CN104668631A - Positioning structure and method of blind holes - Google Patents
Positioning structure and method of blind holes Download PDFInfo
- Publication number
- CN104668631A CN104668631A CN201510038428.XA CN201510038428A CN104668631A CN 104668631 A CN104668631 A CN 104668631A CN 201510038428 A CN201510038428 A CN 201510038428A CN 104668631 A CN104668631 A CN 104668631A
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- China
- Prior art keywords
- hole
- magnetic
- inner body
- exterior part
- magnetic pole
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B49/00—Measuring or gauging equipment on boring machines for positioning or guiding the drill; Devices for indicating failure of drills during boring; Centering devices for holes to be bored
Abstract
The invention belongs to the aircraft riveting assembly techniques and relates to a positioning structure and method of blind holes. The positioning structure comprises an internal part (1), an external part (2), a magnetic pole developer (3) and a magnetic positioner (4); the internal part (1) is provided with a primary hole (5) made in a pre-assembly phase; after assembled, the internal part (1) and the external part (2) form a closed structure; the magnetic positioner (4) is provided with a cross magnetic pole line (7) and a pin (6); the pin (6) can be in tight fit with the primary hole (5); the magnetic pole developer (3) is provided with a cross graduation line (8) and a central hole (9). The positioning structure and method has the advantages that a blind hole of the internal part can be quickly located, the method is simple and practical, aircraft structure is never damaged, the cost is low, maintenance is not required, production efficiency is greatly improved, and aircraft riveting quality is improved.
Description
Technical field
The invention belongs to aircraft riveted joint mounting technology, relate to a kind of blind hole location structure and localization method.
Background technology
In the riveted joint assembling of aircraft product, frequent needs select side part to get out pre-manufactured hole according to drawing in the part participating in assembling, after mounting, on the part of opposite side, place's rivet hole is returned according to the pre-manufactured hole on part, like this can the clearly back gauge size of drilling part when drilling after reflection place, prevent the fault of hole back gauge undersize.But sometimes, because structure is closed, in order to ensure inner body rivet hole back gauge size, pre-manufactured hole needs to drill in advance on the inner body of enclosed construction, then the pre-manufactured hole position of inner body is found from outside, then according to pre-manufactured hole position externally to internal bore.Generally use the method fairlead position of setting-out, but because of the particularity of aircaft configuration, some enclosed construction cannot find position, hole by the method for setting-out, as blindly boring then very easily forms the figure of eight hole of dislocation, so just cause the overproof of aperture, reduce the riveting quality of aircraft.
Summary of the invention
The object of the invention is: propose a kind of simple and practical instrument and the method that can find inner body pre-manufactured hole position fast.
Technical scheme of the present invention is: a kind of blind hole location structure, it comprises inner body 1, exterior part 2, magnetic pole developer sheet 3, magnetic location block 4, inner body 1 is shaped with just hole 5 in the pre-assembled stage, magnetic location block 4 is for match with first hole shape, size, be pre-installed in the locating piece in first hole, after inner body 1 and exterior part 2 assemble, sealing just hole forms enclosed construction, described magnetic pole developer sheet 3 is the transparent sealing sheet of tundish containing the iron powder moved freely, its surface with cross pole line 7 and centre bore 9, for detecting magnetic location block position.
Also comprising size can alignment pin 6 friction tight with first hole 5.
Utilize the method that described blind hole location structure positions, it comprises the steps:
Step 1: described inner body 1 first drills just hole 5 in the pre-assembled stage, after inner body 1 and exterior part 2 are socketed and coordinate, the first hole 5 of inner body 1 is enclosed in exterior part 2 inside;
Step 2: install a magnetic location block 4 in first hole 5, with cross pole line 7 on magnetic location block 4, magnetic location block 4 uses pin 6 to be close tolerance fit with first hole 5, ensures that magnetic location block 4 can be fixed on inner body 1 and does not come off, and carries out structure and close;
Step 3: after structure is closed, exterior part 2 places one piece of magnetic pole developer sheet 3, magnetic pole developer sheet 3 there are cross graduation mark 8 and a centre bore 9, after magnetic pole developer sheet 3 places exterior part 2, magnetic in magnetic pole developer sheet 3 can sense the cross pole line 7 on magnetic location block 4, thus forms cross hairs vestige;
Step 4: when this vestige with magnetic pole developer sheet 3 has cross graduation mark 8 overlap after show that just hole 5 overlaps with centre bore 9, usage flag pen makes a mark on exterior part 2 according to centre bore 9, takes off magnetic pole developer sheet 3;
Step 5: according to centre bore 9 mark internally part 1 hole, then Kong Huiyu just overlaps in hole 5, thus gets out the through hole of through inner body 1 inner body 1 and exterior part 2, ensure that hole tolerance.
