FIELD: engines and pumps.
SUBSTANCE: proposed method consists in that closed chamber is filled at normal pressure and temperature with metastable fluid made up of homogeneous mix of liquid fuel, oxidiser and ballast, to be subjected to electrolysis between electrodes separated by porous material at temperature controlled conditions in presence of electrically conducting and catalytic additives. Produced higher enthalpy gassy detonating mix saturated by gaseous fuel and oxidiser is throttles in foamed state into slotted nozzle for catalytic combustion of superheated metastable fluid and heating of gaseous propulsive jet. Produced two-phase flow is subjected to mechanical effects to form fine propulsive jet. Rocket closed combustion chamber communicates with the nozzle via sealing element, for example, rubber plug, a wad, fitted in throttling tube inner end, said tube being secured in metal chamber convergent section with slotted nozzle secured therein and made up of conical spring made from elastic metal strip. Rocket start-charge device comprises base with guide device to mount the rocket. Box-like base is made from electrical-insulating material and equipped with metal covers and isolating bush of guide rod with slightly conical base. Rocket chamber throttling tube is fitted on said base and electrically connected via slotted nozzle with one of the poles of electric current source. Another pole is connected via inductor and limiting resistor with guide rod base.
EFFECT: higher specific thrust pulse, simplified design and start-charge process.
8 cl, 1 dwg
