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借助于莫尔方法 ,本文对厚度 6mm、干涉量 3.1 %情况下的航空用硬铝合金LY1 2CZ板销钉干涉配合预应力及其在 35 %σ0 .2 ,45 %σ0 .2 ,5 5 %σ0 .2 的拉伸载荷下的变化规律进行了实验研究 .研究显示 ,在 3.1 %干涉水平下 ,干涉配合适宜在中等及其以下的拉载环境中工作 .当载荷水平等于或大于 5 5 %σ0 .2 时 ,预应力的稳定性较差 ,不利于抑制疲劳裂纹的萌生 .
With Mohr method, the interference fit prestress of LY1 2CZ plate for aviation aluminum alloy with thickness of 6mm and interference of 3.1%, the interference prestress of 35% σ0.2, 45% σ0.2, 55% σ0 .2 The experimental results show that the interference fit is suitable for medium and below loading conditions under the 3.1% interference level.When the load level is equal to or greater than 55% σ0 .2, the stability of the prestress is poor, which is not conducive to inhibiting the initiation of fatigue cracks.