CAJ | 학술논문

针对2系列预腐蚀损伤航空铝合金材料进行腐蚀坑当量化技术研究，结果表明，在预腐蚀条件下，疲劳裂纹起始于腐蚀坑底部并呈辐射状向内扩展，降低了材料裂纹萌生寿命。因此，忽略裂纹成核阶段，提出了一种根据面积等效原理将腐蚀坑当量化成半椭圆表面裂纹的当量化处理方法，直接计算材料的疲劳寿命，并利用 NASGRO 软件验证了腐蚀坑当量化以及基于断裂力学预测材料疲劳全寿命方法的可行性。研究结果为复杂结构件的寿命评估提供了依据。
침대2계렬예부식손상항공려합금재료진행부식갱당양화기술연구，결과표명，재예부식조건하，피로렬문기시우부식갱저부병정복사상향내확전，강저료재료렬문맹생수명。인차，홀략렬문성핵계단，제출료일충근거면적등효원리장부식갱당양화성반타원표면렬문적당양화처리방법，직접계산재료적피로수명，병이용 NASGRO 연건험증료부식갱당양화이급기우단렬역학예측재료피로전수명방법적가행성。연구결과위복잡결구건적수명평고제공료의거。
The quantitative techniques of corrosion pits of 2 series pre-corrosive aerial aluminum alloys were investigated.In the pre-corrosive conditions,it is found that the fatigue crack starts at the bottom of its corrosion pit to result in a radial propagation and a decrease of the crack initiation life. Thus,a new quantitative method of corrosion pits was pointed out by ignoring the stages of the crack nucleation.According to the equivalence principles of the area,the corrosion pit was equivalent to a semi-elliptical surface crack in order to directly predict the fatigue life of aluminum alloys.Based on the NASGRO software,the validation of proposed quantitative techniques of corrosion pits and fatigue life prediction methods was performed and the research results enable the possibility of the fatigue life evaluation of complicated structures.