Abstract: A device for monitoring a life condition of a spark igniter in a gas turbine ignition system. The device includes an evaluation circuit having circuit components that include a hold capacitor, a transistor, and an operational amplifier arranged to form a sample-and-hold circuit, wherein an igniter spark impulse signal is applied to an input node of the evaluation circuit causing the transistor to turn on and the hold capacitor to discharge for a duration of the igniter spark impulse signal, and wherein a discharged voltage at the hold capacitor is maintained and output by the operational amplifier, the discharged voltage representing the duration of the igniter spark impulse and indicating the life condition of the spark igniter.

Abstract: A device for monitoring a life condition of a spark igniter in a gas turbine ignition system. The device includes an evaluation circuit having circuit components that include a hold capacitor, a transistor, and an operational amplifier arranged to form a sample-and-hold circuit, wherein an igniter spark impulse signal is applied to an input node of the evaluation circuit causing the transistor to turn on and the hold capacitor to discharge for a duration of the igniter spark impulse signal, and wherein a discharged voltage at the hold capacitor is maintained and output by the operational amplifier, the discharged voltage representing the duration of the igniter spark impulse and indicating the life condition of the spark igniter.

Abstract: A power supply unit that provides uninterrupted power to an aircraft power bus during switchovers of the aircraft bus from one power source to another. The power supply unit includes circuitry to distinguish between loss of bus power due to switchovers between power sources and loss of bus power due to shutdown of the aircraft. The power supply unit includes a low voltage lockout circuit to interrupt the supply of power when the aircraft bus voltage falls below a minimum value.

Abstract: A power supply unit that provides uninterrupted power to an aircraft power bus during switchovers of the aircraft bus from one power source to another. The power supply unit includes circuitry to distinguish between loss of bus power due to switchovers between power sources and loss of bus power due to shutdown of the aircraft. The power supply unit includes a low voltage lockout circuit to interrupt the supply of power when the aircraft bus voltage falls below a minimum value.