FIELD: rocket engines.
SUBSTANCE: method to control ratio of components in hybrid propellant rocket engine includes control of delivery of liquid component by pneumohydraulic system. Mass flow of solid-phase component of propellant is changed by control of acting value of electric current passed through reaction zone of gasification. Current is passed through gasification reaction zone by means of system of foil-type or gauze metal electrodes installed in solid-phase component of propellant. Ratios of flows of combustible and oxidizing components of propellant at different modes of engine operation are maintained within tolerable range.
EFFECT: provision of optimum relation between flows of propellant and oxidizer in combustion chamber when adjusting thrust of hybrid propellant rocket engine.
1 dwg
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