A system for restricting power to a load to prevent engaging circuit protection device for an aircraft. The system includes an energy source of an aircraft. The system further includes a plurality of sensors configured to sense at least an electrical parameter of a load of the plurality of loads. The system further includes an aircraft controller configured to receive electrical parameter of a load of the plurality of loads from the plurality of sensors, compare the electrical parameter to at least a current allocation threshold, detect that the electrical parameter has reached the current allocation threshold, calculate a power reduction to the load, and reduce power from the at least an energy source to each load of the plurality of loads by the power reduction. The system further includes at least an electrical circuit of an aircraft, wherein the electrical circuit comprises a circuit protection device.

A stacked capacitor includes a body having opposing faces, first side faces in a first direction, and second side faces in a second direction. The body includes a first insulation margin without a first metal film and a second insulation margin without a second metal film. The first metal film includes a metal film edge overlapping the second insulation margin. The second metal film includes a metal film edge overlapping the first insulation margin. The first and second metal films each include multiple sub-films separated by multiple first slits. A first slit includes a first portion extending from the first or second insulation margin along the first side faces and a second portion located in the metal film edge and extending at an angle with the first side faces. The second portion has a length in the first direction greater than or equal to an interval between adjacent first slits.

A stacked capacitor includes a body having opposing faces, first side faces in a first direction, and second side faces in a second direction. The body includes a first insulation margin without a first metal film and a second insulation margin without a second metal film. The first metal film includes a metal film edge overlapping the second insulation margin. The second metal film includes a metal film edge overlapping the first insulation margin. The first and second metal films each include multiple sub-films separated by multiple first slits. A first slit includes a first portion extending from the first or second insulation margin along the first side faces and a second portion located in the metal film edge and extending at an angle with the first side faces. The second portion has a length in the first direction greater than or equal to an interval between adjacent first slits.

A method of two-step variable valve lift (VVL) operation learning control for a vehicle may include: applying, by a lift controller, a VVL control to an electric two-step VVL system; determining, by the lift controller, whether the vehicle is running in an electric vehicle (EV) mode; and when the vehicle is running in the EV mode, performing, by the lift controller, a learning time securing control of allowing a VVL operation learning to be performed by engine operating for an operation avoidance area and an operation avoidance time which are applied to a secondary lift of an exhaust valve.

A method of two-step variable valve lift (VVL) operation learning control for a vehicle may include: applying, by a lift controller, a VVL control to an electric two-step VVL system; determining, by the lift controller, whether the vehicle is running in an electric vehicle (EV) mode; and when the vehicle is running in the EV mode, performing, by the lift controller, a learning time securing control of allowing a VVL operation learning to be performed by engine operating for an operation avoidance area and an operation avoidance time which are applied to a secondary lift of an exhaust valve.

A drive system for a rail vehicle includes a plurality of drive motors. The drive motors include at least one permanent magnet motor and at least one asynchronous motor and/or at least one reluctance motor. A rail vehicle having wheelsets, each of which includes two oppositely disposed wheels and which are driven at least partially by the drive system, is also provided.

The present invention relates to a high-power charging system for electric vehicles with energy storage unit.

A refuse vehicle including a chassis a body assembly coupled to the chassis, the body assembly defining a refuse compartment, an electric energy system, and an auxiliary power system comprising a reservoir to hold a hydraulic fluid, and a hydraulic pump powered by an electric motor, wherein the hydraulic pump pressurizes the hydraulic fluid to power one or more actuators, and wherein at least one of the electric energy system or the auxiliary power system is configured to provide power to a carry can.

A refuse vehicle includes a chassis supporting a plurality of wheels, a battery supported by the chassis and configured to provide electrical power to a first motor, and an electric power take-off system coupled to the vehicle body. The electric power-take-off system includes a second motor configured to convert electrical power received from the battery into hydraulic power, an inverter configured to provide electrical power to the second motor from the battery, a heat dissipation device coupled to the inverter, a first sensor configured to detect thermal energy within the inverter, and a controller configured to receive data from the first sensor and provide operating parameters to the heat dissipation device, wherein the controller is further configured to determine if the data from the first sensor is greater than a critical operating condition and shut down the electric power take-off system in response.

An aircraft includes: rotors each driven by an electric motor; a PCU that converts AC power output from a generator into DC power; an inverter that converts DC power supplied from the PCU into AC power and outputs the AC power to the electric motor; a DC wire that connects the PCU and the inverter; and an AC wire that connects the inverter and the electric motor. The AC wire is disposed in a direction orthogonal to a direction in which rotation shafts of the generator and a gas turbine extend.