Abstract: Systems and methods for reducing switching losses in an electrical system in an aircraft are provided. In one example implementation, a method can include receiving DC power at an inverter of an electrical power system of an aircraft. The inverter can be a multiphase inverter having at least one bridge circuit for each output phase of the inverter. Each bridge circuit can include a plurality of switching elements. The method can include generating, by one or more control devices, a plurality of duty cycle commands for operation of the plurality of switching elements for each bridge circuit. The method can include operating, by the one or more control devices, the inverter in accordance with the plurality of duty cycle commands to generate a multiphase AC power output from the inverter. The plurality of duty cycle commands can be generated at least in part using a space vector modulation process.

Abstract: An apparatus and method of operating a set of generators supplying power to a common power bus, includes obtaining a first generator speed signal and a second generator speed signal, determining a common mode torsional oscillation value and a differential mode torsional oscillation value, determining a first generator share command and a second generator share command based on the common mode torsional oscillation value and the differential mode torsional oscillation value, and applying the first and second generator share commands.

Abstract: An apparatus and method of operating a set of generators supplying power to a common power bus, includes obtaining a first generator speed signal and a second generator speed signal, determining a common mode torsional oscillation value and a differential mode torsional oscillation value, determining a first generator share command and a second generator share command based on the common mode torsional oscillation value and the differential mode torsional oscillation value, and applying the first and second generator share commands.

Abstract: Systems and methods for detecting a diode fault are provided. In one example implementation, a method for determining a diode fault condition in a rotating rectifier associated with an electrical machine in an aircraft includes obtaining, by one or more processors, a signal associated with a diode of a rotating rectifier; determining, by the one or more processors, a frequency of interest; isolating, by the one or more processors, the frequency of interest from the signal to generate an isolated signal; determining, by the one or more processors, an amplitude of the isolated frequency of interest; and determining, by the one or more processors, a diode fault condition based on the determined amplitude.

Abstract: Systems and methods for reducing switching losses in an electrical system in an aircraft are provided. In one example implementation, a method can include receiving DC power at an inverter of an electrical power system of an aircraft. The inverter can be a multiphase inverter having at least one bridge circuit for each output phase of the inverter. Each bridge circuit can include a plurality of switching elements. The method can include generating, by one or more control devices, a plurality of duty cycle commands for operation of the plurality of switching elements for each bridge circuit. The method can include operating, by the one or more control devices, the inverter in accordance with the plurality of duty cycle commands to generate a multiphase AC power output from the inverter. The plurality of duty cycle commands can be generated at least in part using a space vector modulation process.