CN202388472U - Plane nail dismantling device - Google Patents
Plane nail dismantling device Download PDFInfo
- Publication number
- CN202388472U CN202388472U CN2011205658546U CN201120565854U CN202388472U CN 202388472 U CN202388472 U CN 202388472U CN 2011205658546 U CN2011205658546 U CN 2011205658546U CN 201120565854 U CN201120565854 U CN 201120565854U CN 202388472 U CN202388472 U CN 202388472U
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- CN
- China
- Prior art keywords
- spring
- inner sleeve
- sleeve
- core body
- nail
- 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
Links
- 239000012634 fragment Substances 0.000 claims description 21
- 230000002093 peripheral effect Effects 0.000 abstract 1
- 230000000694 effects Effects 0.000 description 4
- 210000003813 thumb Anatomy 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000008676 import Effects 0.000 description 1
- 210000003141 lower extremity Anatomy 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
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- Portable Nailing Machines And Staplers (AREA)
Abstract
The utility model discloses a plane nail dismantling device, which comprises a core body, an inner sleeve, an outer sleeve, an outer spring and an inner spring. The core body is arranged in the inner sleeve, the outer sleeve is sleeved on the outer side of the inner sleeve, a spring limit screw is arranged on the core body, guide grooves are arranged on the peripheral walls of the inner sleeve and the outer sleeve, the spring limit screw extends out from the guide grooves of the inner sleeve and the outer sleeve, the inner spring and the outer spring are arranged on the spring limit screw, the inner spring is arranged between the core body and the inner sleeve, the outer spring is arranged between the inner sleeve and the outer sleeve, two or more than two elastic sheets are arranged at the end of the core body, and the diameter of the outer edges of the elastic sheets is larger than the inner diameter of the inner sleeve. When a plane nail is dismantled, the outer sleeve presses a circuit board downwards, and the inner sleeve drives the elastic sheets on the core body to enable side wings of the plane nail to be retracted inwards; and when the inner sleeve rebounds upwards, a supporting arm of the plane nail enables the circuit board to be carried upwards so as to break away from clamping of the side wings of the plane nail. The plane nail is dismantled at one go, and the plane nail dismantling device is simple and rapid to operate.
Description
Technical field
The utility model relates to the provision for disengagement of aircraft nail.
Background technology
The blower fan of the off-premises station of existing fixed frequency air conditioner device adopts direct current generator usually, and for the interchange that will import converts needed direct current to, general direct current generator all is equipped with a dc controlled plate.Because outdoor electrical box is a sheet metal component, runs into electric plate for the pin that prevents automatically controlled plate and causes short circuit, often use the aircraft nail that dc controlled plate mount is being had now on the set through hole of electrical box.When needs dismounting aircraft nail; Automatically controlled plate is pressed down; Making has the slit between flank bottom card shape and the automatically controlled plate upper surface of aircraft nail; Cut or push to the centre with the normal screws cutter or with chisel then, make the flank lower end external diameter of aircraft nail less than the fixed via of automatically controlled plate with the flank of drill bit with aircraft nail.The automatically controlled plate support arm of aircraft nail ejects automatically controlled plate.Because manual steps is loaded down with trivial details, thus the drawback that causes inefficiency and cause device structure spare to damage easily.
The utility model content
The utility model purpose provides the provision for disengagement of a kind of aircraft nail in order to overcome the deficiency that above-mentioned prior art exists, and it is easier that the employee is operated, and improves operating efficiency, reduces and causes the damage of device structure spare.
The technical scheme that the utility model adopts is: the provision for disengagement of aircraft nail, comprise core body, inner sleeve, outer sleeve, outer spring, inner spring, and said core body is arranged in the inner sleeve; The outer sheathed outer sleeve of said inner sleeve, core body is provided with the spacing screw rod of spring, and inner sleeve and outer sleeve perisporium are provided with guide groove; The spacing screw rod of said spring stretches out in the guide groove of inner sleeve and outer sleeve; On the spacing screw rod of spring, be provided with inner spring and outer spring, said inner spring is located between core body and the inner sleeve, and said outer spring is located between inner sleeve and the outer sleeve; The end of said core body is provided with the shell fragment more than two or two, and said shell fragment external profile diameter is greater than the internal diameter of inner sleeve.
