CN206855068U - Aircraft door part air-actuated jaw - Google Patents
Aircraft door part air-actuated jaw Download PDFInfo
- Publication number
- CN206855068U CN206855068U CN201720244997.4U CN201720244997U CN206855068U CN 206855068 U CN206855068 U CN 206855068U CN 201720244997 U CN201720244997 U CN 201720244997U CN 206855068 U CN206855068 U CN 206855068U
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- CN
- China
- Prior art keywords
- aircraft door
- door part
- support
- dovetail
- hold
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- 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
The utility model discloses aircraft door part air-actuated jaw, including support, at least one dovetail fixture for being used to install workpiece is detachably provided with the support, the dovetail fixture is fixed or unclamped with the support by pneuma-lock relieving mechanism by the positioning finger setting that is set on the support.The utility model deft design, it is simple in construction, by setting multiple and aircraft door part match dovetail fixture, and multiple dovetail fixtures are positioned and fastened by combination alignment pin and pneuma-lock relieving mechanism, the clamping of multiple aircraft door parts can once be carried out, operating efficiency is not only increased, and aircraft door part is fixed on dovetail furniture, advantageously ensures that crudy.
Description
Technical field
It the utility model is related to a kind of fixture, more particularly to a kind of aircraft door part air-actuated jaw.
Background technology
When carrying out part processing in aircraft door, clamping originally is carried out using vice, a workpiece can only be processed every time,
Efficiency is low, and clamping is unstable, and certain influence is produced for the quality of part in aircraft door.
Utility model content
The purpose of this utility model is exactly to solve the above-mentioned problems in the prior art, there is provided aircraft door part
Air-actuated jaw.
The purpose of this utility model is achieved through the following technical solutions：
Aircraft door part air-actuated jaw, including support, it is detachably provided with the support at least one being used to pacify
The dovetail fixture of workpiece is filled, the dovetail fixture is released by the positioning finger setting that is set on the support by pneuma-lock
Laying mechanism is fixed or unclamped with the support.
Preferably, described aircraft door part air-actuated jaw, wherein：The pneuma-lock relieving mechanism includes running through institute
The hold-down bolt of support panel is stated, the head of the hold-down bolt is located at the top of the support panel, and the hold-down bolt connects
The cylinder for driving its axial stretching is connect, the cylinder connects source of the gas by supply air line.
Preferably, described aircraft door part air-actuated jaw, wherein：Multiple cylinders comprising an air valve by opening
The supply air line connection source of the gas of pass.
Preferably, described aircraft door part air-actuated jaw, wherein：The dovetail fixture includes being used to install workpiece
Wedge-shaped mounting groove and the neck matched with the hold-down bolt.
Preferably, described aircraft door part air-actuated jaw, wherein：The neck comprises at least the first resettlement section and the
Two resettlement sections, the height of first resettlement section are more than the height on the head, and the width of second resettlement section is less than described
The diameter on head, and the depth of second resettlement section is less than the length of the screw rod of the hold-down bolt.
Preferably, described aircraft door part air-actuated jaw, wherein：The dovetail fixture is six.
The advantages of technical solutions of the utility model, is mainly reflected in：
The utility model deft design, it is simple in construction, by setting multiple and aircraft door part match dovetail fixture,
And multiple dovetail fixtures are positioned and fastened by combination alignment pin and pneuma-lock relieving mechanism, can once carry out multiple aircraft cabins
The clamping of door part, not only increases operating efficiency, and aircraft door part is fixed on dovetail furniture, is advantageous to protect
Demonstrate,prove crudy.
During work, when the aircraft door part on air-actuated jaw is processed, synchronously aircraft door part can be connected
It is connected on dovetail fixture, so as to further improve processing efficiency.
Because multiple cylinders are opened and closed by an air valve switch, therefore the fixation and release operation of multiple dovetail fixtures
Simply.
Brief description of the drawings
Fig. 1 is structure chart of the present utility model；
Fig. 2 is the enlarged drawing of a-quadrant in Fig. 1；
Fig. 3 is the exploded view of dovetail fixture.
Embodiment
The purpose of this utility model, advantage and feature, figure will be carried out by the non-limitative illustration of preferred embodiment below
Show and explain.These embodiments are only the prominent examples using technical solutions of the utility model, all to take equivalent substitution or wait
Effect conversion and formed technical scheme, all fall within the requires of the utility model protection within the scope of.
The utility model discloses a kind of aircraft door part air-actuated jaw, as shown in Figure 1, including support 1, the branch
Frame 1 includes support panel and two parallel bearings below the support panel, and the support panel is preferably to grow
Cube, the bearing are located at the long side both ends of the support panel, are provided with the support panel at least one for placing
One dovetail fixture 2 puts position, and a gap setting is put, and they are respectively positioned in preferably described position of putting for 6 described in six
Between described two bearings, each described put is detachably provided with a dovetail fixture 2 for being used to install workpiece on position, right
Answer, the dovetail fixture 2 is six, thus allows for mass processing, each dovetail fixture 2 by setting thereon
Wedge-shaped mounting groove 21 and workpiece clamping.
As shown in Figure 3, the dovetail fixture 2 includes body 23, and three stepped installations are provided with the body 23
Groove 24, compressing member 25, shape and the mounting groove of the compressing member 25 are each detachably provided with the mounting groove 24
24 match, and, also to be stepped, and be provided with the screw vertical with the support panel, the compressing member 25 passes through spiral shell for it
Bolt 26 is connected with the body 23.
