CN104476454A - Metal clamping plate working profile surface correction and compensation method - Google Patents
Metal clamping plate working profile surface correction and compensation method Download PDFInfo
- Publication number
- CN104476454A CN104476454A CN201410546197.9A CN201410546197A CN104476454A CN 104476454 A CN104476454 A CN 104476454A CN 201410546197 A CN201410546197 A CN 201410546197A CN 104476454 A CN104476454 A CN 104476454A
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- China
- Prior art keywords
- clamp
- profile
- adhesive
- clamping plate
- profile surface
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J15/00—Riveting
- B21J15/38—Accessories for use in connection with riveting, e.g. pliers for upsetting; Hand tools for riveting
- B21J15/42—Special clamping devices for workpieces to be riveted together, e.g. operating through the rivet holes
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Jigs For Machine Tools (AREA)
Abstract
The invention discloses an overproof metal clamping plate profile surface correction and compensation method. The overproof metal clamping plate profile surface correction and compensation method comprises the following steps of knowing a theory shape of a clamping plate working profile, coating adhesive EA9394 on the overproof metal clamping plate profile surface, enabling the piling height of the adhesive to be larger than the theory shape of the clamping plate profile surface and machining the profile surface according to the theory shape of the clamping plate profile surface after the adhesive is solidified.
Description
Technical field
The present invention relates to aero-manufacturing technology field, be applied in the process of supplement production, such as, on frock, fixture, specially for the method for metal card template face correction-compensation in airplane component assembling process.
Background technology
In transporation by plane production process, use assembly jig in a large number, type frame equips clamp, for locating covering.The working surface of clamp determines the theoretical profile of aircraft skin.Only after covering laminating clamp profile, riveted joint assembling could carried out to skin assemblies.Therefore, clamp profile should meet the theoretical profile of aircraft, and produces directly impact to the profile of skin assemblies.
In order to adapt to the requirement of transporation by plane, normally machine adds clamp, milling is to the theoretical profile of aircraft.But in situations, the working surface of clamp can not meet the matching requirements of aircraft spare part: 1. the theoretical profile change of aircraft; 2. clamp profile adds in process overproof at machine; 3. clamp in use weares and teares, damages.At this moment, the theoretical profile of clamp profile and aircraft is not inconsistent, and needs again to make clamp or process existing clamp.It is evident that the cost again making clamp is huge, and processing is compensated to existing clamp not only can reduce costs, can also the manufacturing cycle be shortened.
The key compensating processing to existing clamp is the compensation to clamp surface finished materials, if finished surface principal-employment, can continue to add clamp machine, milling to the theoretical profile of aircraft, if minus tolerance, then need to compensate clamp profile.In actual production process, more generally principal-employment and the interlaced arrangement of minus tolerance, that is, in process, compensates the machine of profile and adds and add mixed in together with the machine on virgin metal surface.This will supplement to repay the material of clamp consistent with intermetallic composite coating parameter, so that the processing of follow-up profile.No matter be principal-employment or minus tolerance, finally according to new theoretical sharp processing, obtain new frock clamp profile.
Consider from the angle of machining, profile compensative material can be selected can processing plastic.Can processing plastic be the epoxy resin that a kind of foamed material is filled, density be low, and machining property is good.Select can processing plastic exist defect be that material hardness is low, intensity is also low, can not meet the requirement of Assembly of the parts.Meanwhile, due to can the hardness of processing plastic low, the rotating speed adding cutter head in man-hour is low, the amount of feeding large, can the parameter of machining and metal inconsistent on processing plastic.This compensative material for clamp profile alternate and metal, need in production frequently to adjust machined parameters, and can not ensure the crudy of profile, and this is fatal problem for batch production.Therefore, the key problem that a kind of adhesive strength is high, machined parameters is consistent with metal adhesive material becomes clamp profile correction-compensation is sought.
Summary of the invention
Object of the present invention is just to provide a kind of method of clamp profile correction-compensation, effectively can ensure that clamp profile meets the theoretical profile of aircraft, after being connected on assembly jig, location covering, and in covering assembling process, support assembling processes such as riveting, be spirally connected, deformation or displacement can not be produced, ensure the profile of load module.
A kind of method of overproof metal card template face correction-compensation, the theoretical profile of known clamp working surface, it is characterized in that, first the clamp profile removing surface by overproof is clean, then at overproof clamp profile surface coating stick EA9394, the theoretical profile allowing adhesive pile the height infused to be greater than clamp profile, after adhesive solidification, according to the theoretical sharp processing profile of clamp profile.
The invention has the beneficial effects as follows the object utilizing the characteristic of material EA9394 to realize clamp profile correction-compensation.On clamp, the correction-compensation of profile needs the problem of solution two aspects, and the first increases material on clamp, and material and metal should possess good adhesion; It two is that the material increased should have machine and adds ability, can realize the processing of profile, thus ensure follow-up assembling.EA9394 can solve this two problems well.EA9394 is two component modified epoxy adhesives, and original state is grey pastel.This paste adhesive viscosity is high, can pile and infuse in metal surface, forms shape to be processed, and keeps this shape always, until solidification terminates.After solidification, the shore D hardness of adhesive is more than 80, is highly stable material.EA9394 is very high to adhesive strengths such as metal, timber, composites, more than 20Mpa.Meanwhile, the machining property of the EA9394 material after solidification and the performance of aluminium basically identical, the EA9394 making simultaneously to process after aluminium and solidification becomes possibility, and does not change cutter and machined parameters.That is, after application EA9394, no matter principal-employment, minus tolerance, the machine of profile add can time processing out.Here it is make use of the basically identical characteristic of the machining property of EA9394 and metallic aluminium after solidification.These characteristics make it become the splendid material of adjustment clamp profile.
