| CPC B64C 13/507 (2018.01) | 15 Claims |

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1. An electromechanical drive system to control a rotating shaft of an aircraft, said drive system comprising:
a transmission shaft of a transmission assembly connectable to a mechanical operating system of said aircraft,
an electric machine configured to impart or receive a torque from said transmission shaft,
a two-way transmission operatively interposed between said transmission shaft and said electric machine,
sensor means configured to detect a physical quantity relating to the operation of said transmission shaft,
an electronic unit electronically connectable to operating systems of said aircraft, to said electric machine and to said sensor means, said electronic unit comprising processing means configured to receive data from said operating systems, said electric machine and said sensor means for controlling said electric machine,
a clutch assembly operatively interposed between said transmission shaft and said two-way transmission,
wherein said two-way transmission is configured, in any direction of rotation of said transmission shaft, to allow the passage of torque:
(i) in a first operation mode, wherein said torque is supplied by said electric machine to said transmission shaft, exclusively between said electric machine and said transmission shaft; or
(ii) in a second operation mode, wherein said torque is supplied by said transmission shaft to said electric machine between said transmission shaft, said clutch assembly and said electric machine.
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