Aviation plug inner core

Abstract

The utility model provides an aviation plug inner core, and relates to the technical field of connectors. Comprising a rubber core and PINs. The rubber core is provided with a plurality of through holes; the PIN needle is of a metal stamping circle wrapping structure, and a gap is formed in the PIN needle in the radial direction, so that the PIN needle forms a non-closed column shape. The support hardware sheet is provided with a plurality of easy-to-break ports, and the easy-to-break ports are connected with the tail ends of the PINs; the number of the PINs connected with each support hardware sheet is the same as the number of the through holes in each rubber core. When the PINs are arranged in the through holes in a penetrating mode, the PINs and the through holes are in interference fit, and the PINs are disconnected from the support hardware sheet through the easy-to-break openings. Through the improvement of the aviation plug inner core structure, the defects of the existing aviation plug inner core structure in the aspects of automatic pin insertion operation, split aging risk and connection stability are overcome, so that the production efficiency is improved, and the performance and reliability of products are improved.

Description

Technical Field

[0001] The utility model relates to the technical field of connectors, in particular to an aviation plug inner core. Background Art

[0002] As an important component of electrical connection, connectors are used in many electronic devices to facilitate the connection of wires between devices for power supply or transmission of data and signals.

[0003] As a kind of connector, aviation plug can also be called plug socket, referred to as aviation plug, which is widely used in various electrical circuits to connect or disconnect the circuit.

[0004] The current aviation plug core structure, refer to Fig. 9 As shown, the inner pin is generally a single loose PIN, and is a front-end pin, that is, the loose PIN is manually inserted into the rubber core for assembly, and it is impossible to realize the automatic pin insertion operation on the automatic machine, which is inefficient. Therefore, the utility model proposes an aviation plug inner core to at least partially solve the problems that may exist in the prior art. Utility Model Content

[0005] In order to overcome the above problems or at least partially solve the above problems, an embodiment of the utility model provides an aviation plug inner core.

[0006] The embodiment of the utility model is achieved as follows:

[0007] The embodiment of the present application provides an aviation plug inner core, including:

[0008] Plastic core and PIN needle;

[0009] The rubber core is provided with a plurality of perforations;

[0010] The PIN pin is a metal stamping round structure with radial gaps on it to form a non-closed column;

[0011] The bracket metal sheet is provided with a plurality of breakable openings, and the breakable openings are connected to the tail ends of the PIN pins; the number of PIN pins connected to each bracket metal sheet is the same as the number of perforations on each rubber core;

[0012] When the PIN needle is inserted into the through hole, the two are interference fit, wherein the PIN needle passes through the easy-to-break opening and is disconnected from the bracket hardware sheet.

[0013] In some embodiments of the present invention, the head end of the rubber core is radially provided with an anti-fool groove;

[0014] The diameter of the perforation at one side of the head end is smaller than the diameter of the end at the tail end, and the PIN is set accordingly.

[0015] In some embodiments of the present invention, a partition is provided between every two through holes at the tail end of the rubber core.

[0016] In some embodiments of the utility model, the perforations are provided with four, and the orthographic projection of the partition is a cross;

[0017] The length of the partition is the same as the length of the PIN needle exposed at the tail end.

[0018] In some embodiments of the present invention, a sealing groove is further provided on the tail end.

[0019] In some embodiments of the present invention, a protrusion is further provided in the middle of the PIN needle, one side of the protrusion is a slope, and the slope faces the head end of the rubber core.

[0020] In some embodiments of the present invention, the PIN needle is located at the head end of the rubber core and is further provided with a six-petal structure; the end of the six-petal structure is provided with an extension port having the same diameter as the head end.

[0021] In some embodiments of the present invention, the PIN needle is provided with an oblique groove at the tail end of the rubber core, and a blockage is provided at the position where the oblique groove and the PIN needle are connected.

[0022] In some embodiments of the present invention, the PIN needle is made of copper alloy.

