CN217405830U - Aviation plug-in component applied to power distribution control equipment - Google Patents
Aviation plug-in component applied to power distribution control equipment Download PDFInfo
- Publication number
- CN217405830U CN217405830U CN202221156770.1U CN202221156770U CN217405830U CN 217405830 U CN217405830 U CN 217405830U CN 202221156770 U CN202221156770 U CN 202221156770U CN 217405830 U CN217405830 U CN 217405830U
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- Prior art keywords
- aviation
- aviation plug
- connecting cylinder
- distribution control
- control equipment
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- Expired - Fee Related
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- 230000000694 effects Effects 0.000 abstract description 3
- 238000010030 laminating Methods 0.000 abstract description 3
- 235000017166 Bambusa arundinacea Nutrition 0.000 abstract description 2
- 235000017491 Bambusa tulda Nutrition 0.000 abstract description 2
- 241001330002 Bambuseae Species 0.000 abstract description 2
- 235000015334 Phyllostachys viridis Nutrition 0.000 abstract description 2
- 239000011425 bamboo Substances 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 3
- 238000006467 substitution reaction Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
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Abstract
An aviation plug assembly for use with power distribution control equipment, comprising: the aviation plug comprises a base, pins and a connecting cylinder, the pins are fixedly connected with the base, the connecting cylinder is sleeved on the base, the connecting cylinder can rotate around the base, and the inner wall of the connecting cylinder is provided with a limiting block; aviation socket, aviation socket is equipped with pin hole and spacing groove, the pin hole corresponds with the pin, the spacing groove is the L type, the lateral wall of spacing groove and the lateral wall laminating of stopper adopt the joint of stopper and spacing groove, realize quick fixed aviation plug and aviation socket through the swivelling joint section of thick bamboo, when having guaranteed fixed effect, improved the convenience of using.
Description
Technical Field
The utility model relates to an aviation plug technical field especially relates to a be applied to distribution control equipment's aviation plug assembly.
Background
Aviation grafting subassembly is called for short and is inserted by plane, generally comprises plug and socket, comes control circuit's intercommunication and disconnection through the connection and the separation of plug and socket, and the connected mode that inserts by plane at present is mostly threaded connection, and the grafting process is too complicated, especially sets up the field at distribution control, and partial installation space is narrow and small, uses threaded connection and inconvenient.
SUMMERY OF THE UTILITY MODEL
In view of the not enough of background art existence, the utility model relates to a be applied to distribution control equipment's aviation plug components adopts the joint of stopper and spacing groove, realizes quick fixed aviation plug and aviation socket through rotary connection section of thick bamboo, when having guaranteed fixed effect, has improved the convenience of using.
The utility model relates to a be applied to distribution control equipment's aviation plug-in components, include: the aviation plug comprises a base, pins and a connecting cylinder, the pins are fixedly connected with the base, the connecting cylinder is sleeved on the base, the connecting cylinder can rotate around the base, and the inner wall of the connecting cylinder is provided with a limiting block; the aviation socket is provided with a pin hole and a limiting groove, the pin hole corresponds to a pin, the limiting groove is L-shaped, and the side wall of the limiting groove is attached to the side wall of the limiting block.
Through adopting above-mentioned scheme, aviation plug and aviation socket are connected the back, can accomplish fixedly with the rotatory hem to the spacing groove of stopper, and the convenience of connection is inserted to the aviation of improvement, and the lateral wall of spacing groove and the lateral wall laminating of stopper improve fixed stability simultaneously.
Furthermore, a plurality of groups of limiting blocks and limiting grooves are arranged.
Through adopting above-mentioned scheme, improve the fixed stability of aviation plug and aviation socket.
Furthermore, two sets of limiting blocks and limiting grooves are arranged.
Through adopting above-mentioned scheme, guarantee the fixed stability of aviation plug and aviation socket.
Furthermore, the connecting pipe is provided with a telescopic structure, the aircraft carrier socket is provided with a pin hole, and the telescopic structure is matched with the pin hole to fix the aviation plug and the aviation socket.
By adopting the above scheme, the phenomenon that the reverse rotation appears in the connecting pipe after the rotation is prevented from leading to the disconnection of aviation plug and aviation socket, improves the stability that aviation plug and aviation socket are connected.
