对T300/QY8911复合材料层板进行了低速冲击、 冲击后压缩以及冲击后疲劳试验研究。通过对冲击后的层板进行目视检测和超声C扫描获得了层板受低速冲击后的若干损伤特征; 在压-压疲劳试验中, 测量了损伤的扩展情况。讨论了冲击能量与损伤面积以及冲击后剩余压缩强度的关系, 分析了含冲击损伤层合板在压缩载荷及压-压疲劳载荷下的主要破坏机制。结果表明, 低速冲击损伤对该类层板的强度和疲劳性能影响很大, 在3.75 J/mm的冲击能量下, 层板剩余压缩强度下降了65%; 在压-压疲劳载荷作用下, 其损伤扩展大致可分为两个阶段, 占整个疲劳寿命约60%的前一阶段损伤扩展较为缓慢; 而疲劳寿命的后半阶段损伤则开始加速扩展, 并导致材料破坏。
Residual compressive strength and compression-compression fatigue tests of T300/QY8911 laminates with low velocity impact damage were studied. The damage characteristic of impacted laminates was measured by visual check and ultrasonic C-scan. Damage propagation in compression-compression fatigue test was measured in detail. The relationship between damage area, compressive strength after impact (CAI) and impact energy was discussed. The major damage mechanism of damaged composites under compressive or compression-compression fatigue load was also analyzed. The results show that low velocity impact damage has a great effect on the compressive strength and fatigue performance of laminates, residual compressive strength reduces by 65% when the laminates is impacted by energy of 3.75 J/mm. The damage propagation under compression-compression fatigue load can divide in two stages, on the first 60% of fatigue life, damage grows slowly; and on the rest of fatigue life, damage has a rapid growth.
参考文献
| [1] | Milan M, Hahn H T, Greg P C, et al. Effect of loading parameters on the fatigue behavior of impact damaged composite laminates [J]. Composites Science and Technology, 1999, 59(14): 2059-2078. |
| [2] | Melin I.G, Sehon J. Buckling behaviour and delamination growth in impacted composite specimens under fatigue load: An experimental study [ J ]. Composites Science and Technology, 2001, 61 (13) : 1841 - 1852. |
| [3] | Melin L (-;, Schon J, Nyman T. Fatigue testing and buckling characteristics of impacted composite specimens [ J ]. International Journal of Fatigue, 2002, 24: 263-272. |
| [4] | Chen A S, Almond D P, Harris B. Impact damage growth in composites under acoustography [J].24: 257-261. fatigue conditions International Journal monitored by of Fatigue, 2002,. |
| [5] | Kang K W, Kim J K. Fatigue life prediction of impacted carbon/epoxy laminates under constant amplitude loading [J]. Composites Part A; Applied Science and Manufacturing, 2004, 35(5): 529-535. |
| [6] | Butler R, Almond D P, Hunt G W, et al. Compressive fatigue limit of impact damaged composite laminates [J]. Composites Part A: Applied Science and Manufacturing, 2007, 38: 529- 535. |
| [7] | Uda N, Ono K, Kunoo K. Compression fatigue failure of CFRP laminates with impact damage[J].Composites Science and Technology, 2009, 69(14): 2308-2314. |
| [8] | 熊峻江,寇长河,程小全,等.光滑与含孔复合材料压一压疲劳实验研究[J].复合材料学报,1998,15(3):99一102. |
| [9] | 徐颖,温卫东,崔海涛.复合材料层合板冲击后压一压疲劳寿命预测方法[J].复合材料学报,2007,24(2):159-167. |
| [10] | NASA RP21142. Standard tests {or toughened resin composites[S]. 1985. |
| [11] | 中国航空工业总公司.HB6739-1993,碳纤维复合材料层合板冲击后压缩试验方法[S].北京:中国航空工业总公司第三О一研究所,1993. |
| [12] | 柴亚南,沈真,李顺和.复合材料层压板疲劳特性的试验研究[J].航空学报,1991,12(12):643-646. |
| [13] | 矫桂琼,卢智先,潘文戈,等.分层缺陷对复合材料层压板疲劳性能的影响[J].机械强度,1998,20(2):142-144. |
- 下载量()
- 访问量()
- 您的评分：
-
10%
-
20%
-
30%
-
40%
-
50%