UC知道急，求高手翻译英语论文
来源：百度知道 编辑：UC知道 时间：2024/05/24 20:11:23
ABSTRACT
Fatigue and crack growth tests have been conducted on 4340 steel and 2024-T3 aluminum alloy, respectively, to assess the effects of shot peening on fatigue life and the effects of shot and laser peening on crack growth. This work is of current interest to the U.S. Air Force as well as the rotorcraft community. Two current programs in the aerospace community involving fixed and rotary-wing aircraft will not be using shot peened structures. The reason for not shot peening these aircraft comes from arguments based on the premise that the shot peening compressive residual stress depth is less than the 0.05-inch initial damage tolerance crack size. Therefore, shot peening should have no beneficial effects toward retarding crack growth. In this study cracks were initiated from an electronic- discharged machining flaw which was cycled to produce a fatigue crack of approximately 0.05-inches in length and then the specimens were peened. Test results showed that after peening the c
Fatigue and crack growth tests have been conducted on 4340 steel and 2024-T3 aluminum alloy, respectively, to assess the effects of shot peening on fatigue life and the effects of shot and laser peening on crack growth. This work is of current interest to the U.S. Air Force as well as the rotorcraft community. Two current programs in the aerospace community involving fixed and rotary-wing aircraft will not be using shot peened structures. The reason for not shot peening these aircraft comes from arguments based on the premise that the shot peening compressive residual stress depth is less than the 0.05-inch initial damage tolerance crack size. Therefore, shot peening should have no beneficial effects toward retarding crack growth. In this study cracks were initiated from an electronic- discharged machining flaw which was cycled to produce a fatigue crack of approximately 0.05-inches in length and then the specimens were peened. Test results showed that after peening the c
摘要
疲劳裂纹扩展试验已进行了4340钢和2024年科技- T3铝合金，分别评估的影响，喷丸强化对疲劳寿命的影响开枪激光冲击裂纹增长。这项工作是当前关心的美国空军以及旋翼机社区。目前两个项目，涉及航空航天界的固定和旋转翼飞机将不会使用开枪peened结构。为何不喷丸这些飞机来自论点依据的前提是压缩的喷丸残余应力深度小于0.05英寸的初始损伤容忍裂纹尺寸。因此，喷丸不应有任何有益的影响对延缓裂纹扩展。在这项研究中的裂缝已开始从电子，出院加工缺陷是循环产生疲劳裂纹大约0.05英寸长，然后标本peened 。试验结果表明，经过强化的裂纹扩展速率明显慢时的裂缝是相当短的两个镜头和激光peened标本导致裂纹扩展的生活，这是一个因素， 2至4倍的结果，平均unpeened测试。一旦达成了裂缝长度约0.1英寸的增长率大致相同的peened和unpeened标本。疲劳试验表明， 4340钢的耐力极限的试样，以0.002英寸深加工类从零开始大约减少了百分之四十。但是，如果“抓”标本被枪杀后，插入peened从无到有，疲劳寿命返回几乎百分之百的unflawed标本原始疲劳寿命。