Electrical power supply device for powering at least one piece of equipment of an aircraft rotor, and an aircraft

1. An electrical power supply device for powering at least one piece of equipment of an aircraft rotor driven by a mast, said device comprising a removable pole suitable for being reversibly secured to said mast, said pole having a rotary casing provided with fastener means for fastening to said mast, and a non-rotary casing secured to link means suitable for being fastened to a reference member of said aircraft, wherein said pole comprises:

a non-rotary converter fastened to the non-rotary casing and provided with an inlet suitable for being fed with electricity coming from an electricity network of said aircraft, said non-rotary converter being an electrical converter that generates AC at a frequency higher than one kilohertz from said electricity fed to the inlet; and

a rotary transformer incorporated in the pole, said transformer having a primary member secured to the non-rotary casing and a secondary member secured to the rotary casing, the primary member being connected to the non-rotary converter to receive said AC, and the secondary member being suitable for electrically powering equipment of a rotor.

2. A device according to claim 1 , wherein said link means comprise firstly coupling means allowing for misalignment between the pole and the reference member, and secondly a jaw clutch for fastening the pole to said reference member.

3. A device according to claim 1 , wherein said non-rotary converter is arranged inside said non-rotary casing.

4. A device according to claim 1 , wherein said pole is provided with a rotary converter fastened to said rotary casing, the rotary converter being connected to said transformer and being provided with at least one outlet for electrically powering equipment of a rotor.

5. A device according to claim 4 , wherein said rotary converter is arranged inside said rotary casing.

6. A device according to claim 1 , wherein said primary member and said secondary member are coaxial, said secondary member surrounding said primary member at least in part, an annular airgap (e 1 ) separating said secondary member from said primary member.

7. A device according to claim 1 , wherein said primary member and said secondary member are coaxial, said primary member surrounding said secondary member at least in part, an annular airgap (e 1 ) separating said secondary member from said primary member.

8. A device according to claim 1 , wherein said primary member and said secondary member are arranged in succession one after another along an axis of rotation (AX) of the rotary casing, a plane airgap (e 2 ) separating said secondary member from said primary member.

9. A device according to claim 1 , wherein said transformer includes a primary member and a secondary member provided in redundant manner.

10. A device according to claim 1 , wherein said transformer is a single-phase transformer.

11. A device according to claim 1 , wherein said transformer is a high frequency transformer operating over a frequency range extending from 1 kHz to 500 kHz.

12. A device according to claim 1 , wherein said pole includes transmission means for transmitting electrical signals by signal modulation.

13. A device according to claim 12 , wherein said signal transmission means includes a non-rotary modulator and a non-rotary demodulator arranged upstream from the transformer and co-operating with a non-rotary interface, together with a rotary modulator and a rotary demodulator arranged downstream from the transformer and co-operating with a rotary interface.

14. An aircraft having an airframe and a non-rotary reference member, the airframe carrying a rotary rotor driven by a mast, said rotor having at least one piece of electrical equipment, wherein the aircraft includes an electrical power supply device according to claim 1 for electrically powering said equipment.