Showing 1 - 6 results of 6 for search 'CHEN XiangMing', query time: 0.03s Refine Results
  1. 1
    DAMAGE EXPANSION OF STIFFENED PANEL WITH PREFABRICATED DEBONDING

    DAMAGE EXPANSION OF STIFFENED PANEL WITH PREFABRICATED DEBONDING by ZHANG Ru, CHAI YaNan, ZHANG Aying, CHEN XiangMing

    Published 2020-01-01
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    Article
  2. 2
    LOAD TRANSFER ANALYSIS IN BONDED-BOLTED HYBRID JOINTS

    LOAD TRANSFER ANALYSIS IN BONDED-BOLTED HYBRID JOINTS by CHEN XiangMing, CHAI YaNan, YUAN Fei, YU Fei, CAO Su

    Published 2017-01-01
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  3. 3
    STIFFENER-SKIN INTERFACE FAILURE CHARACTERIZATION OF THE STIFFENED COMPOSITE PANEL AT POST-BUCKLING STAGE

    STIFFENER-SKIN INTERFACE FAILURE CHARACTERIZATION OF THE STIFFENED COMPOSITE PANEL AT POST-BUCKLING STAGE by HU BoTao, CHAI YaNan, CHEN XiangMing, WEI JingChao

    Published 2019-01-01
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  4. 4
    INTERNAL CLADDING LAYER INFLUENCE ON THE DEBONDING OF HAT-STRINGER STIFFENED COMPOSITE PANELS UNDER AXIAL COMPRESSION (MT)

    INTERNAL CLADDING LAYER INFLUENCE ON THE DEBONDING OF HAT-STRINGER STIFFENED COMPOSITE PANELS UNDER AXIAL COMPRESSION (MT) by YUAN Fei, LIU Fu, CHAI YaNan, CHEN XiangMing, LIN GuoWei, LI XinXiang

    Published 2022-01-01
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  5. 5
    INVESTIGATION OF REPAIR TECHNIQUE FOR AIRCRAFT COMPOSITE WING PANEL WITH DISCRETE-SOURCE DAMAGE

    INVESTIGATION OF REPAIR TECHNIQUE FOR AIRCRAFT COMPOSITE WING PANEL WITH DISCRETE-SOURCE DAMAGE by CHEN XiangMing, ZHANG AYing, CHAI YaNan, LIU HongWu, WANG LiLi, YU Fei

    Published 2017-01-01
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  6. 6
    ASSESSMENT METHOD OF THE REPAIRED AIRCRAFT COMPOSITE WING PANEL WITH DISCRETE-SOURCE DAMAGE

    ASSESSMENT METHOD OF THE REPAIRED AIRCRAFT COMPOSITE WING PANEL WITH DISCRETE-SOURCE DAMAGE by CHEN XiangMing, ZHANG AYing, CHAI YaNan, LIU HongWu, WANG LiLi, YU Fei

    Published 2017-01-01
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