Abstract: A hybrid electric propulsion (HEP) system of an aircraft includes a gas turbine engine configured to generate rotational power, and an electric propulsion system configured to generate at least one of thrust or lift for operation of the aircraft. The propulsion system includes a propulsor and an electric motor configured to drive the propulsor. A controller is in signal communication with the gas turbine engine and the electric propulsion system. The controller operates the gas turbine engine based on an on-board engine model (OEM), monitors electrical parameters of the electric propulsion system, and updates the OEM in response to changes to the electrical parameters.

Abstract: A system includes four high voltage direct current (HVDC) feeders, each having a first contactor configured for selectively connecting a positive terminal of an HVDC source to the respective HVDC feeder, and having a second contactor configured for selectively connecting the respective HVDC feeder to an HVDC bus. A power converter can be configured to use feedback to locate a fault when a fault arises, and to isolate the fault by opening of the contactors as needed for continued operation of as many of the HVDC feeders as possible after clearing the fault.

Abstract: A disconnect mechanism comprises an input shaft defining a drive axis, a disconnect shaft selectively engaged with the input shaft to be driven about the drive axis by the input shaft, and a disconnect ramp operatively connected to the disconnect shaft to axially move the disconnect shaft between at least a first axial position and a second axial position. A disconnect pawl is selectively engaged with the disconnect ramp shaft, and a brake is selectively engaged with the disconnect shaft in the second axial position.

Abstract: A disconnect mechanism comprises an input shaft defining a drive axis, a disconnect shaft selectively engaged with the input shaft to be driven about the drive axis by the input shaft, and a disconnect ramp operatively connected to the disconnect shaft to axially move the disconnect shaft between at least a first axial position and a second axial position. A disconnect pawl is selectively engaged with the disconnect ramp shaft, and a brake is selectively engaged with the disconnect shaft in the second axial position.

Abstract: A disconnect mechanism comprises an input shaft defining a drive axis, a disconnect shaft selectively engaged with the input shaft to be driven about the drive axis by the input shaft, and a disconnect ramp operatively connected to the disconnect shaft to axially move the disconnect shaft between at least a first axial position and a second axial position. A disconnect pawl is selectively engaged with the disconnect ramp shaft, and a brake is selectively engaged with the disconnect shaft in the second axial position.

Abstract: A disconnect mechanism comprises an input shaft defining a drive axis, a disconnect shaft selectively engaged with the input shaft to be driven about the drive axis by the input shaft, and a disconnect ramp operatively connected to the disconnect shaft to axially move the disconnect shaft between at least a first axial position and a second axial position. A disconnect pawl is selectively engaged with the disconnect ramp shaft, and a brake is selectively engaged with the disconnect shaft in the second axial position.

Abstract: An engine system includes a turbine engine having a high pressure spool and a low pressure spool. A transmission includes an input shaft connected to one of the high pressure spool and the low pressure spool, and an output shaft. A clutch is arranged between the input shaft and the output shaft. A generator is connected to the output shaft. A clutch controller activates the clutch when one of the high pressure spool and the low pressure spool, and the generator are operating at a selected speed range.

Abstract: An aircraft includes an electrical system and an electronic controller. The electronic controller includes a main processor and a multi-core processor. The multi-core processor includes a control core in signal communication with the electrical system, and one or more prognostics cores configured to process and analyze prognostics and diagnostics data of the electrical system independently from operation of the control core. A wireless device is in signal communication with one or more of the prognostics cores to receive the prognostics and diagnostics data therefrom. The aircraft further includes a prognostics and health monitoring (PHM) system located remotely from the electronic controller. The PHM system is configured to wirelessly receive the prognostics and diagnostics data from the wireless device.

Abstract: An aircraft includes an electrical system and an electronic controller in signal communication with the electrical system. The electronic controller including a main processor and a multi-core processor. The multi-core processor includes one or more control cores and one or more prognostic cores. The control core is in signal communication with the electrical system to control power delivered thereto. The prognostics core is configured to process prognostics and diagnostics data of the electrical system independently from operation of the control core.

Abstract: An aircraft includes an electrical system and an electronic controller. The electronic controller includes a main processor and a multi-core processor. The multi-core processor includes a control core in signal communication with the electrical system, and one or more prognostics cores configured to process and analyze prognostics and diagnostics data of the electrical system independently from operation of the control core. A wireless device is in signal communication with one or more of the prognostics cores to receive the prognostics and diagnostics data therefrom. The aircraft further includes a prognostics and health monitoring (PHM) system located remotely from the electronic controller. The PHM system is configured to wirelessly receive the prognostics and diagnostics data from the wireless device.

Abstract: An aircraft includes an electrical system and an electronic controller in signal communication with the electrical system. The electronic controller including a main processor and a multi-core processor. The multi-core processor includes one or more control cores and one or more prognostic cores. The control core is in signal communication with the electrical system to control power delivered thereto. The prognostics core is configured to process prognostics and diagnostics data of the electrical system independently from operation of the control core.

Abstract: A method of controlling a motor controller includes receiving respective measurements for each of at least three phase currents or voltages output by the motor controller that were instantaneously sensed at substantially the same instant, determining a magnitude of a model signal that models the sensed phase currents or voltages at the instant of the instantaneous sensing as a function of each of the respective measurements, and controlling the motor controller based on the magnitude of the model signal. A motor controller and a controller of a motor controller using the method are also provided.