FIELD: transportation; aviation.
SUBSTANCE: rocket vehicle (RV) comprises at least one return stage with wings and a fin assembly, a service and a control propulsion systems. The service propulsion system is made in the form of at least one liquid propellant system and is installed in the lower part of the return stage body. The control propulsion system is made in the form of at least one GTE installed in parallel to the LPS. The return stage of the rocket vehicle comprises a body, oxidant and fuel tanks, wings, the fin assembly, at least one liquid fuel sustainer. At least one GTE is installed in the body with the controlled traction vector. The GTE combustion chamber is connected with a gas generator. The GTE may contain a ring header upstream the main combustion chamber. The system of helicopter pick-up of the return stage comprises a parachute, an engagement rope and a helicopter with a cargo runner with a hook at the end. A weight sensor may be installed in the upper part of the power rope.
EFFECT: ensuring serviceability of a gas turbine engine at high altitudes.
11 cl, 24 dwg
