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复合材料结构的耐久性是飞机结构强度设计领域的前沿课题。以铺层方式为[45°/0°-45°/90°/0°_2/45°/0°/-45°/0°]_(2s)的CCF300/5228A复合材料层合板为研究对象,对其进行恒定环境与常幅疲劳载荷的非共同作用试验,采用改进的联合威布尔分布分析复合材料的疲劳寿命分散性,并运用MATLAB软件编写程序,分别计算得到其部件的载荷放大系数。结果表明,在本文研究范围内,随着试验环境中温湿度的增加,复合材料的形状参数单调递减,进而载荷放大系数也单调递增。但载荷放大效果并不明显,不能很好地加速该复合材料层合板的疲劳寿命试验,说明湿热环境导致复合材料力学性能下降,但反映到载荷放大系数的影响不大。
Durability of composite structures is a frontier issue in the field of aircraft structural strength design. The CCF300 / 5228A composite laminates with the layering method of [45 ° / 0 ° -45 ° / 90 ° / 0 ° 2/45 ° / 0 ° / -45 ° / 0 °] _ (2s) , The non-synergistic effect of constant load and fatigue load was tested. The improved joint Weibull distribution was used to analyze the fatigue life dispersion of composite materials. The software was programmed with MATLAB software to calculate the load magnification factor of each component. The results show that, with the increase of temperature and humidity in the experimental environment, the shape parameters of the composites decrease monotonically, and the load amplification coefficient also increases monotonically. However, the effect of load amplification is not obvious, which can not accelerate the fatigue life test of the composite laminates well. It shows that the hot and humid environment leads to the decrease of the mechanical properties of the composites, but it has little effect on the load amplification factor.