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在对母材焊接性及焊接结构特殊性进行分析的基础上,结合试验研究,制定出氩弧焊工艺方案及过程控制和保障措施,实现固体火箭发动机的弹翼支座与其燃烧室壳体异种材料间连接。测试结果表明,焊缝成型良好,接头区域微观组织和性能不均匀性不影响产品使用性能。生产统计数据显示,产品质量与性能稳定,承压能力显著高于设定目标,表明该型号发动机的弹翼支座TIG焊接技术具有切实的可靠性。
Based on the analysis of the weldability of the base metal and the particularity of the welding structure, the welding process scheme and process control and safeguard measures are developed based on the experimental study to realize the difference between the solid propellant rocket engine flaps and the combustion chamber shell Material connection. The test results show that the welding seam is well formed and the microstructure and the non-uniformity of the joint area do not affect the product performance. Production statistics show that the product quality and performance are stable, the pressure capacity is significantly higher than the set target, indicating that this model engine wing wing TIG welding technology with practical reliability.