[0023] The embodiment of the present application provides an aviation socket, in which the aviation plug inner core is provided.

[0024] Compared with the prior art, the embodiments of the present invention have at least the following advantages or beneficial effects:

[0025] Through the rubber core and the PIN needle; the rubber core is provided with a plurality of perforations; the PIN needle is a metal stamping and enveloping round structure, on which a radial gap is provided, so that it forms a non-closed column; the bracket hardware sheet is provided with a plurality of easy-to-break openings, and the easy-to-break openings are connected to the tail end of the PIN needle; the number of PIN needles connected to each of the bracket hardware sheets is the same as the number of perforations on each of the rubber cores; when the PIN needle is inserted into the perforations, the two are interference fit, wherein the PIN needle is disconnected from the bracket hardware sheet through the easy-to-break openings. By improving the inner core structure of the aviation plug, the defects of the existing inner core structure of the aviation plug in terms of automated pin insertion operation, petal aging risk and connection stability are solved, thereby improving production efficiency, as well as product performance and reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the technical solutions of the embodiments of the utility model, the adsorption diagrams required for use in the embodiments are briefly introduced below. It should be understood that the following adsorption diagrams only illustrate certain embodiments of the utility model and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related adsorption diagrams can be obtained based on these adsorption diagrams without creative work.

[0027] Figure 1 This is a three-dimensional structural diagram of an aviation plug inner core provided in one embodiment of the utility model;

[0028] Figure 2 This is a schematic diagram of a three-dimensional perspective structure of a rubber core of an aviation plug inner core provided in one embodiment of the utility model;

[0029] Figure 3 This is a schematic diagram of a three-dimensional cross-sectional structure of a rubber core of an aviation plug inner core provided in one embodiment of the utility model;

[0030] Figure 4 This is a schematic diagram of the PIN needle end surface structure of an aviation plug inner core provided in one embodiment of the utility model;

[0031] Figure 5 This is a schematic diagram of a continuous PIN needle structure provided in one embodiment of the utility model;

[0032] Figure 6 This is a schematic diagram of the structure of an aviation plug inner core provided in one embodiment of the utility model from a side view;

[0033] Figure 7 This is a schematic cross-sectional structure diagram of an aviation plug inner core provided in one embodiment of the utility model;

[0034] Figure 8 This is a schematic diagram of the structure of an aviation plug inner core provided in one embodiment of the utility model from a front view;

[0035] Fig. 9 It is a structural schematic diagram of the inner core of the aviation plug in the prior art.

[0036] In the figure: 101, rubber core; 102, head end; 103, tail end; 104, anti-fool groove; 105, perforation; 106, partition; 107, sealing groove; 201, PIN needle; 202, gap; 203, six-petal structure; 204, protrusion; 205, oblique groove; 206, plugging; 301, bracket hardware piece. DETAILED DESCRIPTION

[0037] In order to make the purpose, technical scheme and advantages of the embodiment of the utility model clearer, the technical scheme in the embodiment of the utility model will be clearly and completely described below in conjunction with the adsorption diagram in the embodiment of the utility model. Obviously, the described embodiment is a part of the embodiment of the utility model, not all of the embodiments. Generally, the components of the embodiment of the utility model described and shown in the adsorption diagram here can be arranged and designed in various different configurations.

[0038] In the following, some embodiments of the present application are described in detail in conjunction with the adsorption diagram. In the absence of conflict, the following embodiments and the features in the embodiments can be combined with each other.

[0039] Please refer to Figures 1 to 8 As shown, an embodiment of the utility model provides an aviation plug inner core, including: a rubber core 101 and a PIN needle 201; the rubber core 101 is provided with a plurality of through holes 105; the PIN needle 201 is a metal stamping and enclosing round structure, on which a gap 202 is radially provided, so that it forms a non-closed column; a bracket hardware sheet 301, on which a plurality of easy-to-break openings 302 are provided, and the easy-to-break openings 302 are connected to the tail ends of the PIN needles 201; the number of PIN needles 201 connected to each of the bracket hardware sheets 301 is the same as the number of through holes 105 on each of the rubber core 101; when the PIN needle 201 is inserted into the through hole 105, the two are interference fit, wherein the PIN needle 201 is disconnected from the bracket hardware sheet 301 through the easy-to-break openings 302.

