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point飞机结构生产过程中,由于设计缺陷或制造公差累积,在装配界面出现不贴合或间隙,如装配过程中未通过加垫等手段消除该间隙而进行强迫装配,导致装配处结构产生装配应力。而机械连接部位往往是金属结构疲劳细节部位,金属结构叠加装配应力后降低连接结构疲劳品质。本文通过试验方法加数据分析,得到某典型铝合金材料存在一定强迫装配应力情况下疲劳额定值DFR最大降低24%。
point In the production process of aircraft structure, due to design defects or manufacturing tolerance accumulation, there is no fit or clearance on the assembly interface. If the gap is not eliminated by padding during assembly, forcing assembly, resulting in assembly stress on the assembly structure . The mechanical connection parts are often the details of the fatigue structure of the metal structure, the metal structure superimposed on the stress after the assembly structure to reduce stress fatigue quality. In this paper, through the test method and data analysis, the DFR of the fatigue rating is reduced by 24% under certain forced assembly stress of a typical aluminum alloy material.