CN206306530U - Strong load numerical control press fuselage - Google Patents
Strong load numerical control press fuselage Download PDFInfo
- Publication number
- CN206306530U CN206306530U CN201620635165.0U CN201620635165U CN206306530U CN 206306530 U CN206306530 U CN 206306530U CN 201620635165 U CN201620635165 U CN 201620635165U CN 206306530 U CN206306530 U CN 206306530U
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- CN
- China
- Prior art keywords
- support frame
- fuselage
- numerical control
- control press
- strong load
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Abstract
Strong load numerical control press fuselage of the present utility model, support column is provided between fuselage and workbench, enhance the bearing capacity of fuselage, simultaneously, the both sides of fuselage are connected with reinforcement support frame, and the lower end for strengthening support frame is installed on workbench, effectively the load-bearing capacity of enhancing numerical control press fuselage, it is prevented effectively from airframe flexure deformation and causes the upper mould of punch press and lower mould axis out-of-alignment situation to occur, it is ensured that the quality of punching processing.
Description
Technical field
The utility model is related to numerical control press technical field, more particularly to a kind of strong load numerical control press fuselage.
Background technology
The numerical control press fuselage for commonly using currently on the market be fuselage simultaneously equipped with upper capstan head, lower capstan head, on mould, under
Mould, attacking head, slider guide seat, sliding block, main transmission part etc., this structure exist a maximum the drawbacks of be exactly:In punching press
During, fuselage can cause deflection deformation in the presence of main load, the deformation by upper capstan head, lower capstan head pass to upper mould,
Lower mould, causes upper and lower mould not coaxial, the phenomenons such as punching precision is overproof occurs.
Therefore, there is problem for of the prior art, a kind of strong load numerical control press technology of offer is provided badly and is seemed particularly
It is important.
Utility model content
The purpose of this utility model is to avoid weak point of the prior art and provide a kind of strong load numerical control press
Fuselage.
The purpose of this utility model is achieved through the following technical solutions：
Strong load numerical control press fuselage, is provided with support column between fuselage and workbench, and the both sides of fuselage are connected with and add
Strong support frame, the lower end for strengthening support frame is installed on workbench.
Preferably, strengthen support frame and be divided into three sections, specially epimere support frame, stage casing support frame and hypomere support frame, on
End support frame is affixed with the top of fuselage, and stage casing support frame is perpendicular with upper end support frame, hypomere support frame and stage casing support frame
It is perpendicular, and the bottom of hypomere support frame and the bottom of fuselage are affixed.
It is furthermore preferred that lower end support frame is trapezoidal with workbench junction position.
Preferably, two drift guide holders are provided with, two drift guide holders are both secured to the fixation of back front end
Plate, and two axis of drift guide holder are located at same straight line.
It is another preferred, be provided with a drift and be oriented to swinging seat, the drift be oriented to swinging seat length be set to 10 ~
16cm。
The beneficial effects of the utility model：
Strong load numerical control press fuselage of the present utility model, is provided with support column between fuselage and workbench, enhances
The bearing capacity of fuselage, meanwhile, the both sides of fuselage are connected with reinforcement support frame, and the lower end for strengthening support frame is installed on workbench,
Effectively the load-bearing capacity of enhancing numerical control press fuselage, is prevented effectively from airframe flexure deformation and causes the upper mould of punch press and lower mould axis
Line out-of-alignment situation occurs, it is ensured that the quality of punching processing.
Brief description of the drawings
The utility model is described further using accompanying drawing, but content in accompanying drawing is not constituted to of the present utility model
What is limited.
Fig. 1 is the structural representation of one embodiment of strong load numerical control press fuselage of the present utility model.
Fig. 2 is another angled arrangement schematic diagram of one embodiment of strong load numerical control press fuselage of the present utility model.
Fig. 3 is the schematic diagram that strong load numerical control press fuselage of the present utility model is applied to punch press.
Fig. 4 is another angle schematic diagram that strong load numerical control press fuselage of the present utility model is applied to punch press.
