CN202989324U - Airplane outer cylinder part inner bore electroplating clamp - Google Patents
Airplane outer cylinder part inner bore electroplating clamp Download PDFInfo
- Publication number
- CN202989324U CN202989324U CN 201220682849 CN201220682849U CN202989324U CN 202989324 U CN202989324 U CN 202989324U CN 201220682849 CN201220682849 CN 201220682849 CN 201220682849 U CN201220682849 U CN 201220682849U CN 202989324 U CN202989324 U CN 202989324U
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- anode
- inner bore
- fixed
- strongback
- outer cylinder
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- Withdrawn - After Issue
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Abstract
The utility model discloses an airplane outer cylinder part inner bore electroplating clamp, relating to the field of airplane part electroplating. The airplane outer cylinder part inner bore electroplating clamp comprises a cathode protection ring (1), an upper anode positioning plate (2), a lower anode positioning plate (3) and a conformal anode (4), wherein the cathode protection ring (1) is fixed at the upper end of an airplane outer cylinder part; the upper anode positioning plate (2) is fixed on the cathode protection ring (1); the lower anode positioning plate (3) is fixed at the bottom of the airplane outer cylinder part; and the conformal anode (4) is fixed at the middle of the upper anode positioning plate (2) and the lower anode positioning plate (3). The specific implementation way solves the problems that an anode and an inner bore are not easily arranged concentrically and coaxially and the conformal anode easily deforms under heat. Therefore, the phenomena of unilateral and elliptical plating and non-uniform plating are avoided, and the requirements for the part inner bore size plating are guaranteed.
Description
Technical field
The utility model relates to the airplane parts field of electroplating, be specifically related to a kind of aircraft urceolus inner bore of part electroplating clamp.
Background technology
The outer barrel part of aircraft requires the endoporus plating chromium, traditional dress is hung mode: part adopts iron sheet to insulate, endoporus adopts sheet lead to do conformal anode, and be fixed with iron wire, this kind method easily causes well centre-lock of conformal anode, cause anode and endoporus can not concentric co-axial and in the process of electroplating sheet lead (δ=1mm) due to overheated easy generation distortion, make coating be that monolateral shape, uneven coating are even, endoporus is ellipticity, port and easily produces the phenomenons such as chromium knurl, do not reach interior hole dimension plating requirement.
The utility model content
For the deficiency that exists on prior art, the utility model purpose is to be to provide a kind of aircraft urceolus inner bore of part electroplating clamp, can make part obtain the coating of size uniform in electroplating process, satisfies the requirement of size plating.And the part port is without long-pending chromium phenomenon.
To achieve these goals; the utility model is to realize by the following technical solutions: aircraft urceolus inner bore of part electroplating clamp; comprise galvanic protection ring, Anodic strongback; lower anode strongback and conformal anode; the galvanic protection ring is fixed on barrel part upper end outside aircraft; the Anodic strongback is fixed on the galvanic protection ring, and lower anode strongback is fixed on bottom the outer barrel part of aircraft, and conformal anode is fixed on the middle part of Anodic strongback and lower anode strongback.
According to above-mentioned aircraft urceolus inner bore of part electroplating clamp, wherein, described conformal anode adopts the stereotype of δ=4mm to make, and surface uniform distribution Φ 10mm is cellular aperture.
The utility model has increased the galvanic protection ring, has solved the long-pending chromium problem of part, and the while is the position of Anodic strongback fixedly.Increased up and down anode strongback, solved the problem that conformal anode and endoporus are difficult for concentric co-axial, the stereotype of conformal anode employing δ=4mm is made, and surface uniform distribution Φ 10mm is cellular aperture, has solved the conformal anode yielding problem of being heated.Solve coating more than comprehensive and be the even phenomenon of monolateral shape, ellipticity and uneven coating, guaranteed the requirement of inner bore of part size plating.
Description of drawings
Describe the utility model in detail below in conjunction with the drawings and specific embodiments.
Fig. 1 is structural representation of the present utility model.
Embodiment
For technique means, creation characteristic that the utility model is realized, reach purpose and effect is easy to understand, below in conjunction with embodiment, further set forth the utility model.
With reference to Fig. 1; this embodiment is by the following technical solutions: aircraft urceolus inner bore of part electroplating clamp; comprise galvanic protection ring 1, Anodic strongback 2; lower anode strongback 3 and conformal anode 4; galvanic protection ring 1 is fixed on barrel part upper end outside aircraft; Anodic strongback 2 is fixed on galvanic protection ring 1, and lower anode strongback 3 is fixed on bottom the outer barrel part of aircraft, and conformal anode 4 is fixed between Anodic strongback 2 and lower anode strongback 3.
