Wheel motorizing system, notably for an aircraft wheel

1. A wheel motorization system useable for an aircraft to run along a ground surface, the system comprising:

an electric motor;

a driver securable to a hub of a wheel of the aircraft; and

a clutch connecting an output shaft of the motor to the driver via a reducer,

wherein the clutch includes a freewheel structured to allow transmission of a rotational torque only in a first torque transmission direction when the aircraft is travelling forwards,

wherein the freewheel includes non-return elements mounted between an inner ring and an outer ring of the clutch, and

wherein the clutch includes a lock that locks a freewheeling function of the freewheel, the lock including:

a locking bell that is coaxial with an axis of the freewheel,

peripheral driving claws extending from a periphery of the locking bell, the peripheral driving claws being structured to cooperate with the outer ring, and

central driving claws positioned at a central region of the locking bell, the central driving claws being structured to cooperate with the inner ring.

2. The wheel motorization system according to claim 1 , wherein the lock is manually or electrically actuatable.

3. The wheel motorization system according to claim 1 , wherein the reducer includes a drive pinion attached to the output shaft of the motor, and wherein the reducer is structured to engage with an intermediate shaft.

4. The wheel motorization system according to claim 1 , wherein the reducer includes at least two reduction stages.

5. The wheel motorization system according to claim 4 , wherein the reducer includes two reduction stages, and the freewheel is disposed between the two reduction stages.

6. The wheel motorization system according to claim 1 , wherein the reducer includes first, second, and third reduction stages.

7. The wheel motorization system according to claim 6 , wherein:

the first reduction stage corresponds to an engagement of a drive pinion and a first toothed wheel attached to a first intermediate shaft,

the second reduction stage corresponds to an engagement of a first reduction pinion attached to the first intermediate shaft and a second toothed wheel attached to a second intermediate shaft, and

the third reduction stage corresponds to an engagement of a second reduction pinion attached to the second intermediate shaft and the driver.

8. The wheel motorization system according to claim 7 , wherein the clutch is disposed between the second and third reduction stages.

9. The wheel motorization system according to claim 8 ,

wherein the peripheral driving claws of the locking bell are spaced apart from one another and structured to cooperate with first recesses located on the second toothed wheel, the first recesses being complementary in shape to the peripheral driving claws, and

wherein the central driving claws of the locking bell are spaced apart from one another and structured to cooperate with second recesses located at an end of the second intermediate shaft, the second recesses being complementary in shape to the central driving claws.

10. The wheel motorization system according to claim 7 , wherein the first and second intermediate shafts are arranged parallel to an axis of the hub of the wheel.

11. The wheel motorization system according to claim 1 , wherein the driver is a toothed gear ring.

12. The wheel motorization system according to claim 1 , further comprising a mechanical overtorque protection structure to protect against an overtorque decoupling of the driver from the hub of the wheel when a torque transmitted by the driver to the hub of the wheel is greater than a threshold value.

13. An aircraft comprising at least one motorized wheel, wherein each motorized wheel includes:

a wheel; and

a wheel motorization system that includes:

an electric motor,

a driver securable to a hub of the wheel, and

a clutch connecting an output shaft of the motor to the driver via a reducer,

wherein the clutch includes a freewheel structured to allow transmission of a rotational torque only in a first torque transmission direction when the aircraft is travelling forwards,

wherein the freewheel includes non-return elements mounted between an inner ring and an outer ring of the clutch, and

wherein the clutch includes a lock that locks a freewheeling function of the freewheel, the lock including:

a locking bell that is coaxial with an axis of the freewheel,

peripheral driving claws extending from a periphery of the locking bell, the peripheral driving claws being structured to cooperate with the outer ring, and

central driving claws positioned at a central region of the locking bell, the central driving claws being structured to cooperate with the inner ring.

14. The aircraft according to claim 13 , wherein the aircraft includes two motorized wheels corresponding to the at least one motorized wheel, the two motorized wheels forming a part of a landing gear system of the aircraft.

15. The aircraft according to claim 13 , wherein the aircraft is a helicopter.

16. The wheel motorization system according to claim 8 ,

wherein the hub of the second toothed wheel acts as the outer ring for the non-return elements, and

wherein the second intermediate shaft acts as the inner ring for the non-return elements.