Be provided with inner sleeve spring limiting stand in the said inner sleeve, an end of said inner spring is resisted against on the inner sleeve spring limiting stand.
Be provided with outer sleeve spring limiting stand in the said outer sleeve, an end of said outer spring is resisted against on the outer sleeve spring limiting stand.
The spacing screw rod of said spring is criss-cross, and four guide grooves evenly are set respectively on said inner sleeve and the outer sleeve perisporium.
The beneficial effect of the utility model is:
During dismounting aircraft nail; Through outer sleeve with circuit board slightly to pressing down, the shell fragment that makes core body with inner sleeve more inwardly is retracted to the internal diameter less than circuit board apertures with the flank of aircraft nail, when outer sleeve makes progress resilience; Each goes up and holds up the support arm of aircraft nail with circuit board, breaks away from the buckle that aircraft is followed closely flank.The dismounting of aircraft nail is accomplished without any letup, and is simple and quick.
The aircraft nail provision for disengagement of the utility model has advantage efficient, that minimizing causes the damage of device structure spare when dismounting aircraft nail.
Description of drawings
Fig. 1 is the core sketch map of the utility model aircraft nail provision for disengagement;
Fig. 2 is the inner sleeve structural representation of the utility model aircraft nail provision for disengagement;
Fig. 3 is the core body of the utility model aircraft nail provision for disengagement and the assembling sketch map of inner sleeve;
Fig. 4 is the outer sleeve structure sketch map of the utility model aircraft nail provision for disengagement;
Fig. 5 is the dismounting original state sketch map of the utility model aircraft nail provision for disengagement;
Fig. 6 is the unloading process sketch map of the utility model aircraft nail provision for disengagement;
Fig. 7 is the disassembly status enlarged drawing of the utility model aircraft nail provision for disengagement.
The specific embodiment
Below pass through the specific embodiment, and combine accompanying drawing that the utility model is described further.
Like Fig. 1, Fig. 2, Fig. 3, Fig. 4, shown in Figure 5, the provision for disengagement of aircraft nail comprises core body 1, inner sleeve 2, outer sleeve 3, outer spring 4, inner spring 5.
As shown in Figure 1, wherein core body 1 comprises the spacing screw rod in core body top 11, core body connecting rod 12, spring 13, slit 14, inclined-plane 15, core body bottom, shell fragment 16.Said core body top 11 is positioned at the core body top, and external diameter is less than the internal diameter in first chamber 22 of core body connecting rod 12 and inner sleeve.Said core body connecting rod 12 is connected core body top 11 with inclined-plane 15, core body bottom, external diameter is less than the internal diameter in second chamber 23 of inner sleeve.The spacing screw rod 13 of said spring is around core body connecting rod 12 middle parts, and the spacing screw rod 13 of spring is the consistent screw rod of four shapes that evenly is provided with, and four spacing screw rods 13 of spring are on same plane.The length of the spacing screw rod 13 of spring guarantees to pass inner sleeve guide groove 24 and outer sleeve guide groove 32 simultaneously.Said core body inclined-plane 15, bottom and shell fragment 16 are arranged on core body 1 bottom, and core body inclined-plane 15, bottom and shell fragment 16 residing positions are hollow.Said shell fragment 16 is connected with inclined-plane 15, core body bottom, and the external diameter of shell fragment 16 is greater than the internal diameter in second chamber 23 of inner sleeve, and the internal diameter of shell fragment 16 is slightly less than the external diameter of flank 71 bottoms of aircraft nail.Said slit 14 is arranged on core body inclined-plane 15, bottom and shell fragment 16 centres.
As shown in Figure 2, inner sleeve comprises pressing down section 21, first chamber 22, second chamber 23, inner sleeve guide groove 24, inner sleeve spring limiting stand 25; Said pressing down section 21 is arranged on inner sleeve 2 tops, is cylindrical structural.Said first chamber 22 and second chamber 23 are positioned at inner sleeve 2 centers, and first chamber 22 is connecting pressing down section 21, the second chambeies 23 and connecting first chamber 22, and wherein the internal diameter in first chamber 22 is littler than second chamber 23.Said inner sleeve guide groove 24 evenly is arranged on around inner sleeve 2 middle parts, and the width of inner sleeve guide groove 24 is greater than the external diameter of the spacing screw rod 13 of spring.
