细节疲劳额定强度形状参数取值  

Shape Parameter in Detail Fatigue Rating

作　　者：郭翔[1] 刘建中[1] 胡本润[1] 黄啸[1] 

机构地区：[1]北京航空材料研究院航空材料检测与评价北京市重点实验室,北京100095

出　　处：《航空材料学报》2014年第2期77-83,共7页Journal of Aeronautical Materials

摘　　要：为了得到DFR方法中更准确可靠的α值,对头两序数估计法进行说明并验证,并通过蒙特卡洛模拟对多种估计方法合理性评价。运用头两序数估计方法处理实测的大量数据,对钛合金、铝合金、钢等多种航空国产材料的α值进行系统的参数估计,并对影响疲劳寿命分散性的因素进行分析。给出了常用国产航空材料α的取值范围为4.85到6.71,并对腐蚀环境下各类材料以及新型航空材料铝锂合金、金属纤维层板提出了新的α估计值。In order to obtain more accurate and reliable DFR value, two-ordered statistic （TOS） method is introduced and verified. An assessment for TOS and common estimators is made by Monte Carlo simulation, and TOS method is used for analyzing a large amount of measured data. Systematical parameter estimation and analysis are taken for aviation materials including steel, aluminum and titanium. A further analysis is taken for factors which may affect scatter in fatigue life. As a resuh, TOS has high accuracy in calculating α. Val- ue life range has an obvious impact on domestic aviation materials＇α. Ultimate strength and corrosive environments have impact on sev- eral materials. Recommended a values for common domestic material are in the range of 4.85 -6.71. And new α estimated values of new aviation material aluminum lithium alloy, fiber metal laminates under the corrosive environment is given out.

关 键 词：运输类飞机 细节疲劳额定强度 威布尔分布 形状参数 

分 类 号：V221[航空宇航科学与技术—飞行器设计]