A kind of laser welding method
A laser welding and groove welding technology, applied in the aerospace field, can solve the problems of unstable welding quality, complex process equipment and high structural strength, and achieve the effects of fast welding speed, high structural strength and low line energy.
Active Publication Date: 2020-11-10
HUBEI SANJIANG AEROSPACE GRP HONGYANG ELECTROMECHANICAL
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[0005] The embodiment of the present invention provides a laser welding method, which is used to solve the problem of long manufacturing cycle, unstable welding quality and complex process equipment caused by casting and other welding process methods in the lightweight skeleton of the titanium alloy cabin in the prior art The technical effects of stable and reliable joint welding quality, fast welding speed, high manufacturing precision of titanium alloy cabin frame, high structural strength and low manufacturing cost have been achieved.
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Embodiment 1
[0038] The embodiment of the present invention provides a laser welding method, please refer to Figure 1 to Figure 10 , the method includes:
[0039] The front end frame 2 and the rear end frame 3 are assembled using a butt joint, wherein the blunt edge of the welding groove is attached.
[0040] Further, the front-end frame 2 is formed by machining a titanium alloy thick plate or a forging, wherein the method further includes: machining four butt joint bosses 2-1 on the inner end surface of the front-end frame 2, and connecting with the longitudinal ribs in the rib assembly 4 The front end of 4-1 forms a butt joint; the lower part of the front frame 2 reserves a straight edge 2-2, which forms a butt joint with the first butt joint boss 1-3. The welding groove is the multi-pass welding of the rear end frame 3, and the thickness t of the rear end frame 3, the blunt side of the groove a, the opening b, the fillet R, the reverse deformation angle α, and the number of welding la...
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Abstract
The invention discloses a laser welding method. The method comprises: assembling the front end frame and the rear end frame with a butt joint, wherein the blunt edge of the welding groove is bonded together; sticking adhesive tape on the reverse side of the weld seam to form a cavity with a certain volume , and reserve an air-inflating port and an air-outlet, wherein, the air-inflating port is fed with Ar gas to protect the reverse side of the weld; laser welding is performed on the front-end frame and the rear-end frame; rib welding is performed, wherein the rib welding is also It includes: welding at the intersection of the longitudinal rib and the circumferential rib; welding at the joint of the rib assembly and the butt joint boss on the lower bottom plate, the front frame, and the rear frame. Solve the technical problems of long manufacturing cycle, unstable welding quality, and complicated process equipment caused by casting and other welding process methods for the lightweight skeleton of the titanium alloy cabin section in the prior art, and realize stable and reliable joint welding quality and fast welding speed. The titanium alloy cabin frame has the technical effect of high manufacturing precision, high structural strength and low manufacturing cost.
Description
technical field [0001] The invention relates to the field of aerospace technology, in particular to a laser welding method. Background technique [0002] Modern aerospace vehicles are developing in the direction of high Mach, long endurance, high maneuverability, and high penetration capabilities. The aircraft structure is required to have good specific strength, specific stiffness, high-temperature bearing capacity and high-temperature durability. Therefore, the titanium alloy skin skeleton is light. A large number of quantitative structures have been adopted, and gradually have a tendency to develop into the main structure of the aircraft. [0003] However, in the process of implementing the technical solutions in the embodiments of the present application, the inventors of the present application found that the above-mentioned prior art has at least the following technical problems: [0004] In the prior art, the lightweight skeleton of the titanium alloy cabin section a...
Claims
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IPC IPC(8): B23K26/348B23K26/60B23K101/24
CPCB23K26/348B23K26/60B23K2101/24
Inventor 王维新刘巨锋宋豫娟李春光成唤豹张如平
Owner HUBEI SANJIANG AEROSPACE GRP HONGYANG ELECTROMECHANICAL