The invention belongs to the technical field of aircraft spar fatigue test load spectrum design, and particularly relates to an aircraft spar fatigue test load spectrum design method, which comprises the following steps of: drawing stress spectrums of an upper edge strip and a lower edge strip of an aircraft spar under various working conditions; stress spectrums of the upper edge strip and the lower edge strip of the aircraft spar under various working conditions are converted into load spectrums at test loading points; carrying out inclusion analysis on the load spectrum at the test loading point under each working condition, and taking a numerical value with the maximum absolute value; a load spectrum at a test loading point is converted into a multi-stage constant-amplitude spectrum.

    本申请属于飞机翼梁疲疲劳试验载荷谱设计技术领域,具体涉及一种飞机翼梁疲劳试验载荷谱设计方法,包括:绘制飞机翼梁上缘条、下缘条在各种工况下的应力谱;将飞机翼梁上缘条、下缘条在各种工况下的应力谱,折算为试验加载点处的载荷谱;对试验加载点处的载荷谱,在各个工况下进行包容分析,取绝对值最大的数值;将试验加载点处的载荷谱,折算为多级等幅谱。


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    Title :

    Aircraft spar fatigue test load spectrum design method


    Additional title:

    一种飞机翼梁疲劳试验载荷谱设计方法


    Contributors:
    ZHAO TIANJIAO (author) / LEI XIAOXIN (author) / ZHANG YANJUN (author) / LI XIAOPENG (author)

    Publication date :

    2023-01-24


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    G06F ELECTRIC DIGITAL DATA PROCESSING , Elektrische digitale Datenverarbeitung / 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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