Abstract: In examples, a clutch assembly includes a first clutch member disposed near a first end of a first shaft. The first clutch member defines a first surface. The first shaft includes a starter motor coupled to a second end of the first shaft. The clutch assembly includes a second clutch member disposed near a first end of a second shaft. The second clutch member defines a second surface opposing the first surface, and the second shaft includes an accessory gearbox of a gas turbine engine coupled to a second end of the second shaft. The surfaces of the first and second clutch member engage such that rotational motion is transferred between the first clutch member and the second clutch member. The first clutch member and the second clutch member are configured to passively disengage from each other and actively reengage with each other.

Abstract: A power supply for an aircraft comprises: an input configured to receive electrical power from an energy source, an output for supplying electrical power, a plurality of converters, each of which being electrically connected to the input to receive electrical power from the input and being configured to convert the electrical power and to provide the converted electrical power to the output, and a control unit being configured to individually control each of the plurality of converters.

Abstract: An example system includes a first gas-turbine engine (GTE) of a plurality of GTEs that are configured to propel an aircraft, the first GTE comprising: a first air-turbine starter (ATS) of a plurality of ATSs, the first ATS configured to rotate a spool of the first GTE; and a first electric starter of a plurality of electric starters, the first electric starter configured to rotate the spool of the first GTE; a second GTE of the plurality of GTEs, the second gas-turbine engine comprising: a second ATS of the plurality of ATSs, the second ATS configured to rotate a spool of the GTE; and a second electric starter of the plurality of electric starters, the second electric starter configured to rotate the spool of the GTE; and one or more controllers configured to control the plurality of GTEs.

Abstract: An example system includes a first gas-turbine engine configured to propel an aircraft, the first gas-turbine engine comprising a first electric starter, the first electric starter configured to rotate a spool of the first gas-turbine engine; and one or more controllers collectively configured to: cause, following operation of the first gas-turbine engine, the first electric starter to perform barring of the first gas-turbine engine; measure, during the barring of the first gas-turbine engine, values of one or more parameters of the first gas-turbine engine; and determine, based on the values of the one or more parameters, whether the first electric starter is available for use in performing mid-air restart of the first gas-turbine engine.

Abstract: An example system includes a common electric starter controller configured to control electric starters of a plurality of gas-turbine engines that are configured to propel an aircraft, wherein the common electric starter comprises: a driver configured to generate, using electrical energy sourced from a battery of the aircraft, power signals that control the electric starters; and a plurality of bus bars configured to directly connect the common electric starter controller to the battery and transport the electrical energy from the battery to the common electric starter controller.

Abstract: In examples, a clutch assembly includes a first clutch member disposed near a first end of a first shaft. The first clutch member defines a first surface. The first shaft includes a starter motor coupled to a second end of the first shaft. The clutch assembly includes a second clutch member disposed near a first end of a second shaft. The second clutch member defines a second surface opposing the first surface, and the second shaft includes an accessory gearbox of a gas turbine engine coupled to a second end of the second shaft. The surfaces of the first and second clutch member engage such that rotational motion is transferred between the first clutch member and the second clutch member. The first clutch member and the second clutch member are configured to passively disengage from each other and actively reengage with each other.

Abstract: A power supply for an aircraft comprises: an input configured to receive electrical power from an energy source, an output for supplying electrical power, a plurality of converters, each of which being electrically connected to the input to receive electrical power from the input and being configured to convert the electrical power and to provide the converted electrical power to the output, and a control unit being configured to individually control each of the plurality of converters.

Abstract: A power system for an aircraft includes at least one power distribution unit. The at least one power distribution unit includes at least one input configured to receive electrical power from at least one energy source, and at least one output configured to provide electrical power from the at least one input to at least one electrical load. The at least one power distribution unit also includes a control system configured to detect a condition, and to perform an action based on the detected condition.

Abstract: An electrical machine which includes a housing defining a cavity and a drain port. The housing is configured to retain a cooling fluid within the cavity. The electrical machine further includes a dual-purpose connector which includes both a drain plug configured to seal the drain port and an electrical connector configured to transfer electrical power or information to the electrical machine.

