To quantitatively evaluate the effects of corrosion during grounding onfatigue life of aircraft structures, a new power equation is proposed using two-variable linearregression method. That the slope is a constant and...To quantitatively evaluate the effects of corrosion during grounding onfatigue life of aircraft structures, a new power equation is proposed using two-variable linearregression method. That the slope is a constant and the logarithmic intercept is a linear functionof pre-corrosion time makes this equation advantageous: it has a simple form, its parameters haveunambiguous technical and geometrical meanings, and it facilitates engineering applications.Three-parameter equations after pre-corrosion are obtained from back-calculation of fatigue limits,which have been successfully used to predict safe life of aircraft structures in corrosiveenvironment.展开更多
Low cycle fatigue tests were conducted on the single crystal nickel-based superalloy, DD6, with different crystallographic orientations （i.e., [001], [011], and [111]） and strain dwell types （i.e, tensile, compress...Low cycle fatigue tests were conducted on the single crystal nickel-based superalloy, DD6, with different crystallographic orientations （i.e., [001], [011], and [111]） and strain dwell types （i.e, tensile, compressive, and balanced types） at a certain high temperature. Given the material anisotropy and mean stress, both orientation factor and stress range were introduced to the Smith, Watson, and Topper （SWT） stress model to predict the fatigue life. Experimental results indicated that the fatigue properties of DD6 depend on both crystallographic orientation and loading types. The fatigue life of the tensile, compressive, and balanced strain dwell tests are shorter than those of continuous cycling tests without strain dwell because of the important creep effect. The predicted results of the proposed modified SWT stress method agree well with the experimental data.展开更多
文摘To quantitatively evaluate the effects of corrosion during grounding onfatigue life of aircraft structures, a new power equation is proposed using two-variable linearregression method. That the slope is a constant and the logarithmic intercept is a linear functionof pre-corrosion time makes this equation advantageous: it has a simple form, its parameters haveunambiguous technical and geometrical meanings, and it facilitates engineering applications.Three-parameter equations after pre-corrosion are obtained from back-calculation of fatigue limits,which have been successfully used to predict safe life of aircraft structures in corrosiveenvironment.
基金The financial support for this work from the National Natural Science Foundation of China （Grant No. 51341001） is appreciated.
文摘Low cycle fatigue tests were conducted on the single crystal nickel-based superalloy, DD6, with different crystallographic orientations （i.e., [001], [011], and [111]） and strain dwell types （i.e, tensile, compressive, and balanced types） at a certain high temperature. Given the material anisotropy and mean stress, both orientation factor and stress range were introduced to the Smith, Watson, and Topper （SWT） stress model to predict the fatigue life. Experimental results indicated that the fatigue properties of DD6 depend on both crystallographic orientation and loading types. The fatigue life of the tensile, compressive, and balanced strain dwell tests are shorter than those of continuous cycling tests without strain dwell because of the important creep effect. The predicted results of the proposed modified SWT stress method agree well with the experimental data.
