摘要
针对传统铝合金焊缝残余应力测试方法结果波动大的问题,采用电子散斑干涉法测量了5 mm厚载人航天器密封舱5A06铝合金变极性等离子弧对接和T型交叉焊缝的残余应力,分析了影响测量结果的因素,结果表明对接焊缝熔合线附近残余应力接近5A06屈服强度(约160 MPa);T型焊缝远离交叉区域,残余应力分布规律接近对接焊缝;在交叉区域附近,由于平行、垂直焊缝方向的残余应力的相互影响,这一区域焊缝残余应力状态十分复杂,且由于残余应力叠加,使得在部分小区域内残余应力值超过材料屈服强度。
The measurement of the residual stress in aluminum alloy weld measured by traditional method has the large fluctuation problem. So, the Electronic Speckle Pattern Interferometry method was used to measure the residual stress distribution of 5 mm thick 5 A06 aluminum alloy with variable polarity plasma arc butt and cross welds in Manned Spacecraft Cabin.The factors affecting the measurement results were analyzed. The results show that the residual stress near the fusion line of the butt weld was close to the 5 A06 yield strength(about 160 MPa);As to the T type weld, the distribution of residual stress away from the cross area iswas close to that of the butt weld.Near the cross area, the residual stress was very complex because of the interaction of residual stresses in parallel and vertical welding directions. Due to the superposition of residual stresses, the residual stress in some small areas was larger than the yield strength.
引文
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