FIELD: transportation; aviation.
SUBSTANCE: return stage of a rocket vehicle comprises a body, oxidant and fuel tanks, wings, and at least one liquid propellant system and at least two control engines. Two side units with GTE are attached to the body. An ozone generator may be installed inside the main combustion chamber directly upstream a mixing header. The main combustion chamber may contain at least one ignition device. The method of operation of the return stage of the rocket vehicle includes its speed-up in the active area of the trajectory with the help of the LPS, control with the help of control engines and return with the help of two GTEs. GTEs are started in the rarefied atmospheric slices using auxiliary gas generators operating with excess oxidant and compensating lack of atmospheric air for GTE operation. Generator gas prior to supply to the main combustion chamber is ozonized. When flying in the dense atmospheric slices, auxiliary gas generators are switched off.
EFFECT: provision of reliable operation of a return stage and operation of GTE at high altitudes.
11 cl, 22 dwg
