High-velocity impact damage behavior of hybrid fiber reinforced epoxy composites
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摘要: 开展了混杂纤维自动铺丝环氧树脂复合材料层合板高速冲击失效行为的研究。首先,测试了纯碳纤维增强环氧树脂层合板和纯芳纶纤维增强环氧树脂层合板的准静态力学性能,以获得其力学性能参数;然后,以芳纶纤维质量分数为基准,开展了不同混杂比层合板的钛合金弹体高速冲击试验,探究混杂比对混杂纤维增强环氧树脂复合材料抗冲击性能的影响;接着,建立了混杂纤维增强环氧树脂复合材料层合板的高速冲击有限元模型,基于Murakami-Ohno损伤演化理论建立了复合材料层合板的渐进损伤本构模型,并引入应变率效应系数以考虑应变率的影响,采用损伤变量和单元畸变协同控制单元删除。开展了不同混杂比层合板的高速冲击模拟,分别得到了相应的临界穿透速度。高速冲击试验结果表明,临界穿透速度随着混杂比的增加呈现逐渐增加的趋势,具有正混杂效应。通过与相应的准静态及高速冲击试验结果对比,该模型能够比较准确的预测混杂纤维增强环氧树脂复合材料层合板的准静态力学响应和高速冲击响应,临界穿透速度结果相差在4.5%以内。Abstract: This paper is aimed to perform a numerical simulation study on the high-velocity impact failure behavior of hybrid fiber reinforced epoxy composite laminates based on the finite element model. Firstly, quasi-static mechanical tests of pure carbon fiber reinforced epoxy composites and pure aramid fiber reinforced epoxy composites were carried out to obtain their basic mechanical properties. Then, high-velocity impact tests were conducted to determine the critical penetration velocity and explore the influence of hybrid ratio on the impact resistance of hybrid composite reinforced composite laminates. The finite element model of high-velocity impact for hybrid fiber laminates was established, and the progressive damage constitutive of composite laminates was developed on the basis of the Murakami-Ohno damage evolution theory. The strain rate effect coefficient was introduced to consider strain rate dependency, and the element deletion was co-controlled by damage variable and element distortion in parallel. Then the high-velocity impact simulation for different hybrid ratio laminates was carried out and the corresponding critical penetration velocity was obtained respectively. The experimental results of high-velocity impact show that the critical penetration velocity increases with the increasing hybrid ratio, exhibiting a positive hybrid effect. Compared with the experimental results, the proposed model can accurately predict the quasi-static mechanical response and high-velocity impact response for the hybrid fiber reinforced epoxy composites, and the difference of the critical penetration velocity is less than 4.5%.
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表 1 混杂纤维复合材料混杂参数
Table 1. Hybrid parameters of hybrid fiber composites
Hybrid ratio (by mass)/% Number of carbon unit layer Number of aramid layer Thickness of laminate/mm 0 18 0 8.586 25.20 14 21 9.198 36.04 12 30 9.324 42.40 11 36 9.567 67.70 6 56 9.582 79.30 4 68 10.068 100.00 0 83 9.960 表 2 碳纤维(CF)层合板和芳纶纤维(AF)层合板的弹性常数
Table 2. Elastic parameters of carbon fiber (CF) laminate and aramid fiber (AF) laminate
Material E11/GPa E22=E33/GPa G12= G13/GPa G23/GPa ν12 ν13 ν23 CF laminate 146.0 8.01 5.06 3.86 0.32 0.32 0.30 AF laminate 38.3 32.30 1.73 1.38 0.068 0.33 0.33 Notes: E11, E22, E33—Elastic modulus (direction 11, 22, 33); G12, G13, G23—Shear modulus (direction 12, 13, 23); ν12, ν13, ν23—Poission’s ratio (direction 12, 13, 23). 表 3 CF层合板和AF层合板的强度常数
Table 3. Strength parameters of CF laminate and AF laminate
Material XT/MPa XC/MPa YT/MPa YC/MPa S12/MPa S23/MPa Gft/(kJ·m−2) Gfc/(kJ·m−2) Gmt/(kJ·m−2) Gmc/(kJ·m−2) CF laminate 2160 1290 45.9 226 99.3 99.3 133 40 1 1 AF laminate 923 180 668.0 172 72.9 27.4 200 40 1 1 Notes: XT, XC—Tensile strength, compression strength along fiber direction; YT, YC—Transverse tensile strength, transverse compression strength; S12, S23—Shear strength (direction 12, 23); Gft, Gfc, Gmt, Gmc—Fracture energy (fiber tensile, fiber compression, matrix tensile, matrix compression). 表 4 钛合金弹体性能参数
Table 4. Properties of titanium alloy projectile
Property Value Density /(g·cm−3) 4.4 Elastic modulus E/GPa 110 Poission’s ratio ν 0.31 Mass/g 66 表 5 混杂纤维复合材料层合板的临界穿透速度试验与模拟结果对比
Table 5. Comparison of test and simulation results of critical penetration velocity for hybrid fiber composite laminates
Hybrid ratio
/%Test/
(m·s−1)Fitting/
(m·s−1)Simulation/
(m·s−1)Error/% 0.00 136 135.500 134-138 0.37 25.20 173-174 171.571 170-177 1.12 36.04 193 187.062 185-190 0.23 42.40 188-189 196.242 200-210 4.46 67.70 226 232.530 235-240 2.14 79.30 256 249.168 243-250 1.07 100.00 >256 278.860 265-275 3.18 Note: Error—Comparison between simulation results and fitting results. -
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