CN106272676B - Punching production method after satellite protective cover elder generation coating based on automation cutting - Google Patents
Punching production method after satellite protective cover elder generation coating based on automation cutting Download PDFInfo
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- CN106272676B CN106272676B CN201510317433.4A CN201510317433A CN106272676B CN 106272676 B CN106272676 B CN 106272676B CN 201510317433 A CN201510317433 A CN 201510317433A CN 106272676 B CN106272676 B CN 106272676B
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- protective cover
- cut
- satellite
- material core
- cutting
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Abstract
The invention discloses punching production method after a kind of satellite protective cover elder generation coating based on automation cutting; this method cuts file by producing non-porous and porose two cuttings to each satellite protective cover, perimeter line is not cut when making to cut by varying cutting cutter parameters；Material core is cut using the non-porous file that cuts, produces material core and pattern；Coating is carried out to material core and hole machined is carried out to coating protective cover；Protective cover is punched out using there is hole to cut file；Head will be cut to translate to tailstock, whether observation luminous point, which deflects away from, cuts edge；Gas is removed if deflecting away from, position adjustment is carried out to material core, luminous point is moved all the time along pattern edge when translating；Automatic cutting bed completion punching is used after fixing protective cover.The present invention is solved in satellite protective cover manufacturing process, after film manual punched-tape come it is of low quality, less efficient the problem of, improve the production technique of satellite protective cover.
Description
Technical field
The present invention relates to punching production method after a kind of satellite protective cover elder generation coating based on automation cutting, this method can
Directly apply to satellite protective cover production field.
Background technology
During using automatic cutting bed progress satellite protective cover processing, since protective cover material core external demand cladding is one layer thin
Film, and protective cover integrally needs to rush some circular holes for being fixed to satellite surface.Automation is utilized in protective cover material core
Cutting can not carry out the cladding of protective film before cutting shaping, and otherwise protective film will be consistent with material core size, can not will material core edge
All protections.And after shaping, if disposably completing punching to material core using cutting in forming process, hole can be wrapped by material again
The film covering of core, can not play fixed purpose, so that the processing of satellite protective cover pin hole rests on manually all the time
The mode of punching, causes the decline of installation accuracy, the reduction of efficiency.If material core and protective film are punched out protect again respectively
The cladding of cuticula, the alignment of pin hole between the two is carried out so in assembling process can greatly increase operation difficulty again, and consumption is more
More operating times.And similar product is can not find in other industry at present and solve the problems, such as this processing method.For this, there is provided one
Punching production method after satellite protective cover elder generation coating of the kind based on automation cutting, the not punching when processing protective cover material core,
Recycle a series of technological means to realize cutting punching after completing outer membrane cladding, eliminate manual processing link, improve whole
The gentle producing efficiency of body Automated water.
The content of the invention
, should it is an object of the invention to provide punching production method after the satellite protective cover elder generation coating based on automation cutting
Method directly applies to the making of satellite protective cover, eliminates manual processing link well, improves integrated automation level and system
Make efficiency.
Punching production method after a kind of satellite protective cover elder generation coating based on automation cutting, comprises the following steps：
1) two cuttings are made to each satellite protective cover and cuts file
When using AutoCAD when two-dimensional graphics Software on Drawing satellite protective cover shape graph, proposition two parts of drawings of drafting, one
A no pin hole, one has pin hole, wherein the drawing without pin hole is used to process protective cover material core, the drawing for having pin hole is used
Protective cover after to coating is punched out.Deletion has inside line segment and perforate of the pin hole pattern in addition to pin hole, prevents right
When having wrapped the protective cover of film and carrying out abatement nail, then cut an internal openings and original perforate is damaged.Then utilize
Cutting control software AutoCAD is generated respectively cuts file, and to there is pin hole to cut file by varying cutting cutter parameters
Perimeter line (graphic outer contour line) is not cut when making to cut, otherwise since coating rear perimeter edge size can increase, by former ruler
Very little cutting will destroy protective cover；
2) first use no pin to cut file when making satellite protective cover and cut material core
Brown paper and satellite protective cover material core raw material are sequentially placed on the automatic cutting bed processing surface of a wound, utilization is automatic cutting bed
Carry out brown paper satellite protective cover material core to cut, this cuts the file that cuts using no pin, and satellite protection is produced after cutting
The brown paper of cover material core and same shape；
3) coating is carried out to material core
Coating is carried out to satellite protective cover material core, confirms cladding face；
4) stone before punching
When carrying out pin hole machined to the satellite protective cover of coating, first satellite protective cover and material core are cut caused by
Pattern is stacked to cutting successively, expects that approximately equal is answered in core edge beyond pattern edge after vacuumizing；
5) determine to cut origin
Using pattern as reference data, origin will be cut and cut due to pattern at origin；
6) satellite protective cover paving location detects
The head that cuts of cutting is translated to tailstock, observation cuts whether position instruction luminous point deflects away from pattern edge；
7) satellite protective cover paving location adjusts
Edge is cut if cutting position instruction luminous point and deflecting away from, gas is removed and position adjustment is carried out to material core, when translating luminous point
All the time moved along pattern edge；
8) automatic cutting bed completion punching is used after fixing satellite protective cover.
