CN204003819U - Limit, a kind of hole extruder - Google Patents
Limit, a kind of hole extruder Download PDFInfo
- Publication number
- CN204003819U CN204003819U CN201420185187.2U CN201420185187U CN204003819U CN 204003819 U CN204003819 U CN 204003819U CN 201420185187 U CN201420185187 U CN 201420185187U CN 204003819 U CN204003819 U CN 204003819U
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- CN
- China
- Prior art keywords
- hole
- limit
- utility
- model
- bolt
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- Expired - Lifetime
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- 230000002929 anti-fatigue Effects 0.000 abstract description 4
- 208000037656 Respiratory Sounds Diseases 0.000 abstract description 2
- 238000010276 construction Methods 0.000 abstract description 2
- 230000001934 delay Effects 0.000 abstract description 2
- 230000009395 genetic defect Effects 0.000 abstract description 2
- 238000005728 strengthening Methods 0.000 abstract description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 229910001200 Ferrotitanium Inorganic materials 0.000 description 2
- 229910001069 Ti alloy Inorganic materials 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000011229 interlayer Substances 0.000 description 1
- 239000010410 layer Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012797 qualification Methods 0.000 description 1
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- Connection Of Plates (AREA)
Abstract
The utility model discloses limit, a kind of hole extruder, for the limit, hole of aircraft assembling fastener hole is pushed, comprising: two impress lining, bolt, nut; Described two impression linings are located at respectively the both sides on limit, hole, and described bolt impresses linings and fixes with nut through two.The utility model not only can form strengthening compressive stress layer at Kong Bianchu, but also can eliminate limit, hole genetic defects (as: microfissure, machinery scuffing etc.), effectively delays germinating and the expansion of crackle.Because aircaft configuration fatigue ftractures in fastening piece (bolt) Kong Bianchu more, just seem particularly important so improve the anti-fatigue ability on limit, hole for the fatigue characteristic that increase housing construction.The utility model can not increase under structure weight condition, effectively to increase the fatigue resistance of structure.
Description
Technical field
The utility model relates to aircaft configuration antifatigue field, and limit, a kind of hole extruder is specifically provided.
Background technique
The extruding of limit, hole is a kind of conventional strong technology in low cost hole, be applied to aircaft configuration antifatigue field, due to the innovation of aircraft, all there is a large amount of qualifications in its structure thickness of interlayer, material type, hole gauge lattice and structural type etc., and original method can not cover practical structures condition far away.The common opening character of aircraft assembling fastener hole be restricted or part larger, be difficult to carry out valid function with equipment such as press machinees.Therefore, be necessary to provide a kind of limit, hole extruder meeting the demands.
Model utility content
The purpose of this utility model is to provide limit, a kind of hole extruder, can effectively address the above problem.
The technical solution of the utility model is: limit, a kind of hole extruder, for the limit, hole of aircraft assembling fastener hole is pushed, comprising: two impress lining 1, bolt 2, nut 3; Described two impression linings 1 are located at respectively the both sides on limit, hole, and described bolt is through two impression linings 1 fixing with nut 3.
Preferably, described impression lining 1 comprises limiting board 1a, extruding work fillet 1b and pilot sleeve 1c; Described pilot sleeve is located on limiting board 1a by extruding work fillet 1b.
Working principle of the present utility model is: by the both sides of two impression lining 1 patchholes, then a side penetrates bolt 2, one sides and is screwed into nut 3, when pretension, by torque wrench, reaches after formulating moment and completes the stress coining to limit, hole.Torque wrench is assembly plant common tool, and bolt, nut are also the common workpiece in assembly plant, and the utility model utilizes torsion to be changed to specified pressure and operates, and has both solved the restriction to instrument, is not subject to again the conditionality of part scale and assembling opening character.
The utility model is mainly for the limit, hole of hard aluminium alloy structure hole, and titanium alloy and steel components also can be used for reference within the specific limits.Due to the restriction of fastener threads intensity, the utility model structure hole for Φ 6～Φ 16 specifications.
