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对含低速冲击损伤的蜂窝夹芯板试件进行了拉伸试验,用X光技术、热揭层技术和外观检测等对拉伸破坏过程进行了研究,分析了剩余拉伸强度与冲击能量的关系.结果表明:拉伸过程中,四种破坏形式同时存在且相互作用;冲击损伤严重影响了蜂窝夹芯板的抗拉能力.

参考文献

[1] 程小全, 寇长河, 郦正能. 复合材料蜂窝夹芯板低速冲击损伤研究.,1998,15(3):119~123
[2] 中国航空研究院编. 复合材料飞机结构耐久性/损伤容限设计指南. 北京:航空工业出版社,1995
[3] Palm T E. Impact resistance and residual compression strength of composite sandwich panel. In: Honolulu H I, Covina C A, eds. Composites: Design, Manufacture, and Application; Proceedings of the 8th International Conference on Composite Materials (ICCM/8). Society for the Advancement of Material and Process Engineering, 1991, 3-G-1~14
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[6] Chang K Y, Liu S, Chang F K. Damage tolerance of laminated composites containing an open hole and subjected to tensile loadings. J of Composite Materials, 1991, 25: 274~301
[7] Abrate S. Impact on laminate composite materials. Applied Mechanics Review, 1991, 44(4): 155~190
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