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航空技术装备的使用效率在很大程度上取决于航空结构中所采用的材料性能,及其抵制疲劳裂纹发展的能力。材料抵制裂纹能力的指标之一是在给定载荷下的临界裂纹长度和平面应变断裂韧性K_(1c)。本文研究的是在阻蚀液中进行冷磷化处理对Д16T合金5毫米厚板材试样临界裂纹长度和断裂韧性的影响。用30个阳极氧化的(供货状态)和30个阴蚀处理的试样(由同一板材制成)做了对比试验,试样宽45毫
The efficiency of the use of aviation technology and equipment depends to a large extent on the material properties used in the aeronautical structure and their ability to resist the development of fatigue cracks. One of the indicators of material resistance to crack capacity is the critical crack length and plane strain fracture toughness K_ (1c) at a given load. In this paper, the influence of cold phosphating treatment on the critical crack length and fracture toughness of Д16T alloy 5 mm thick plate specimen was studied. A comparative test was made with 30 anodized (as supplied) and 30 under-etched specimens (made from the same sheet) with a specimen width of 45 milliliters