FIELD: engines and pumps.
SUBSTANCE: injection and ignition system for rocket engine includes the first and the second injection elements and discharge exciter assembly. The first injection element has conducting layer electrically connected to discharge exciter and non-conducting layer located on external part of conducting layer. The second injection element includes conducting material and has the hole passing through it and interconnected via fluid medium with combustion chamber. End of the first injection element is located at the hole in the second injection element or near this hole. Discharge exciter can create electric arc between electrically conductive layer of the first injection element and the second injection element. There proposed is version of design of injection system, as well as low-thrust rocket engine.
EFFECT: improving injection and ignition reliability of non-hypergol rocket propellant.
20 cl, 7 dwg
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