CN105436297B - A kind of electrothermal tube machine for shrinking fuselage - Google Patents
A kind of electrothermal tube machine for shrinking fuselage Download PDFInfo
- Publication number
- CN105436297B CN105436297B CN201510754305.6A CN201510754305A CN105436297B CN 105436297 B CN105436297 B CN 105436297B CN 201510754305 A CN201510754305 A CN 201510754305A CN 105436297 B CN105436297 B CN 105436297B
- Authority
- CN
- China
- Prior art keywords
- oil
- fuselage
- positioning
- hole
- calibration
- 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.)
- Expired - Fee Related
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D31/00—Other methods for working sheet metal, metal tubes, metal profiles
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Earth Drilling (AREA)
- Auxiliary Devices For Machine Tools (AREA)
Abstract
A kind of electrothermal tube machine for shrinking fuselage of the present invention, fuselage is provided with multigroup pressing tool, and fuselage roof is provided with working position, and main shaft fixed bit, working position bottom is provided with oil-containing groove；Fuselage interior is provided with oil return system, including return flange and oil return bucket, oil-recovery tank is formed between return flange and working position bottom plate, central plate is provided with spill port, and spill port bottom is connected with oil return pipe；Using the method fixed support of three-point fix so that support fixing-stable on fuselage, and fuselage interior oil return system uses integral type Closed oil tank, solves oil return sealing problem.
Description
Technical field
The present invention relates to electrothermal tube machine for shrinking.
Background technology
The machine for shrinking used in the market, because support positioning is unreasonable during the draw, determines one flat with 2 points
The electrothermal tube that face is allowed to more than the calibers of φ 14 is flexible, and support is unstable.In terms of oil circuit oil return, mainly steel plate was taken in the past
The method of welding carries out connecing oil, and seal degree is bad, easy oil leakage, cause to waste and influence working environment.
The content of the invention
The invention aims to overcome above deficiency, there is provided a kind of electrothermal tube machine for shrinking fuselage.Using three-point fix
Method fixed support so that support fixing-stable on fuselage, and fuselage interior oil return system use integral type Closed oil tank,
Solve oil return sealing problem；Former main shaft lower end is changed to double bond, driving force is improved.
The purpose of the present invention is achieved in that：
A kind of electrothermal tube machine for shrinking fuselage, wherein, the fuselage roof is provided with working position, and the working position section is in triangle
Shape is recessed, and working position both sides side plate is provided with two row's main shaft fixed bits, and the main shaft fixed bit is square, and the main shaft is consolidated
Provided with positioning through hole and calibration screw in positioning, the positioning through hole quantity is two, including the first positioning through hole and second
Positioning through hole, second positioning through hole is located at the first positioning through hole lower end, including one first calibration screw and two
Second calibration screw, the first calibration screw is located at the first positioning through hole crown center position, the second calibration spiral shell
Hole position is in the second positioning through hole two bottom sides；The working position bottom is provided with oil-containing groove, and the oil-containing groove is square groove,
Several oil leaking holes are provided with the oil-containing groove；The fuselage interior is provided with oil return system, and the oil return system includes return flange
And oil return bucket, the return flange is in integral structure, and the return flange includes two supporting plates and central plate, the supporting plate
Section is L-shaped, is axisymmetricly distributed, and the central plate is transverse slat, and the supporting plate is located at the central plate both sides, supporting plate top
Portion and bottom are welded on the fuselage interior, form oil-recovery tank between the return flange and the working position bottom plate, it is described in
Core is provided with spill port, and the spill port is located at the center of the central plate, and the spill port bottom is connected with oil return
Pipe, the oil return bucket is arranged on below the oil return pipe；Upper calibration bolt, second school are provided with the first calibration screw
Lower calibration bolt is provided with quasi- screw.
A kind of above-mentioned electrothermal tube machine for shrinking fuselage, wherein, the calibration screw quantity is three.
Compared with prior art, beneficial effects of the present invention are：
1. coordinate colonel's calibration spiral shell using three calibration screws using 3 fixed racks in chassis plane and lathe bed joint portion
Bolt, can be adjusted to the position of upper and lower bracket by bolt above and below adjustment, realize the fine setting of backing positions, three of its uniqueness
Screw is designed in three-legged structure, and its Stability Analysis of Structures is high, is allowed to more stablize at work, the product quality processed is more added with guarantor
Card.
2. especially setting oil return system in fuselage interior, its special return flange design, integrated formed structure forms one
Formula Closed oil tank, had both solved the problem of oil return of oil circuit, again solve because bottom is yielding and increases the bulk strength of lathe bed
The problem of.
Brief description of the drawings
Fig. 1 is the fuselage schematic cross-sectional view of the present invention.
Fig. 2 is the fuselage top view of the present invention.
Embodiment
The invention will be further described below in conjunction with the accompanying drawings.
