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碳纤维复合材料力学性能优异,在航空航天等领域广泛使用,其在热-力联合作用下的损伤失效研究对于结构的损伤破坏和强度预测具有重要意义。发展了热力耦合条件下复合材料结构渐进损伤分析方法,建立了三维有限元热烧蚀模型,并验证了计算模型的可靠性;采用三维Hashin失效准则,结合材料刚度突然退化模式,建立了失效分析模型,仿真分析了热-力联合作用下复合材料层合板损伤演化全过程。结果表明,该方法不仅能够较好地模拟复合材料层合板从局部失效的萌生、扩展直至结构完全失效的全过程,而且可以直观地显示结构的损伤失效模式,预测结构在不同条件下的承载能力。
Carbon fiber composites have excellent mechanical properties and are widely used in aerospace and other fields. The study of damage and failure under the action of thermo-mechanical interaction is of great significance for structural damage and strength prediction. The progressive damage analysis of composite structures under the condition of thermal coupling was developed. The three-dimensional finite element thermal ablation model was established and the reliability of the calculation model was verified. By using the three-dimensional Hashin failure criterion and the abrupt degradation of material stiffness, a failure analysis Model, the whole process of damage evolution of the composite laminates under the action of thermo-force was simulated and analyzed. The results show that this method not only can simulate the whole process of local failure, but also can directly display the damage failure mode of the structure and predict the bearing capacity of the composite under different conditions .