The invention discloses a rotor wing control mechanism for a coaxial helicopter. The mechanism comprises an outer shaft, an inner shaft, an inner and outer shaft supporting base, an outer automatic tilting device, an inner automatic tilting device, a middle ring, a third connecting device, a plurality of lower pull rods, a plurality of first connecting devices, a plurality of lower horizontal rods, a plurality of second connecting devices, a plurality of lower rotor wing
propeller hubs which are mounted on the
propeller hub head of the outer shaft, a plurality of upper rotor wing
propeller hubs which are mounted on the propeller hub head of the inner shaft, a plurality of upper rotor wing variable-
pitch rocker arms which are connected with the inner ends of the upper rotor wing propeller hubs, and a plurality of lower rotor wing variable-
pitch rocker arms which are connected with the inner ends of the lower rotor wing propeller hubs. Lower rotor wing control mechanisms are distributed into a helicopter body fairing and a lower rotor wing fairing, and upper rotor wing control mechanisms are distributed in a rotor wing shaft. Through the adoption of the mutual matching and control of the lower pull rods and long pull rods, the
synchronous control of the total distance, the differential
action control of the total distance, and the control of the cyclic variable
pitch for an upper rotor wing and a lower rotor wing can be realized through all parts.