采用热塑性颗粒对HT7/5228、HT3/NY9200G和HT3/5224三种高温固化环氧基体复合材料层压板进行层间增韧.为了提高冲击后压缩强度(CAI)和考察损伤阻抗,测试了平均分层起始能量eⅡc以及接触力-凹坑深度关系.试验结果表明,增韧颗粒和基体树脂形成的层间区域能有效地吸收断裂能量并抑制分层的发生,eⅡc显著提高.在静压痕力下,层间增韧复合材料层压板具有较深的凹坑深度和较小的损伤面积.层间增韧的几何效应、裂纹传播路径控制、颗粒桥联以及裂尖屏蔽是主要的增韧机理,颗粒的塑性变形和最终失效也耗散了大量断裂能量.
参考文献
[1] | Odagiri N, Muraki T, Tobukuro K. Toughness improved high performance torayca prepreg T800H/3900 series[A]. In: Gilberto C E D, Newell W D, Brown P P, eds. Proceedings 33rd International SAMPE Symposium[C]. Covina, CA: Society for the Advancement of Material and Process Engineering, 1988. 272-283. |
[2] | Odagiri N, Kishi H, Nakae H. T800H/3900-2 toughened epoxy prepreg system: Toughening concept and mechanism[A]. In: Proc of the 6th Conf of the American Society for Composites[C]. New Yoke: America Society for Composite, 1991. 43-52. |
[3] | Groleau M R, Shi Y B, Yee A F, et al. Mode Ⅱ fracture of composites interlayered with nylon particles[J]. Composites Science and Technology, 1996, 56(11):1223-1240. |
[4] | Sue H J, Jones R E, Garcia-Meitin E I. Fracture behaviour of toughened composites under mode Ⅰ and mode Ⅱ delamination[J]. Journal of Materials Science, 1993, 28:6381-6391. |
[5] | Volker A, Dale G, Michael S. Interlaminar crack growth in third-generation thermoset prepreg system[J]. Polymer, 1993, 34(4): 907-909. |
[6] | National Materials Advisory Board. New Materials for Next-Generation Commercial Transport[M]. Washington D C: National Academy Press, 1996. 38. |
[7] | Greenhalgh E S, Hiley M J. The assessment of novel materials and processes for the impact tolerant design of stiffened composite aerospace structures[J]. Composites Part A, 2003, 34(2):151-161. |
[8] | Nettles A T, Douglas M J. A comparison of quasi-static indentation to low-velocity impact[R]. NASA/TP-2000-210481. Springfield: NASA, 2000. |
[9] | Yang X, Shen Z, Yan Y, et al. New methodology for evaluation toughness of composite laminates-investigation of da-mage resistance [J]. Chinese Journal of Aeronautics, 2003,16(2):73-79. |
[10] | ASTM D6264-98. Standard test method for measuring the damage resistance of a fiber-reinforced polymer-matrix composite to a concentrated quasi-static indentation force[S]. |
[11] | 张彦中,宁荣昌.复合材料层合板抗冲击损伤的参数表征[J].航空材料学报,1995,15(1): 56-62.Zhang Y Z, Ning R C. The characterizing parameters of impact resistance damage composite laminates[J]. Journal of Aeronautical Materials, 1995, 15(1): 56-62. |
[12] | Duarte A, Herszberg I, Paton R. Impact resistance and tolerance of interleaved tape laminates[J]. Composite Structure, 1999, 47(1-4): 753-758. |
[13] | Kageyama K, Kimpara I, Ohsawa I, et al. Mode Ⅰ and mode Ⅱ delamination growth of interlayer toughened carbon/epoxy (T800H/3900-2) composite system[A]. In:Martin R H, ed. Composite Materials: Fatigue and Fracture[C]. Philadelphia: American Society for Testing and Materials, 1995. 19-37. |
[14] | Dejan S. Delamination properties of a vinyl-ester/glass fibre composite toughened by particulate-modified interlayers[D]. Canberra: Department of Engineering, Australian National University, 2001. |
[15] | Pearson R A. Toughening Epoxies Using Rigid Thermoplastic Particles[A]. In: Keith C R, Antony J K, eds. Toughened Plastics Ⅰ[C]. Washington D C: American Chemical Society, 1993. |
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