The invention relates to an aircraft comprising a fuselage and at least
two substantially hollow cylindrical lifting bodies which are applied to
the fuselage and comprise a plurality of rotor blades which extend over
the periphery of the lifting bodies, the periphery of the lifting bodies
being partially covered by at least one tail surface. The aim of the
invention is to provide an aircraft with an extremely high degree of
maneuverability, compact dimensions and economy of fuel. To this end, the
lifting bodies are driven by at least one drive unit and respectively
comprise a cylindrical axis which is substantially parallel to a
longitudinal axis (1a) of the aircraft.