CN105673651A - Anti-loosening locking mechanism - Google Patents
Anti-loosening locking mechanism Download PDFInfo
- Publication number
- CN105673651A CN105673651A CN201610177994.3A CN201610177994A CN105673651A CN 105673651 A CN105673651 A CN 105673651A CN 201610177994 A CN201610177994 A CN 201610177994A CN 105673651 A CN105673651 A CN 105673651A
- Authority
- CN
- China
- Prior art keywords
- locking mechanism
- loosening
- pin
- locating
- locating pin
- 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.)
- Pending
Links
- 238000004519 manufacturing process Methods 0.000 abstract description 3
- 125000006850 spacer group Chemical group 0.000 description 8
- 238000010586 diagram Methods 0.000 description 3
- 238000006073 displacement reaction Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B19/00—Bolts without screw-thread; Pins, including deformable elements; Rivets
- F16B19/02—Bolts or sleeves for positioning of machine parts, e.g. notched taper pins, fitting pins, sleeves, eccentric positioning rings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B21/00—Means for preventing relative axial movement of a pin, spigot, shaft or the like and a member surrounding it; Stud-and-socket releasable fastenings
- F16B21/02—Releasable fastening devices locking by rotation
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Pivots And Pivotal Connections (AREA)
Abstract
The invention belongs to the airplane tool manufacturing technology, and relates to a locking mechanism for eliminating locking pin loosening. The anti-loosening locking mechanism comprises a locating pin (1) and a motion limiting shaft (2). The locating pin (1) is of a hollow structure, a groove opening is formed in the top of the locating pin (1), and the inner wall of the bottom of the locating pin (1) is of a threaded structure. The head of the motion limiting shaft (2) is in threaded fit with the inner wall of the bottom of the locating pin, the middle segment of the motion limiting shaft (2) is of a cone structure, and a pulling structure is arranged at the top of the motion limiting shaft (2). According to the anti-loosening locking mechanism, the locating pin can be prevented from loosening in a locating hole of a tool, the situation that the precision of an airplane tool is reduced, and a locating piece shifts is avoided, and therefore the mounting surface quality of an airplane product is effectively improved, and the problems that in a work site, the locating pin is lost, standard storage is hard, and damage is caused are solved. In addition, locating and taking out in the locating hole of the tool are convenient and simple, safety and reliability are achieved, and high practical application value is achieved.
Description
Technical field
The invention belongs to Aircraft Tools manufacturing technology, relate to a kind of solve alignment pin loosen locking mechanism.
Background technology
In Aircraft Tools assembling process, it is common to adopting alignment pin to position, alignment pin is generally the head simple entity column structure with chamfering, position by squeezing into hole, location. But due to alignment pin smooth surface, and it is overproof easily to there is cooperation when manufacturing, and therefore the matching loose of alignment pin and hole, location often occurs during real work, thus causing Aircraft Tools degree of accuracy to reduce, keeper displacement, have a strong impact on aircraft product installation quality.
Summary of the invention
It is an object of the invention to: the anti-loosening locking mechanism of alignment pin that can effectively prevent loosening and can conveniently take out is provided.
The present invention the specific scheme is that a kind of anti-loosening locking mechanism, it includes alignment pin 1 and restraint axle 2, wherein, alignment pin 1 is hollow structure, top has notch, and bottom interior wall has helicitic texture, described restraint axle 2 head and alignment pin bottom interior wall threaded engagement, stage casing is taper structure, and top is provided with can drawing structure.
Described can drawing structure be the collar being socketed in restraint axle top.
Head diameter is less than the minimum place diameter of stage casing taper structure.
Alignment pin 1 be hollow endoporus except bottom thread hole, remainder is unthreaded hole.
Advantages of the present invention
The present invention can prevent alignment pin from loosening in the hole, location of frock, it is to avoid Aircraft Tools degree of accuracy reduces, keeper displacement, thus being effectively increased aircraft product to install surface quality, solving working site alignment pin and losing, be difficult to specification and deposit and damage problem. It addition, the present invention position in the hole, location of frock and convenient to remove succinctly, safe and reliable, there is bigger actual application value.
Accompanying drawing explanation
Fig. 1 is that the present invention can prevent from loosening locating pin structure schematic diagram;
Fig. 2 is the pivot pin schematic diagram that the present invention can prevent from loosening alignment pin;
Fig. 3 is the spacer pin schematic diagram that the present invention can prevent from loosening alignment pin,
Wherein, 1-pivot pin, 2-restraint axle, 3-bracelet, 4-unthreaded hole, 5-screwed hole, 6-elongated slot, the 7-axis of cone, 8-thread spindle, 9-through hole.
Detailed description of the invention
Below in conjunction with drawings and Examples, the present invention will be further described:
Please refer to Fig. 1, Fig. 2 and Fig. 3, the anti-loosening locking mechanism of the present invention includes pivot pin 1, restraint axle 2 and bracelet 3.
Wherein, pivot pin 1 is cylinder, axial line radial top at pivot pin 1 has a unthreaded hole 4, a screwed hole 5 is had in the axial line radially bottom of pivot pin 1, unthreaded hole 4 and screwed hole 5 with one heart and communicate, having an elongated slot 6 at the end face center of pivot pin 1, the depth dimensions of elongated slot 6 is less than the length dimension of unthreaded hole 4.
