Abstract: An aircraft that includes a hybrid-electric propulsion system is provided. In one aspect, the hybrid-electric propulsion system includes at least one propulsor that includes a gas turbine engine and an electric machine mechanically coupled with a spool of the gas turbine engine. When idle operation is commanded, electrical power is provided to the electric machine to cause the electric machine to apply torque to the spool and fuel provided to the engine can be reduced. Thus, the electric machine is controlled to provide a power assist to maintain the engine at the commanded idle speed whilst reducing fuel consumption.

Abstract: Aspects of the disclosure generally relate to an aircraft propulsion system for an aircraft. The aircraft propulsion system can include at least an electric power source, an electric machine, and a voltage regulator. The voltage regulator regulates the electrical power provided to the electric machine from the electrical power source. The electric power source is capable of providing an AC or DC electrical output and can include a combustion engine with a generator or an electrical storage device.

Abstract: A hybrid-electric or all-electric powertrain may include a power control unit electrically coupled to an energy storage system. The power control unit may determine a power level command based at least in part on a power level request for the powertrain, and a power level-UCL and/or a power level-LCL. The power level-UCL and/or the power level-LCL may be based at least in part on an aggregate obverse power level request representing a requested power level for one or more obverse powertrains electrically coupled to the energy storage system. The power level commands may be limited by the power level-UCL and/or the power level-LCL. The power level-UCL may be set equal to either an available discharge power capacity or an apportionate discharge power capacity. The power level-LCL may be set equal to either an available storage power capacity or an apportionate storage power capacity.

Abstract: A system for controlling power distribution is provided. The system includes an engine operably coupled to an electric machine and a first power electronics device configured in a power control mode to modulate power extracted by the electric machine. A second power electronics device is configured in a voltage control mode and is operably coupled to a load device to modulate power received by the load device from the first power electronics device. Modulating power received by the load device is based at least on an operating limit corresponding to the load device, a voltage of the electric bus, or both. A computing system is operably coupled to the engine and the first power electronics device, wherein the computing system is configured to send control commands to the engine and the first power electronics device.

Abstract: A system for controlling a motor includes a controller module comprising a controller portion, a regulator portion and an integrator portion. The regulator portion includes a set of regulator modules communicatively coupled in a sequence. Each regulator module configured to receive a respective input signal, indicative of a target or selected value, from the controller portion or the immediately preceding regulator module in the sequence, determine a respective selectable value; select one of the respective selectable value and the value indicated by the received input signal; and provide the selected value as an output signal to the next regulator module in the sequence or the integrator module. The integrator module is configured to receive the output signal from the last regulator module in the sequence, calculate a final demand value based on the received signal, and provide an output signal indicative of the final demand value.

Abstract: An aircraft that includes a hybrid-electric propulsion system is provided. In one aspect, the hybrid-electric propulsion system includes at least one propulsor that includes a gas turbine engine and an electric machine mechanically coupled with a spool of the gas turbine engine. When idle operation is commanded, electrical power is provided to the electric machine to cause the electric machine to apply torque to the spool and fuel provided to the engine can be reduced. Thus, the electric machine is controlled to provide a power assist to maintain the engine at the commanded idle speed whilst reducing fuel consumption.

Abstract: A system for controlling a motor includes a controller module comprising a controller portion, a regulator portion and an integrator portion. The regulator portion includes a set of regulator modules communicatively coupled in a sequence. Each regulator module configured to receive a respective input signal, indicative of a target or selected value, from the controller portion or the immediately preceding regulator module in the sequence, determine a respective selectable value; select one of the respective selectable value and the value indicated by the received input signal; and provide the selected value as an output signal to the next regulator module in the sequence or the integrator module. The integrator module is configured to receive the output signal from the last regulator module in the sequence, calculate a final demand value based on the received signal, and provide an output signal indicative of the final demand value.

Abstract: Aspects of the disclosure generally relate to an aircraft propulsion system for an aircraft. The aircraft propulsion system can include at least an electric power source, an electric machine, a voltage regulator, and at least one propeller. The voltage regulator regulates the electrical power provided to the electric machine from the electrical power source. The electric power source is capable of providing an AC or DC electrical output and can include a combustion engine with a generator or an electrical storage device.

