CN106346050A - Method for relocation of hole site - Google Patents
Method for relocation of hole site Download PDFInfo
- Publication number
- CN106346050A CN106346050A CN201510423388.0A CN201510423388A CN106346050A CN 106346050 A CN106346050 A CN 106346050A CN 201510423388 A CN201510423388 A CN 201510423388A CN 106346050 A CN106346050 A CN 106346050A
- Authority
- CN
- China
- Prior art keywords
- circle
- lamella lucida
- hole
- transparent board
- center
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B47/00—Constructional features of components specially designed for boring or drilling machines; Accessories therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B2226/00—Materials of tools or workpieces not comprising a metal
- B23B2226/27—Composites
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Perforating, Stamping-Out Or Severing By Means Other Than Cutting (AREA)
- Drilling And Boring (AREA)
Abstract
The invention discloses a method for relocation of hole site. The steps include: drilling locating holes after solidification and demoulding of the composite material part, and finding out misplaced locating holes; drawing a series of circles on a transparent board according to the size of the locating hole, and marking the center of the circles; fitting the circles on the transparent board with the correct locating hole site; fixing the transparent board to the part, and drawing two position lines on both the transparent board and the part; correcting the misplaced locating holes; fixing the transparent board to the part again, and ensuring the transparent board lies in the same position for the best fit before according to the position line; drilling again through the best-fit circles; according to the working principle to position the center of circle based on the circular arc, the theoretical center of circle of the locating hole is set on the composite material part by the adoption of the transparent board, which reduces artificial errors, improves the drilling accuracy of parts, precisely corrects the locating hole of parts, reduces repeated corrections, ensures the accuracy of follow-up mechanical processing, and improves the speed of delivery of parts.
Description
Technical field
The invention belongs to multiple and material parts machining technology field, more particularly, it is related to one kind with saturating
Bright version is medium, the method reorientating hole position being fitted with different circles.
Background technology
It is requisite a kind of means in composite material parts forming parts manufacture field that machine adds boring, and zero
Part needs just to carry out machining in the case of having location hole, and the positional precision of location hole is of crucial importance,
And location hole is typically all that workman by frock, hole by hand by positioning, the therefore inclined situation of positioning hole drill is very general
Time.Because application needs, part need to carry out plug-hole repairing, and in the case of there is no frock and aid
Reorientate boring, now reorientating of this hole seems very important.
By analysis, traditional redrilling localization method is that part is reapposed in laying frock, right
Location hole hole position in quasi- frock, with the overproof value of the rough labelling of marker pen, is carried out again according to labelling after repairing
Boring.However, the labelling on part only marked the edge in hole it is impossible to confirm the center of circle, in redrilling
When be only capable of holing with feeling, the bore edges of matching labelling, this resulted in again boring dislocation；And,
It is necessary on Over Difference Hole side with marker pen labelling, the program such as cleaning during repairing is likely to result in labelling and is cleaned by
Fall or unintelligible, this further increases the inclined probability of brill during redrilling.
In order to solve this problem, present applicant proposes one kind reorientates hole position method, the method is directed to any
The part that hole position brill need to be repaired partially, using the circle of lamella lucida and some row different-diameters, by former location hole
The matching of circular arc, finds center of circle positioning, is holed according to this center of circle after repairing.On the one hand pass through the center of circle
Positioning substantially increases accuracy rate, on the other hand avoids and makes marks in repairing area.The method is accurately and reliably
The fault reorientated hole position, effectively reduce the appearance of the factors such as artificial feel and experience, and significantly
Reduce the probability repeatedly repaired.
Content of the invention
After High Temperature High Pressure solidification, before the demoulding, can there is stress because expanding with heat and contract with cold in part to composite, should
Power is easy to the deviation causing to hole.It is an object of the invention to overcoming the shortcoming of existing method, provide one kind
Find the localization method in the center of circle with lamella lucida and different circular fitting, by the method to repairing part again
Positioning, and redrilling is carried out according to this center of circle, decrease repairing number of times, improve the precision of drilling part.
To achieve these goals, technical solution of the present invention is as follows:
A kind of method reorientating hole position, its step includes:
A., after the composite material parts solidification demoulding, the positioner according to laying frock bores location hole, boring
Compare the positioner of laying frock afterwards, check the location hole of error bit；
B. prepare a lamella lucida, draw a series of circles with reference to location hole size, and mark the center of circle；
C. with the circle in lamella lucida and the hole position matching of correct positioning, find best-fit-circle, determine this circle
The heart；
In fixing lamella lucida and part, and draw two together with part vertically with marking pen in lamella lucida
Position line；
D. repair the location hole of dislocation；
E. retighten lamella lucida on part, ensure that lamella lucida is consistent with original position according to position line；
F. redrilling is carried out by the center of circle of best-fit-circle in lamella lucida.
Further, correct positioning hole position is the print during positioner solidification of laying frock on part
Trace.The positioner of laying frock includes, the projection in laying frock, groove or perforate, positioner
During solidification, due to the mobility of resin in composite, laying device can be caused on part
With the presence of impression, this impression seeks to the correct positioning hole position bored.
