Hamilton Sundstrand Corporation

Jonathan Mark Roadley-Battin

Rodrigo Fernandez-Mattos

Andrei Dinu

Ponggorn Kulsangcharoen

Mital Shah

Stefanos Skoulaxinos

An electric motor drive system for a propulsion device. The system includes a battery stack having an earth terminal and an end terminal and an electric motor electrically connected to be powered by the battery stack. The motor is configured to be connected to drive the propulsion device, The system also includes: a power converter electrically connected between the battery stack and the electric motor; and a switch between the power converter and the battery stack. The switch is arranged to switch between a first state electrically connecting the end terminal of the battery stack to the power converter to provide a maximum battery voltage to the power converter, and a second state electrically connecting a tap point from one or more intermediate nodes, intermediate the earth terminal and the end terminal, of the battery stack, to provide a voltage less than the maximum battery voltage to the power converter.

Electric power arrangement for propulsion

An active rectifier circuit for providing a rectified voltage output to a point of regulation that is located downstream of the active rectifier circuit. The active rectifier circuit includes rectifying circuitry and control circuitry operable to control the rectifying circuitry based on voltage feedback to provide a certain voltage output at the point of regulation. The control circuitry is configured to obtain voltage feedback from a first point associated with the point of regulation and to obtain parallel voltage feedback from a second, different point, and to control the rectifying circuitry based on both the voltage feedback from the first point and the voltage feedback from the second point.

Weighted setpoint for active rectifier stability

A voltage converter for an aircraft electrical system includes an input power line configured to receive input electrical power, an output power line configured to supply output electrical power to aircraft loads, conversion circuitry, and a controller. The conversion circuitry is configured to convert the input electrical power to supply the output electrical power based on one or more control parameters. The controller is configured to receive data relating to the aircraft loads and modify at least one control parameter based on the data.

Aircraft electrical system

A bootstrap gate driver charging circuit arranged to drive the gate of an upper switch (Q) and a lower switch (Q) connected in series to provide an AC output voltage () voltage by alternatively turning on and off according to a predetermined duty cycle of alternate upper switch turn-on and lower switch turn-on phases, the bootstrap gate driver charging circuit comprising: an input terminal; an output terminal; an H-bridge inverter with an inverter input and an inverter output; a charging path; and a bootstrap capacitor. The input inverter is electrically connected to the input terminal, the inverter output is electrically connected to a first end of the bootstrap capacitor, the charging path is electrically connected between a second end of the bootstrap capacitor and a gate driver supply voltage; wherein in response to the lower switch being turned ON and providing a path to ground with respect to the supply voltage.

H-bridge circuit with bootstrap capacitor gate drive charging circuit

Methods of operating electric motor systems that comprise electric motors comprising a rotor having a magnet mounted thereto. The electric motor is initially operated in an open loop mode in which the rotor angle is estimated based on the input voltage frequency. Once the motor is running at sufficient speed, a transition to closed loop mode operation is performed, wherein the rotor angle is determined using an observed back EMF. To provide a smoother open loop to closed loop transition, the rotor angle is determined during a transition period as a function of both the open loop rotor angle and the closed loop rotor angle.

Electric motor control

A closed loop control system for controlling a plant comprises a controller includes an input arranged to receive a feedback signal from the plant. The controller is arranged to compare a value of the feedback signal to a set point value x(s) and to produce an error signal &#x3b5;(s) that is at least partially dependent on a difference between the value of the feedback signal and the set point value. The controller also includes an output arranged to supply the error signal &#x3b5;(s) to the plant. A monitor is arranged to compare a value of the error signal &#x3b5;(s) produced by the controller to a threshold value and to produce a warning signal when the value of the error signal &#x3b5;(s) exceeds the threshold value for a period of time greater than a predetermined period.

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Birmingham, United Kingdom

Jonathan Mark Roadley-Battin