FIELD: machine building.
SUBSTANCE: ion-propellant engine comprises interconnected and coaxial combustion chamber and supersonic gas-dynamic nozzle. Combustion chamber comprises a head with an injector plate for spraying fuel components, a cylindrical part, and a convergent-divergent part, to which a magnetic plasma accelerator is connected. Supersonic gas-dynamic nozzle has convergent and divergent parts. Corona-forming electrode is installed on the plate in the internal cavity of the combustion chamber. Accelerating electrode is installed at output of magnetic accelerator inside it. Nozzle electrode is arranged at nozzle outlet end. Nozzle is made with cooling clearance along walls, clearance cavity is connected with fuel manifold installed concentrically to outlet end of nozzle. Between the "cold" and "hot" walls of the combustion chamber, the magnetic amplifier and the supersonic jet nozzle there is a cooling gap; injector nozzles of the propellant are installed on the injector plate, and the igniter is made in the form of a laser spark plug.
EFFECT: disclosed is an ionic rocket engine and a method of operation thereof.
6 cl, 3 dwg
