The invention relates to a whole aircraft drop simulation predication and testing method. The method comprises whole aircraft drop simulation predication analysis and whole aircraft drop test; a drop height and a pitch angle of a whole aircraft are obtained and are used as state parameters of the whole aircraft drop test; the whole aircraft drop test is carried out according to theoretical simulation predication so as to obtain an acceleration impact environment capable of being borne by equipment on the aircraft in a landing impact process, and provide important test evidences to check the accuracy of test technological conditions of a landing impact mechanical environment; meanwhile, whether indications including designed routes and the like of an undercarriage buffering system under the landing impact environment meet the requirements or not is realized; when a whole aircraft is at an electrified closed loop working state of a GNC (Global Navigation Chart) system, the GNC system has adaptability to a landing large-impact load environment, and important guarantees are provided for the success of an aircraft flying verification test.


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    Title :

    Whole aircraft drop simulation predication and testing method


    Contributors:
    HE YONGMEI (author) / HAI ERHAN (author) / CHEN HONGBO (author) / CAO XIAORUI (author) / ZHANG JIAXIONG (author) / ZHANG HUASHAN (author) / YANG YONG (author) / PENG XIAOBO (author) / LI ZHIPING (author) / HUANG YUQIU (author)

    Publication date :

    2015-05-27


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    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



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