Be illustrated in figure 3 as the assembling sketch map of core body 1 and inner sleeve 2.Core body 1 places in the inner sleeve 2, and inner spring 5 one ends are resisted against inner sleeve spring limiting stand 25, and the other end is resisted against on the spacing screw rod 13 of spring.The spacing screw rod 13 of spring stretches out from inner sleeve guide groove 24.Look for when inner sleeve 2 and core body 1 are seated, core body top 11 is in 1/4 place in first chamber 22 of inner sleeve 2.Core body connecting rod 12 is in second chamber 23 of inner sleeve 2, and core body inclined-plane 15, bottom and shell fragment 16 are in outside the bottom of inner sleeve 2.Inner spring 5 length between sleeve 2 and the core body 1 slightly are longer than the distance between the inner sleeve spring limiting stand 25 of spacing screw rod 13 of spring and sleeve 2.Under the effect of spring 5 elastic force, the spacing screw rod 13 of spring is being pressed inner sleeve guide groove 24 bottoms of inner sleeve 2.The top of inner spring 5 heads on inner sleeve spring limiting stand 25.When the pressing down section 21 that presses down inner sleeve 2 with thumb, this moment inner spring 5 stress and deformations.The inwall of inner sleeve 2 bottoms moves down along inclined-plane 15, core body bottom, and core body inclined-plane 15, bottom and shell fragment 16 are inwardly pushed, and makes core body inclined-plane 15, bottom and shell fragment 16 inwardly shrink internal diameter and diminishes.
As shown in Figure 4, outer sleeve 4 comprises handle portion 31, outer sleeve guide groove 32, outer sleeve bottom 33, outer sleeve spring limiting stand 34.Said handle portion 31 is arranged on the top of outer sleeve 4; Said outer sleeve guide groove 32 evenly be positioned at outer sleeve 4 middle parts around; Outer sleeve guide groove 32 length equal inner sleeve guide groove 24 width; And greater than spacing screw rod 13 external diameters of spring, the bottom that said outer sleeve bottom 33 is positioned at outer sleeve 4 is connected with handle portion 31, and the external diameter of outer sleeve bottom 33 is less than the external diameter of handle portion 31.Said outer sleeve spring limiting stand 34 is arranged on the interior top of chamber of outer sleeve 4.
As shown in Figure 5, the aircraft nail provision for disengagement of the utility model is assemblied by inside and outside sleeve and core body 1, and wherein, core body 1 is assemblied in the inner sleeve 2, and inner sleeve 2 then is assemblied in the outer sleeve 3, and interior outer spring all is resisted against on the spacing screw rod 13 of spring.When being seated, outer sleeve 3 is enclosed within on the inner sleeve 2, and the bottom of inner sleeve 2 slightly is longer than in the bottom of outer sleeve 3, but does not comprise the inclined-plane, bottom 15 and the shell fragment 16 of core body 1.Under the elastic force effect of outer spring 4, the spacing screw rod 13 of spring is pushed down the bottom of outer sleeve guide groove 32, outer spring 4 head on outer sleeve spring limiting stand 34.
