An aircraft (101) comprising a plurality of rotors (109) and a propulsion system (120) for controlling propulsion of the aircraft (101). The propulsion system (120) comprises: a plurality of electric motors (122) including for each rotor (109) of the plurality of rotors, two or more electric motors coupled therewith, for driving the rotors; a propulsion motor control (130) comprising: a plurality of propulsion control units (132), wherein each propulsion control unit (132) is electrically coupled to a pair of electric motors of the plurality of electric motors (122), wherein one of the electric motors of the pair of electric motors is coupled with a first rotor and wherein the other of the electric motors of the pair of electric motors is coupled with a second rotor diagonally positioned relative to the first rotor, wherein each propulsion control unit (132) is configured to actuate a respective pair of the electric motors (122), and at least one battery (134a-f) electrically connected with at least one of the plurality of propulsion control units (132) of the propulsion motor control (130) and at least one electric motor of the plurality of electric motors (122), wherein the at least one battery (134a-f) is configured to provide power to the at least one propulsion control unit and the at least one electric motor; and a flight control (140) coupled with the plurality of propulsion control units (132), wherein the flight control (140) is configured to transmit a desired torque level to the plurality of propulsion control units (132). The propulsion motor control (130) is configured to actuate the plurality of electric motors (122) based on the desired torque level to drive each rotor (109) to provide propulsion of the aircraft (101).
REDUNDANT ELECTRIC PROPULSION SYSTEM
REDUNDANTES ELEKTRISCHES ANTRIEBSSYSTEM
SYSTÈME DE PROPULSION ÉLECTRIQUE REDONDANT
2023-03-29
Patent
Electronic Resource
English