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针对某型飞机垂尾梁误加工损伤进行了激光沉积修复研究,根据其服役时受力特点设计了力学性能试样,对不同沉积修复试样及同批锻件基材进行室温静载拉伸对比实验,同时对修复试样显微组织、硬度进行分析及测试。结果表明:沉积修复区组织为细小α/β片层组织,无明显缺陷,修复区与修复基体形成致密的冶金结合;修复区至修复基体显微硬度分布呈逐步降低的趋势,修复区显微硬度相对修复基体提高约12%;无论修复试样标距中心是否预制孔,修复试样室温静载抗拉强度均高于锻件基材,但塑性比锻件基材略低;同时,在优化垂尾梁修复工艺参数的基础上,对沉积修复试样侧边塌边缺陷产生的原因进行分析并给出解决措施,以期消除塌边缺陷提高修复质量。
Aiming at the mistreatment of the vertical tail beam of a certain type of aircraft, the laser deposition repair was carried out. According to the mechanical characteristics of the vertical tail beam during service, the mechanical properties specimens were designed. At the same time, the microstructure and hardness of the repaired sample were analyzed and tested. The results showed that the microstructure of the repaired area was fine α / β lamellar structure with no obvious defects. The repaired area formed a dense metallurgical bond with the repaired substrate. The distribution of microhardness of the repaired area to the repaired substrate tended to decrease gradually. The hardness is about 12% higher than that of the repaired substrate. Regardless of whether the center of the gage is prefabricated or not, the static tensile strength at room temperature of the repaired specimen is higher than that of the forging substrate, but the plasticity is slightly lower than that of the forging substrate. Tail girder repair process parameters, based on the analysis of the causes of sedimentation repair side collapse of the specimen defects and give solutions to eliminate collapse defects to improve the quality of repair.