FIELD: rocket construction.
SUBSTANCE: invention relates to rocketry and can be used for reusable return rocket and space systems able to perform controlled flights in the atmosphere. Return carrier rocket stage comprising a fuselage, oxidizer and fuel tanks, wings and at least one liquid propellant rocket engine, according to the invention four side units are attached to fuselage, in which there are gas-turbine engines and the oxidizer tanks, all the gas-turbine engines have a nozzle with a controlled thrust vector, the main combustion chamber and a gas generator connected to the main combustion chamber, in the upper part of the side units there are air intakes. Gas-turbine engine includes before the main combustion chamber an annular collector, whereto the gas duct is connected, and the annular collector cavity is connected with the air duct through holes or branch pipes. Annular collector is made perforated and installed inside the air duct. Main combustion chamber and the gas generator comprise at least one ignition device each. Gas generator is connected via the oxidizer and fuel pipelines with a turbo pump unit having pumps for fuel, the oxidizer and a turbine. Return carrier rocket stage comprises roll nozzles units fitted on the side units and connected by pipelines with the gas duct of one or several liquid-propellant rocket engines.
EFFECT: invention provides improved launching characteristics of the carrier rocket and simplified control system in the angles of pitch, yaw and roll.
8 cl, 19 dwg
