Electron beam welding tooling and welding process for aircraft cylinder body and wing

Abstract

The invention relates to an electron beam welding tool and a welding process for a cylinder and wings of an aircraft. The welding tool comprises a plurality of groups of annular hoops, base plates, a center shaft and an inner supporting disc, wherein each group of annular hoops is formed by abutting joint of a plurality of arc-shaped hoops end to end; the center shaft is arranged through the inner part of the cylinder; and the inner supporting disc can sleeve the center shaft and the outer circumferential surface of the inner supporting disc props against the inner wall of the cylinder. The welding process comprises the following steps: during welding, forming a to-be-welded accessory by the cylinder, the wings and the welding tool; finally, putting the to-be-welded accessory in a vacuum chamber for electron beam welding; after welding, performing vacuum cooling for 10min; removing vacuum and taking out a welded test piece; and disassembling the welding tool to finish welding. According to the electron beam welding tool and the welding process for the cylinder and wings of the aircraft provided by the invention, the wings and the cylinder in the aircraft are welded by virtue of an electron beam welding technology which is centralized in energy density and small in heat input, and meanwhile, being matching with the welding tool for controlling the deformation precision, the welding quality and the post-welding dimensional precision can be remarkably improved, and at the same time, the welding stability and the welding efficiency are improved.

Description

technical field [0001] The invention relates to the technical field of metal material welding, in particular to an electron beam welding tool and a welding process for an aircraft cylinder body and wings. Background technique [0002] In order to reduce the weight of the aircraft and improve the flight distance and balance control of the aircraft, the lightweight, high-strength titanium alloy frame structure is widely used in this type of aircraft. It is a very difficult problem in processing. Since the wall thickness of the cylinder and the wing plate are very thin, and the structural form is a T-joint, traditional welding methods such as TIG welding and MIG welding are very prone to uncontrollable deformation and weld penetration. , causing catastrophic damage. Therefore, in the current aircraft, riveting is the main form. First, the bottom of the wing is designed as a thick-bottomed T-shaped structure, and then the cylinder and the wing are connected by riveting. However...

AI Technical Summary

Problems solved by technology

However, there are very few experimental studies on such dissimilar titanium alloy T-joints by electron beam processing technology, and there are no relevant reports and studies on the special joint form and size in aircraft.

In addition, in the literature and patent technology search, no relevant research reports have been found on the design of the welding deformation control tooling for the wing and the barrel.

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