The invention belongs to the technical field of aircraft wing fatigue tests, and particularly relates to an aircraft wing fatigue test follow-up control system and method, and the method comprises the steps: detecting a rotation angle signal of an aircraft wing, and obtaining the rotation angle of the aircraft wing; corresponding to the rotation angle of the aircraft wing, the force control actuating cylinder is controlled to stretch out and draw back, so that the follow-up frame rotates to the corresponding rotation angle.

    本申请属于飞机翼疲劳试验技术领域,具体涉及一种飞机翼疲劳试验随动控制系统及其方法,其中,飞机翼疲劳试验随动控制方法,包括:检测飞机机翼的转动角度信号,得到飞机机翼转动角度;对应于飞机机翼转动角度,控制力控作动筒伸缩,使随动框架转动到对应的转动角度。


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    Titel :

    Aircraft wing fatigue test follow-up control system and method thereof


    Weitere Titelangaben:

    一种飞机翼疲劳试验随动控制系统及其方法


    Beteiligte:
    LIU ZHENYU (Autor:in) / ZHENG JIANJUN (Autor:in) / MAO SHUANG (Autor:in) / MU BIN (Autor:in) / LI XIAONING (Autor:in) / SHENG KAI (Autor:in)

    Erscheinungsdatum :

    20.09.2022


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    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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