As illustrated, a kind of electrothermal tube machine for shrinking fuselage, the top of fuselage 1 is provided with working position 12, the working position 12
Section depression triangular in shape, the both sides side plate of working position 12 is provided with two row's main shaft fixed bits 13, the main shaft fixed bit 13
It is square, provided with positioning through hole 14 and calibration screw 15 in the main shaft fixed bit 13, the quantity of positioning through hole 14 is two
It is individual, including the first positioning through hole 141 and the second positioning through hole 142, it is logical that second positioning through hole 142 is located at the described first positioning
The lower end of hole 141, the quantity of calibration screw 15 is three, including one first calibration screw 151 and two second calibration screws
152, the first calibration screw 151 is located at the crown center position of the first positioning through hole 141, the second calibration screw
152 are located at the two bottom sides of the second positioning through hole 142；The bottom of working position 12 is provided with oil-containing groove 16, the oil-containing groove 16
Be square groove, provided with three oil leaking holes 17 in the oil-containing groove 16；The inside of fuselage 1 is provided with oil return system 18, described time
Oil system 18 includes return flange 181 and oil return bucket 182, and the return flange 181 is in integral structure, and the return flange 181 is wrapped
Two supporting plates 1811 and central plate 1812 are included, the section of supporting plate 1811 is L-shaped, is axisymmetricly distributed, the central plate
1812 be transverse slat, and the supporting plate 1811 is located at the both sides of central plate 1812, and the top and bottom of supporting plate 1811 is welded on
Inside the fuselage 1, oil-recovery tank 19, the central plate 1812 are formed between return flange 181 and the working position 12 bottom plate
Spill port 1813 is provided with, the spill port 1813 is located at the center of the central plate 1812, the bottom of spill port 1813
Portion is connected with oil return pipe 1814, and the oil return bucket 182 is arranged on the lower section of oil return pipe 1814；The first calibration screw 151
Interior be provided with upper calibration bolt, the second calibration screw 152 is provided with lower calibration bolt.
Compared with prior art, beneficial effects of the present invention are：
In chassis plane and lathe bed joint portion using 3 fixed racks, coordinate colonel's calibration spiral shell using three calibration screws
Bolt, can be adjusted to the position of upper and lower bracket by bolt above and below adjustment, realize the fine setting of backing positions, three of its uniqueness
Screw is designed in three-legged structure, and its Stability Analysis of Structures is high, is allowed to more stablize at work, the product quality processed is more added with guarantor
Card.
Oil return system is especially set in fuselage interior, its special return flange design, integrated formed structure formation integral type
Closed oil tank, both solved the problem of oil return of oil circuit, solve again because bottom is yielding and increases the bulk strength of lathe bed
Problem.
Above example is served only for that the present invention is further described, it is impossible to be interpreted as the limit to the scope of the present invention
System, some nonessential modifications and adaptations that those skilled in the art makes according to the above of the present invention belong to this hair
Bright protection domain.
Claims (2)
1. a kind of electrothermal tube machine for shrinking fuselage, it is characterised in that the fuselage roof is provided with working position, and the working position section is in
Triangular shaped recess, working position both sides side plate is provided with two row's main shaft fixed bits, and the main shaft fixed bit is square, the master
Provided with positioning through hole and calibration screw in axle fixed bit, the positioning through hole quantity is two, including the first positioning through hole with
Second positioning through hole, second positioning through hole be located at the first positioning through hole lower end, including one first calibration screw with
Two second calibration screws, the first calibration screw is located at the first positioning through hole crown center position, second school
Quasi- screw is located at the second positioning through hole two bottom sides；The working position bottom is provided with oil-containing groove, and the oil-containing groove is square
Several oil leaking holes are provided with groove, the oil-containing groove；The fuselage interior is provided with oil return system, and the oil return system includes back
Oiled-plate method and oil return bucket, the return flange is in integral structure, and the return flange includes two supporting plates and central plate, the branch
Fagging section is L-shaped, is axisymmetricly distributed, and the central plate is transverse slat, and the supporting plate is located at the central plate both sides, support
Plate top and bottom is welded on the fuselage interior, forms oil-recovery tank between the return flange and the working position bottom plate, institute
Central plate is stated provided with spill port, the spill port is located at the center of the central plate, and the spill port bottom is connected with
Oil return pipe, the oil return bucket is arranged on below the oil return pipe；Upper calibration bolt, described the are provided with the first calibration screw
Lower calibration bolt is provided with two calibration screws.
2. a kind of electrothermal tube machine for shrinking fuselage as claimed in claim 1, wherein, the calibration screw quantity is three.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510754305.6A CN105436297B (en) | 2015-11-09 | 2015-11-09 | A kind of electrothermal tube machine for shrinking fuselage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510754305.6A CN105436297B (en) | 2015-11-09 | 2015-11-09 | A kind of electrothermal tube machine for shrinking fuselage |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105436297A CN105436297A (en) | 2016-03-30 |
| CN105436297B true CN105436297B (en) | 2017-08-22 |
Family
ID=55547184
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510754305.6A Expired - Fee Related CN105436297B (en) | 2015-11-09 | 2015-11-09 | A kind of electrothermal tube machine for shrinking fuselage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105436297B (en) |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| IT1129074B (en) * | 1980-04-16 | 1986-06-04 | Metalli Ind Spa | EQUIPMENT FOR POINTING THE END OF A METAL TUBE BY MEANS OF A DRAWING OPERATION |
| CN2199827Y (en) * | 1994-05-04 | 1995-06-07 | 江西机床厂 | Cantilever diminishing pipe machine |
| CN2411861Y (en) * | 1999-12-22 | 2000-12-27 | 王冰石 | Rolling type contracted pipe machine |
| CN201006552Y (en) * | 2006-11-20 | 2008-01-16 | 张海勇 | Machine for shrinking one of the parts of tube |
| CN201572858U (en) * | 2009-12-23 | 2010-09-08 | 李振文 | Pipe reducing machine |
-
2015
- 2015-11-09 CN CN201510754305.6A patent/CN105436297B/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CN105436297A (en) | 2016-03-30 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170822 Termination date: 20171109 |