FIELD: transport.
SUBSTANCE: invention relates to VTOL aircraft. Proposed aircraft comprises axisymmetric airframe, fuel tank, instrumentation compartment, gas turbine engine arranged along airframe vertical axis and including compressor, combustion chamber, and jet nozzle. Engine segmented combustion chamber incorporates fuel systems including fuel rate regulator for every chamber section. Turbine comprises adjustable nozzle vanes, each being provided with drive. Adjustable distributor is arranged behind the compressor with every vane equipped with drive. Liquid-propellant rocket engine is mounted inside jet nozzle.
EFFECT: improved controllability.
9 dwg
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