FIELD: ignition devices for liquid-propellant rocket engines. SUBSTANCE: proposed device has body where electric spark-plug is fitted centrally, reaction chamber narrowing towards outlet of combustion chamber, fuel delivery chamber and oxidizer supply manifold. Ignition device is also provided with mixing member inside which reaction chamber is formed and its outer surface if provided with auger. Oxidizer supply manifold is located at auger outlet on side of combustion chamber. Fuel delivery chamber is formed in bush forming under-plug which is connected via central hole made in bush with fuel delivery chamber and through holes made in bush around fuel delivery chamber, with reaction chamber of mixing member mounted at spaced relation on side of combustion chamber. EFFECT: possibility of starting the chamber working on non-hypergolic propellant components at low-energy of electric spark-plug discharge, at small pressure differential (0.2 to 0.4 kgf/sq.cm) at liquid propellant injection orifices. 1 dwg
