NOZZLE FOR ROCKET ENGINE Russian patent published in 1995 - IPC

FIELD: rocket engineering. SUBSTANCE: nozzle for rocket engine consists of supersonic nozzle 1 wherein deflector 4 is coaxially mounted. The deflector is made up as a streamlined conical body. Pairs of electrically discharging electrodes 5 are uniformly arranged over the circular cross-section. The electrodes are incorporated in the multi-phase system of dischargers, two pairs of electrodes 5 by each phase, and arranged from the opposite faces of deflector 4 and connected with a source in accordance with the number of the phase of the discharger through thyristor circuit for generating discharges of controlled frequency. When power is supplied to the dischargers, shock waves are created around the dischargers in the flow of working fluid of nozzle 1 which is in operation. After reflecting from the surface of nozzle 1 the shock waves form common front of a shock wave in the direction of the outlet of nozzle 1, the jet being accelerated. EFFECT: enhanced efficiency. 3 dwg