FIELD: transport.
SUBSTANCE: invention relates to aircraft engineering, particularly, to various-purpose light small-size drone aircraft. Proposed drone aircraft comprises fuselage 1, wings 2, control surfaces 3 and power plant 4 with annular air intake 5, combustion chamber 6 and nozzle apparatus 7. Resonator 8 is arranged in fuselage nose. Said resonator has sharp saw-like inlet edge 9 and perforated side and face walls 10 communicated via adjustable perforations with hydrogen generator 11 of fuel cartridge 12. Incoming flow power is partially consumed for hydrogen generation, its heating, dissociation, and recovery in combustion chamber 6 and nozzle apparatus 7. Due to lower mean molecular mass of hydrogen containing gas in fuselage boundary layer, viscosity and friction are reduced.
EFFECT: lower weight, reduced sizes, improved operating performances.
3 cl, 1 dwg
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