FIELD: machine building.
SUBSTANCE: plasma rocket engine comprises interconnected coaxial combustion chamber consisting of ignition and combustion chamber of propellant and oxidant fuel components and having propellant supply nozzles and an oxidiser and a divergent toroidal portion, to which a magnetic plasma accelerator is connected, and a supersonic gas-dynamic nozzle with convergent torus and conical divergent parts. Corona-forming electrodes are arranged on torus divergent part of the chamber.
EFFECT: chamber and nozzle have cooling gap along walls, clearance cavity is connected with fuel manifold on nozzle lower end, and igniters are made in form of laser spark plugs.
3 cl, 2 dwg
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