The invention belongs to the technical field of structural strength design, and discloses a helicopter blade pin fatigue life evaluation method considering folding and mooring overload, and the method comprises the following steps: 1, evaluating the blade pin load and fatigue damage of a blade in a folding state; 2, evaluating the load and fatigue damage of the blade pin under mooring overload; and 3, evaluating the fatigue life of the blade pin under the folding state superposition mooring overload.

    本发明属于结构强度设计技术领域,公开了一种考虑折叠和系留过载的直升机桨叶销疲劳寿命评估方法,步骤如下:步骤一:评估桨叶折叠状态下的桨叶销载荷及疲劳损伤;步骤二:评估系留过载下桨叶销载荷及疲劳损伤;步骤三:评估折叠状态叠加系留过载下的桨叶销疲劳寿命。


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    Title :

    Helicopter blade pin fatigue life evaluation method considering folding and mooring overload


    Additional title:

    考虑折叠和系留过载的直升机桨叶销疲劳寿命评估方法


    Contributors:
    CHENG XIONG (author) / ZHU MINFENG (author) / ZHENG RUNHAO (author) / MU JUNWU (author) / LIU MUDONG (author)

    Publication date :

    2025-01-03


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    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 / G06F ELECTRIC DIGITAL DATA PROCESSING , Elektrische digitale Datenverarbeitung



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