The invention belongs to a helicopter blade vibration absorber fatigue test technology, and relates to a helicopter blade vibration absorber fatigue test device, which simulates the installation boundary condition of a helicopter blade vibration absorber, and applies a centrifugal force load and a shimmy force load to the helicopter blade vibration absorber to test the helicopter blade vibration absorber. The helicopter blade vibration absorber loading device simulates the real stress state of a helicopter blade vibration absorber on a helicopter, is simple in structure, good in economical efficiency and stable and reliable in working performance, can guarantee the loading precision, and can well meet the test requirements.

    本发明属于直升机桨叶吸振器疲劳试验技术,涉及一种直升机桨叶吸振器疲劳试验装置,模拟了直升机桨叶吸振器的装机边界条件,同时通过对直升机桨叶吸振器施加离心力载荷和摆振力载荷,模拟直升机桨叶吸振器在直升机上的真实受力状态,其结构简单、经济性好,且工作性能稳定可靠,能保证加载精度,可以很好的满足试验要求。


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    Title :

    Helicopter blade vibration absorber fatigue test device


    Additional title:

    一种直升机桨叶吸振器疲劳试验装置


    Contributors:
    ZHONG XIANGFU (author) / MA FENGTAO (author) / LUO WEI (author) / CAI MING (author)

    Publication date :

    2023-05-02


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    G01M TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES , Prüfen der statischen oder dynamischen Massenverteilung rotierender Teile von Maschinen oder Konstruktionen / 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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