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焊接结构在运载火箭结构设计中应用十分广泛。随着我国宇航事业的发展,焊接工艺质量有很大提高。但是,由于焊接接头的存在和焊接时加热的影响,焊接结构焊缝附近的材料强度有一定削弱。在结构设计和强度计算中,这种削弱一般以焊接系数表示。如LF6材料σ_b的焊接系数为0.7-0.8,σ_(0.2)的焊接系数为0.5-0.6,带加强高的试片比不带加强高的焊接系数稍高。试验还表明,在正常焊接(自动钨极氩弧焊)条件下,材料厚度2mm时,热影响区宽度约为30mm;厚度8mm时,热影响区宽度约为60mm。焊接工艺除使材料强度降低外,还造成焊缝附近严重的几
Welding structure in the design of launch vehicle structure is widely used. With the development of China’s aerospace industry, welding quality has greatly improved. However, due to the presence of welded joints and the effects of heating during welding, the strength of the material near the weld of the welded structure is somewhat weakened. In structural design and strength calculation, this weakening is generally expressed in terms of welding factor. Such as LF6 material σ_b welding coefficient of 0.7-0.8, σ_ (0.2) of the welding factor of 0.5-0.6, with the strengthening of the test piece without strengthening higher than the welding coefficient slightly higher. The test also shows that the width of heat affected zone is about 30mm when the material thickness is 2mm and the width of heat affected zone is about 60mm when the thickness is 8mm under normal welding conditions (automatic TIG welding). In addition to the welding process to reduce the strength of the material, but also caused a serious weld near a few