| 摘要 |
A device for igniting an aircraft engine, comprising at least two spark plugs, the device comprising a power supply, a first path for supplying a first spark plug with power and a second path for supplying a second spark plug with power, said paths being connected to the power supply by distribution means of the power supply which are controlled by a FADEC-type control system, wherein said distribution means comprise a first circuit that is configured to alternately supply said first path or said second path with power, and a second circuit for simultaneously supplying said first and second paths with power, the device being configured to use either the first circuit or the second circuit during start-up. |
