Composite material is used in the wing structure of M2 light sport aircraft. The strength of the wing is verified by static test. It is of great significance to find the weak links in the wing structure design and the structural modification and development. Firstly, the requirements of strength airworthiness clause of ASTM F2245-16 wing are analyzed. Then, the composite wing loads are calculated by studying the load envelope, environmental impact factor, limiting load and ultimate load of M2 aircraft. Finally, the static test of wing limited load, wing ultimate load and wing damage load are carried out, and the test results are analyzed. The results show that the ultimate load of M2 aircraft meets the test requirements, the deviation of the damage load of composite wing test from the design limit load is 2%, and the structural design of composite wing of M2 aircraft meets the static strength design requirements.


    Access

    Download


    Export, share and cite



    Title :

    Static Strength Load and Experimental Study of Composite Wing of M2 Aircraft


    Contributors:
    Mao Yiqing (author) / Yang Fei (author) / Wang Le (author)


    Publication date :

    2019




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    Unknown




    Wing static load strength testing method

    TIAN YU / DAI CHUNXU | European Patent Office | 2023

    Free access

    Aircraft flexible wing static load type weighing equipment

    WANG ZHENG | European Patent Office | 2022

    Free access

    Aircraft wing load alleviation device and aircraft wing load alleviation method

    HIRABAYASHI DAISUKE / AKIBA KOUSABUROU | European Patent Office | 2020

    Free access

    AIRCRAFT WING LOAD REDUCTION DEVICE AND AIRCRAFT WING LOAD REDUCTION METHOD

    HIRABAYASHI DAISUKE / AKIBA KOSABURO | European Patent Office | 2019

    Free access

    AIRCRAFT WING LOAD ALLEVIATION DEVICE AND AIRCRAFT WING LOAD ALLEVIATION METHOD

    HIRABAYASHI DAISUKE / AKIBA KOUSABUROU | European Patent Office | 2019

    Free access