FDM工艺CF/PEEK棒材不同温度条件下的单轴力学行为及损伤机理

The uniaxial mechanical behavior and damage mechanism of FDM process CF/PEEK rods under different temperature conditions

  • 摘要: 熔融沉积成型(FDM)技术制备的短切碳纤维增强聚醚醚酮(CF/PEEK)复合材料,在航空航天等领域中具有广阔应用前景,但FDM工艺固有缺陷导致其力学行为与损伤机理尚不明确。本文以10%体积分数短切CF/PEEK复合材料为研究对象,通过系统开展不同温度、应变率及应变幅下的单调拉伸与循环拉压试验,结合扫描电镜(SEM)微观表征探究其单轴力学行为与损伤机理,并进一步探究了Chaboche本构模型与Manson-Coffin方程在该材料中的适用性。结果表明,该复合材料单调拉伸应力-应变曲线呈现线弹性、屈服软化、稳态流动三段式特征,力学性能受温度与应变率影响显著,温度升高会导致基体软化,降低材料强度和刚度,失效遵循“界面弱化-基体失效-纤维断裂”的递进式模式;循环拉压载荷下,材料ε-N疲劳寿命曲线三阶段特征明显,中高应变幅下循环软化显著,损伤以界面疲劳脱粘、基体微裂纹扩展及层间剪切滑移为主。基于Manson-Coffin方程对材料低周疲劳寿命进行拟合,得到的拟合寿命均在2倍分散带以内;基于Chaboche模型对其力学响应进行数值模拟,单调拉伸和疲劳稳态环应力应变曲线拟合相对误差分别为3.34%和4.82%。

     

    Abstract: Carbon fiber reinforced polyetheretherketone (CF/PEEK) composites prepared by fused deposition modeling (FDM) have broad application prospects in aerospace and other fields, but the inherent defects of the FDM process lead to unclear mechanical behavior and damage mechanism. This study focuses on a 10% volume fraction short-cut CF/PEEK composite, systematically investigating its monotonic tensile and cyclic tension-compression behaviors under various temperatures, strain rates, and strain amplitudes. Microscopic characterization via scanning electron microscopy (SEM) is employed to explore the material's uniaxial mechanical response and damage mechanisms. The results showed that the stress-strain curve of the composite under uniaxial tension presented three typical stages: linear elasticity, yield softening and steady-state flow. Its mechanical properties were significantly affected by temperature and strain rate; the increase of temperature led to matrix softening, which reduced the material strength and stiffness, and the failure followed a progressive mode of "interface weakening-matrix failure-fiber fracture". Under cyclic tension-compression loading, the ε-N fatigue life curve of the material had obvious three-stage characteristics, cyclic softening was significant under medium and high strain amplitudes, and the damage was mainly dominated by interface fatigue debonding, matrix microcrack propagation and interlayer shear slip. The low-cycle fatigue life predicted using the Manson-Coffin equation falls within two times the scatter band. Numerical simulation of its mechanical response was carried out based on the Chaboche model, and the relative fitting errors of the stress-strain curves of uniaxial tension and fatigue steady-state loop were 3.34% and 4.82%, respectively. This study clarifies the mechanical response rules and damage evolution characteristics of FDM-processed CF/PEEK composites under complex loads, and provides reliable theoretical and experimental support for their engineering application in aerospace and other fields.

     

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