Braking differential type rotor wing propeller fixed wing helicopter

Abstract

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.

Description

technical field [0001] The invention relates to a braking differential rotor propeller fixed-wing helicopter that can be pulled by a propeller and fly forward by taxiing at an airport, or can vertically lift, hover, and fly forward, backward, left, and right with multi-rotors independent of the airport. Background technique [0002] At present, there are known successful methods that can realize helicopters that can use the airport to slide forward, or can not rely on the airport to adopt multi-rotor vertical lift, hover, front, back, left, and right. The successful method is the tilt rotor, which has the advantage of large load capacity and horizontal flight. The speed is fast, and its disadvantage is that the rotor is set at both ends of the fixed wing, which requires high strength of the spar, and the rapid tilting of the huge rotor produces a large gyro force, which requires high strength of the tilting mechanism, and the horizontal structure of the rotor is easy The vor...

AI Technical Summary

Problems solved by technology

[0002] At present, there are known successful methods that can realize the helicopter that can use the airport to slide forward, or can not rely on the airport to adopt multi-rotor vertical lift, hover, front, back, left, and right flight. The tilt rotor has the advantage of large load capacity and horizontal flight. The speed is fast, and its disadvantage is that the rotor is set at both ends of the fixed wing, which requires high strength of the spar, and the rapid tilting of the huge rotor produces a large gyro force, which requires high strength of the tilting mechanism, and the horizontal structure of the rotor is easy. The vortex ring effect is generated and rolls to one side, causing accidents. The flight efficiency of the large propeller rotor is low

Images