Described herein is electrically powered aircraft comprising: a first propulsion system comprising a first propeller, a first drive shaft drivingly coupled to the first propeller, a first primary winding configured for rotating the first drive shaft, and a first redundant winding configured for rotating the first drive shaft; a second propulsion system comprising a second propeller, a second drive shaft drivingly coupled to the second propeller, a second primary winding configured for rotating the second drive shaft, and a second redundant winding configured for rotating the second drive shaft; a third propulsion system comprising a third propeller, a third drive shaft drivingly coupled to the third propeller, a third primary winding configured for rotating the third drive shaft, and a third redundant winding configured for rotating the third drive shaft; a fourth propulsion system comprising a fourth propeller, a fourth drive shaft drivingly coupled to the fourth propeller, a fourth primary winding configured for rotating the fourth drive shaft, and a fourth redundant winding configured for rotating the fourth drive shaft; a first battery; a second battery; a first power distribution circuit configured to transfer electrical power from the first battery to the first primary winding and the fourth primary winding; a second power distribution circuit configured to transfer electrical power from the second battery to the second primary winding and the third primary winding; a third power distribution circuit configured to transfer electrical power from the first battery to the second redundant winding and the third redundant winding; and a fourth power distribution circuit configured to transfer electrical power from the second battery to the first redundant winding and the fourth redundant winding.
Electrically powered propulsion systems for aircraft
2024-12-19
Patent
Electronic Resource
English