Furthermore, the telescopic structure comprises a pin column and a self-locking switch mechanism, and the distance between the central point of the pin column and the central point of the pin hole is equal to the length of the L-shaped limit groove folded edge.
By adopting the scheme, the pin column is ensured to correspond to the pin hole.
Furthermore, the connecting cylinder and the aviation socket are both provided with fool-proof marks.
Through adopting above-mentioned scheme, the relative position of aviation plug and aviation socket of being convenient for operating personnel discernment prevents to appear inserting wrong phenomenon.
Drawings
FIG. 1 is a schematic structural diagram of an aviation plug-in assembly according to embodiment 1 of the present invention;
fig. 2 is a schematic structural diagram of an aviation plug in embodiment 1 of the present invention;
fig. 3 is a schematic structural diagram of an aviation plug-in assembly according to embodiment 2 of the present invention.
Reference numerals: 110. a base; 111. an annular groove; 120. a connecting cylinder; 121. a limiting block; 122. an annular rim; 123. a pin; 124. a self-locking switch mechanism; 130. a pin; 200. an aviation socket; 210. a limiting groove; 220. a pin hole; 300. fool-proof marks.
Detailed Description
The technical solution in the embodiments of the present invention will be clearly and completely described and discussed below with reference to the accompanying drawings of the present invention, and it is obvious that only some examples, not all examples, of the present invention are described herein, and all other embodiments obtained by a person of ordinary skill in the art without creative work belong to the protection scope of the present invention based on the embodiments of the present invention.
To facilitate understanding of the embodiments of the present invention, the following detailed description will be given by way of example with reference to the accompanying drawings, and each embodiment is not limited to the embodiments of the present invention.
The embodiment 1 of the utility model relates to as shown with reference to fig. 1 and fig. 2, relate to an aviation plug assembly applied to distribution control equipment, including aviation plug and aviation socket 200, the cross-section of aviation plug and aviation socket 200 is circular, aviation plug includes base 110, pin 130 and connecting cylinder 120, pin 130 and base 110 fixed connection, connecting cylinder 120 cover is located base 110, base 110 is equipped with ring channel 111, connecting cylinder 120 bottom is equipped with annular chimb 122, annular chimb 122 cover is located ring channel 111, connecting cylinder 120 can rotate around base 110, the inner wall of connecting cylinder 120 is equipped with stopper 121; aviation socket 200 is equipped with pin 130 hole and spacing groove 210, the width of ring channel 111 is wider than the width of annular chimb 122, makes things convenient for operating personnel to be in contrast pin 130 and pin 130 hole, pin 130 hole corresponds with pin 130, spacing groove 210 is the L type, the lateral wall of spacing groove 210 and the lateral wall laminating of stopper 121, connecting cylinder 120 and aviation socket 200 all are equipped with prevents slow-witted mark 300, and when stopper 121 corresponds with the position of spacing groove 210, prevent that the position of slow-witted mark 300 corresponds, the operating personnel of being convenient for can discern the connecting cylinder 120 fast and the correct hookup location of aviation socket 200, prevent simultaneously that the inserting of dislocation from leading to pin 130 the problem of being damaged.
The limiting blocks 121 and the limiting grooves 210 are provided with multiple groups, the limiting grooves 210 are evenly arranged along the circular aviation socket 200, and the limiting blocks 121 correspond to the limiting grooves 210 one to one.
The two sets of the limiting blocks 121 and the limiting grooves 210 are optimal, and under a general condition, the two sets of the limiting blocks 121 and the limiting grooves 210 can meet the fixation of the aviation plug and the aviation socket 200.
The working principle of the embodiment is as follows:
the pin 130 corresponds to the pin 130 hole, the connecting cylinder 120 corresponds to the fool-proof mark 300 of the aviation socket 200, the aviation plug is inserted into the aviation socket 200, meanwhile, the limiting block 121 of the connecting cylinder 120 enters along the long edge of the L-shaped limiting groove 210, when the aviation plug is connected with the aviation socket 200, the limiting block 121 also reaches the bottom end of the long edge of the L-shaped limiting groove 210, then the connecting cylinder 120 is rotated, and the limiting block 121 is moved to the short edge of the L-shaped limiting groove 210 to fix the aviation plug and the aviation socket 200.
