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在液氢液氧火箭改进贮箱系统的研制中,很重要的研究课题之一是选择材料和焊接工艺方法。尤其是贮箱材料,在-253℃的液氢温度要求它必须具有良好的机械性能及焊接性能。过去都用铝合金,奥氏体不锈钢及钛合金作贮箱材料,其中,2014-T6铝合金在美国液氢液氧火箭的实际应用中获得了很好的效果。因此,这里就2014-T6薄板及2219-T87铝合金锻件作贮箱壳体和Y形环材料的应用的可能性问题分别进行讨论,并在室温至-269℃的液氦温度的不同温度下,对于母材和直流正极惰性气体保护钨弧焊(DCSP-TIG)接头进行了拉伸试验及缺口拉伸试验。试验结果表明,2014-T6薄板和2014/2319焊接接头的超低温机械性能及缺口韧性都很好,作液氢液氧火箭贮箱材料完全适合。此外,还提出了一种按断裂韧性值设计的先进接头的方法。
In the liquid hydrogen oxygen rocket tank system to improve the development, one of the most important research topics is the choice of materials and welding process. Especially the tank material, liquid-hydrogen temperature of -253 ℃ requires it must have good mechanical properties and welding performance. In the past, aluminum alloy, austenitic stainless steel and titanium alloy were used as storage tank materials. Among them, the 2014-T6 aluminum alloy obtained good effect in the practical application of liquid oxygen-liquid oxygen rockets in the United States. Therefore, the possibility of application of 2014-T6 sheet and 2219-T87 aluminum alloy forgings as tank shell and Y-ring material will be discussed respectively here, and at different temperatures of liquid helium from room temperature to -269 ° C Tensile test and notched tensile test were carried out on base metal and DC positive electrode inert gas shielded tungsten arc welding (DCSP-TIG) joints. The test results show that the low temperature mechanical properties and notch toughness of the 2014-T6 sheet and the 2014/2319 welded joint are very good, and the liquid hydrogen-oxygen rocket storage tank material is completely suitable. In addition, a method of advanced joints designed according to the fracture toughness value has also been proposed.