The invention relates to a balance test system of a four-rotor aircraft. The balance test system comprises a rotor test device, an accelerator drive proportion measuring module, a pressure test device, an acceleration sensor and a processor. The accelerator drive proportion measuring module, the pressure test device and the acceleration sensor are all connected with the processor through a line, and the pressure test device and the acceleration sensor are both arranged on the rotor test device; the processor is connected with an outer computer system through a line; and the aircraft required to be tested is placed on the rotor test device. Compared with the prior art, the balance test system is simple in structure and low in cost, aircrafts in different sizes can be tested, and a real-time lift test and a balance test of the aircraft can be carried out.


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    Title :

    Balance test system of four-rotor aircraft


    Contributors:
    JING BENQIN (author) / GE RENHUA (author) / LIU GANGLING (author) / ZHAN JIALI (author)

    Publication date :

    2015-11-25


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen



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