A battery control apparatus for a battery system includes: a first operation unit that computes a first state of charge of a battery according to a first technique on the basis of an electric current value, a voltage value, and an internal resistance value of the battery; a second operation unit that computes a second state of charge of the battery according to a second technique different from the first technique; and a correction unit that corrects the internal resistance value of the battery. if a difference equal to or more than a specified value is detected between the first state of charge and the second state of charge, the correction unit corrects the internal resistance value of the battery with a resistance correction amount according to the difference and the electric current value.

Provided is a system including: a management unit configured to manage a plurality of battery packs connected in parallel, in which the management unit is configured to control the plurality of battery packs to cause the plurality of battery packs to be discharged alternately so that a discharge rate of each of the plurality of battery packs becomes higher than the discharge rate in a case of discharging all of the plurality of battery packs. The plurality of battery packs include a plurality of left-hand side battery packs and a plurality of right-hand side battery packs, and the management unit is configured to manage the plurality of battery packs to cause at least one of the plurality of battery packs in each of the plurality of left-hand side battery packs and the plurality of right-hand side battery packs to be discharged at a time in order.

Examples described herein provide a computer-implemented method that includes providing the hybrid electric engine, the hybrid electric engine having a gas generating core and an electric machine powered by electric energy. The method further includes determining, by a processing device, whether a use of the electric energy will increase time on wing of the hybrid electric engine of the aircraft a threshold amount. The method further includes, responsive to determining that the use of energy will increase time on wing the threshold amount, apportioning the electric energy from a battery system of the aircraft to increase the time on wing.

Examples described herein provide a computer-implemented method that includes providing the hybrid electric engine, the hybrid electric engine having a gas generating core and an electric machine powered by electric energy. The method further includes determining, by a processing device, whether a use of the electric energy will increase time on wing of the hybrid electric engine of the aircraft a threshold amount. The method further includes, responsive to determining that the use of energy will increase time on wing the threshold amount, apportioning the electric energy from a battery system of the aircraft to increase the time on wing.

A hybrid electric propulsion system includes a gas turbine engine having a low speed spool and a high speed spool. The low speed spool includes a low pressure compressor and a low pressure turbine, and the high speed spool includes a high pressure compressor and a high pressure turbine. The hybrid electric propulsion system also includes an energy storage system, an electric motor configured to augment rotational power of the high speed spool, and a controller. The controller is operable to detect a start condition of the gas turbine engine, control power delivery from the energy storage system to the electric motor based on detecting the start condition, and provide a compressor stall margin using a power-assist provided by the electric motor to the high speed spool over a targeted speed range during starting of the gas turbine engine.

A hybrid electric propulsion system includes a gas turbine engine having a low speed spool and a high speed spool. The low speed spool includes a low pressure compressor and a low pressure turbine, and the high speed spool includes a high pressure compressor and a high pressure turbine. The hybrid electric propulsion system also includes an energy storage system, an electric motor configured to augment rotational power of the high speed spool, and a controller. The controller is operable to detect a start condition of the gas turbine engine, control power delivery from the energy storage system to the electric motor based on detecting the start condition, and provide a compressor stall margin using a power-assist provided by the electric motor to the high speed spool over a targeted speed range during starting of the gas turbine engine.

A ducted propulsion assembly for an aircraft includes a duct and a plurality of stators. The distal ends of the stators are coupled to the duct. The ducted propulsion assembly includes a line replaceable centerbody assembly isostatically coupled to the proximal ends of the stators. The line replaceable centerbody assembly includes one or more electric motors driving an output driveshaft. The ducted propulsion assembly also includes a proprotor assembly interchangeably coupled to and rotatable with the output driveshaft of the line replaceable centerbody assembly. The proprotor assembly is rotatable in a rotational plane to generate thrust.

A ducted propulsion assembly for an aircraft includes a duct and a plurality of stators. The distal ends of the stators are coupled to the duct. The ducted propulsion assembly includes a line replaceable centerbody assembly isostatically coupled to the proximal ends of the stators. The line replaceable centerbody assembly includes one or more electric motors driving an output driveshaft. The ducted propulsion assembly also includes a proprotor assembly interchangeably coupled to and rotatable with the output driveshaft of the line replaceable centerbody assembly. The proprotor assembly is rotatable in a rotational plane to generate thrust.

A ground fault detection device compatible with Y capacitors of various capacities without increasing the capacitance of a detection capacitor is provided. The ground fault detection device includes a first detection capacitor that operates as a flying capacitor, a second detection capacitor that operates as a flying capacitor, a control unit measures the charging voltage of the first detection capacitor and the second detection capacitor, a switching unit that switches between a state using a first measurement system in which the first detection capacitor is charged with the high voltage battery and the charging voltage of the first detection capacitor is measured by the control unit, and a state using a second measurement system in which the second detection capacitor is charged with the high voltage battery and the charging voltage of the second detection capacitor is measured by the control unit.

A ground fault detection device compatible with Y capacitors of various capacities without increasing the capacitance of a detection capacitor is provided. The ground fault detection device includes a first detection capacitor that operates as a flying capacitor, a second detection capacitor that operates as a flying capacitor, a control unit measures the charging voltage of the first detection capacitor and the second detection capacitor, a switching unit that switches between a state using a first measurement system in which the first detection capacitor is charged with the high voltage battery and the charging voltage of the first detection capacitor is measured by the control unit, and a state using a second measurement system in which the second detection capacitor is charged with the high voltage battery and the charging voltage of the second detection capacitor is measured by the control unit.