Abstract: A method for controlling the supply of power to a power system for an aircraft having a plurality of power-consuming components includes supplying power to the power system with a generator having a power output, determining a power requirement of the power system, and supplying the power to the power-consuming components.

Abstract: A power system for an aircraft having a plurality of power-consuming components, some of which have transient power requirements, which is greater than the average power requirement, the power system includes at least one generator, a power distribution buss, a non-battery power source, a battery power source, and a power controller selectively coupling the non-battery power source and the battery power source to the power distribution buss to satisfy the transient power requirements.

Abstract: An inverter phase leg for a DC-AC inverter includes a high supply line and a low supply line across which a DC voltage is provided. A high side gate controlled switch is connected to the high supply line and a low side gate controlled switch is connected to the low supply line, with an output node between the high side switch and the low side switch. An inverting driver is connected to the high side gate controlled switch. The inverting driver's voltage source is configured in such a way as to hold the high side gate controlled switch off during the turn on cycle until the driver output has overcome the negative bias generated across the high side switch gate, producing high immunity to spurious turn on. A digital isolator is connected between the inverting driver and a control signal for switching the inverter phase leg. A differential transmitter and differential receiver may be used to further increase noise immunity.

Abstract: An inverter phase leg for a DC-AC inverter includes a high supply line and a low supply line across which a DC voltage is provided. A high side gate controlled switch is connected to the high supply line and a low side gate controlled switch is connected to the low supply line, with an output node between the high side switch and the low side switch. An inverting driver is connected to the high side gate controlled switch. The inverting driver's voltage source is configured in such a way as to hold the high side gate controlled switch off during the turn on cycle until the driver output has overcome the negative bias generated across the high side switch gate, producing high immunity to spurious turn on. A digital isolator is connected between the inverting driver and a control signal for switching the inverter phase leg. A differential transmitter and differential receiver may be used to further increase noise immunity.

Abstract: A method for controlling the supply of power to a power system for an aircraft having a plurality of power-consuming components includes supplying power to the power system with a generator having a power output, determining a power requirement of the power system, and supplying the power to the power-consuming components.

Abstract: A power system for an aircraft having a plurality of power-consuming components, some of which have transient power requirements, which is greater than the average power requirement, the power system includes at least one generator, a power distribution buss, a non-battery power source, a battery power source, and a power controller selectively coupling the non-battery power source and the battery power source to the power distribution buss to satisfy the transient power requirements.