According to above-mentioned, wherein, described conformal anode 4 adopts the stereotype of δ=4mm to make, and surface uniform distribution Φ 10mm is cellular aperture.
A galvanic protection ring 1 has been loaded onto in this embodiment barrel part upper end outside aircraft; fixed an Anodic strongback 2 on galvanic protection ring 1; a lower anode strongback 3 has been placed in the part bottom, and conformal anode 4 is fixed between Anodic strongback 2 and lower anode strongback 3.
This embodiment has solved anode and endoporus and has been difficult for concentric co-axial and the conformal anode yielding problem of being heated.Solve coating more than comprehensive and be the even phenomenon of monolateral shape, ellipticity and uneven coating, guaranteed the requirement of inner bore of part size plating.
Above demonstration and described ultimate principle of the present utility model and principal character and advantage of the present utility model.The technician of the industry should understand; the utility model is not restricted to the described embodiments; that describes in above-described embodiment and specification sheets just illustrates principle of the present utility model; under the prerequisite that does not break away from the utility model spirit and scope; the utility model also has various changes and modifications, and these changes and improvements all fall in claimed the utility model scope.The claimed scope of the utility model is defined by appending claims and equivalent thereof
Claims (2)
1. aircraft urceolus inner bore of part electroplating clamp; it is characterized in that; comprise galvanic protection ring (1), Anodic strongback (2); lower anode strongback (3) and conformal anode (4); galvanic protection ring (1) is fixed on barrel part upper end outside aircraft; Anodic strongback (2) is fixed on galvanic protection ring (1); lower anode strongback (3) is fixed on bottom the outer barrel part of aircraft, and conformal anode (4) is fixed on the middle part of Anodic strongback (2) and lower anode strongback (3).
2. aircraft urceolus inner bore of part electroplating clamp according to claim 1, is characterized in that, described conformal anode (4) adopts the stereotype of δ=4mm to make, and surface uniform distribution Φ 10mm is cellular aperture.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220682849 CN202989324U (en) | 2012-12-12 | 2012-12-12 | Airplane outer cylinder part inner bore electroplating clamp |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220682849 CN202989324U (en) | 2012-12-12 | 2012-12-12 | Airplane outer cylinder part inner bore electroplating clamp |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202989324U true CN202989324U (en) | 2013-06-12 |
Family
ID=48560520
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220682849 Withdrawn - After Issue CN202989324U (en) | 2012-12-12 | 2012-12-12 | Airplane outer cylinder part inner bore electroplating clamp |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202989324U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103031589A (en) * | 2012-12-12 | 2013-04-10 | 江西洪都航空工业集团有限责任公司 | Inner hole electroplating fixture for airplane outer barrel part |
| CN104818514A (en) * | 2015-05-07 | 2015-08-05 | 哈尔滨飞机工业集团有限责任公司 | Chromium-plated tooling |
| CN104818507A (en) * | 2015-04-02 | 2015-08-05 | 中航飞机股份有限公司西安飞机分公司 | Method for preventing cracking of electroplated chrome layer at internal cylinder part slope |
| CN114232044A (en) * | 2021-05-18 | 2022-03-25 | 西比里电机技术(苏州)有限公司 | Thermoelectric chemical oxidation clamp |
-
2012
- 2012-12-12 CN CN 201220682849 patent/CN202989324U/en not_active Withdrawn - After Issue
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103031589A (en) * | 2012-12-12 | 2013-04-10 | 江西洪都航空工业集团有限责任公司 | Inner hole electroplating fixture for airplane outer barrel part |
| CN103031589B (en) * | 2012-12-12 | 2015-09-30 | 江西洪都航空工业集团有限责任公司 | A kind of airplane outer barrel inner bore of part electroplating clamp |
| CN104818507A (en) * | 2015-04-02 | 2015-08-05 | 中航飞机股份有限公司西安飞机分公司 | Method for preventing cracking of electroplated chrome layer at internal cylinder part slope |
| CN104818514A (en) * | 2015-05-07 | 2015-08-05 | 哈尔滨飞机工业集团有限责任公司 | Chromium-plated tooling |
| CN114232044A (en) * | 2021-05-18 | 2022-03-25 | 西比里电机技术(苏州)有限公司 | Thermoelectric chemical oxidation clamp |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20130612 Effective date of abandoning: 20150930 |
|
| RGAV | Abandon patent right to avoid regrant |