Cutting-off device for coating-resistant film of aviation cylindrical part

Abstract

The utility model relates to a cutting device for a coating film of an aviation cylindrical part. The cutting device comprises a supporting column body, a first sleeving body and a second sleeving body, the supporting column body is of a cylinder structure, and the outer diameter of the supporting column body is larger than the inner diameter of the aviation cylindrical part to be machined. The first sleeving body and the second sleeving body are both of a cylinder structure, are detachably fixed to the two ends of the supporting column body respectively and share the same axis with the supporting column body; the height of the first sleeving body is equal to the distance between the top of the area, needing to be plated with the protective layer, of the aviation cylindrical part and the bottom of the aviation cylindrical part; the height of the second sleeving body is equal to the distance between the top of the area, needing to be plated with the protective layer, of the aviation cylindrical part and the bottom of the aviation cylindrical part; and blades are arranged at the end parts of the outer sides of the first sleeving body and the second sleeving body through bolts. The device can rapidly cut off the group coating film needing to be plated with the protective layer in the part, and the machining efficiency is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of metal surface treatment, in particular to a device for removing resist coating from aviation tubular parts. Background Art

[0002] like Figure 1 The figure below shows the structure of an aviation cylindrical part with a through hole on its outer wall. Electrochemical treatment is required to form a protective layer on a specific area of the part's inner wall. One end of the through hole extends all the way to the inner wall where the protective layer is required, while the rest of the part's inner wall and the inner wall of the through hole do not require a protective layer. While resist plating on the inner wall of the through hole is relatively simple, simply inserting a resist pin into the hole, treating specific areas of the part's inner wall is more complex.

[0003] At present, resist coating is usually applied above and below the inner wall of the part where the protective layer needs to be formed. However, since the aperture of the through hole of the above-mentioned aviation tubular part is not large, it is difficult to accurately apply the resist coating, and the width of the protective layer formed subsequently often does not meet the design requirements.

[0004] Therefore, it is desired to provide an apparatus for removing resist coating from aviation tubular parts to solve the above technical problems. Utility Model Content

[0005] The purpose of the utility model is to provide a device for removing the resist coating on an aviation tubular part, which can quickly remove the group coating that needs to be coated with a protective layer in the part, thereby improving processing efficiency.

[0006] In order to achieve the purpose of the above utility model, the utility model of the aircraft cylindrical parts resist coating removal device includes a support column, a first sleeve body and a second sleeve body;

[0007] The support column is a cylindrical structure, and the outer diameter of the support column is larger than the inner diameter of the aviation tubular part to be processed;

[0008] The first sleeve body and the second sleeve body are both cylindrical structures, and the first sleeve body and the second sleeve body are detachably fixed to the two ends of the support column, and share the same axis with the support column;

[0009] The height of the first sleeve is equal to the distance between the top of the area of the aviation cylindrical part requiring protective coating and the bottom of the aviation cylindrical part;

[0010] The height of the second sleeve is equal to the distance between the top of the area of the aviation cylindrical part requiring protective coating and the bottom of the aviation cylindrical part;

[0011] The outer ends of the first sleeve body and the second sleeve body are both provided with blades through bolts.

[0012] Preferably, studs are fixed at the center positions of both ends of the support column, and threaded holes are provided at the bottom center positions of the first sleeve body and the second sleeve body. The first sleeve body and the second sleeve body are threadedly connected to the studs at both ends of the support column through the threaded holes.

[0013] Preferably, both blades are provided with connecting through holes, and the connecting through holes are plugged with plug posts;

[0014] The connecting through hole is provided with a first connecting hole and a second connecting hole on a track rotating around the bolt;

[0015] When the connecting through hole is rotated to be just above the first connecting hole, the entire blade is located in the socket body;

[0016] When the through hole is rotated to be just above the second connecting hole, the blade extends out of the sleeve body and is matched with the inner wall of the aviation cylindrical part.

[0017] Preferably, a non-slip rubber layer is provided on the side wall of the support column.

[0018] Compared with the existing technology, the utility model of the aircraft cylindrical parts resist coating removal device has the following advantages:

[0019] (1) By detachably setting two sleeves at both ends of the support column and setting blades on the end faces of the sleeves, the coating layer that needs to be plated on the part can be quickly cut off, thereby improving processing efficiency;

[0020] (2) Simple structure and easy to use. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a structural diagram of an aviation cylindrical part in the background art;

[0022] Figure 2 Schematic diagram of the structure of the support column in this embodiment;

[0023] Figure 3 This is a schematic structural diagram of the first socket body without blades in this embodiment;

[0024] Figure 4 This is a schematic structural diagram of a device for removing resist coating from an aviation tubular part without inserting a pin in this embodiment;

[0025] Figure 5 Schematic diagram of the structure of the resist film removal device for aviation tubular parts according to this embodiment. DETAILED DESCRIPTION

[0026] The present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0027] Example 1

[0028] The invention discloses a device for removing resist coating from an aviation tubular part, comprising a supporting column 1, a first sleeve 2 and a second sleeve 3.

