CN207240003U - Aircraft floor agility alignment system - Google Patents
Aircraft floor agility alignment system Download PDFInfo
- Publication number
- CN207240003U CN207240003U CN201721048331.8U CN201721048331U CN207240003U CN 207240003 U CN207240003 U CN 207240003U CN 201721048331 U CN201721048331 U CN 201721048331U CN 207240003 U CN207240003 U CN 207240003U
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- CN
- China
- Prior art keywords
- axis
- pedestal
- agility
- stent
- alignment system
- 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.)
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Abstract
Aircraft floor agility alignment system, the stent rear portion both sides of pedestal are flexibly connected two parallel connecting rod one end by axis, two connecting rod other ends are movably installed on down-pressed pole by axis, down-pressed pole one end passes through axis connection rod rear end top, rod rear end lower part is movably installed in stent front portion by axis, briquetting is installed in bar front end, and stent front portion is located on pedestal and is equipped with locating piece.The aircraft floor agility alignment system of the utility model, integrates positioning, clamping function, particularly at least lifts one times than original positioning and clamping mechanism efficiency there are during multiple anchor points in equipment.
Description
Technical field
It the utility model is related to clamping tool technical field, more particularly to the positioning clamping tool of large-scale workpiece.
Background technology
Traditional clamping mechanism is only used for the clamping of the parts such as workpiece or frock, it is impossible to be used in positioning is, it is necessary to separately
Design Orientation mechanism, personnel need to divide two parts to be operated positioning and clamping in operation, are particularly deposited in equipment
In multiple anchor points, inefficiency.
Utility model content
In order to solve the above problem existing for conventional pliers mechanism, the utility model provides a kind of collection positioning, clamps work(
Can be in the clamping mechanism of one.
Used technical solution is the utility model to achieve the above object：Aircraft floor agility alignment system, pedestal 7
6 rear portion both sides of stent two parallel 5 one end of connecting rod are flexibly connected by axis 3, two 5 other ends of connecting rod pass through the activity of axis 3
It is installed on down-pressed pole 4,4 one end of down-pressed pole is installed by 3 connecting rod of axis, 2 upper rear end, 2 rear end lower of bar by the activity of axis 3
Anterior in stent 6, briquetting 1 is installed in 2 front end of bar, and the front portion of stent 6 is located on pedestal 7 and is equipped with locating piece 10.
The first gasket 9 is equipped between 10 lower part of locating piece and pedestal 7,7 lower part of pedestal is equipped with the second gasket 8.
The aircraft floor agility alignment system of the utility model, integrates positioning, clamping function, is particularly deposited in equipment
In multiple anchor points, one times is at least lifted than original positioning and clamping mechanism efficiency.
Brief description of the drawings
Fig. 1 is the utility model aircraft floor agility alignment system open mode main structure figure.
Fig. 2 is the utility model aircraft floor agility alignment system closure state main structure figure.
Fig. 3 is the utility model aircraft floor agility alignment system closure state three-dimensional structure diagram.
In figure：1st, briquetting, 2, bar, 3, axis, 4, down-pressed pole, 5, connecting rod, 6, stent, 7, pedestal, the 8, second gasket, 9, first
Gasket, 10, locating piece, 11, dead-centre position.
Embodiment
The aircraft floor agility positioning system structure of the utility model as shown in Figs. 1-3, by compact heap, linkage, is determined
A few part compositions such as position block, pedestal, adjust pad, 7 top of pedestal are equipped with stent 6, and pedestal 7 and stent 6 are structure as a whole, stent
6 rear portions both sides are flexibly connected two parallel 5 one end of connecting rod by axis 3, and two 5 other ends of connecting rod are movably installed in by axis 3
On down-pressed pole 4,4 one end of down-pressed pole is movably installed in stent 6 by 3 connecting rod of axis, 2 upper rear end, 2 rear end lower of bar by axis 3
Front portion, 2 front end of bar installation briquetting 1, is equipped with locating piece 10 positioned at stent 6 is anterior on pedestal 7,10 lower part of locating piece and pedestal 7 it
Between be equipped with the first gasket 9,7 lower part of pedestal is equipped with the second gasket 8.
In use, by pushing down-pressed pole 1, linked by connecting rod 5, bar 2, drive briquetting 1 to push and carry out clamping of assaulting fortified position, when
After clamp is by dead-centre position 11, bar 2 is positioned block 10 and limits position so as to fulfill positioning, closure state such as Fig. 2 and Fig. 3 institutes
Show.
Claims (2)
1. aircraft floor agility alignment system, it is characterised in that：Pedestal（7）Stent（6）Rear portion both sides pass through axis（3）Activity is even
Connect two parallel connecting rods（5）One end, two connecting rods（5）The other end passes through axis（3）It is movably installed in down-pressed pole（4）On, push
Bar（4）One end passes through axis（3）Connecting rod（2）Upper rear end, bar（2）Rear end lower passes through axis（3）It is movably installed in stent（6）Before
Portion, bar（2）Front end is installed by briquetting（1）, pedestal（7）It is upper to be located at stent（6）Front portion is equipped with locating piece（10）.
2. aircraft floor agility alignment system according to claim 1, it is characterised in that：The locating piece（10）Lower part with
Pedestal（7）Between be equipped with the first gasket（9）, pedestal（7）Lower part is equipped with the second gasket（8）.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721048331.8U CN207240003U (en) | 2017-08-21 | 2017-08-21 | Aircraft floor agility alignment system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721048331.8U CN207240003U (en) | 2017-08-21 | 2017-08-21 | Aircraft floor agility alignment system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207240003U true CN207240003U (en) | 2018-04-17 |
Family
ID=61882200
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721048331.8U Active CN207240003U (en) | 2017-08-21 | 2017-08-21 | Aircraft floor agility alignment system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207240003U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107520773A (en) * | 2017-08-21 | 2017-12-29 | 大连四达高技术发展有限公司 | Aircraft floor agility alignment system |
-
2017
- 2017-08-21 CN CN201721048331.8U patent/CN207240003U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107520773A (en) * | 2017-08-21 | 2017-12-29 | 大连四达高技术发展有限公司 | Aircraft floor agility alignment system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |