LIQUID-PROPELLANT THRUSTER Russian patent published in 2001 - IPC

FIELD: aircraft industry; thrust building devices. SUBSTANCE: two ring electrodes made of heat-resistant material are introduced additionally into combustion chamber of two-component liquid-propellant thruster. Inner diameter of ring electrodes is equal to inner diameter of combustion chamber. Electrodes are connected with corresponding current leads found in outer longitudinal slots of bushing, are insulated from housing, are brought out of housing and are connected to electric current source. Self-ignition components of rocket fuels are delivered under gauge pressure into engine chamber through nozzles in mixing head. Components are mixed and combustion in chamber. Heated combustion products flow out through reaction nozzle, thus creating thrust. At combustion products temperature of approximately 3.000 K dissociated elements featuring electric conductivity are present in combustion products. When electrodes are connected to external power supply source, ionization of combustion products takes place with formation and maintaining of arc discharge. EFFECT: possibility of supply of additional energy to combustion products with resulting increase of working medium temperature and specific impulse. 2 cl, 1 dwg