An auxiliary power unit (APU) generator system for an APU can include a doubly-fed induction generator (DFIG) configured to be operatively connected to an APU to be turned by an APU and to have an output frequency that is a function of an excitation frequency and an APU speed. The system can include a generator control module configured to control the excitation frequency to the DFIG to output a substantially constant frequency with changing APU speed to supply the substantially constant frequency to a load.

An electric power generation controller for use in an aircraft to control an electric power generating apparatus including a manual transmission which changes speed of rotational power of an aircraft engine, transmits the rotational power to an electric power generator, and includes a plurality of gear stages. The electric power generation controller includes: a rotational frequency receiving section configured to receive an input rotational frequency or an output rotational frequency of the manual transmission as a monitoring rotational frequency; and a manual transmission control section configured to, when the monitoring rotational frequency exceeds a first threshold, output a shift-down signal to perform shift-down from an upper stage to a lower stage, and when the monitoring rotational frequency falls below a second threshold, output a shift-up signal to perform shift-up from the lower stage to the upper stage, the first threshold being set to a value larger than the second threshold.

Controlling a DC-AC inverter of an electric machine, where the electric machine comprises a resonant main exciter having rotary transformer. A voltage level of DC power received at a DC-AC inverter is monitored and the frequency of AC power generated by the DC-AC inverter and supplied to the rotary transformer is controlled based at least in part on the voltage level of the DC power.

A generator system can include a dual stator generator comprising a first stator and a second stator, a first rectifier operatively connected to the first stator to receive AC from the first stator, a second rectifier operatively connected to the second stator to receive AC from the second stator, and a first DC output line and a second DC output line. The first rectifier and the second rectifier can be connected in parallel to the first DC output line and a second DC output line without an inter phase transformer (IPT) to output DC to the first DC output line and the second DC output line.

An aircraft electromechanical actuator control system for an aircraft having a direct current (DC) voltage bus includes an actuator controller that is coupled to receive a first DC voltage from the aircraft DC voltage bus, where the first DC voltage has a first voltage magnitude. The actuator controller selectively supplies AC voltage to an electromechanical actuator and includes a bidirectional DC/DC converter, an inverter, and actuator control logic. The bidirectional DC/DC converter receives the first DC voltage and supplies a second DC voltage having a second voltage magnitude that is less than the first voltage magnitude. The inverter receives the second DC voltage converts it to the AC voltage. The actuator control logic receives actuator commands and supplies inverter control signals to the inverter.

An architecture for an electric distributed propulsion system includes one or more generators connected to a gearbox, a first and a second plurality of motors connected to the one or more generators, each motor of the plurality of motors connected to a blade to provide thrust, a first and a second power bus electrically connected between the one or more generators and the first and the second plurality of motors, each power bus independent of the other power bus, a first and a second controller independently connected to each of the first and second plurality of motors, each of the first and second controllers serving as a primary and a backup controller, and dual channels in communication between pilot input sensors and the first and the second controllers, and the dual channels including an additional channel to provide redundant communication to the first and second controllers.

A turbomachine is provided. In one aspect, the turbomachine includes a rotating component and an electric machine that includes a stator assembly and a rotor assembly rotatable with the rotating component relative to the stator assembly. Further, the turbomachine includes an actuator coupled with the rotor assembly, the stator assembly, or both for moving the rotor assembly, the stator assembly, or both relative to one another. In addition, the turbomachine includes a controller configured to receive data indicating an operating state of the rotating component and cause the actuator to adjust a position of at least one of the stator assembly and the rotor assembly based at least in part on the operating state of the rotating component.

A high-integrity electromechanical actuator control system includes a system function controller, a plurality of actuator controllers, and at least one electromechanical actuator. Each actuator controller includes a first controller, a second controller, and a duty cycle computation circuit. The first controller receives digital actuator control commands supplied from two of the function control channels and supplies first digital duty cycle commands. The second controller receives digital actuator control commands supplied from two function control channels and supplies second digital duty cycle commands. The duty cycle computation circuit receives the first digital duty cycle commands and the second digital duty cycle commands, computes an average of the first and second duty cycle commands, and generates pulse width modulated (PWM) commutation control signals based on the computed average.

A hybrid electric aircraft propulsion system and method of operation are described. The system comprises a thermal engine, a generator coupled to the thermal engine, a first electric propulsor operatively connected to the generator to receive alternating current (AC) electric power therefrom, a second electric propulsor, a generator inverter operatively connected to the generator to convert AC electric power to direct current (DC) electric power, and a first motor inverter operatively connected to the generator inverter and selectively connected to one of the first electric propulsor and the second electric propulsor and configured to receive the DC electric power and provide the first electric propulsor and the second electric propulsor with AC electric power, respectively.

An actuating device of a pump of a fuel pumping system of an engine, including a motor, a generator, an inverter, a switching member and a control member, the motor including a first rotor coupled to the pump and a first stator including at least one input stator winding, the generator including a second rotor coupled to a drive shaft of the engine, and a second stator including at least one output stator winding, the control member being configured to control the switching member in order to selectively connect each input stator winding: to a corresponding output stator winding if a speed of the engine is higher than or equal to a predetermined speed; to a corresponding output of the inverter, otherwise.