In step 1, in order to complete connection, first hole 5 position from exterior part 2 internally part 1 hole, to ensure to overlap with first hole 5 when from exterior part 2, internally part 1 is holed, thus the whole bore dia ensureing to run through inner body 1 and exterior part 2 meets the hole tolerance requirement of engineering design.
Advantage of the present invention is: a kind of blind hole location structure of the present invention and localization method can find the blind hole position of inner body fast, method simple practical, not wrap up structure, with low cost, Maintenance free, improves production efficiency greatly, improves the riveting quality of aircraft.
Accompanying drawing explanation
Fig. 1 is the structural representation of a kind of blind hole location structure of the present invention and localization method;
Fig. 2 is the A-A sectional view of Fig. 1;
Fig. 3 is the structural representation of magnetic location block 4;
Fig. 4 is the top view of Fig. 3;
Wherein, 1-inner body, 2-exterior part, 3-magnetic pole developer sheet, 4-magnetic location block, 5-just hole, 6-pin, 7-cross pole line, 8-cross graduation mark, 9-centre bore.
Detailed description of the invention
Below the present invention is described in further details.
Refer to Fig. 1,2, wherein, Fig. 1 is the structural representation of frock datum level corrosion protection structure of the present invention, and Fig. 2 is the top view of Fig. 1 Fig. 1.Relate to a kind of blind hole location structure and localization method.Described blind hole location structure is made up of inner body 1, exterior part 2, magnetic pole developer sheet 3, magnetic location block 4.Inner body 1 is shaped with just hole 5 in the pre-assembled stage, enclosed construction can be formed after inner body 1 and exterior part 2 assemble, with cross pole line 7 and pin 6 on magnetic location block 4, pin 6 can with first hole 5 tight fit, with cross pole line 8 and a centre bore 9 on magnetic pole developer sheet 3.
Its localization method is: described inner body 1 has drilled just hole 5 in the pre-assembled stage according to engineering drawing, after inner body 1 and exterior part 2 are socketed and coordinate, the first hole 5 of inner body 1 is enclosed in exterior part 2 inside, in order to complete connection, need first hole 5 position from exterior part 2 internally part 1 hole, in order to overlap with first hole 5 when ensureing that internally part 1 is holed from exterior part 2, thus the whole bore dia ensureing to run through inner body 1 and exterior part 2 meets the hole tolerance requirement of engineering design.Then in first hole 5, a magnetic location block 4 is installed, with cross pole line 7 on magnetic location block 4, magnetic location block 4 uses pin 6 and first hole 5 to be close tolerance fit, ensure that magnetic location block 4 can be fixed on inner body 1 not come off, after structure is closed, exterior part 2 places one piece of magnetic pole developer sheet 3, magnetic pole developer sheet 3 there are cross graduation mark 8 and a centre bore 9, after magnetic pole developer sheet 3 places exterior part 2, magnetic in magnetic pole developer sheet 3 can sense the cross pole line 7 on magnetic location block 4, thus form cross hairs vestige, when this vestige with magnetic pole developer sheet 3 has cross graduation mark 8 overlap after show that just hole 5 overlaps with centre bore 9, usage flag pen makes a mark on exterior part 2 according to centre bore 9, take off magnetic pole developer sheet 3, according to centre bore 9 mark internally part 1 hole, then Kong Huiyu just overlaps in hole 5, thus get out the through hole of through inner body 1 inner body 1 and exterior part 2, there is hole off(-)center when preventing boring and occur figure of eight hole, ensure that hole tolerance.
Blind hole location structure of the present invention and localization method can find the blind hole position of inner body fast, method simple practical, and wrap up structure, not with low cost, and Maintenance free improves production efficiency greatly, improves the riveting quality of aircraft.
Claims (4)
1. a blind hole location structure, it is characterized in that, comprise inner body (1), exterior part (2), magnetic pole developer sheet (3), magnetic location block (4), inner body (1) is shaped with just hole (5) in the pre-assembled stage, magnetic location block (4) is and first hole shape, size matches, be pre-installed in the locating piece in first hole, after inner body (1) and exterior part (2) assemble, sealing just hole forms enclosed construction, described magnetic pole developer sheet (3) is for tundish is containing the transparent sealing sheet of the iron powder moved freely, its surface is with cross pole line (7) and centre bore (9), for detecting magnetic location block position.
2. blind hole location structure according to claim 1, is characterized in that, also comprise size can with first hole (5) friction tight alignment pin (6).