Included in Fig. 1 to Fig. 4：
1 --- fuselage, 2 --- workbench, 3-1 --- support column, 3-2 --- reinforcement support frame,
4 --- fixed plate, 5 --- drift guide holders.
Specific embodiment
The utility model is described in further detail with the following Examples.
Embodiment 1
Referring to shown in Fig. 1 to 4, the strong load numerical control press fuselage of the present embodiment is set between fuselage 1 and workbench 2
The both sides for having support column 3-1, fuselage 1 are connected with reinforcement support frame 3-2, and the lower end for strengthening support frame 3-2 is installed on workbench 2.
In the present embodiment, it is three sections, specially epimere support frame, stage casing support frame and hypomere support frame, upper end to strengthen support frame 3-2 points
Support frame is affixed with the top of fuselage 1, and stage casing support frame is perpendicular with upper end support frame, hypomere support frame and stage casing support frame phase
Vertically, and hypomere support frame bottom it is affixed with the bottom of fuselage 1, and lower end support frame and the junction position of workbench 2 are ladder
Shape.
In order to the upper mould for being further ensured that punch press is coaxial all the time in process with lower mould, two drift guide holders are provided with
5, two drift guide holders 5 are both secured to the fixed plate 4 of the top front end of fuselage 1, and the axis of two drift guide holders 5 is located at
Same straight line.
Embodiment 2
The main technical schemes of the present embodiment are substantially the same manner as Example 1, the feature not laid down a definition in the present embodiment, adopt
With the explanation in embodiment 1, no longer repeated herein.The strong load numerical control press fuselage of the present embodiment is provided with a drift
Swinging seat is oriented to, the length that the drift is oriented to swinging seat is set to 10 ~ 16cm.
Finally it should be noted that above example is merely to illustrate the technical solution of the utility model rather than to this practicality
The limitation of novel protected scope, although being explained in detail to the utility model with reference to preferred embodiment, the common skill of this area
Art personnel should be appreciated that can modify or equivalent to the technical solution of the utility model, without deviating from this practicality
The spirit and scope of new technique scheme.
Claims (5)
1. strong load numerical control press fuselage, it is characterised in that：Support column is provided between fuselage and workbench, the fuselage
Both sides are connected with reinforcement support frame, and the lower end of the reinforcement support frame is installed on workbench.
2. strong load numerical control press fuselage according to claim 1, it is characterised in that：The reinforcement support frame is divided into three
Section, specially epimere support frame, stage casing support frame and hypomere support frame, the epimere support frame are consolidated with the top of the fuselage
Connect, the stage casing support frame is perpendicular with the epimere support frame, the hypomere support frame is perpendicular with the stage casing support frame,
And the bottom of the hypomere support frame is affixed with the workbench.
3. strong load numerical control press fuselage according to claim 2, it is characterised in that：The hypomere support frame and the work
It is trapezoidal to make platform junction position.
4. strong load numerical control press fuselage according to claim 1, it is characterised in that：Two drift guide holders are provided with,
Two drift guide holders are both secured to the fixed plate of back front end, and two axis of drift guide holder are located at always
Line.
5. strong load numerical control press fuselage according to claim 1, it is characterised in that：It is provided with a drift and is oriented to length
Seat, the length that the drift is oriented to swinging seat is set to 10 ~ 16cm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620635165.0U CN206306530U (en) | 2016-06-24 | 2016-06-24 | Strong load numerical control press fuselage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620635165.0U CN206306530U (en) | 2016-06-24 | 2016-06-24 | Strong load numerical control press fuselage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206306530U true CN206306530U (en) | 2017-07-07 |
Family
ID=59241887
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620635165.0U Expired - Fee Related CN206306530U (en) | 2016-06-24 | 2016-06-24 | Strong load numerical control press fuselage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206306530U (en) |
-
2016
- 2016-06-24 CN CN201620635165.0U patent/CN206306530U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 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: 20170707 Termination date: 20180624 |