Below in conjunction with embodiment accompanying drawing, this application is described in further details:
Accompanying drawing explanation
Fig. 1 is the metal clamp after profile correction-compensation
Number description: 1 clamp, 2 working surfaces, 3 clamp locating holes, 4 adhesive
Detailed description of the invention
See accompanying drawing, clamp 1 is typical transporation by plane form component on aircraft, and for covering location, the profile of this clamp determines the theoretical profile of final assembly.Profile according to the theoretical sharp processing of aircraft in early stage out.Due to the theoretical profile change of aircraft, occur minus tolerance between clamp and covering, working surface 2 and covering are not fitted, and make existing metal clamp become overproof clamp.Common method is discarded existing clamp, again processes.In order to utilize existing clamp, avoiding waste, employing this patent method, coating adhesive 4 in the profile of clamp, and heap infuses adhesive to exceeding new profile, after adhesive 4 solidifies, add according to the theoretical profile machine of the aircraft after change, form the working surface of new composite demand.Clamp after profile correction-compensation meets spare part production requirement completely.It is emphasised that, on the former overproof working surface 2 of clamp 1, heap infuses adhesive 4, the side of clamp can maintain adhesive heap and infuse performance, form the requisite part of adhesive strength, clamp locating hole 3 is benchmark functional holes of clamp itself, for the location with frock clamp, being the basis forming the theoretical profile of aircraft, is also the benchmark of the theoretical profile of clamp.
Through overtesting, the application selects adhesive EA9394 to carry out material compensation to clamp profile.Shown below is overall process embodiment:
1, clamp is cleared up
Use the profile that No. 180 sand papering metal clamps are overproof.Butanone or acetone is used to clear up the profile of polishing.At room temperature dry 10 minutes to 15 minutes.Repeat above-mentioned operation, until completely clean.
2, adhesive is configured
Base cream and the curing agent of EA9394 is weighed, thoroughly mixing two adhesive components, until mixture no color differnece according to the ratio of 100:17.The adhesive of mixing is placed in vacuum still and vacuumizes, get rid of the bubble in adhesive.
3, gluing
With scraper, the adhesive mixed is coated in clamp profile.Adhesive should be piled and infuse, and highly exceedes the theoretical profile height of clamp.
4, cured adhesive
At room temperature place adhesive solidification after 24 hours.The method of another solidification is placed in an oven by glue-coated clamp, solidifies 1.5 hours, at least place 4 hours after cooling at 50 DEG C ~ 60 DEG C.
5, machine adds profile
According to new theoretical profile, the clamp machine after solidification is added to new profile.The processing technology of mechanical processing technique parameters selection aluminum alloy materials.
6, repair
Remove unnecessary adhesive.Finishing clamp profile.
Claims (1)
1. the method for an overproof metal card template face correction-compensation, the theoretical profile of known clamp working surface, it is characterized in that, first the clamp profile removing surface by overproof is clean, then at overproof clamp profile surface coating stick EA9394, the theoretical profile allowing adhesive pile the height infused to be greater than clamp profile, after adhesive solidification, according to the theoretical sharp processing profile of clamp profile.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410546197.9A CN104476454A (en) | 2014-10-15 | 2014-10-15 | Metal clamping plate working profile surface correction and compensation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410546197.9A CN104476454A (en) | 2014-10-15 | 2014-10-15 | Metal clamping plate working profile surface correction and compensation method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104476454A true CN104476454A (en) | 2015-04-01 |
Family
ID=52751127
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410546197.9A Pending CN104476454A (en) | 2014-10-15 | 2014-10-15 | Metal clamping plate working profile surface correction and compensation method |
Country Status (1)
| Country | Link |
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| CN (1) | CN104476454A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109622778A (en) * | 2018-11-12 | 2019-04-16 | 东风模具冲压技术有限公司 | A kind of type face compensation method for die debugging |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020049263A1 (en) * | 1999-08-12 | 2002-04-25 | Kocsis Betty H. | Method for restoring a surface on a metal substrate |
| CN1466188A (en) * | 2002-07-05 | 2004-01-07 | 旺宏电子股份有限公司 | Method for correcting convex block outline |
| CN1613888A (en) * | 2003-11-05 | 2005-05-11 | 北京航空航天大学 | Ultra-low temperature adhesive of epoxy resin and preparation thereof |
| CN102762336A (en) * | 2010-02-10 | 2012-10-31 | 斯奈克玛 | Method for repairing a flange of a housing |
| CN103785988A (en) * | 2012-11-02 | 2014-05-14 | 深圳市百安百科技有限公司 | Method for restoring and repairing damaged equipment and parts |
-
2014
- 2014-10-15 CN CN201410546197.9A patent/CN104476454A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020049263A1 (en) * | 1999-08-12 | 2002-04-25 | Kocsis Betty H. | Method for restoring a surface on a metal substrate |
| CN1466188A (en) * | 2002-07-05 | 2004-01-07 | 旺宏电子股份有限公司 | Method for correcting convex block outline |
| CN1613888A (en) * | 2003-11-05 | 2005-05-11 | 北京航空航天大学 | Ultra-low temperature adhesive of epoxy resin and preparation thereof |
| CN102762336A (en) * | 2010-02-10 | 2012-10-31 | 斯奈克玛 | Method for repairing a flange of a housing |
| CN103785988A (en) * | 2012-11-02 | 2014-05-14 | 深圳市百安百科技有限公司 | Method for restoring and repairing damaged equipment and parts |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109622778A (en) * | 2018-11-12 | 2019-04-16 | 东风模具冲压技术有限公司 | A kind of type face compensation method for die debugging |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150401 |