The invention relates to the technical field of aviation machine tests, in particular to a rotor wing distance adjusting structure of a helicopter test bed and an upper rotor wing assembly. The structure comprises an upper propeller hub, locating keys and a limiting pin. Axial sliding key grooves are formed in the inner wall of a mounting hole of the upper propeller hub, and the locating keys arranged on the outer wall of an inner shaft are vertically matched with the axial sliding key grooves in a sliding manner; when the upper propeller hub is mounted on the inner shaft, the locating keys axially enter the axial sliding key grooves, and then according to the needed rotor wing distance, the locating keys are screwed into peripheral locating key grooves in the side edges of the axial sliding key grooves to axially limit the locating keys; then, the limiting pin is inserted into the axial sliding key grooves, and therefore, the locating keys are circumferentially limited, and fixed mounting of the upper propeller hub and an upper rotor wing and the locking state of the upper propeller hub and the upper rotor in the rotating process are achieved; and in the mounting process, the locating keys on the outer wall of the inner shaft are matched with the circumferential locating keys respectively, the rotor wing distance can be adjusted according to actual needs, and pneumatic performance researches of a helicopter are facilitated.


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    Title :

    Rotor wing distance adjusting structure of helicopter test bed and upper rotor wing assembly


    Contributors:
    SHANG HONGXING (author) / LI SHU (author) / AN QIANGLIN (author) / LING AIMIN (author) / HE TIANPENG (author) / LI YUAN (author)

    Publication date :

    2015-09-16


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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