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: Systems for a cascaded multiple feedback generator controller are provided. Aspects include a direct current (DC) power supply comprising a generator and a rectifier circuit connected to a load, a first voltage sensing device coupled to a first point of regulation, a second voltage sensing device coupled to a second point of regulation, a generator controller configured to receive a first voltage signal from the first voltage sensing device, receive a second voltage signal from the second voltage sensing device, determine an adjustment for the generator, the adjustment comprising a transient performance response and a voltage droop response, wherein the transient performance response is determined based on the first voltage signal, and wherein the voltage droop response is determined based on the second voltage signal, and operate the generator based on the adjustment for the generator.

Abstract: An engine system for an aircraft comprising a propulsor configured to drive the aircraft, a thermal combustion engine configured to drive the propulsor, an electric motor connected to the thermal combustion engine and configured to drive the propulsor, a power converter configured to apply a torque to the electric motor and generate electric energy from the torque applied to the electric motor, and an engine controller, the engine controller being configured to determine a current power output of the thermal combustion engine, determine an optimum power output of the thermal combustion engine based on current operating conditions, and vary the torque applied to the electric motor so as to vary a load on the thermal combustion engine, wherein the torque may be varied by an amount required to vary the power output of the thermal combustion engine to the determined optimum power output.

Abstract: A power distribution controller includes a solid state power controller (SSPC), a power system, and a backup power system. The SSPC is configured to selectively deliver a first power from a first power source to at least one electrical load. The power system is in signal communication with the at least one SSPC. The backup power system includes a first output in signal communication with the SSPC and a second output in signal communication with the power system.

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 first voltage sensor is connected to sense voltage of the first DC bus. A second voltage sensor is connected to sense voltage of the second DC bus. A ram air turbine (RAT) automatic deployment controller is operatively connected to the first voltage sensor and to the second voltage sensor to automatically deploy a RAT based on the combined status of the first voltage sensor and the second voltage sensor.

Abstract: A battery charging system for a hybrid electric powerplant can be configured to determine a maximum available charging power available from windmilling and/or excess thermal engine power available, and to use up to the maximum available charging power and/or the excess thermal engine power available to charge a battery. In certain embodiments, a control module can be configured to determine the maximum available charging power available from windmilling.

Abstract: A control system for an electric motor powered by a battery can be configured to receive an input power or torque command corresponding to a commanded power or torque. The control system can be configured to determine if the battery is capable of supplying and/or permitted to supply the commanded power or torque over a time period based on a state of charge (SOC) of the battery. The control system can be configured such that if the battery is capable of supplying and/or permitted to supply the commanded power or torque over the time period, the control system outputs the input power or torque command, and such that if the battery is not capable of supplying and/or not permitted to supply the commanded power or torque over the time period, the control system outputs an available maximum power or torque command corresponding to an available maximum power or torque over the time period that is less than the commanded power or torque.

Abstract: A control system for an electric motor powered by a battery can be configured to receive an input instantaneous power or torque command corresponding to a commanded instantaneous power or torque. The control system can be configured to determine if the battery is capable of supplying and/or permitted to supply the commanded instantaneous power or torque based on a state of charge (SOC) of the battery. The control system can be configured such that if the battery is capable of supplying and/or permitted to supply the commanded instantaneous power or torque, the control system outputs the input instantaneous power or torque command, and such that if the battery is not capable of supplying and/or not permitted to supply the commanded instantaneous power or torque, the control system outputs an available maximum instantaneous power or torque command corresponding to an available maximum instantaneous power or torque that is less than the commanded instantaneous power or torque.

Abstract: An engine system for an aircraft comprising a propulsor configured to drive the aircraft, a thermal combustion engine configured to drive the propulsor, an electric motor connected to the thermal combustion engine and configured to drive the propulsor, a power converter configured to apply a torque to the electric motor and generate electric energy from the torque applied to the electric motor, and an engine controller, the engine controller being configured to determine a current power output of the thermal combustion engine, determine an optimum power output of the thermal combustion engine based on current operating conditions, and vary the torque applied to the electric motor so as to vary a load on the thermal combustion engine, wherein the torque may be varied by an amount required to vary the power output of the thermal combustion engine to the determined optimum power output.

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 first voltage sensor is connected to sense voltage of the first DC bus. A second voltage sensor is connected to sense voltage of the second DC bus. A ram air turbine (RAT) automatic deployment controller is operatively connected to the first voltage sensor and to the second voltage sensor to automatically deploy a RAT based on the combined status of the first voltage sensor and the second voltage sensor.

Abstract: An auxiliary power unit (APU) system for an aircraft can include a fuel consuming system configured to generate and output electrical energy for use by one or more aircraft systems and a battery system configured to output stored electrical energy for use by the one or more aircraft systems. The fuel consuming system can include a fuel consuming APU, and an APU generator operatively connected to the fuel consuming APU and configured to convert APU motion into APU generator alternating current (AC). The system can include a high voltage AC line operatively connected to the generator. The battery system can include a battery configured to output battery direct current (DC).

Abstract: A hybrid electric aircraft powerplant controller for controlling an engine and an electric motor-generator can include an engine recharging module. The engine recharging module can be configured to operate the engine to produce a desired output power to a propulsor and to produce additional power to drive the electric motor-generator to produce electrical output from the electric motor-generator to recharge an electrical storage device during at least one power setting and/or flight phase where the electric motor-generator is not driving the propulsor.

Abstract: A power distribution controller includes a solid state power controller (SSPC), a power system, and a backup power system. The SSPC is configured to selectively deliver a first power from a first power source to at least one electrical load. The power system is in signal communication with the at least one SSPC. The backup power system includes a first output in signal communication with the SSPC and a second output in signal communication with the power system.

Abstract: A power quality control circuit is connected to monitor an AC input power and selectively connect the AC input power through a contactor. The power quality control circuit includes power quality monitor circuitry that determines whether the AC input power has an overfrequency condition, an underfrequency condition, an overvoltage condition or an undervoltage condition, and prevents closing of the contactor in response to a determination of any of those conditions.

Abstract: A system, method, and computer readable medium directed to communication with a remote component in an aircraft environment are described. The system includes the remote component in the aircraft environment to control a single phase alternating or direct current input drawn from a constant voltage power source, and a controller in the aircraft environment configured to monitor the current input to the remote component and determine a message from the remote component based on a current pattern in the current input.

Abstract: A power distribution system includes multiple uniform power distribution modules and multiple uniform mating connectors. A portion of the mating connectors are connected to the power distribution modules directly and the remainder are connected to the power distribution modules via a ground fault interrupt adapter.

Abstract: A system, method, and computer readable medium directed to communication with a remote component in an aircraft environment are described. The system includes the remote component in the aircraft environment to control a single phase alternating or direct current input drawn from a constant voltage power source, and a controller in the aircraft environment configured to monitor the current input to the remote component and determine a message from the remote component based on a current pattern in the current input.

Abstract: A power distribution system includes multiple uniform power distribution modules and multiple uniform mating connectors. A portion of the mating connectors are connected to the power distribution modules directly and the remainder are connected to the power distribution modules via a ground fault interrupt adapter.