An ignition circuit and a method of operating an igniter (preferably a traveling spark igniter) in an internal combustion engine, including a high pressure engine. A high voltage is applied to electrodes of the igniter, sufficient to cause breakdown to occur between the electrodes, resulting in a high current electrical discharge in the igniter, over a surface of an isolator between the electrodes, and formation of a plasma kernel in a fuel-air mixture adjacent said surface. Following breakdown, a sequence of one or more lower voltage and lower current pulses is applied to said electrodes, with a low simmer current being sustained through the plasma between pulses, preventing total plasma recombination and allowing the plasma kernel to move toward a free end of the electrodes with each pulse.

In at least some implementations, an auxiliary power supply in an ignition system for a light-duty combustion engine includes a first auxiliary winding and a second auxiliary winding coupled in parallel with the first auxiliary winding such that both windings are arranged to provide power to an auxiliary load. The first auxiliary winding may include a greater number of turns than the second auxiliary winding. A ratio of the number of turns in the first auxiliary winding to the number of turns in the second auxiliary winding may be between 1.5:1 and 10:1, the first auxiliary coil and the second auxiliary coil may have between 50 and 2,000 turns, and the first auxiliary coil and the second auxiliary coil are formed from wire between 25 and 45 gauge.

In at least some implementations, an auxiliary power supply in an ignition system for a light-duty combustion engine includes a first auxiliary winding and a second auxiliary winding coupled in parallel with the first auxiliary winding such that both windings are arranged to provide power to an auxiliary load. The first auxiliary winding may include a greater number of turns than the second auxiliary winding. A ratio of the number of turns in the first auxiliary winding to the number of turns in the second auxiliary winding may be between 1.5:1 and 10:1, the first auxiliary coil and the second auxiliary coil may have between 50 and 2,000 turns, and the first auxiliary coil and the second auxiliary coil are formed from wire between 25 and 45 gauge.

In at least some implementations, a control and communication system for a light-duty combustion engine includes a circuit card, an ignition circuit carried by the circuit card and configured to control an ignition timing of the engine, and a short range wireless communication circuit carried by the circuit card. The communication circuit may include a Bluetooth Low Energy antenna. The ignition circuit may include an ignition capacitor that when drained induces an ignition pulse adapted to fire a spark plug. The system may further include a microprocessor that is coupled to and controls the ignition and communication circuits, and/or a clocking circuit adapted to provide a clocking frequency associated with the timing of the ignition circuit and associated with the communication circuit via a short range wireless communication protocol. The clocking circuit may include a crystal oscillator.

In at least some implementations, a control and communication system for a light-duty combustion engine includes a circuit card, an ignition circuit carried by the circuit card and configured to control an ignition timing of the engine, and a short range wireless communication circuit carried by the circuit card. The communication circuit may include a Bluetooth Low Energy antenna. The ignition circuit may include an ignition capacitor that when drained induces an ignition pulse adapted to fire a spark plug. The system may further include a microprocessor that is coupled to and controls the ignition and communication circuits, and/or a clocking circuit adapted to provide a clocking frequency associated with the timing of the ignition circuit and associated with the communication circuit via a short range wireless communication protocol. The clocking circuit may include a crystal oscillator.

An ignition device for an internal combustion engine with a charging coil, in particular disposed on a yoke core, with a starter wheel to induce a charging voltage in the charging coil by its rotation, with a first energy store which is connected to the charging coil via a rectifier, as well as with an electrical load which for its power supply, in particular during the starting process of the internal combustion engine is connected to a second energy store, wherein the second energy store is connected to the first energy store via a voltage converter. Furthermore, the invention relates to an internal combustion engine with such an ignition device and a method for its operation.

An internal combustion engine for an aircraft can include a crankshaft configured to drive a propeller; a camshaft coupled to the crankshaft; and an ignition controller coupled to the camshaft and including a visual indicator, the visual indicator configured to produce a visual signal at a predetermined angular position of the engine. An ignition controller for an internal combustion engine can include a housing and a P-lead connection extending from the housing, the ignition controller configured to selectively supply or cut main electrical power from the engine via the P-lead connection, the ignition controller also configured to selectively supply its own power.

An internal combustion engine for an aircraft can include a crankshaft configured to drive a propeller; a camshaft coupled to the crankshaft; and an ignition controller coupled to the camshaft and including a visual indicator, the visual indicator configured to produce a visual signal at a predetermined angular position of the engine. An ignition controller for an internal combustion engine can include a housing and a P-lead connection extending from the housing, the ignition controller configured to selectively supply or cut main electrical power from the engine via the P-lead connection, the ignition controller also configured to selectively supply its own power.

An internal combustion engine for an aircraft can include a crankshaft configured to drive a propeller; a camshaft coupled to the crankshaft; and an ignition controller coupled to the camshaft and including a visual indicator, the visual indicator configured to produce a visual signal at a predetermined angular position of the engine. An ignition controller for an internal combustion engine can include a housing and a P-lead connection extending from the housing, the ignition controller configured to selectively supply or cut main electrical power from the engine via the P-lead connection, the ignition controller also configured to selectively supply its own power.

An ignition control system includes a spark plug including a cylindrical ground electrode, a cylindrical insulator having a protruding portion held inside the ground electrode and protruding toward a tip side the spark plug relative to the ground electrode, and a center electrode held inside the insulator and exposed from the insulator, an ignition coil including a primary coil and a secondary coil, and a primary current control unit performing creeping discharge control for generating a creeping discharge along a surface of the insulator, and air discharge transition control for stopping the creeping discharge occurring in the spark plug after the creeping discharge control is performed, and cutting off primary current after a discharge stop period ends, in one combustion cycle of the engine.