Further, the lamella lucida size described in step b is less than part edge.Preferably ensure transparent
Edges of boards edge is about in the middle of part hole position and edge.
Further, the picture circle described in step b is to point at circular diameter to answer reference location bore dia by little big
Gradual change is it is ensured that positioning bore dia theoretical value is in wherein, and draws bowlder and should mark this in lamella lucida
The position of the round heart.
Matching be by the circular arc in lamella lucida and positioner the impression on part be fitted it is ensured that
In lamella lucida, the circular arc of circle and positioning impression circular arc are completely superposed, and now in lamella lucida, the center of circle of this circle is
The subsequently center of circle of boring, now this position on part is hole.
When find lamella lucida on existing circular arc with positioning impression cannot matching completely when, repeat step b, continue
Continuous picture circle, until complete matching.
Constant in order to ensure the center of circle found, lamella lucida is fixed on part, increases position line simultaneously.
Reappose lamella lucida refer to complete matching position line it is ensured that place lamella lucida and plug-hole before transparent
Board position is completely the same, and now center of circle position is composite repair materials, and pointed cone does in part circle centre position
Labelling, it is ensured that pointed cone punctures part material, has center mark on part after removing lamella lucida.
By part requirements boring, during boring, drill bit is directed at the center of circle, and using bushing it is ensured that drill bit is not inclined
Move.
The helpful effect of the present invention is as follows:
1. theory orientation hole is justified by the operation principle based on circular arc positioning centre for the present invention by means of lamella lucida
The heart is placed on multiple material part, reduces the error of artifact, improves the precision of drilling part；
2. the accurate location hole repairing part, decreases the number of times repeatedly repaired it is ensured that what follow-up machine added
Accuracy, improves part Delivery speed.
Brief description
Fig. 1 mistake matching illustrates
Fig. 2 best fit illustrates
The telltale mark of Fig. 3 lamella lucida
Specific embodiment
The invention will be further described below in conjunction with the accompanying drawings.
Fig. 1 is wrong matching diagram.
See Fig. 2, Fig. 3, composite material parts front-axle beam, be with carbon fiber and High temp. epoxy resinses as base material,
In 175 DEG C of curing moldings, after demoulding boring, the inclined 0.58mm of centralized positioning hole drill, causes part no
Method carries out next step Water Cutting positioning；The laying frock using is the positioner with tapered protrusion,
After part removal, tapered protrusion can show circular pit on part, and this pit is that location hole is located
Position；A diameter of 6.35 (0 ,+0.1) mm of this location hole.Prepare a 30cm*10cm lamella lucida, use
Circle drawn by compasses, and diameter of a circle is respectively 6.30mm, 6.35mm, 6.40mm, 6.45mm, 6.50mm,
And to number be a, b, c, d, e, draw bowlder compasses diameter pierce through lamella lucida.This lamella lucida is placed
Bore off normal in hole position to put, remove matching tapered protrusion circular arc with this five circles respectively, find that c circular arc is less than normal,
D circular arc is bigger than normal.Lamella lucida is drawn again and justifies, a diameter of 6.42,6.44,6.46,6.48, and number
For f, g, h, i, draw bowlder compasses diameter pierce through lamella lucida, again with tapered protrusion circular fitting,
Find g circle and the raised complete matching of circular arc.Lamella lucida during matching is adjacent to part completely it is ensured that transparent
Seamless between plate and part, fix this lamella lucida with adhesive tape, and with black marking pen in lamella lucida and zero
Two vertical position lines are drawn together on part.The distance of the measurement and positioning center of circle to part edge is respectively
15.3cm and 15.3cm.Subsequently cut off adhesive tape with blade, take off lamella lucida.
Carry out plug-hole using multiple material structure repair double-component resin and glass cloth: seal the bag face in hole with adhesive tape
Side, fills hole with the multiple material structure repair double-component resin of the glass fibre sawing powder with 40%, goes
Bubble removing；It is blended in embedding in 30 minutes.Carry out repairing solidification using heating blanket after playing bag.Solidification completes to tear open
After bag with sand skew rays more than 200 mesh along polishing bonding layer to smoothly transitting, check do not damage adjacent
Surface.
