T300/BPM316复合材料层合板的载荷放大系数确定

在加速飞机复合材料结构耐久性验证的试验过程中,载荷放大系数(LEF)的求解精度对试验持续时间有着重要的影响。以铺层方式为[45/-45/0/0/-45/90/0/90/45/0]_s 的T300/BPM316 复合材料层合板为研究对象,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,计算得到其部件的载荷放大系数。结果表明:在该文研究范围内,T300/BMP316 复合材料层合板的载荷放大系数随试验持续时间的增加而减小;部件试验件数对耐久性验证试验的可靠性影响很小,对载荷放大系数的影响可忽略不计;验证了采用改进的联合威布尔分布的联合载荷放大系数法的正确性,并发现其不受原始载荷放大系数法的求解限制,具有推广应用价值。

DETERMINATION OF LOAD ENHANCEMENT FACTOR OF T300/BPM316 COMPOSITE LAMINATES

The test duration of composites is highly dependent on the accuracy required for load enhancement factor (LEF) in accelerated test methods to verify the durability of aircraft composite structures. The T300/BPM316 composite laminate with the layer mode for [45/-45/0/0/-45/90/0/90/45/0]_s is studied in this paper. The fatigue life scatter of composites is analyzed by modified joint Weibull distribution, and MATLAB software is used, based on which the load enhancement factor is calculated. The results show that the LEF of T300/BMP316 composites laminates decreased when the test duration is increased; while the influence of test number is very small on the reliability of durability test, and its influence on the load enhancement factor can be ignored. The combined load enhancement factor method is validated by using modified joint Weibull distribution to analyze the fatigue life of composite material scatter, and it is not affected by the original load enhancement factor, which demonstrates its potential wide application.