Wherein, two-dimensional graphics software is AutoCAD softwares.
Wherein, using by hand to satellite protective cover material core progress coating in step 3).
Wherein, pin hole is the circular hole of diameter 4mm, for fixed satellite protective cover.
Wherein, expect that core edge must be wrapped in protective film after coating.
Wherein, the coating is to increase the polyester film that layer of surface is coated with metal outside Multi-layer material core.
Wherein, the detection of satellite protective cover paving location and adjustment can be completed by home-made contrivance, make protection shroud rim with cutting out
Bed sides aligned parallel.
The method of the present invention has taken into full account all key links that satellite protective cover makes, by the mode of former manual punching
The direct punching of cutting is changed to, and can ensure that punching position is accurate, solves the orientation problem processed again, including cutting is processed
Initial point and protective cover position determine, and successfully complete the making of satellite protective cover, improve processing quality, efficiency and automation
Degree.
Brief description of the drawings
Fig. 1 is the shape graph using two parts of satellite protective covers of AutoCAD Software on Drawing.
Wherein, 1- has pin hole pattern, 4- internal openings, 5- perimeter lines without pin hole pattern, 2- pin holes, 3-；
Satellite protective cover and pattern are laid with, cut the location drawing of origin setting when Fig. 2 is punching.
Wherein, 21- satellites protective cover, 22- cut origin, 23- patterns, 24- cutting machined surfaces.
Embodiment
Punching production method after the satellite protective cover elder generation coating based on automation cutting is made below in conjunction with the accompanying drawings further
Explanation.
The satellite of the present invention is realized with complicated surface high-temperature three-dimensional Multi-layer design production method by following steps：
1) as shown in Figure 1, going out two cuttings to each satellite protective cover cuts file
When using AutoCAD when two-dimensional graphics Software on Drawing satellite protective cover shape graph, proposition two parts of drawings of drafting, one
A no pin hole Fig. 1, one has pin hole Fig. 3, wherein the drawing without pin hole is used to process protective cover material core, there is pin hole
Drawing is used to be punched out the protective cover after coating.Deletion has inside line segments and perforate of the pin hole Fig. 3 in addition to pin hole 2,
Prevent when the protective cover to having wrapped film carries out abatement nail, then cut an internal openings 4 and original perforate is damaged.
Then generated respectively using cutting control software AutoCAD and cut file, and to there is pin hole to cut file by varying cutting
Perimeter line (graphic outer contour line) is not cut when cutter parameters make to cut, otherwise since coating rear perimeter edge size can increase
Greatly, protective cover will be destroyed by being cut by full size；
Wherein, the perforate of first figure is internal openings 4 in Fig. 1, and internal openings 4 are the perforates needed on protective cover,
Need to be processed when cutting material core, and after outer membrane wrap, when reusing cutting abatement nail, using there is pin
The figure in hole, is processed because having completed internal openings (non-pin hole) when core is expected in processing before, to remove inside and open
Hole 4 (non-pin hole), if bad original hole can be cut out on the contrary by cutting one time again.Perimeter line 5 refers to the outer contour of figure.
