A method for operating an eVTOL multirotor aircraft having distributed actuators activated by controllers that each determines an associated manipulated variable signal at least for a subset of actuators and provides it for the relevant actuator. The method provides that for an actuator: i) assigning a different priority ranking for each controller; ii) determining, by way of a given controller having a given priority ranking, at least one manipulated variable signal for the actuator and transmitting the signal identified by the given priority ranking to the relevant actuator and to a controller having a successive priority ranking; iii) receiving, via a given controller having a given priority ranking, manipulated variable signals from controllers having higher priority ranking and relaying these signals to the actuator and to a controller having a successive priority ranking; and iv) activating the actuator using the manipulated variable signal identified by the highest priority ranking.

An electric propulsion system for use with a mast defining an axis of rotation and one or more rotor blades which rotate about the axis of rotation, includes a yoke assembly, electric motor, motor support housing, and overrunning clutch. The yoke assembly is rotatable with respect to the mast, and configured to support one or more of the rotor blades. The motor includes a motor-stator and a motor-rotor, and is arranged circumferentially around the mast. The housing circumferentially surrounds the mast and includes a rotatable portion attached to and rotatable with the yoke assembly. The overrunning clutch includes an inner hub rotatable with the motor-rotor, and an outer hub rotatable with the rotatable portion of the housing. The overrunning clutch is configured to transfer torque from the motor to the yoke assembly in a drive mode, and configured to disengage the yoke assembly from the motor in an overrunning mode.

A system for an aircraft includes a tiltable proprotor that is tiltable between a lift position for providing lift for the aircraft and a forward flight position for providing forward propulsion for the aircraft is provided. The system includes at least one actuator for adjusting a tilt angle of the tiltable proprotor; and at least one passive damper connected to the tiltable proprotor and configured to limit a rate of change of the tilt angle of the tiltable proprotor.

An apparatus for facilitating propulsion of a vehicle. The apparatus comprises a housing with an interior space, an inlet, and an outlet, a propulsion mechanism, and a gimbal. The propulsion mechanism is disposed in the interior space and comprises and an upper rotor and a lower rotor rotatably mounted on a first portion and a second portion of a spindle. The upper rotor rotates in a first direction and the lower rotor rotates in a second direction opposite to the first direction. Upper rotor blades have a first blade pitch and lower rotor blades have a second blade pitch opposite to the first blade pitch. The rotating of the upper rotor and the lower rotor creates a fluid flow from the inlet to the outlet for generating a directional thrust. The gimbal rotatably attaches the propulsion mechanism to the housing. The housing is rotatable for vectoring the directional thrust.

An apparatus for facilitating propulsion of a vehicle. The apparatus comprises a housing with an interior space, an inlet, and an outlet, a propulsion mechanism, and a gimbal. The propulsion mechanism is disposed in the interior space and comprises and an upper rotor and a lower rotor rotatably mounted on a first portion and a second portion of a spindle. The upper rotor rotates in a first direction and the lower rotor rotates in a second direction opposite to the first direction. Upper rotor blades have a first blade pitch and lower rotor blades have a second blade pitch opposite to the first blade pitch. The rotating of the upper rotor and the lower rotor creates a fluid flow from the inlet to the outlet for generating a directional thrust. The gimbal rotatably attaches the propulsion mechanism to the housing. The housing is rotatable for vectoring the directional thrust.

A coaxial direct drive system includes at least two prime movers mounted to a motor carrier member about a common axis. Each prime mover includes a stator affixed to the motor carrier member, and each prime mover further includes a rotor which can rotate about the common axis. Each rotor has a driven member affixed to it, which rotates with the respective rotor, and to which driven objects, such as aero foil blades, etc. can be affixed. The motor carrier member can be directly mounted to an object to be propelled by the coaxial direct drive system, or can be hollow to receive a support mast which is mounted to the object to be driven. The driven objects can have different rotational senses, such that when the prime movers counter rotate, the driven objects generate trust in the same direction.

Modular heavy-duty drive train comprising a plurality of drive modules and an output element, wherein each drive module comprises at least two electric drive units for driving a first summing gear and one load transmission device, wherein the at least two electric drive units drive the load transmission device of the respective drive module via the first summing gear, and wherein the load transmission devices are each coupled to the output element for parallel transmission of the drive power from the plurality of drive modules to the output element.

Modular heavy-duty drive train comprising a plurality of drive modules and an output element, wherein each drive module comprises at least two electric drive units for driving a first summing gear and one load transmission device, wherein the at least two electric drive units drive the load transmission device of the respective drive module via the first summing gear, and wherein the load transmission devices are each coupled to the output element for parallel transmission of the drive power from the plurality of drive modules to the output element.

A system for flight control in electric aircraft includes a flight controller configured to provide an initial vehicle torque signal including a plurality of attitude commands. The system includes a mixer configured to receive the initial vehicle torque signal and a vehicle torque limit, receive prioritization data including a prioritization datum corresponding to each of the plurality of attitude command, determine a plurality of modified attitude commands as a function of the vehicle torque limit, the attitude commands, and the prioritization data, generate, as a function of modified attitude commands, an output torque command including the initial vehicle torque signal adjusted as a function of the vehicle torque limit, generate, as a function of the output torque command, a remaining vehicle torque. The system includes a display, wherein the display is configured to present, to a user, the remaining vehicle torque and the output torque command.

An assembly for a propulsion system of an aircraft includes an electric motor, a first gearbox module, a second gearbox module, and a propeller. The electric motor includes a rotor. The rotor includes a first axial end and a second axial end. The first gearbox module includes a first gear assembly. The first gear assembly is coupled to the first axial end. The second gearbox module includes a second gear assembly. The second gear assembly is coupled to the second axial end. The propeller is coupled to the first gear assembly. The first gear assembly is configured to drive rotation of the propeller in response to rotation of the rotor.