FIELD: rocket technology.
SUBSTANCE: group of inventions 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, a liquid-propellant engine (LPE) and at least two steering engines, in compliance with the invention two side units are attached to the fuselage, in which there are gas turbine engines (GTE) with a steering rocket engine installed inside the exhaust nozzle, the main combustion chamber and an auxiliary gas generator connected via a mixing collector to the main combustion chamber with a gas duct, and in the upper part of the side units are air intakes. In the gas duct there can be installed a ozonizer. Oxidizer and fuel supply to the auxiliary gas generator can be made through an additional turbo-pump unit (TPU), which includes an electric generator. Ozonizer can be installed inside the main combustion chamber immediately before the mixing collector. 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. Gas turbine engine includes before the main combustion chamber a connected with the gas duct an annular perforated collector installed inside the air duct. Gas turbine engine includes before the main combustion chamber an annular collector. Gas turbine engines can be equipped with a nozzle with controlled thrust vector. Disclosed is a method of a return carrier rocket stage operation, including its boosting on the active path by means of the LPE and controlling by means of the steering engines and return by means of two GTE, herewith the GTE are started in the rarefied atmosphere using the auxiliary gas generators operating with excess of the oxidizer and compensating the lack of atmospheric air for the GTE operation, the generator gas before feeding into the main combustion chamber is ozonized, and when flying in the dense atmosphere the auxiliary gas generators are switched off. Disclosed is a gas turbine engine with a compressor, the main combustion chamber, a turbine and an exhaust nozzle, herewith it contains a steering engine installed inside the exhaust nozzle, the main combustion chamber and an auxiliary gas generator connected with a gas duct via a mixing collector to the main combustion chamber with a gas duct. In the gas duct there can be installed a ozonizer. In the mixing collector an ozonizer is installed. In the air duct between the compressor and the main combustion chamber there is an ozonizer. Ozonizer can comprise two annular electrodes arranged coaxially on both sides of the mixing collector.
EFFECT: invention provides improved launching characteristics of the carrier rocket and simplified control system in the angles of pitch, yaw and roll and providing its operability at any height.
17 cl, 22 dwg
