论文部分内容阅读
采用静拉伸应变测量试验的方法,确定了典型飞机复杂结构在载荷作用下的应变分布,并准确判断出其疲劳危险部位。对典型飞机复杂结构模拟件进行了等幅加载疲劳试验,并在疲劳试验过程中采用着色探伤方法测得了疲劳裂纹扩展数据。在此基础上,提出并建立了一种适用于确定复杂结构疲劳裂纹萌生寿命的工程方法,包括疲劳裂纹萌生寿命反推法和含有不确定寿命样本的统计推断方法。根据该方法对试验样本疲劳数据进行处理得出了裂纹萌生中值寿命及其在95%置信水平下的单侧置信下限。
Static tensile strain measurement test method was used to determine the strain distribution of a typical aircraft complex structure under load and accurately determine the risk of fatigue. The fatigue test of the typical aircraft complex structure was performed with constant amplitude loading fatigue test, and the fatigue crack growth data was obtained by the color inspection method during the fatigue test. On this basis, an engineering method suitable for determining the initiation life of fatigue crack in complex structures is proposed and established, including the fatigue crack initiation life regression method and the statistical inference method with uncertain life samples. According to this method, the fatigue life of the test specimen was processed to obtain the median lifetime of crack initiation and its lower confidence limit at 95% confidence level.