Eccentric bushing alignment and recovery method based on alignment and recovery assembly

Abstract

The invention relates to the technical field of part assembly, in particular to an eccentric bushing alignment and recovery method based on an alignment and recovery assembly, a bushing inner hole positioning pin sequentially penetrate through an inner hole of an intersection bushing I on a first layer of lug piece and a bottom hole in a second layer of lug piece; an adapter bushing is inserted between the bushing inner hole positioning pin and the bottom hole in the second layer of lug piece; a marking bushing is arranged on the adapter bushing, then a bushing to be recovered is arranged on the bushing inner hole positioning pin in a sleeving mode, and the bushing to be recovered is rotated till the bushing to be recovered can completely enter the marking bushing; after the bushing to be recovered is pressed into 2/3 of the bottom hole in the second layer of lug piece, the marking bushing is detached, and then the recovery bushing is completely pressed into the bottom hole in the second layer of lug piece; and finally, the rest structure of the alignment and recovery assembly is detached from an insertion lug structure of an aircraft intersection point. According to the technical scheme, the recovery and replacement technological process for the eccentric bushing of the aircraft insertion lug structure is greatly simplified, the operation time can be effectively shortened, and the alignment and recovery assembly is simple in structure, light and convenient to carry.

Description

technical field [0001] The invention relates to the technical field of component assembly, in particular to an alignment restoration method for an eccentric bush based on an alignment restoration assembly. Background technique [0002] The wing-body joints of existing military aircraft generally adopt the lug structure. In order to improve the anti-extrusion strength, service life and subsequent maintainability, steel bushings are usually installed in the aluminum matrix structure. In order to ensure that each lug The inner hole of the bushing on the chip is coaxial, and the inner hole of the bushing is usually reamed. There is a certain amount of eccentricity between the inner hole of the bushing and the bottom hole on the base, and the eccentricity is generally 1 to 2 mm. [0003] Since the aircraft is prone to stress deformation at the intersection of the wing and body after flight, and the fuselage and wing parts are easily disassembled, the bushes will easily fall off, ...

AI Technical Summary

Problems solved by technology

[0003] After the aircraft is in flight, stress deformation is likely to occur at the junction of the wing and body, and the fuselage and wing parts are likely to cause the bushing to fall off when the fuselage and wing parts are disassembled. The worn bushes may also need to be replaced during aircraft maintenance

Because there is an eccentricity of 1 to 2mm between the inner hole and the outer circle of the bushing, there is no mature technology for correcting the eccentricity when restoring the bushing to ensure the coaxiality of the bushings on the lugs of each layer. Therefore, the bushing should be replaced The accuracy cannot be guaranteed, and the replacement efficiency of the bushing cannot be improved

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