During dismounting aircraft nail, according to Fig. 5, Fig. 6, shown in Figure 7.Flank 71 peripheries that only need the core body inclined-plane 15, bottom and the shell fragment 16 of core body 1 be enclosed within the aircraft nail.Then with outer sleeve 3 to pressing down.At this moment, outer spring 4 deformation.Outer sleeve 3 bottom lower limbs are with automatically controlled plate 6 pressed downward.The 72 downward deformation of aircraft nail support arm; Extrude an interspace between the card shape of flank 71 bottoms of aircraft nail and the automatically controlled plate 6.Press down the pressing down section 21 of inner sleeve 2 then with thumb; Inner spring 5 stress and deformations; The bottom interior wall of inner sleeve 2 moves down along inclined-plane 15, core body bottom, and core body inclined-plane 15, bottom and shell fragment 16 are inwardly pushed, and makes core body inclined-plane 15, bottom and shell fragment 16 inwardly shrink internal diameter and diminishes.The flank 71 of shell fragment 16 inwalls extruding aircraft nail makes it shrink to the center; When pressing down section 21 is pressed down to maximum displacement; The maximum position of flank 71 bottoms of aircraft nail is less than fixed via 61 internal diameters of automatically controlled plate 6; Unclamp outer sleeve 3 then, this moment automatically controlled plate 6 at automatically controlled plate support arm 72 reinstatement elastic force to top offset; Outer sleeve 3 moves up at the active force that the elastic force and the automatically controlled plate 6 of outer spring 4 makes progress.Automatically controlled plate 6 to top offset, makes the flank 71 lower end card shapes of aircraft nail break away from the upper surface of automatically controlled plate 6 at automatically controlled plate support arm 72 reinstatement elastic force.Unclamp the pressing down section 21 of core body 1 at last.Core body 1 moves up in the elastic force effect of inner spring 5, sets back.Inclined-plane 15, core body bottom and shell fragment 16 are in the effect reinstatement down of self elastic force.
Claims (4)
1. aircraft nail provision for disengagement, it is characterized in that: comprise core body, inner sleeve, outer sleeve, outer spring, inner spring, said core body is arranged in the inner sleeve; The outer sheathed outer sleeve of said inner sleeve, core body is provided with the spacing screw rod of spring, and inner sleeve and outer sleeve perisporium are provided with guide groove; The spacing screw rod of said spring stretches out in the guide groove of inner sleeve and outer sleeve; On the spacing screw rod of spring, be provided with inner spring and outer spring, said inner spring is located between core body and the inner sleeve, and said outer spring is located between inner sleeve and the outer sleeve; The end of said core body is provided with the shell fragment more than two or two, and said shell fragment external profile diameter is greater than the internal diameter of inner sleeve.
2. aircraft nail according to claim 1 provision for disengagement, it is characterized in that: be provided with inner sleeve spring limiting stand in the said inner sleeve, an end of said inner spring is resisted against on the inner sleeve spring limiting stand.
3. aircraft nail according to claim 1 provision for disengagement, it is characterized in that: be provided with outer sleeve spring limiting stand in the said outer sleeve, an end of said outer spring is resisted against on the outer sleeve spring limiting stand.
4. aircraft nail according to claim 1 provision for disengagement, it is characterized in that: the spacing screw rod of said spring is criss-cross, and four guide grooves evenly are set respectively on said inner sleeve and the outer sleeve perisporium.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011205658546U CN202388472U (en) | 2011-12-29 | 2011-12-29 | Plane nail dismantling device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011205658546U CN202388472U (en) | 2011-12-29 | 2011-12-29 | Plane nail dismantling device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202388472U true CN202388472U (en) | 2012-08-22 |
Family
ID=46663423
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011205658546U Expired - Fee Related CN202388472U (en) | 2011-12-29 | 2011-12-29 | Plane nail dismantling device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202388472U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108972435A (en) * | 2018-08-31 | 2018-12-11 | 国网山东省电力公司宁津县供电公司 | A kind of screw socket with pickup function |
| CN110405697A (en) * | 2019-07-31 | 2019-11-05 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of pulling device and its application method |
| CN114618679A (en) * | 2022-03-16 | 2022-06-14 | 宁波招宝磁业有限公司 | Telescopic magnetic rod with movable magnet |
-
2011
- 2011-12-29 CN CN2011205658546U patent/CN202388472U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108972435A (en) * | 2018-08-31 | 2018-12-11 | 国网山东省电力公司宁津县供电公司 | A kind of screw socket with pickup function |
| CN110405697A (en) * | 2019-07-31 | 2019-11-05 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of pulling device and its application method |
| CN114618679A (en) * | 2022-03-16 | 2022-06-14 | 宁波招宝磁业有限公司 | Telescopic magnetic rod with movable magnet |
| CN114618679B (en) * | 2022-03-16 | 2024-03-08 | 宁波招宝磁业有限公司 | Telescopic magnetic rod with movable magnet |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20120822 Termination date: 20121229 |