Abstract: A solid state spark device that operates as a two terminal spark gap in a CDI exciter of an aircraft ignition system. The device includes a triggering transformer, a triggering circuit, and a control circuit. The triggering circuit is electrically connected to a first coil of the transformer and includes circuit elements connected to supply current to the first coil upon charging of the triggering circuit up to a triggering voltage. This current through the first coil of the triggering transformer induces an output in a second coil of the transformer. The control circuit is electrically connected to the second coil and includes a switch controlled by the output from the second coil. The switch, when activated by the triggering circuit, discharges energy from the exciter into an igniter of the aircraft ignition system.

Abstract: A solid state spark device that operates as a two terminal spark gap in a CDI exciter of an aircraft ignition system. The device includes a triggering transformer, a triggering circuit, and a control circuit. The triggering circuit is electrically connected to a first coil of the transformer and includes circuit elements connected to supply current to the first coil upon charging of the triggering circuit up to a triggering voltage. This current through the first coil of the triggering transformer induces an output in a second coil of the transformer. The control circuit is electrically connected to the second coil and includes a switch controlled by the output from the second coil. The switch, when activated by the triggering circuit, discharges energy from the exciter into an igniter of the aircraft ignition system.

Abstract: An aircraft ignition system having a power circuit, a control circuit, and a discharge circuit and coupled to the spark plugs of an aircraft engine. The power circuit may include two independent power sources; e.g., alternator power (such as a permanent magnet alternator) and power from aircraft or DC power bus. The control circuit may control one or more aspects of the discharge circuit, e.g., the ignition timing. And the discharge circuit may trigger a capacitive discharge ignition event to the spark plugs.

Abstract: A switching assembly is disclosed for a high voltage aircraft ignition system. The switching assembly includes a ceramic substrate and switch die that includes an anode bonded to an electrical pad on the ceramic substrate. The switch die includes a semiconductor device having a plurality of interleaved gates and cathodes, and includes a ceramic cap having at least one gate pad connected to the gates and at least one cathode pad connected to the cathodes. The switching assembly includes leads connected to the gate pad, the cathode pad, and the electrical pad on the substrate. The switch die and a portion of the leads are potted to form the completed assembly.

Abstract: A switching assembly is disclosed for a high voltage aircraft ignition system. The switching assembly includes a ceramic substrate and switch die that includes an anode bonded to an electrical pad on the ceramic substrate. The switch die includes a semiconductor device having a plurality of interleaved gates and cathodes, and includes a ceramic cap having at least one gate pad connected to the gates and at least one cathode pad connected to the cathodes. The switching assembly includes leads connected to the gate pad, the cathode pad, and the electrical pad on the substrate. The switch die and a portion of the leads are potted to form the completed assembly.

Abstract: An inductive ignition circuit (10) especially adapted for use with micro-turbine and other small-sized turbine engines such as are used in electric generators. The inductive ignition circuit (10) includes a flyback transformer (14), a drive circuit (16) for energizing the primary (22) of the transformer (14), and a control circuit (18) that temporarily disables the drive circuit (16) once the transformer primary (22) has been sufficiently energized. The drive circuit includes a switching transistor (20) which is biased on to draw current through the primary (22). The control circuit (18) includes two feedback circuits (42,44), one of which initiates disabling of the transistor (20) to cause the transformer flyback and the second of which sets the spark rate. The first feedback circuit (42) monitors the primary current and disables the transistor (20) once the current exceeds a pre-selected level.

Abstract: An improved turbine engine ignition exciter circuit. Energy stored in an exciter tank capacitor is subsequently switched to the load (igniter plug) through a novel thyristor switching device specifically designed for pulse power applications. The switching device is designed and constructed to include, for example, a highly interdigitated cathode/gate structure. The semiconductor switching device is periodically activated by a trigger circuit which may be comprised of either electromagnetic or optoelectronic triggering circuitry to initiate discharge of energy stored in exciter tank capacitor to mating ignition lead and igniter plug. Likewise, the present invention allows new flexibility in the output PFN (Pulse Forming Network) stage, eliminating need for specialized protective output devices such as saturable output inductors. Due to considerably higher di/dt performance of the device, true high voltage output pulse networks may be utilized without damage to the semiconductor switching device.