Abstract: An apparatus may include a generator, an electrical converter, and multiple ice protection heaters. The generator may be configured to generate alternating current (AC) along AC feeders. The electrical converter may be configured to convert the AC from the generator to direct current (DC). The ice protection heaters may include at least one ice protection heater connected to each of the AC feeders prior to the electrical converter. The ice protection heaters may be configured to generate heat at surfaces susceptible to icing using the AC from the generator.

Abstract: A fluid delivery system is provided including a reservoir including oil, a hydraulic pump in fluid communication with the reservoir, and a heat exchanger system. The heat exchanger system is in fluid communication with the hydraulic pump, a generator, and an engine gearbox. The hydraulic pump is configured to deliver the oil to the heat exchanger system. The heat exchanger system is configured to provide the oil according to first temperature criteria to the generator and provide the oil according to second temperature criteria to the engine gearbox.

Abstract: A fluid delivery system is provided including a reservoir including oil, a hydraulic pump in fluid communication with the reservoir, and a heat exchanger system. The heat exchanger system is in fluid communication with the hydraulic pump, a generator, and an engine gearbox. The hydraulic pump is configured to deliver the oil to the heat exchanger system. The heat exchanger system is configured to provide the oil according to first temperature criteria to the generator and provide the oil according to second temperature criteria to the engine gearbox.

Abstract: A power generation system for an aircraft. The system includes an auxiliary power unit (APU), an APU generator mechanically linked to the APU, a generator control unit controllably coupled to the APU and an electromagnetic windmilling brake connected to APU generator. The electromagnetic windmilling brake includes a number of switched phase connections equal to a number of phases and the switched phase connections are configured to connect each output phase to an adjacent phase.

Abstract: A method of controlling dissipation of regenerated power in a multi-channel drive system having a plurality of inverters connected in parallel across an input power supply to drive one or more loads via one or more motors. The method includes determining a circulation current demand for the inverters when the drive system is operating in regenerative mode, the circulating current demand being dependent on the regenerated power and applied to the inverters such that the regenerated power flows through the inverters and is dissipated by the inverters.

Abstract: A series hybrid propulsion system of an aircraft includes a gas turbine engine, an electrical generator operably connected to the gas turbine engine configured to generate electrical power from operation of the gas turbine engine, and one or more electrically-driven propulsors configured to provide propulsion for the aircraft, and an electrical power grid configured to distribute electrical power generated at least at the electrical generator to the one or more electrically-driven propulsors. A voltage regulator is positioned downstream of the electrical generator and is configured to take one or more actions to compensate for a loss of load on the generator.

Abstract: A propulsion system includes a propulsion unit including a multi-stage fan having a first fan stage including a first rotor and a second fan stage including a second rotor. At least one propulsion motor is operably coupled to the first rotor and to the second rotor to drive the first rotor and the second rotor about a fan axis. A controller is configured to determine a position of at least one of the first rotor and the second rotor in response to an electrical signature of the at least one propulsion motor and adjust one or more operating parameters of at least one of the first rotor and the second rotor to reduce a noise produced by rotation of the first rotor and the noise produced by rotation of the second rotor in combination.

Abstract: A system includes a first AC bus configured to supply power from a first AC power source. A second AC bus is configured to supply power from a second AC power source. A first transformer rectifier unit (TRU) connects a first DC bus to the first AC bus through a first TRU contactor (TRUC). A second TRU connects a second DC bus to the second AC bus through a second TRUC. A ram air turbine (RAT) automatic deployment controller is operatively connected to the first TRUC and to the second TRUC to automatically deploy a RAT based on the combined status of the first TRUC and the second TRUC.

Abstract: A system includes a first AC bus configured to supply power from a first generator. A second AC bus is configured to supply power from a second generator. An AC essential bus tie contactor (AETC) selectively connects between an AC essential bus and the first and second AC busses. An AETC controller is connected to switch the AETC between a first state connecting the AC essential bus to the first AC bus and a second state connecting the AC essential bus to the second AC bus. A sensor system is configured to detect at least one of delta current and overcurrent in the AC essential bus and in at least one of the first AC bus and the second AC bus. The sensor system is operatively connected to the AETC controller for switching the AETC between the first state and the second state based on input from the sensor system.

Abstract: A method of controlling dissipation of regenerated power in a multi-channel drive system having a plurality of inverters connected in parallel across an input power supply to drive one or more loads via one or more motors. The method includes determining a circulation current demand for the inverters when the drive system is operating in regenerative mode, the circulating current demand being dependent on the regenerated power and applied to the inverters such that the regenerated power flows through the inverters and is dissipated by the inverters.

Abstract: A system includes a first AC bus configured to supply power from a first generator. A first generator line contactor (GLC) selectively connects the first AC bus to the first generator. A second AC bus is configured to supply power from a second generator. A second GLC selectively connecting the second AC bus to the second generator. An auxiliary generator line contactor (ALC) is connected to selectively supply power to the first and second AC buses from an auxiliary generator. A first bus tie contactor (BTC) electrically connects between the first GLC and the ALC. A second BTC electrically connects between the ALC and the second GLC. A ram air turbine (RAT) automatic deployment controller is operatively connected to automatically deploy a RAT based on the combined status of the first GLC, the second GLC, the ALC, the first BTC, and the second BTC.

Abstract: A system includes a first AC bus configured to supply power from a first AC power source. A second AC bus is configured to supply power from a second AC power source. A first transformer rectifier unit (TRU) connects a first DC bus to the first AC bus through a first TRU contactor (TRUC). A second TRU connects a second DC bus to the second AC bus through a second TRUC. A ram air turbine (RAT) automatic deployment controller is operatively connected to the first TRUC and to the second TRUC to automatically deploy a RAT based on the combined status of the first TRUC and the second TRUC.

Abstract: A system includes a first AC bus configured to supply power from a first generator. A second AC bus is configured to supply power from a second generator. An AC essential bus tie contactor (AETC) selectively connects between an AC essential bus and the first and second AC busses. An AETC controller is connected to switch the AETC between a first state connecting the AC essential bus to the first AC bus and a second state connecting the AC essential bus to the second AC bus. A sensor system is configured to detect at least one of delta current and overcurrent in the AC essential bus and in at least one of the first AC bus and the second AC bus. The sensor system is operatively connected to the AETC controller for switching the AETC between the first state and the second state based on input from the sensor system.

Abstract: A system includes a first AC bus configured to supply power from a first generator. A first generator line contactor (GLC) selectively connects the first AC bus to the first generator. A second AC bus is configured to supply power from a second generator. A second GLC selectively connecting the second AC bus to the second generator. An auxiliary generator line contactor (ALC) is connected to selectively supply power to the first and second AC buses from an auxiliary generator. A first bus tie contactor (BTC) electrically connects between the first GLC and the ALC. A second BTC electrically connects between the ALC and the second GLC. A ram air turbine (RAT) automatic deployment controller is operatively connected to automatically deploy a RAT based on the combined status of the first GLC, the second GLC, the ALC, the first BTC, and the second BTC.

Abstract: An electrical power system is disclosed for an aircraft having a hybrid-electric propulsion system, which includes a battery assembly for storing energy, an electric motor controller operatively connected to the battery assembly for conditioning and controlling power to an electric motor, and an electric motor receiving power through the motor controller for delivering torque to a shaft of the hybrid-electric propulsion system.