Comparision of vibration fatigue behaviors of 2.5D woven composites in warp and weft directions
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摘要: 2.5D机织复合材料抗分层、耐冲击，在航空发动机结构上具有巨大的应用前景。本文对一种2.5D机织碳纤维增强双马树脂基复合材料经向和纬向试件，开展了不同名义应力水平下的一阶弯曲共振疲劳试验。试验结果表明：经向试件的振动疲劳性能优于纬向试件，随着应力水平的提高，经向和纬向试件的寿命明显缩短，而固有频率下降百分比增加，试件内部的损伤严重程度和损伤扩展速度都随之提高。2.5D机织复合材料经向和纬向试件在共振疲劳试验过程中的主要失效模式是纱线与基体之间脱粘造成的结构完整性丧失，从而导致试件的刚度持续下降。试件内部损伤的三维电子计算机断层扫描(Computerized tomography，CT)重构图像表明，损伤散布于试件工作段区域，应力水平越高，2.5D机织复合材料经向和纬向试件内部损伤范围越大，损伤程度越高，而且纬向试件内部损伤状态比经向试件严重。利用双对数线性寿命模型，对经向和纬向试件在不同名义应力水平下的共振疲劳试验数据进行拟合，得到2.5D机织复合材料经向和纬向试件共振疲劳应力-寿命(Stress-life，S-N)曲线的数学模型，得到的S-N曲线可用于预测2.5D机织复合材料的寿命。Abstract: 2.5D woven composites are resistant to delamination and impact, which have great application prospects in aeroengine structures. The first-order bending vibration fatigue tests under different stress levels were carried out for the specimens made of 2.5D woven carbon fiber reinforced bismaleimide resin matrix composites in the warp direction and weft direction, respectively. The experimental results show that the vibration fatigue performance of the warp specimens is better than that of the weft specimens. With the increase of stress levels, the lives of the specimens are shortened obviously, and the decline percentage of natural frequency increase, and the damage degree and damage propagation speed within specimens also increase. In the process of vibration fatigue test, the main failure mode of 2.5D woven composites was the loss of structural integrity caused by the debonding of the yarns and the matrixes, which leaded to the continuous decrease of the stiffness of the specimens. 3D CT reconstruction images of the internal damage of the specimens show that the damages spread throughout in the working section of the specimens. The higher the stress levels are, the greater the internal damage ranges and the higher the damage degrees are. And the internal damage state of the warp specimens is more serious than that of the weft specimens. The mathematical model of stress-life (S-N) curve of vibration fatigue of 2.5D woven composites is obtained by data fitting for vibration fatigue results under different nominal stress levels by using the log-log-linear life model, which can be used to predict the life of 2.5D woven composites.
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Keywords:
- composites /
- carbon fiber /
- 2.5D woven /
- vibration fatigue /
- life prediction
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图 2 2.5D机织复合材料试件的构型和尺寸
Figure 2. Configuration and dimension of 2.5D woven composite specimens
R—Radius of circular hole
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图 4 2.5D机织复合材料拉伸应力-应变曲线
Figure 4. Tensile stress-strain curves of 2.5D woven composites
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图 5 2.5D机织复合材料振动疲劳试件典型的幅频曲线
Figure 5. Typical amplitude-frequency curve of vibration fatigue specimen made of 2.5D woven composite
f0—Initial natural frequency
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图 6 2.5D机织复合材料试件应变-位移标定曲线
Figure 6. Strain-displacement calibration curves of 2.5D woven composite specimens
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图 7 2.5D机织复合材料振动疲劳试件归一化共振频率f/f0随循环次数的变化曲线
Figure 7. Variation curves of normalized resonance frequency f/f0 with the number of cycles for the 2.5D woven composite vibration fatigue specimens
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图 8 2.5D机织复合材料经向试件不同名义应力水平下共振疲劳试验后断口形貌
Figure 8. Fracture morphologies of warp-direction 2.5D woven composite specimens after vibration fatigue tests under different nominal stress levels
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图 9 2.5D机织复合材料纬向试件不同应力水平下共振疲劳试验后断口形貌
Figure 9. Fracture morphologies of weft-direction 2.5D woven composite specimens after vibration fatigue tests under different nominal stress levels
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图 10 2.5D机织复合材料经向试件内部损伤CT图像
Figure 10. CT images of internal damage of warp 2.5D woven composite specimens
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图 11 2.5D机织复合材料纬向试件内部损伤CT图像
Figure 11. CT images of internal damage of weft 2.5D woven composite specimens
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图 12 2.5D机织复合材料振动疲劳应力-寿命(S-N)曲线
Figure 12. Vibration fatigue stress-life (S-N) curves of 2.5D woven composites
Nf—Cumulative fatigue cycle life of specimen under failure
表 1 不同应力水平下2.5D机织复合材料经向和纬向试件共振疲劳试验参数
Table 1 Vibration fatigue test parameters of warp and weft 2.5D woven composite specimens under different nominal stress levels
Type Stress
level/MPaStrain
level/%No. Amplitude/
mmf0/Hz Warp 0.24X1 0.25 J-1 2.38 204 J-2 2.50 211 J-3 2.57 202 0.26X1 0.27 J-4 2.60 204 J-5 2.71 209 J-6 2.63 211 0.28X1 0.29 J-7 2.82 208 J-8 2.69 215 J-9 2.75 211 0.32X1 0.33 J-10 3.09 215 J-11 3.34 212 J-12 3.44 207 Weft 0.18X2 0.20 W-1 2.64 226 W-2 2.41 231 W-3 2.03 227 0.24X2 0.27 W-4 2.80 229 W-5 3.08 227 W-6 2.68 226 0.26X2 0.29 W-7 2.86 215 W-8 3.02 220 W-9 2.92 224 0.29X2 0.32 W-10 3.30 213 W-11 3.68 217 W-12 3.45 220 Notes: X1, X2—Tensile strengths of the 2.5D woven composites in the warp direction and weft direction, respectively. 
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表 2 不同名义应力水平下2.5D机织复合材料经向和纬向试件共振疲劳测试结果
Table 2 Vibration fatigue results of warp and weft 2.5D woven composite specimens under different nominal stress levels
Type Stress level/ MPa No. Decline percentage of natural frequency/% Cycles Warp 0.24X1 J-1 1.70 10000300 J-2 2.59 10000200 J-3 2.28 10002900 0.26X1 J-4 4.73 3451410 J-5 5.53 5839000 J-6 5.21 6143660 0.28X1 J-7 6.13 761800 J-8 6.04 1402170 J-9 5.79 1820000 0.32X1 J-10 9.70 162823 J-11 8.64 102829 J-12 8.86 175556 Weft 0.18X2 W-1 1.03 10002900 W-2 2.06 10003000 W-3 1.70 10003000 0.24X2 W-4 5.37 2374300 W-5 5.67 2272020 W-6 5.17 4338750 0.26X2 W-7 6.03 736122 W-8 6.08 931322 W-9 6.07 436673 0.29X2 W-10 7.98 250112 W-11 7.80 72917 W-12 8.25 194576
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