The invention discloses a braking differential type rotor wing
propeller fixed wing helicopter. Two rotor wings are arranged on wing-shaped small towers at the head and the
tail of a
fuselage. The paddles of the rotor wings are connected with a rotor wing shaft through a
paddle shell which is provided with a
flapping hinge, a shimmy hinge and a variable-
pitch hinge. A total
pitch controller and aperiodic variable
pitch controller are arranged to control the
paddle pitch of the rotor wings. An upper single-wing
fixed wing with high
aspect ratio is arranged in the middle of the
fuselage, and variable-pitch propellers are arranged on the left and right of the
fixed wing. An engine is arranged to drive a differential mechanism through a gearbox and a
clutch. A first output shaft of the differential mechanism drives the two rotors through an overrunning
clutch, a universal shaft and a rotor synchronous reverser. A second output shaft of the differential mechanism drives the left and rightvariable-pitch propellers through an overrunning
clutch, a universal shaft and a
propeller synchronous reverser. A wheel type undercarriage is arranged, and different output shafts of the differentialmechanism are braked through a
brake. The power of the engine is distributed to the rotor wings or variable-pitch propellers, and various flight
modes of helicopters, fixed wings and autorotation rotor wings are freely switched. The helicopter has the advantages of being high in speed, low in
energy consumption and suitable for taking-off and landing occasions requiring no airports.