The invention belongs to the technical field of aircraft fatigue tests, and particularly relates to a full-aircraft fatigue test loading design method based on internal force and service life control. The minimum influence of a test loading scheme on stress/life is directly taken as a design optimization target, and the influence of a test centralized loading scheme on test assessment is quantified, so that the whole-aircraft fatigue test is closer to assessment verification under an external field actual flight load, and the test quality and the test result reliability are improved.

    本发明属于飞机疲劳试验技术领域,具体涉及一种基于内力与寿命控制的全机疲劳试验加载设计方法。直接以试验加载方案对应力/寿命的影响最小为设计优化目标,量化试验集中加载方案对试验考核的影响,使全机疲劳试验更加接近外场实际飞行载荷下的考核验证,提高试验质量和试验结果可靠性。


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    Title :

    Full-aircraft fatigue test loading design method based on internal force and life control


    Additional title:

    一种基于内力与寿命控制的全机疲劳试验加载设计方法


    Contributors:
    XIAO FENG (author) / ZHONG GUIYONG (author) / WANG FAN (author) / LIU XIAODONG (author) / DONG JIANG (author) / WANG YONGJUN (author)

    Publication date :

    2024-01-23


    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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