FIELD: engines and pumps.
SUBSTANCE: proposed engine comprises structural frame, combustion chamber with head, cylindrical section and controlled nozzle with extending tip, suspension assembly to allow driven swinging in to planes, drives secured to power ring arranged on combustion chamber, gas generator and turbo pump assembly including, in its turn, turbine, oxidiser pump, fuel pump, and gas duct communicating turbine outlet with combustion chamber head via suspension assembly. In compliance with this invention, is differs from known designs in that bank nozzles are grouped into pairs and fitted on lower power ring mounted on nozzle lower section and connected with nozzle edge. Gas generator gas fee pipelines are connected via gas and fuel three-way valves to bank nozzles. Opposite ends of gas generator are connected by gas bleed pipeline and fuel pipelines. Note here that bank nozzle units are secured on lower power ring attached to extending tip. Bank nozzle unit comprises two bank nozzles integrated in one unit. Note here that said unit includes three-way gas and fuel valves fitted between said nozzles and provided with common drive. All nozzles are equipped with ignition device.
EFFECT: higher reliability of thrust vector and rocket bank control.
3 cl, 5 dwg
