Ignition system for a combustion chamber of a turboshaft engine

An aircraft, comprising:

• at least one turboshaft engine, the at least one turboshaft engine including:
• a plurality of start-up injectors which lead into said combustion chamber and are configured to inject fuel into said chamber during a combustion-initiating phase;
• a start-up circuit configured to supply fuel to said start-up injectors;
• and
• a plurality of main injectors which lead into said combustion chamber and are configured to inject fuel into said combustion chamber so as to maintain the combustion once said combustion has been initiated by said start-up injectors;
• wherein said start-up circuit comprises:
• (i) a primary sub-circuit, configured to supply fuel to a subset of said plurality of start-up injectors;
• (ii) a secondary sub-circuit, configured to supply fuel to the remaining start-up injectors of said plurality of start-up injectors;
• wherein said primary sub-circuit and said secondary sub-circuit each comprise a start-up valve configured to be controlled by a control unit so as to allow or prevent the supply of fuel to said start-up injectors.