| 摘要 |
The invention relates to an aircraft comprising a fuselage (1) and at least two essentially hollow cylindrical lifting bodies (2, 3, 4, 5) which are applied to the fuselage (1) and comprise a plurality of rotor blades (8) whi ch extend over the periphery of the lifting bodies (2, 3, 4, 5), the periphery of the lifting bodies (2, 3, 4, 5) being partially covered by at least one tail surface (49, 50). The aim of the invention is to provide an aircraft with an extremely high degree of manoeuvrability, compact dimensions and economy of fuel. To this end, the lifting bodies (2, 3, 4, 5) are driven by at least on e drive unit and respectively comprise a cylindrical axis which is essentially parallel to a longitudinal axis (1a) of the aircraft.
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