A motor driven propulsor of an aircraft includes magnets disposed in fan shrouds of fan blades connected with a fan hub, a stator having individual conductive coils in a nacelle located radially outside of the fan hub, and a distributed inverter assembly having several inverter power stages and gate drivers, each of the inverter power stages coupled with a separate gate driver of the gate drivers and a separate coil of the coils in the stator. Each of the gate drivers is configured to individually control supply of direct current to the corresponding inverter power stage. Each of the inverter power stages is configured to convert the direct current supplied to the inverter power stage to an alternating current that is supplied to the corresponding coil in the stator to rotate the magnets and the fan blades around a center line of the fan hub for propelling the aircraft.

A motor driven propulsor of an aircraft includes magnets disposed in fan shrouds of fan blades connected with a fan hub, a stator having individual conductive coils in a nacelle located radially outside of the fan hub, and a distributed inverter assembly having several inverter power stages and gate drivers, each of the inverter power stages coupled with a separate gate driver of the gate drivers and a separate coil of the coils in the stator. Each of the gate drivers is configured to individually control supply of direct current to the corresponding inverter power stage. Each of the inverter power stages is configured to convert the direct current supplied to the inverter power stage to an alternating current that is supplied to the corresponding coil in the stator to rotate the magnets and the fan blades around a center line of the fan hub for propelling the aircraft.

An electrical system includes a cycloidal electric machine having a stator and an eccentric rotor. An airgap is defined between the stator and the rotor. The rotor moves with two degrees of freedom (2DOF), including rotating motion about the rotor axis and orbiting motion about the stator axis. A rotor constraint mechanism (RCM) constrains rotor motion to enable output torque to transfer to a coupled load in at least one of the 2DOF. The machine includes a structural element connected to or formed integrally with the rotor or stator that minimizes and substantially equalizes a size of the airgap around a circumference of the rotor. The element may be a crescent-shaped race of ferrous material coupled to a rotor shaft. The stator may include stator teeth, the rotor may include lobes, and the stator teeth and rotor lobes may have cycloid-profiled surfaces that form the structural element.

An electrical system includes a cycloidal electric machine having a stator and an eccentric rotor. An airgap is defined between the stator and the rotor. The rotor moves with two degrees of freedom (2DOF), including rotating motion about the rotor axis and orbiting motion about the stator axis. A rotor constraint mechanism (RCM) constrains rotor motion to enable output torque to transfer to a coupled load in at least one of the 2DOF. The machine includes a structural element connected to or formed integrally with the rotor or stator that minimizes and substantially equalizes a size of the airgap around a circumference of the rotor. The element may be a crescent-shaped race of ferrous material coupled to a rotor shaft. The stator may include stator teeth, the rotor may include lobes, and the stator teeth and rotor lobes may have cycloid-profiled surfaces that form the structural element.

A circuit includes a bandpass filter and a self-tracking circuit. The bandpass filter has a first input node configured to receive an input square wave signal and an output node configured to provide an output sine wave signal. The bandpass filter includes a first binary-weighted programmable resistor array. The self-tracking circuit includes a second input node coupled to the output node. The self-tracking circuit includes a counter, and the counter includes an output node coupled to the first binary weighted programmable resistor array.

A circuit includes a bandpass filter and a self-tracking circuit. The bandpass filter has a first input node configured to receive an input square wave signal and an output node configured to provide an output sine wave signal. The bandpass filter includes a first binary-weighted programmable resistor array. The self-tracking circuit includes a second input node coupled to the output node. The self-tracking circuit includes a counter, and the counter includes an output node coupled to the first binary weighted programmable resistor array.

A power conversion device includes a first inverter connected to first ends of windings of each phase of a motor, a second inverter connected to second ends of the windings of each phase, and a first switching circuit including at least one of a first switch to switch between whether the first inverter and a power supply are connected or disconnected and a second switch to switch between whether the first inverter and a ground are connected or disconnected. The power conversion device has a first operation mode when the motor is driven at a low speed, and a second operation mode when the motor is driven at a high speed.

A power conversion device includes a first inverter connected to first ends of windings of each phase of a motor, a second inverter connected to second ends of the windings of each phase, and a first switching circuit including at least one of a first switch to switch between whether the first inverter and a power supply are connected or disconnected and a second switch to switch between whether the first inverter and a ground are connected or disconnected. The power conversion device has a first operation mode when the motor is driven at a low speed, and a second operation mode when the motor is driven at a high speed.

A motor driven propulsor of an aircraft includes magnets disposed in fan shrouds of fan blades connected with a fan hub, a stator having individual conductive coils in a nacelle located radially outside of the fan hub, and a distributed inverter assembly having several inverter power stages and gate drivers, each of the inverter power stages coupled with a separate gate driver of the gate drivers and a separate coil of the coils in the stator. Each of the gate drivers is configured to individually control supply of direct current to the corresponding inverter power stage. Each of the inverter power stages is configured to convert the direct current supplied to the inverter power stage to an alternating current that is supplied to the corresponding coil in the stator to rotate the magnets and the fan blades around a center line of the fan hub for propelling the aircraft.

A motor driven propulsor of an aircraft includes magnets disposed in fan shrouds of fan blades connected with a fan hub, a stator having individual conductive coils in a nacelle located radially outside of the fan hub, and a distributed inverter assembly having several inverter power stages and gate drivers, each of the inverter power stages coupled with a separate gate driver of the gate drivers and a separate coil of the coils in the stator. Each of the gate drivers is configured to individually control supply of direct current to the corresponding inverter power stage. Each of the inverter power stages is configured to convert the direct current supplied to the inverter power stage to an alternating current that is supplied to the corresponding coil in the stator to rotate the magnets and the fan blades around a center line of the fan hub for propelling the aircraft.