2) first use no pin to cut file when making satellite protective cover and cut material core
Brown paper and satellite protective cover material core raw material are sequentially placed on the automatic cutting bed processing surface of a wound, utilization is automatic cutting bed
Carry out satellite protective cover material core to cut, this cuts the file that cuts using no pin, and satellite protective cover material core is produced after cutting
And the brown paper of same shape, while material core processing is completed, provided for follow-up progress satellite protective cover paving location detection
Pattern, processing times are saved while material core and pattern uniformity is ensured；
3) coating is carried out to material core
By hand to satellite protective cover material core carry out coating, due to protective film only coat protective cover outwardly one side (relative to
Towards the one side of satellite), it should be noted and confirm cladding face；
4) as shown in Fig. 2, stone before punching
When carrying out pin hole machined to the satellite protective cover 21 of coating, first by satellite protective cover 21 with expecting that core is cut when, produces
Raw pattern 23 is stacked to cutting successively, is expected that approximately equal is answered in core edge beyond 23 edge of pattern after vacuumizing, is proposed with side
The neat pattern 23 of edge avoids satellite for reference data and protects the irregular increase operator of film edge to carry out satellite protective cover paving
If the difficulty of position detection；
5) as shown in Fig. 2, determining to cut origin
Using pattern as reference data, origin 22 will be cut and cut due to pattern at origin；
6) satellite protective cover paving location detects
Head will be cut to translate to tailstock, observation cuts whether position instruction luminous point deflects away from pattern edge, using cutting in itself
Function, does not increase extra cost, completes position detection；
7) satellite protective cover paving location adjusts
Edge is cut if cutting position instruction luminous point and deflecting away from, removes vacuum suction, and position adjustment is carried out to material core, makes light
Moved all the time along pattern edge during point translation, be punched out processing using the file that cuts for having pin hole at this time, it is ensured that pin
Hole is located at correct position；
8) automatic cutting bed completion punching is used after fixing satellite protective cover.
Although giving detailed description and explanation to the embodiment of the present invention above, it should be noted that
We can carry out the above embodiment various equivalent changes and modification according to the conception of the present invention, its caused function is made
, should all be within protection scope of the present invention during with the spirit still covered without departing from specification and attached drawing.
Claims (6)
1. punching production method after a kind of satellite protective cover elder generation coating based on automation cutting, comprises the following steps：
1）Two cuttings are made to each satellite protective cover and cut file
Using two-dimensional graphics Software on Drawing satellite protective cover shape graph when, draw two parts of drawings, one without pin hole, one has
Pin hole, and the internal openings for having pin hole pattern are deleted, the drawing of no pin hole is used to process protective cover material core, there is pin hole
Drawing is used to be punched out the protective cover after coating, is then generated respectively using cutting software and cuts file, and to there is pin
Cutting when file makes to cut by varying cutting cutter parameters for hole does not cut graphic outer contour line；
2）First use no pin hole to cut file when making satellite protective cover and cut material core
Brown paper and satellite protective cover material core raw material are sequentially placed on the automatic cutting bed processing surface of a wound, utilize automatic cutting bed progress
Satellite protective cover material core is cut, this cuts use and cuts file without pin hole, and satellite protective cover material core and phase are produced after cutting
The brown paper of similar shape；
3）Coating is carried out to material core
Coating is carried out to satellite protective cover material core, confirms cladding face；
4）Stone before punching
When carrying out pin hole machined to the satellite protective cover of coating, satellite protective cover and material core are first cut into caused pattern
Stack successively to cutting, expect that approximately equal is answered in core edge beyond pattern edge after vacuumizing；
5）Determine to cut origin
Using pattern as reference data, origin will be cut and cut due to pattern at origin；
6）Satellite protective cover paving location detects
The head that cuts of cutting is translated to tailstock, observation cuts whether position instruction luminous point deflects away from pattern edge；
7）Satellite protective cover paving location adjusts
If cutting position instruction luminous point deflects away from pattern edge, remove gas and position adjustment is carried out to material core, when translating luminous point all the time
Moved along pattern edge；
8）Automatic cutting bed completion punching is used after fixing satellite protective cover.