Place lamella lucida, the matching position before boring is found according to position line, adhesive tape etc., now measure thoroughly
The distance at the center of circle on isotropic disk to part two ends is respectively 15.3cm and 15.3cm, confirms transparent Board position
Do not become, fixed with adhesive tape afterwards.Subsequently prick saturating lamella lucida with pointed cone, and hole positioning is pricked on part.With
Little drill bit subdrilling goes out draws hole, bores location hole afterwards again.
To be again hole-drilled added, milling goes out External Shape.
Claims (4)
1. a kind of method reorientating hole position, the steps include:
A., after the composite material parts solidification demoulding, the positioner according to laying frock bores location hole, compares the positioner of laying frock after boring, checks the location hole of error bit；
B. prepare a lamella lucida, draw a series of circles with reference to location hole size, and mark the center of circle；
C. with the circle in lamella lucida and the hole position matching of correct positioning, find best-fit-circle；
D. fix on lamella lucida and part, and draw two position lines together with part in lamella lucida；
E. repair the location hole of dislocation；
F. retighten on lamella lucida and part, lamella lucida and former best fit position consistency are ensured according to position line；
G. redrilling is carried out by the center of circle of best-fit-circle in lamella lucida.
2. a kind of method reorientating hole position according to claim 1 is it is characterised in that described correct positioning hole position is the impression during positioner solidification of laying frock on part.
3. a kind of method reorientating hole position according to claim 1 it is characterised in that during described lamella lucida matching size be less than part edge.
4. a kind of method reorientating hole position according to claim 1 is it is characterised in that two position lines described in step d are mutually perpendicular to.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510423388.0A CN106346050B (en) | 2015-07-17 | 2015-07-17 | A method of repositioning hole position |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510423388.0A CN106346050B (en) | 2015-07-17 | 2015-07-17 | A method of repositioning hole position |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106346050A true CN106346050A (en) | 2017-01-25 |
| CN106346050B CN106346050B (en) | 2018-11-02 |
Family
ID=57842470
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510423388.0A Active CN106346050B (en) | 2015-07-17 | 2015-07-17 | A method of repositioning hole position |
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| Country | Link |
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| CN (1) | CN106346050B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109177179A (en) * | 2018-09-30 | 2019-01-11 | 中煤航测遥感集团有限公司 | Mash welder and spot welding system |
| CN113618835A (en) * | 2021-07-30 | 2021-11-09 | 中国航空工业集团公司济南特种结构研究所 | Method for positioning metal connecting piece hole in composite material component |
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| CN103286767A (en) * | 2013-06-13 | 2013-09-11 | 沈阳飞机工业（集团）有限公司 | Drilling lineation method for skin part |
| CN103601528A (en) * | 2013-08-30 | 2014-02-26 | 航天材料及工艺研究所 | Local coating defect repairing method for carbon/carbon composite material |
| CN104668631A (en) * | 2015-01-26 | 2015-06-03 | 哈尔滨飞机工业集团有限责任公司 | Positioning structure and method of blind holes |
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2015
- 2015-07-17 CN CN201510423388.0A patent/CN106346050B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004358577A (en) * | 2003-06-02 | 2004-12-24 | Hitachi Via Mechanics Ltd | Printed circuit board processing machine |
| US20050084344A1 (en) * | 2003-10-20 | 2005-04-21 | The Boeing Company | Drill template with integral vacuum attach |
| CN201124252Y (en) * | 2007-12-19 | 2008-10-01 | 成都飞机工业（集团）有限责任公司 | Reticle centering drilling mould |
| CN102658378A (en) * | 2012-05-22 | 2012-09-12 | 西安飞机工业（集团）有限责任公司 | Drilling method for wall plate skin of airplane |
| CN202976673U (en) * | 2012-11-20 | 2013-06-05 | 鞍钢集团矿业公司 | Coordinate positioning rule |
| CN103286767A (en) * | 2013-06-13 | 2013-09-11 | 沈阳飞机工业（集团）有限公司 | Drilling lineation method for skin part |
| CN103601528A (en) * | 2013-08-30 | 2014-02-26 | 航天材料及工艺研究所 | Local coating defect repairing method for carbon/carbon composite material |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109177179A (en) * | 2018-09-30 | 2019-01-11 | 中煤航测遥感集团有限公司 | Mash welder and spot welding system |
| CN109177179B (en) * | 2018-09-30 | 2024-03-01 | 中煤航测遥感集团有限公司 | Spot welding machine and spot welding system |
| CN113618835A (en) * | 2021-07-30 | 2021-11-09 | 中国航空工业集团公司济南特种结构研究所 | Method for positioning metal connecting piece hole in composite material component |
| CN113618835B (en) * | 2021-07-30 | 2022-09-20 | 中国航空工业集团公司济南特种结构研究所 | Method for positioning metal connecting piece hole in composite material component |
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| Publication number | Publication date |
|---|---|
| CN106346050B (en) | 2018-11-02 |
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