[0029] The support column 1 is a cylindrical structure, and the outer diameter of the support column 1 is larger than the inner diameter of the aviation tubular part to be processed.

[0030] The first sleeve body 2 and the second sleeve body 3 are both cylindrical structures, and the first sleeve body 2 and the second sleeve body 3 are detachably fixed to the two ends of the support column 1 respectively, and share the same axis with the support column 1.

[0031] In this embodiment, if Figure 1 As shown, studs 4 are fixed at the center positions of both ends of the support column 1, and threaded holes are provided at the bottom center positions of the first sleeve body 2 and the second sleeve body 3. The first sleeve body 2 and the second sleeve body 3 are threadedly connected to the studs 4 at both ends of the support column 1 through the threaded holes to achieve a detachable connection.

[0032] like Figure 3 and Figure 4 As shown, the height of the first sleeve body 2 is equal to the distance between the top of the area of the aviation tubular part that needs to be coated with a protective layer and the bottom of the aviation tubular part; the height of the second sleeve body 3 is equal to the distance between the top of the area of the aviation tubular part that needs to be coated with a protective layer and the bottom of the aviation tubular part.

[0033] The outer ends of the first sleeve body 2 and the second sleeve body 3 are both provided with blades 6 through bolts 5 .

[0034] After the inner wall of the aviation tubular part is affixed with the resist coating, loosen the bolt 5, rotate the blade 6 to be located as a whole within the end face of the first sleeve body 2, insert the first sleeve body 2 into the aviation tubular part, rotate the blade 6 again so that it partially extends out of the end face of the first sleeve body 2, tighten the bolt 5, rotate the support column 1, and the blade 6 cuts the group coating along the rotation trajectory; then take out the first sleeve body 2, insert the second sleeve body 3, repeat the above operation again, and finally use the external stick to pass through the through hole on the outer wall of the aviation tubular part to peel off the cut group coating.

[0035] In this embodiment, if Figure 5 As shown, both blades 6 are provided with a connecting through hole 7, and a plug post 8 is inserted into the connecting through hole 7; the connecting through hole 7 is provided with a first connecting hole 9 and a second connecting hole 10 on the trajectory of rotation around the bolt 5. When the connecting through hole is rotated to the top of the first connecting hole, the entire blade is located in the socket.

[0036] When the through hole is rotated to be directly above the second connecting hole 10 , the blade 6 extends out of the socket body and fits with the inner wall of the aviation cylindrical part.

[0037] With such an arrangement, the position of the blade 6 can be controlled more accurately to avoid scratching the inner wall of the aviation tubular part.

[0038] In this embodiment, a non-slip rubber layer (not shown) is provided on the side wall of the support column 1 to facilitate the user's grip.

[0039] Although the embodiments of the present invention have been shown and described above, it can be understood that the above embodiments are illustrative and cannot be understood as limitations on the present invention. Ordinary technicians in this field can change, modify, replace and modify the above embodiments within the scope of the present invention.

Claims

1. An apparatus for removing resist coating from aviation tubular parts, characterized in that: It includes a supporting column, a first sleeve body and a second sleeve body; The support column is a cylindrical structure, and the outer diameter of the support column is larger than the inner diameter of the aviation tubular part to be processed; The first sleeve body and the second sleeve body are both cylindrical structures, and the first sleeve body and the second sleeve body are detachably fixed to the two ends of the support column, and share the same axis with the support column; The height of the first sleeve is equal to the distance between the top of the area of the aviation cylindrical part requiring protective coating and the bottom of the aviation cylindrical part; The height of the second sleeve is equal to the distance between the top of the area of the aviation cylindrical part requiring protective coating and the bottom of the aviation cylindrical part; The outer ends of the first sleeve body and the second sleeve body are both provided with blades through bolts.

2. The apparatus for removing resist coating from an aviation tubular part according to claim 1, characterized in that: Studs are fixed at the center positions of both ends of the support column, and threaded holes are provided at the center positions of the bottoms of the first sleeve and the second sleeve. The first sleeve and the second sleeve are threadedly connected to the studs at both ends of the support column through the threaded holes.

3. The apparatus for removing resist coating from an aviation tubular part according to claim 1, characterized in that: Both blades are provided with connecting through holes, and the connecting through holes are plugged with plug posts; The connecting through hole is provided with a first connecting hole and a second connecting hole on a track rotating around the bolt; When the connecting through hole is rotated to be just above the first connecting hole, the entire blade is located in the socket body; When the through hole is rotated to be just above the second connecting hole, the blade extends out of the sleeve body and is matched with the inner wall of the aviation cylindrical part.

4. The apparatus for removing resist coating from an aviation tubular part according to any one of claims 1 to 3, characterized in that: An anti-slip rubber layer is provided on the side wall of the support column.

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