The utlity model has following useful effect:
The utility model not only can form strengthening compressive stress layer at Kong Bianchu, but also can eliminate limit, hole genetic defects (as: microfissure, machinery scuffing etc.), effectively delays germinating and the expansion of crackle.Because aircaft configuration fatigue ftractures in fastening piece (bolt) Kong Bianchu more, just seem particularly important so improve the anti-fatigue ability on limit, hole for the fatigue characteristic that increase housing construction.The utility model can not increase under structure weight condition, effectively to increase the fatigue resistance of structure.
Brief description of the drawings
Fig. 1 is structural representation of the present utility model.
Embodiment
Below in conjunction with drawings and Examples, the utility model is described in detail.
As shown in Figure 1, limit, a kind of hole extruder, for the limit, hole of aircraft assembling fastener hole is pushed, comprising: two impress lining 1, bolt 2, nut 3; Described two impression linings 1 are located at respectively the both sides on limit, hole, and described bolt is through two impression linings 1 fixing with nut 3.
Described impression lining 1 comprises limiting board 1a, extruding work fillet 1b and pilot sleeve 1c; Described pilot sleeve is located on limiting board 1a by extruding work fillet 1b.
Working principle of the present utility model is: by the both sides of two impression lining 1 patchholes, then a side penetrates bolt 2, one sides and is screwed into nut 3, when pretension, by torque wrench, reaches after formulating moment and completes the stress coining to limit, hole.Torque wrench is assembly plant common tool, and bolt, nut are also the common workpiece in assembly plant, and the utility model utilizes torsion to be changed to specified pressure and operates, and has both solved the restriction to instrument, is not subject to again the conditionality of part scale and assembling opening character.
The utility model is mainly for the limit, hole of hard aluminium alloy structure hole, and titanium alloy and steel components also can be used for reference within the specific limits.Due to the restriction of fastener threads intensity, the utility model structure hole for Φ 6～Φ 16 specifications.
Above-described embodiment is only explanation technical conceive of the present utility model and feature, and its object is to allow person skilled in the art can understand content of the present utility model and implement according to this, can not limit protection domain of the present utility model with this.All equivalences of doing according to the utility model Spirit Essence change or modify, within all should being encompassed in protection domain of the present utility model.
Claims (1)
1. limit, a hole extruder, for the limit, hole of aircraft assembling fastener hole is pushed, is characterized in that, comprising: two impress lining (1), bolt (2), nut (3); Described two impression linings (1) are located at respectively the both sides on limit, hole, and described bolt is through two impression linings (1) fixing with nut (3); Described impression lining (1) comprises limiting board (1a), extruding work fillet (1b) and pilot sleeve (1c); Described pilot sleeve is located on limiting board (1a) by extruding work fillet (1b).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420185187.2U CN204003819U (en) | 2014-04-16 | 2014-04-16 | Limit, a kind of hole extruder |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420185187.2U CN204003819U (en) | 2014-04-16 | 2014-04-16 | Limit, a kind of hole extruder |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204003819U true CN204003819U (en) | 2014-12-10 |
Family
ID=52043826
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420185187.2U Expired - Lifetime CN204003819U (en) | 2014-04-16 | 2014-04-16 | Limit, a kind of hole extruder |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204003819U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107674952A (en) * | 2017-09-15 | 2018-02-09 | 西安冠泰检测技术有限公司 | A kind of cold extrusion impressing coupling and intensifying process equipment and method |
| CN108870057A (en) * | 2018-06-05 | 2018-11-23 | 西北工业大学 | Reinforced member and reinforced structure |
| CN111609027A (en) * | 2020-06-03 | 2020-09-01 | 西北工业大学 | Bushing and method for compensating deviation of connecting hole of aircraft wall plate |
-
2014
- 2014-04-16 CN CN201420185187.2U patent/CN204003819U/en not_active Expired - Lifetime
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107674952A (en) * | 2017-09-15 | 2018-02-09 | 西安冠泰检测技术有限公司 | A kind of cold extrusion impressing coupling and intensifying process equipment and method |
| CN108870057A (en) * | 2018-06-05 | 2018-11-23 | 西北工业大学 | Reinforced member and reinforced structure |
| CN111609027A (en) * | 2020-06-03 | 2020-09-01 | 西北工业大学 | Bushing and method for compensating deviation of connecting hole of aircraft wall plate |
| CN111609027B (en) * | 2020-06-03 | 2021-10-01 | 西北工业大学 | Method for compensating deviation of connecting hole of aircraft wall plate |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20141210 |