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针对老龄飞机7150铝合金结构普遍存在的剥蚀问题,在海洋性盐雾环境下,通过T73时效态不受载和悬臂梁加载剥蚀试验,以及T77时效态波音737CL龙骨梁下缘条不受载和受载剥蚀试验,研究了正应力对7150铝合金剥蚀的影响。结果表明:T73时效态剥蚀,L轴向拉应力作用表面最轻,其次为不受载表面,L轴向压应力作用表面最严重。T77时效态龙骨梁下缘条剥蚀,在L轴向压应力作用下的产生和扩展速度,比不受载状态下快得多。由此认为:L轴向压应力可以加速7150铝合金剥蚀的形成和扩展,而L轴向拉应力可以抑制剥蚀的形成和扩展。
In view of the common denudation problem of aged aircraft 7150 aluminum alloy structure, under the sea salt spray environment, the T73 aging state is not affected by the loading and cantilever loading and the lower edge of the T77 aging Boeing 737CL keel beam is not affected by the loading and The load-bearing erosion test was carried out to study the effect of normal stress on denudation of 7150 aluminum alloy. The results show that when T73 is aged, the effect of L-axial tensile stress is the lightest, followed by the unloaded surface and the L-axial compressive stress is the most serious. T77 eroded keel lower edge of the erosion, in the L-axial compressive stress under the action of the generation and expansion rate, faster than the unloaded state. It is considered that: L axial compressive stress can accelerate the formation and expansion of 7150 aluminum alloy erosion, and L axial tensile stress can inhibit the formation and expansion of erosion.