3. the method utilizing the blind hole location structure described in claim 1 or 2 to position, is characterized in that, comprise the steps:
Step 1: described inner body (1) first drills just hole (5) in the pre-assembled stage, after inner body (1) and exterior part (2) are socketed and coordinate, it is inner that the first hole (5) of inner body (1) is enclosed in exterior part (2);
Step 2: install a magnetic location block (4) in first hole (5), with cross pole line (7) on magnetic location block (4), magnetic location block (4) uses pin (6) and first hole (5) to be close tolerance fit, ensure that magnetic location block (4) can be fixed on inner body (1) and do not come off, and carry out structure and close;
Step 3: after structure is closed, the upper placement one piece of magnetic pole developer sheet (3) of exterior part (2), magnetic pole developer sheet (3) there are cross graduation mark (8) and a centre bore (9), after magnetic pole developer sheet (3) places exterior part (2), magnetic in magnetic pole developer sheet (3) can sense the cross pole line (7) on magnetic location block (4), thus forms cross hairs vestige;
Step 4: when this vestige with magnetic pole developer sheet (3) has cross graduation mark (8) overlap after show that just hole (5) overlaps with centre bore (9), usage flag pen makes a mark on exterior part (2) according to centre bore (9), takes off magnetic pole developer sheet (3);
Step 5: according to mark internally part (1) boring of centre bore (9), then Kong Huiyu just overlaps in hole (5), thus get out the through hole of through inner body (1) inner body (1) and exterior part (2), ensure that hole tolerance.
4. blind hole localization method according to claim 3, it is characterized in that, in order to complete connection, first hole (5) position from exterior part (2) internally part (1) boring, to ensure to overlap with first hole (5) when internally part (1) is holed from exterior part (2), thus the whole bore dia ensureing to run through inner body (1) and exterior part (2) meets the hole tolerance requirement of engineering design.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510038428.XA CN104668631A (en) | 2015-01-26 | 2015-01-26 | Positioning structure and method of blind holes |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510038428.XA CN104668631A (en) | 2015-01-26 | 2015-01-26 | Positioning structure and method of blind holes |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104668631A true CN104668631A (en) | 2015-06-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510038428.XA Pending CN104668631A (en) | 2015-01-26 | 2015-01-26 | Positioning structure and method of blind holes |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104668631A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106346050A (en) * | 2015-07-17 | 2017-01-25 | 成都飞机工业（集团）有限责任公司 | Method for relocation of hole site |
| CN106552961A (en) * | 2015-09-25 | 2017-04-05 | 波音公司 | Blind hole positions instrument |
| CN107745825A (en) * | 2017-09-28 | 2018-03-02 | 国营芜湖机械厂 | It is a kind of to draw aperture apparatus and its application method using Magnetic oriented |
| CN109396748A (en) * | 2017-08-15 | 2019-03-01 | 中航贵州飞机有限责任公司 | A kind of aircraft skin magnetic imaging pilot hole method |
| CN110672005A (en) * | 2019-11-05 | 2020-01-10 | 杭州冰玉科技有限公司 | A simple and easy detection device of substrate roughness for water-soluble membrane |
| 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 |
| CN114719727A (en) * | 2022-03-25 | 2022-07-08 | 四川腾盾科技有限公司 | Method for assembling, positioning and detecting aircraft finished product based on magnet heteropolar attraction |
| CN116408686A (en) * | 2023-06-08 | 2023-07-11 | 成都飞机工业（集团）有限责任公司 | Hole guiding device and hole guiding method based on magnetic force |
-
2015
- 2015-01-26 CN CN201510038428.XA patent/CN104668631A/en active Pending
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106346050A (en) * | 2015-07-17 | 2017-01-25 | 成都飞机工业（集团）有限责任公司 | Method for relocation of hole site |
| CN106552961B (en) * | 2015-09-25 | 2022-12-20 | 波音公司 | Blind hole positioning tool |
| CN106552961A (en) * | 2015-09-25 | 2017-04-05 | 波音公司 | Blind hole positions instrument |
| CN109396748A (en) * | 2017-08-15 | 2019-03-01 | 中航贵州飞机有限责任公司 | A kind of aircraft skin magnetic imaging pilot hole method |
| CN109396748B (en) * | 2017-08-15 | 2021-11-12 | 中航贵州飞机有限责任公司 | Magnetic imaging hole leading method for aircraft skin |
| CN107745825A (en) * | 2017-09-28 | 2018-03-02 | 国营芜湖机械厂 | It is a kind of to draw aperture apparatus and its application method using Magnetic oriented |
| CN107745825B (en) * | 2017-09-28 | 2021-02-12 | 国营芜湖机械厂 | Hole guiding device positioned by magnetic field and using method thereof |
| CN110672005A (en) * | 2019-11-05 | 2020-01-10 | 杭州冰玉科技有限公司 | A simple and easy detection device of substrate roughness for water-soluble membrane |
| 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 |
| CN114719727A (en) * | 2022-03-25 | 2022-07-08 | 四川腾盾科技有限公司 | Method for assembling, positioning and detecting aircraft finished product based on magnet heteropolar attraction |
| CN116408686A (en) * | 2023-06-08 | 2023-07-11 | 成都飞机工业（集团）有限责任公司 | Hole guiding device and hole guiding method based on magnetic force |
| CN116408686B (en) * | 2023-06-08 | 2023-10-03 | 成都飞机工业（集团）有限责任公司 | Hole guiding device and hole guiding method based on magnetic force |
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Application publication date: 20150603 |