Abstract: An example system includes a power electronics system; a starter electrically connected to the power electronics system and configured to start a gas-turbine engine of an aircraft; and an energy storage system electrically connected to the power electronics system and configured to provide direct current (DC) electrical energy to the power electronics system, wherein the power electronics system is configured to deliver alternating current (AC) electrical energy to the starter to start the gas-turbine engine using the DC electrical energy from the energy storage system and AC electrical energy sourced from an AC electrical bus of the aircraft.

Abstract: A system platform includes a gas turbine engine coupled to a generator. The generator, driven by the gas turbine engine, supplies power to subsystems of the platform.

Abstract: A gearbox rigidly coupled to a static structure; a driven component rigidly coupled to another static structure; a clutch assembly floating between and coupled to the gearbox and driven component. The clutch may have aligned output and input shafts, defining an engagement surface, a bearing, and a magnetic friction plate coupled and rotating with the input shaft. The plate may have a friction-engagement face, and a magnetic flux generator. The magnetic flux generator may be rigidly coupled to a static housing and partially surrounded in the radial direction by a structure configured to reduce leakage of a magnetic flux, by defining a plurality of voids, which direct multiple passes of the magnetic flux through the engagement surface of the output shaft. The magnetic flux generator may create the magnetic flux that creates a magnetic force between the engagement face and the magnetic friction plate that causes them to engage.

Abstract: Systems and methods are provided for decreasing thermalization time and/or increasing coefficients of performance by adding waste heat. A thermal management system may include a coolant loop and be configured to cool a target component via the coolant loop, the thermal management system may be further configured to heat the target component during a thermalization period with a waste heat source via the same coolant loop with which the thermal management system is configured to cool the target component.

Abstract: A gearbox rigidly coupled to a static structure; a driven component rigidly coupled to another static structure; a clutch assembly floating between and coupled to the gearbox and driven component. The clutch may have aligned output and input shafts, defining an engagement surface, a bearing, and a magnetic friction plate coupled and rotating with the input shaft. The plate may have a friction-engagement face, and a magnetic flux generator. The magnetic flux generator may be rigidly coupled to a static housing and partially surrounded in the radial direction by a structure configured to reduce leakage of a magnetic flux, by defining a plurality of voids, which direct multiple passes of the magnetic flux through the engagement surface of the output shaft. The magnetic flux generator may create the magnetic flux that creates a magnetic force between the engagement face and the magnetic friction plate that causes them to engage.

Abstract: Systems and methods for thermal management are provided. Thermal management components may include an electrical source and a cooling source. The electrical source may supply electricity to an electrical apparatus. In addition, the thermal management components store thermal energy. A controller may cause the electrical apparatus to be cooled by the cooling source and delay or suspend cooling the electrical source with the cooling source while a state of charge of the electrical source is greater than a predefined value for the electrical source. The state of charge of the electrical source may include a measurement of cooling capacity available by the electrical source.

Abstract: A system platform includes a gas turbine engine coupled to a high power generator. The high power generator, driven by the gas turbine engine, supplies power to high power subsystems of the platform.

Abstract: A system platform includes a gas turbine engine coupled to a high power generator. The high power generator, driven by the gas turbine engine, supplies power to high power subsystems of the platform.

Abstract: Systems and methods are provided for decreasing thermalization time and/or increasing coefficients of performance by adding waste heat. A thermal management system may include a coolant loop and be configured to cool a target component via the coolant loop, the thermal management system may be further configured to heat the target component during a thermalization period with a waste heat source via the same coolant loop with which the thermal management system is configured to cool the target component.

Abstract: Systems and methods for thermal management are provided. Thermal management components may include an electrical source and a cooling source. The electrical source may supply electricity to an electrical apparatus. In addition, the thermal management components store thermal energy. A controller may cause the electrical apparatus to be cooled by the cooling source and delay or suspend cooling the electrical source with the cooling source while a state of charge of the electrical source is greater than a predefined value for the electrical source. The state of charge of the electrical source may include a measurement of cooling capacity available by the electrical source.

Abstract: A system platform includes a gas turbine engine coupled to a high power generator. The high power generator, driven by the gas turbine engine, supplies power to high power subsystems of the platform.