The invention relates to a high-lift-wing aircraft, belonging to the technical field of aviation. The high-lift-wing aircraft comprises a fuselage, an empennage, a left wing, a right wing, a left rotating vane device, a right rotating vane device, a left motor, a right motor, a towing force device and an undercarriage. The left wing and the right wing are the same in structure and are symmetrically arranged at the left and right sides of the fuselage. The left rotating vane device is mounted in a left groove. A main shaft of the left rotating vane device is connected with the left motor. A right rotating vane device and the left rotating vane device are the same in structure and working principle and are arranged symmetrically. The left motor and the right motor are the same and are mounted symmetrically. The left rotating vane device comprises a main shaft, a center half-tooth gear and three or four rotating vanes of the same structure. The transmission ratio of the center half-tooth gear to a vane gear is 1:1. When an arm shaft is located at a vertical position just above a main shaft, the rotating vanes and the arm shaft are in the same transverse vertical plane. Due to the left rotating vane device and the right rotating vane device, airflow over the upper surfaces of the left and right wings can be accelerated, and thus, the generation of lift is facilitated. The aircraft can achieve STOL (Short Take-Off and Landing) and aerial ultra-low-speed flight and is high in maneuverability and good in safety.


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    Title :

    High-lift-wing aircraft


    Contributors:

    Publication date :

    2015-04-01


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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