The invention relates to a ducted coaxial helicopter control mechanism, which aims at solving the flight
coupling problem of ducted coaxial helicopters, and realizes the
control effect of obtaining single output by single input. According to the control mechanism, an upper and a lower rotor systems are distributed at the middle part of a helicopter body; the upper and the lower rotors are provided with three control channels respectively, that is, two more channels are provided than a common ducted coaxial helicopter; the six control channels are respectively collective
pitch synchronous control, collective
pitch differential control, vertical periodic variable
pitch synchronous control, vertical periodic variable pitch differential control, horizontal periodic variable pitch
synchronous control, horizontal periodic variable pitch differential control; the
forward speed, lateral speed, vertical speed,
pitch angle, roll angle, and course angle of an aircraft can be controlled individually. The control mechanism offsets
coupling caused by control through symmetry, realizes decoupling control; an aircraft with the decoupling
control system solves the control
coupling problem of few input and excessive output by a
control mode of six freedom degrees, and the control of the aircraft becomes simpler. The control mechanism has wide application prospects in military and civil fields.