Each dovetail fixture 2 is positioned by the alignment pin 3 set on the support 1, specifically, the alignment pin
3 on the support panel, and the alignment pin 3 for each putting two gap settings at position coordinates the dovetail fixture
2 positioning, the bottom of each dovetail fixture 2 are provided with the positioning hole matched with two alignment pins 3（Not shown in figure）.
Now, although each dovetail fixture 2 can be positioned on the support panel, do not fix, therefore each
The dovetail fixture 2 is fixed or unclamped with the support panel by pneuma-lock relieving mechanism 4.
Specifically, the pneuma-lock relieving mechanism 4 includes the hold-down bolt 41 through the support panel, this implementation
In example, the hold-down bolt 41 is two, and the central point of two hold-down bolts 41 and two alignment pins is located at straight line
On, the head 411 of two hold-down bolts 41 is located at the top of the support panel, and two hold-down bolts 41 are located at institute
The cylinder 42 that one end below support panel is all connected with driving its axial stretching is stated, the cylinder 42 is fixed on the support 1,
And the cylinder 42 connects source of the gas by supply air line 43, further, for the ease of control, six cylinders 42 pass through bag
Supply air line 43 containing an air valve switch 44 connects source of the gas.
It is corresponding, in order to which the dovetail fixture 2 is fixed on into the branch by the stretching motion of the hold-down bolt 41
Support on panel, the dovetail fixture 2 includes the neck 22 matched with the hold-down bolt 41, and the neck 22 is pacified with the wedge shape
Tankage 21 is detailed backwards to setting, and the neck 22 is two and shape is close with the hold-down bolt 41, the neck 22 to
Include the first resettlement section 221 and the second resettlement section 222 less, as shown in Figure 2, the height a of first resettlement section 221 is more than institute
The height a1 on head 411 is stated, the width b of second resettlement section 222 is less than the diameter b1 on the head 411, and described second
The depth h of resettlement section 222 is less than the length of the screw rod 412 of the hold-down bolt 41.
During using aircraft door part air-actuated jaw of the present utility model, the cylinder 42 is set to drive the hold-down bolt 41
Stretching state is kept, two compressions for then putting the neck 22 of each dovetail fixture 2 for being provided with workpiece and one at position
The correspondence of bolt 41, and two hold-down bolts 41 is contained in two necks 22, now, two put at position are fixed
Position pin 3 be located in the positioning hole of the dovetail fixture 2, by all dovetail fixtures 2 be placed on described in put position after, press the gas
Threshold switch 44 drives all hold-down bolts 41 to move down and the head 411 of each hold-down bolt 41 is pressed in described first and houses
At the step surface in portion 221, it is fixed on so as to which book dovetail fixture 2 will be searched on the support panel.
When needing to remove dovetail fixture 2 from the support panel, start the air valve switch 44 and drive the pressure
Tight bolt 41, which moves up, separates its head 411 and the step surface of first resettlement section 221, so as to discharge all swallows simultaneously
Tail fixture 2, now manually the dovetail fixture 2 is removed from the support panel, changes the dovetail clip for being provided with workpiece
Tool 2.
The utility model still has numerous embodiments, all technologies formed using equivalents or equivalent transformation
Scheme, all fall within the scope of protection of the utility model.
Claims (4)
1. aircraft door part air-actuated jaw, including support（1）, it is characterised in that：The support（1）On be detachably provided with
At least one dovetail fixture for being used to install workpiece（2）, the dovetail fixture（2）Pass through the support（1）The positioning of upper setting
Pin（3）Positioning, and pass through pneuma-lock relieving mechanism（4）With the support（1）Fixed or release；The pneuma-lock machine for releasing
Structure（4）Including the hold-down bolt through support panel（41）, the hold-down bolt（41）Head（411）Positioned at the supporting surface
The top of plate, the hold-down bolt（41）Connection drives the cylinder of its axial stretching（42）, the cylinder（42）Pass through air supply pipe
Road（43）Connect source of the gas, the dovetail fixture（2）Including the wedge-shaped mounting groove for installing workpiece（21）And with the compression
Bolt（41）The neck of matching（22）.
2. aircraft door part air-actuated jaw according to claim 1, it is characterised in that：Multiple cylinders（42）Pass through
Include an air valve switch（44）Supply air line（43）Connect source of the gas.
3. aircraft door part air-actuated jaw according to claim 1, it is characterised in that：The neck（22）Comprise at least
First resettlement section（221）With the second resettlement section（222）, first resettlement section（221）Height be more than the head（411）'s
Highly, second resettlement section（222）Width be less than the head（411）Diameter, and second resettlement section（222）
Depth be less than the hold-down bolt（41）Screw rod（412）Length.
4. according to any described aircraft door part air-actuated jaws of claim 1-3, it is characterised in that：The dovetail fixture
（2）For six.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720244997.4U CN206855068U (en) | 2017-03-14 | 2017-03-14 | Aircraft door part air-actuated jaw |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720244997.4U CN206855068U (en) | 2017-03-14 | 2017-03-14 | Aircraft door part air-actuated jaw |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206855068U true CN206855068U (en) | 2018-01-09 |
Family
ID=60814157
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720244997.4U Active CN206855068U (en) | 2017-03-14 | 2017-03-14 | Aircraft door part air-actuated jaw |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206855068U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109131934A (en) * | 2018-08-30 | 2019-01-04 | 哈尔滨飞机工业集团有限责任公司 | A kind of cabin testing equipment frame fixed transfer structure |
-
2017
- 2017-03-14 CN CN201720244997.4U patent/CN206855068U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109131934A (en) * | 2018-08-30 | 2019-01-04 | 哈尔滨飞机工业集团有限责任公司 | A kind of cabin testing equipment frame fixed transfer structure |
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