Spacer pin 2 is stepped cylindrical body, include the axis of cone 7 and thread spindle 8, the axis of cone 7 and thread spindle 8 are concentric, the bottom excircle dimension of the axis of cone 7 is less than unthreaded hole 4 diameter dimension, the top excircle dimension of the axis of cone 7 is more than unthreaded hole 4 diameter dimension, the length dimension of the axis of cone 7 is more than the length dimension of unthreaded hole 4, and the external screw thread size of thread spindle 8 is identical with the dimension of inner screw thread of screwed hole 5, and the length dimension of thread spindle 8 is identical with the length dimension of screwed hole 5; The bottom face distance having a through hole 9, through hole 9 bottom surface and the axis of cone 7 in the cylindrical side, top of the axis of cone 7 is sized larger than the length dimension of unthreaded hole 4.
Bracelet 3 is annulus, and it closes through through hole 9.
The operation principle of the present invention is:
When needs can prevent loosening alignment pin to be operated, first assemble by figure and can prevent from loosening alignment pin, insert in the hole, location of Aircraft Tools by preventing alignment pin, make pivot pin 1 completely into the location Kong Zhonghou of Aircraft Tools, rotate clockwise bracelet 3, the thread spindle 8 driving spacer pin 2 rotates in the screwed hole 5 of pivot pin 1, the axis of cone 7 simultaneously making spacer pin 2 progresses in the incidence hole 4 of pivot pin 1, owing to the top excircle dimension of the axis of cone 7 of spacer pin 2 is more than unthreaded hole 4 diameter dimension, therefore when the axis of cone 7 of spacer pin 2 progresses in the incidence hole 4 of pivot pin 1 after certain depth size, the becoming large-sized of elongated slot 6 at the top of pivot pin 1 can be made, the hole, location making pivot pin 1 and Aircraft Tools is tightly secured together. make pivot pin 1 cannot loosen in the hole, location of frock.
When needs take out in the hole, location of frock and can prevent from loosening alignment pin, rotate counterclockwise bracelet 3, the thread spindle 8 driving spacer pin 2 rotates in the screwed hole 5 exiting pivot pin 1, the axis of cone 7 simultaneously making spacer pin 2 is gradually backed out in the incidence hole 4 of pivot pin 1, the size restoration of the elongated slot 6 at the top of pivot pin 1 can be made, the hole, location making pivot pin 1 and Aircraft Tools is tightly fastened state and is changed to loosening state, upwards lift bracelet 3, takes out and can prevent from loosening alignment pin in the hole, location of frock.
Claims (4)
1. an anti-loosening locking mechanism, it is characterized in that, including alignment pin (1) and restraint axle (2), wherein, alignment pin (1) is hollow structure, and top has notch, and bottom interior wall has helicitic texture, described restraint axle (2) head and alignment pin bottom interior wall threaded engagement, stage casing is taper structure, and top is provided with can drawing structure.
2. anti-loosening locking mechanism according to claim 1, it is characterised in that described can drawing structure be the collar being socketed in restraint axle top.
3. anti-loosening locking mechanism according to claim 1, it is characterised in that head diameter is less than the minimum place diameter of stage casing taper structure.
4. anti-loosening locking mechanism according to claim 1, it is characterised in that alignment pin (1) is for hollow endoporus except bottom thread hole, and remainder is unthreaded hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610177994.3A CN105673651A (en) | 2016-03-25 | 2016-03-25 | Anti-loosening locking mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610177994.3A CN105673651A (en) | 2016-03-25 | 2016-03-25 | Anti-loosening locking mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105673651A true CN105673651A (en) | 2016-06-15 |
Family
ID=56225288
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610177994.3A Pending CN105673651A (en) | 2016-03-25 | 2016-03-25 | Anti-loosening locking mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105673651A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1638387A1 (en) * | 1988-09-02 | 1991-03-30 | Предприятие П/Я Р-6896 | Parts joint |
| CN201159225Y (en) * | 2007-12-29 | 2008-12-03 | 成都飞机工业（集团）有限责任公司 | Screw-in type self-locking position pin |
| CN201486976U (en) * | 2009-07-23 | 2010-05-26 | 中国航空工业第六一八研究所 | High precision repetitive installation positioning mechanism |
| CN203214524U (en) * | 2013-03-30 | 2013-09-25 | 北京三兴汽车有限公司 | Inserting pin |
| CN103398063A (en) * | 2013-07-29 | 2013-11-20 | 无锡市张泾宇钢机械厂 | Clamp pin easy to dismount |
| JP2014062361A (en) * | 2012-09-20 | 2014-04-10 | Hamanaka Nut Co Ltd | Post-installed anchor set |
| CN204942190U (en) * | 2015-08-12 | 2016-01-06 | 合肥凯创汽车零部件有限公司 | A kind of expansion can clamping and positioning pin |
-
2016
- 2016-03-25 CN CN201610177994.3A patent/CN105673651A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1638387A1 (en) * | 1988-09-02 | 1991-03-30 | Предприятие П/Я Р-6896 | Parts joint |
| CN201159225Y (en) * | 2007-12-29 | 2008-12-03 | 成都飞机工业（集团）有限责任公司 | Screw-in type self-locking position pin |
| CN201486976U (en) * | 2009-07-23 | 2010-05-26 | 中国航空工业第六一八研究所 | High precision repetitive installation positioning mechanism |
| JP2014062361A (en) * | 2012-09-20 | 2014-04-10 | Hamanaka Nut Co Ltd | Post-installed anchor set |
| CN203214524U (en) * | 2013-03-30 | 2013-09-25 | 北京三兴汽车有限公司 | Inserting pin |
| CN103398063A (en) * | 2013-07-29 | 2013-11-20 | 无锡市张泾宇钢机械厂 | Clamp pin easy to dismount |
| CN204942190U (en) * | 2015-08-12 | 2016-01-06 | 合肥凯创汽车零部件有限公司 | A kind of expansion can clamping and positioning pin |
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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 | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160615 |
|
| RJ01 | Rejection of invention patent application after publication |