings are jointed at the front end thereof on the fixed nacelle structure along a joint axis in a transverse plane of the nacelle.

4. The aircraft according to claim 1 , wherein the one or more movable cowlings are jointed at the front end thereof on the fixed nacelle structure along a joint axis oriented tangentially to the nacelle.

5. The aircraft according to claim 1 , wherein the one or more movable cowlings have an axial length that is between and including 30% and 90% of a total axial length of the nacelle.

6. The aircraft according to claim 1 , wherein the one or more movable cowlings each cover at least a part of the gas generator.

7. The aircraft according to claim 1 , wherein the one or more movable cowlings are arranged to cover an entire circumference of an aerodynamic surface between the air intake and the receiver.

8. The aircraft of claim 1 , wherein the one or more movable cowlings comprise a plurality of movable cowlings.

9. The aircraft according to claim 8 , wherein the plurality of movable cowlings comprise at least two movable cowlings, which are distributed about the longitudinal axis of the assembly and follow one another in a circumferential direction of the nacelle.

10. The aircraft according to claim 8 , wherein the plurality of movable cowlings comprise at least four movable cowlings, which are distributed about the longitudinal axis of the assembly and follow one another in a circumferential direction of the nacelle.

11. The aircraft according to claim 8 , wherein the plurality of movable cowlings comprise an upper cowling and a lower cowling, wherein an interface between the upper and lower cowlings is located in a plane that is perpendicular to a height of the assembly.

12. The aircraft according to claim 1 , comprising an annular space defined between the engine housing and an internal surface of the one or more movable cowlings.

13. The aircraft according to claim 12 , wherein the annular space is configured for housing equipment for the engine assembly, wherein movement of at least one of the one or more movable cowlings to an open position allows ground maintenance to be performed on the equipment for the engine assembly.