2. the method for claim 1, wherein two-dimensional graphics software is AutoCAD softwares.
3. the method for claim 1, wherein pin hole is the circular hole of diameter 4mm, for fixed satellite protective cover.
4. the method for claim 1, wherein step 3）It is middle that coating is carried out to satellite protective cover material core using manual.
5. method as claimed in claim 4, wherein, expect that core edge must be wrapped in protective film after coating.
6. method as claimed in claim 4, wherein, the coating is to increase layer of surface outside Multi-layer material core to be coated with metal
Polyester film.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510317433.4A CN106272676B (en) | 2015-06-11 | 2015-06-11 | Punching production method after satellite protective cover elder generation coating based on automation cutting |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510317433.4A CN106272676B (en) | 2015-06-11 | 2015-06-11 | Punching production method after satellite protective cover elder generation coating based on automation cutting |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106272676A CN106272676A (en) | 2017-01-04 |
| CN106272676B true CN106272676B (en) | 2018-04-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510317433.4A Expired - Fee Related CN106272676B (en) | 2015-06-11 | 2015-06-11 | Punching production method after satellite protective cover elder generation coating based on automation cutting |
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| CN87209072U (en) * | 1987-06-10 | 1988-04-27 | 钟有学 | Grinding type pulverizer |
| US5651296A (en) * | 1990-11-06 | 1997-07-29 | Agence Spatiale Europeenne | Device for providing protection against debris produced by a pyro bolt cutter |
| CN1322611A (en) * | 2000-05-08 | 2001-11-21 | 鲍勃斯脱股份有限公司 | Blind pressing plate for shaping press |
| CN101483976A (en) * | 2008-01-11 | 2009-07-15 | 精工爱普生株式会社 | Method for manufacturing flexible substrate and flexible substrate punching device |
| CN106134328B (en) * | 2008-12-29 | 2014-02-26 | 上海空间推进研究所 | The drilling method of the outer coated metallized film of spacecraft |
| CN104384558A (en) * | 2014-11-24 | 2015-03-04 | 首都航天机械公司 | Local positioning and clean drilling device and method for thin-wall barrel section |
| CN204297211U (en) * | 2014-11-17 | 2015-04-29 | 苏州赛腾精密电子有限公司 | Automatic feed mechanism |
| CN204673703U (en) * | 2015-04-08 | 2015-09-30 | 安徽港源家居工艺品有限公司 | A kind of cutting die for creasing and cutting machine |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR101275130B1 (en) * | 2011-06-23 | 2013-06-17 | 영신기계(주) | The sheet blanking method that used cutting machine |
-
2015
- 2015-06-11 CN CN201510317433.4A patent/CN106272676B/en not_active Expired - Fee Related
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN87209072U (en) * | 1987-06-10 | 1988-04-27 | 钟有学 | Grinding type pulverizer |
| US5651296A (en) * | 1990-11-06 | 1997-07-29 | Agence Spatiale Europeenne | Device for providing protection against debris produced by a pyro bolt cutter |
| CN1322611A (en) * | 2000-05-08 | 2001-11-21 | 鲍勃斯脱股份有限公司 | Blind pressing plate for shaping press |
| CN101483976A (en) * | 2008-01-11 | 2009-07-15 | 精工爱普生株式会社 | Method for manufacturing flexible substrate and flexible substrate punching device |
| CN106134328B (en) * | 2008-12-29 | 2014-02-26 | 上海空间推进研究所 | The drilling method of the outer coated metallized film of spacecraft |
| CN204297211U (en) * | 2014-11-17 | 2015-04-29 | 苏州赛腾精密电子有限公司 | Automatic feed mechanism |
| CN104384558A (en) * | 2014-11-24 | 2015-03-04 | 首都航天机械公司 | Local positioning and clean drilling device and method for thin-wall barrel section |
| CN204673703U (en) * | 2015-04-08 | 2015-09-30 | 安徽港源家居工艺品有限公司 | A kind of cutting die for creasing and cutting machine |
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|---|---|
| CN106272676A (en) | 2017-01-04 |
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