Aviation anti-vibration copper bush contracted pipe machining tool and using method

Abstract

The invention discloses a machining tool for an anti-vibration copper bush contracted pipe for aviation and a using method. The tool is composed of a clamping assembly and a supporting assembly. The clamping assembly is a circular sleeve, and a conical through hole is formed in the sleeve. The supporting assembly is a circular sleeve, and a straight-barrel-shaped through hole is formed in the sleeve. The using method comprises the steps that firstly, a copper bush raw material is blanked and loaded into the clamping assembly of the clamp, the raw material is extruded into the conical through hole of the clamping assembly by closing the jaw of the vice, and therefore the raw material is compressed to the required size of a part. The problems that in the prior art, due to the fact that the specification of raw materials is single, diversified part specifications cannot be met, materials of other specifications are used for substitute material machining, raw material waste is caused, and the part machining efficiency is reduced are solved.

Description

Technical Field

[0001] This invention relates to a tooling and method for machining anti-vibration copper sleeves for aviation, belonging to the field of mechanical processing. Background Technology

[0002] In the existing processing of vibration-damping copper bushings, due to the characteristics of the copper bushing material, processing technology, and the requirements of part dimensions, tubular material with the same inner diameter as the part is often selected for machining. During blanking, only the end face of the part needs to be polished, and the outer diameter machined to ensure the outer diameter dimension, and then the part is cut according to the process dimensions. However, due to material limitations, materials with the same inner diameter as all part models are not available in actual operation. If a material smaller than the inner diameter is selected, both the inner and outer diameters must be machined simultaneously to ensure the inner diameter and outer diameter dimensions of the part. This results in waste of raw materials, reduced processing efficiency, and more process failures. Therefore, developing an effective machining tooling to improve the applicability of vibration-damping copper bushing materials is particularly important. Summary of the Invention

[0003] The present invention addresses the problem that, in practical operations, materials with the same inner hole dimensions as all parts are unavailable. If a material smaller than the part's inner hole is selected, both the inner hole and outer diameter must be machined simultaneously to ensure the correct inner hole diameter and outer diameter. This results in wasted raw materials, reduced machining efficiency, and increased process failures.

[0004] To solve the above-mentioned technical problems, the present invention adopts the following technical solution: A tooling for machining anti-vibration copper sleeves for aviation applications comprises two parts: a clamping assembly and a supporting assembly. The clamping assembly is a circular sleeve with a tapered through hole inside. The supporting assembly is a circular sleeve with a straight cylindrical through hole inside.

[0005] A method for using a machining tool for shrinking and compressing anti-vibration copper sleeves for aviation involves first loading the raw copper sleeve material into the clamping assembly of the fixture, then squeezing the raw material into the tapered through hole of the clamping assembly by closing the jaws of the vise, thereby compressing the raw material to the required size of the part.

[0006] The beneficial effects of adopting the above technical solution are: This invention solves the problem in the prior art where the limited specifications of raw materials cannot meet the diverse specifications of parts, leading to the use of other materials for substituting materials, resulting in waste of raw materials and reduced parts processing efficiency. Attached Figure Description

[0007] Figure 1 This is a schematic diagram of the tooling used for machining the anti-vibration copper sleeve shrink tube of the present invention.

[0008] In the diagram: 1-clamping assembly, 2-support assembly, 3-vibration-resistant copper sleeve, 4-flat vise base.

[0009] Figure 2 for Figure 1 Schematic diagram of the clamping assembly.

[0010] Figure 3 for Figure 2 Top view.

[0011] In the figure: 1.1 - tapered through hole.

[0012] Figure 4 for Figure 1 Schematic diagram of the supporting component structure.

[0013] Figure 5 for Figure 4 Top view.

[0014] In the figure: 2.1 - Straight cylindrical through hole. Detailed Implementation

[0015] To make the objectives, technical solutions, and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only for explaining the present invention and are not intended to limit the present invention.

[0016] like Figure 1 As shown, the anti-vibration copper sleeve shrinking tooling of the present invention includes a flat-jaw vise base, a support assembly 2, and a clamping assembly 1. The base provides a stable foundation for the entire tooling, the support assembly 2 supports the clamping assembly 1, and the clamping assembly 1 is used to fix the anti-vibration copper sleeve 3, ensuring its stability during processing. After the raw material of the anti-vibration copper sleeve 3 is cut to a certain length, it is placed into the clamping assembly of the fixture. By closing the jaws of the vise, the raw material is squeezed into the tapered through hole 1.1 of the clamping assembly 1, thereby compressing the size of the raw material to the required size of the part.

Claims

1. A tooling for machining anti-vibration copper sleeves for aviation applications, characterized in that: It consists of two parts: a clamping assembly (1) and a support assembly (2); the clamping assembly (1) is a circular sleeve with a tapered through hole (1.1) inside; the support assembly (2) is a circular sleeve with a straight cylindrical through hole (2.1) inside.

2. The method of using the aerospace anti-vibration copper sleeve shrinking tooling as described in claim 1, characterized in that: First, the copper sleeve raw material is cut and loaded into the clamping assembly (1). The raw material is squeezed into the tapered through hole (1.1) of the clamping assembly (1) by closing the jaws of the vise, thereby compressing the size of the raw material to the required size of the part.

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