Abstract: A multi-spool turbomachine having an electric machine that can be controlled to input power to one of the spools of the turbomachine is provided. In one aspect, the multi-spool turbomachine can be a hybrid electric gas turbine engine for an aircraft. The hybrid electric gas turbine engine can include a first spool, a second spool, and an electric machine operatively coupled with the first spool. In response to an increase in thrust demand, the electric motor receives electrical power from an electrical power source. In turn, the electric machine applies a torque to the first spool, causing the first spool to increase in rotational speed. In this manner, the electric machine can electrically assist the turbomachine to meet the increase in thrust demand.

Abstract: A multi-spool turbomachine having an electric machine that can be controlled to input power to one of the spools of the turbomachine is provided. In one aspect, the multi-spool turbomachine can be a hybrid electric gas turbine engine for an aircraft. The hybrid electric gas turbine engine can include a first spool, a second spool, and an electric machine operatively coupled with the first spool. In response to an increase in thrust demand, the electric motor receives electrical power from an electrical power source. In turn, the electric machine applies a torque to the first spool, causing the first spool to increase in rotational speed. In this manner, the electric machine can electrically assist the turbomachine to meet the increase in thrust demand.

Abstract: Aspects of the disclosure generally relate to an aircraft propulsion system for an aircraft. The aircraft propulsion system can include at least an electric power source, an electric machine, a voltage regulator, and at least one propeller. The voltage regulator regulates the electrical power provided to the electric machine from the electrical power source. The electric power source is capable of providing an AC or DC electrical output and can include a combustion engine with a generator or an electrical storage device.

Abstract: Methods for detecting events, e.g., failures, in actuating systems for turbine engines are provided. In one exemplary aspect, a first slope and a second slope are determined. The first slope is determined by calculating the slope of an engine operating characteristic as a function of time prior to an actuation command. The second slope is determined by calculating the slope of the engine operating characteristic as a function of time after the actuation command. Thereafter, a delta slope is generated based at least in part on the difference between the first slope and the second slope. The delta slope is then compared to a predetermined threshold to determine whether a failure in the actuating system has occurred. Turbine engines configured to detect such events are also provided.

Abstract: Methods for detecting events, e.g., failures, in actuating systems for turbine engines are provided. In one exemplary aspect, a first slope and a second slope are determined. The first slope is determined by calculating the slope of an engine operating characteristic as a function of time prior to an actuation command. The second slope is determined by calculating the slope of the engine operating characteristic as a function of time after the actuation command. Thereafter, a delta slope is generated based at least in part on the difference between the first slope and the second slope. The delta slope is then compared to a predetermined threshold to determine whether a failure in the actuating system has occurred. Turbine engines configured to detect such events are also provided.

Abstract: An adjustably attenuating ear plug adapted for use in an ear canal, includes a flexible body, and a valve assembly further comprising a disk and knob translatable relative to the disk, wherein the knob defines at least one inlet, the disk alternately defines at least one shield and hole, and the inlet is alternatively aligned with the hole and shield to varying degrees, so as to selectively and variably expose the canal to the environment.

Abstract: An adjustably attenuating ear plug adapted for use in an ear canal, includes a flexible body, and a valve assembly further comprising a disk and knob translatable relative to the disk, wherein the knob defines at least one inlet, the disk alternately defines at least one shield and hole, and the inlet is alternatively aligned with the hole and shield to varying degrees, so as to selectively and variably expose the canal to the environment.

Abstract: An adjustably attenuating ear plug adapted for use in an ear canal, includes a flexible body, and a valve assembly further comprising a disk and knob translatable relative to the disk, wherein the knob defines at least one inlet, the disk alternately defines at least one shield and hole, and the inlet is alternatively aligned with the hole and shield to varying degrees, so as to selectively and variably expose the canal to the environment.

Abstract: The present invention provides a system and method to efficiently generate and switch page display views on a portable electronic book. The method includes generating an ebook binary file including a plurality of book views, each of the plurality of book views including information needed to generate page display images representing content of a reading material in a font having a particular font point size. The method further includes parsing the ebook binary file and generating the page display images representing content of a reading material.