FIELD: aviation.
SUBSTANCE: proposed method is used for forming flow over propeller blades at thickness ratio of 4-6% by increase of rotational speed of lifting propeller to magnitude of tip speed exceeding the sonic speed. Aero-space system includes aircraft stage 1, space stage 2 and alighting column with swivel brackets. Fuselages of stages are interconnected by means of coupling unit 3. Aircraft stage 1 has fuselage, wing 4, high-lift devices, power plant 7 and coaxial propeller. Each blade of coaxial propeller is mounted in hub by means of flexible spar 9 wound on drum which is connected with hub by means of clamp and lag hinge. Fuselage is provided with swivel stops of alighting gear. Space stage 2 has payload container, elevator and rudder.
EFFECT: reduced mass.
3 cl, 4 dwg
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