The embodiment 2 of the utility model relates to fig. 3 and shows, on embodiment 1's basis extending structure has been add on the connecting pipe, has deleted simultaneously and has prevented slow-witted mark 300, the aircraft carrier socket is equipped with pinhole 220, extending structure includes round pin post 123 and self-locking switch mechanism 124, round pin post 123 can realize pressing down fixedly through self-locking switch mechanism 124 cooperation, presses the effect of bounce again, distance between the central point of round pin post 123 and pinhole 220 central point equals the length of the spacing groove 210 hem (being the minor face of spacing groove 210) of L type, guarantees connecting cylinder 120 swivelling joint back, round pin post 123 and pinhole 220 central line are located same straight line, owing to add extending structure, operating personnel can refer to the position of round pin post 123 and pinhole 220, so can delete and prevent slow-witted mark 300.
The working principle of the embodiment is as follows:
on the basis of the working principle of embodiment 1, the connecting cylinder 120 is rotated, the limiting block 121 is moved to the short side of the L-shaped limiting groove 210 to fix the aviation plug and the aviation socket 200, the pin 123 is pressed down, the pin 123 is fixed in the pin hole 220, the phenomenon that the connection pipe rotates reversely after rotation causes disconnection between the aviation plug and the aviation socket 200, and the connection stability between the aviation plug and the aviation socket 200 is improved.
Finally, it should be noted that: the above-mentioned embodiments are only specific embodiments of the present invention, and are not intended to limit the technical solutions of the present invention, and the protection scope of the present invention is not limited thereto, although the present invention is described in detail with reference to the foregoing embodiments, those skilled in the art should understand that: those skilled in the art can still modify or easily conceive of changes in the technical solutions described in the foregoing embodiments or make equivalent substitutions for some technical features within the technical scope of the present disclosure; such modifications, changes or substitutions do not substantially depart from the spirit and scope of the embodiments of the present invention, and are intended to be included within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (6)
1. An aviation plug assembly applied to power distribution control equipment, comprising:
the aviation plug comprises a base, pins and a connecting cylinder, the pins are fixedly connected with the base, the connecting cylinder is sleeved on the base, the connecting cylinder can rotate around the base, and the inner wall of the connecting cylinder is provided with a limiting block;
the aviation socket is provided with a pin hole and a limiting groove, the pin hole corresponds to a pin, the limiting groove is L-shaped, and the side wall of the limiting groove is attached to the side wall of the limiting block.
2. The aviation plug assembly applied to power distribution control equipment according to claim 1, wherein: the limiting blocks and the limiting grooves are provided with multiple groups.
3. The aviation plug assembly applied to the power distribution control equipment in claim 2, wherein: two sets of limiting blocks and limiting grooves are arranged.
4. An aviation plug assembly applied to power distribution control equipment according to claim 3, wherein: the connecting cylinder is provided with a telescopic structure, the aviation socket is provided with a pin hole, and the telescopic structure is matched with the pin hole to fix the aviation plug and the aviation socket.
5. The aviation plug assembly applied to power distribution control equipment according to claim 4, wherein: the telescopic structure comprises a pin column and a self-locking switch mechanism, and the distance between the central point of the pin column and the central point of the pin hole is equal to the length of the L-shaped limit groove folded edge.
6. The aviation plug assembly applied to power distribution control equipment according to claim 5, wherein: the connecting cylinder and the aviation socket are both provided with fool-proof marks.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221156770.1U CN217405830U (en) | 2022-05-13 | 2022-05-13 | Aviation plug-in component applied to power distribution control equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221156770.1U CN217405830U (en) | 2022-05-13 | 2022-05-13 | Aviation plug-in component applied to power distribution control equipment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217405830U true CN217405830U (en) | 2022-09-09 |
Family
ID=83145132
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221156770.1U Expired - Fee Related CN217405830U (en) | 2022-05-13 | 2022-05-13 | Aviation plug-in component applied to power distribution control equipment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217405830U (en) |
-
2022
- 2022-05-13 CN CN202221156770.1U patent/CN217405830U/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 |
Granted publication date: 20220909 |
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| CF01 | Termination of patent right due to non-payment of annual fee |