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 traditionalmethod has the large fluctuation problem. So, the Electronic Speckle Pattern Interferometry methodwas used to measure the residual stress distribution of 5 mm thick 5A06 aluminum alloy with variablepolarity plasma arc butt and cross welds in Manned Spacecraft Cabin. The factors affecting the meas-urement results were analyzed. The results show that the residual stress near the fusion line of thebutt weld was close to the 5A06 yield strength （about 160 MPa）;As to the T type weld, the distri-bution of residual stress away from the cross area iswas close to that of the butt weld. Near the crossarea, the residual stress was very complex because of the interaction of residual stresses in paralleland vertical welding directions. Due to the superposition of residual stresses, the residual stress insome small areas was larger than the yield strength.
作者
张天弛
张明
李博
孙利
祁俊峰
朱小溪
ZHANG Tianchi;ZHANG Ming;LI Bo;Sun Li;QI Junfeng;ZHU Xiaoxi(Beijing Spacecrafts Manufacturing Factory,Beijing 100094,China;China Academy of Space Technology,Beijing 100094,China)
出处
《载人航天》
CSCD
北大核心
2018年第5期674-678,共5页
Manned Spaceflight
基金
载人航天预先研究项目(040302)
关键词
残余应力
电子散斑
铝合金
变极性等离子弧
residual stress
Electronic Speckle Pattern Interferometry （ ESPI）
aluminum alloy
Variable Polarity Plasma Arc（VPPA）