[0040] In the present embodiment, the above-mentioned aviation plug inner core solves the problem of the traditional aviation plug inner core structure. The loose PINs are manually inserted into the rubber core for assembly, and the automated pin insertion operation cannot be realized on the automatic machine, resulting in low efficiency. Specifically, the tail end of the PIN pin 201 is connected to the PIN pin 201 by using the easy-to-break opening 302 provided on the bracket hardware sheet 301, so that the terminal PIN pin 201 can be directly assembled and inserted into the rubber core from the rear end jack of the rubber core in the automated equipment, so as to realize the pin insertion operation on the automated production operation machine. After being inserted into the above-mentioned rubber core 101, the above-mentioned PIN pin 201 is disconnected from the easy-to-break opening 302 of the above-mentioned bracket hardware sheet 301, thereby improving the production efficiency.

[0041] Secondly, the PIN pin 201 of the metal stamping and enclosing round structure is provided with a radial gap 202 to form a non-closed column. Since the metal itself has a certain elasticity, when the PIN pin 201 is inserted into the through hole 105 of the rubber core 101, the PIN pin 201 and the through hole 105 have an interference fit, which ensures the tightness between the PIN pin 201 and the rubber core 101, thereby improving the stability and reliability of the connection.

[0042] Next, an aviation plug inner core in this exemplary embodiment will be further described.

[0043] In the embodiments of this application, refer to Figures 1 to 8 As shown, the head end 102 of the rubber core 101 is radially provided with an anti-mock groove 104; the diameter of the through hole 105 located on one side of the head end 102 is smaller than the diameter of one end located at the tail end 103, and the PIN needle 201 is correspondingly arranged; thereby, it is convenient for the PIN needle 201 to be inserted into the through hole 105 from the tail end 103 of the above-mentioned rubber core 101 toward the head end 102 for assembly; since the above-mentioned PIN needle 201 is a metal stamping and enclosing round structure, a gap 202 is radially provided on it, so that it has a certain elasticity, so that the above-mentioned PIN needle 201 can have a certain elastic space, so that the above-mentioned PIN needle 201 can be stuck in the above-mentioned through hole 105; through the above-mentioned anti-mock groove 104, when the above-mentioned aviation plug inner core is assembled into an aviation socket for use, it can be easily aligned when docking, and it cannot be inserted when it is not aligned to the correct position, thereby preventing insertion into the wrong position.

[0044] In the embodiment of the present application, at the tail end 103 of the rubber core 101, a partition 106 is provided between every two of the through holes 105; through the partition 106 provided between the through holes 105, after the PIN needle 201 is assembled into the through hole 105, the tail end of the PIN needle 201 is isolated to prevent the PIN needle 201 from causing a short circuit when being connected to the wire.

[0045] In the embodiments of this application, refer to Figure 1 and Figure 2 As shown, there are four through holes 105, and the positive projection of the partition 106 is a cross shape; the length of the partition 106 is the same as the length of the PIN needle 201 exposed at the tail end 103; the above-mentioned through holes 105 are provided with four, so that the pin density will not be too large, ensuring that each PIN needle 201 has good insulation, and the above-mentioned partition is combined with the PIN needle 201 made of copper alloy, which can support a larger current.

[0046] In the embodiments of this application, refer to Figures 1 to 3 by Figure 5 and Figure 7 As shown, a sealing groove 107 is further provided on the tail end 103. When assembled into an aviation plug, an O-ring can be provided in the sealing groove 107 to ensure the airtightness between the rubber core 101 and the aviation socket housing.

[0047] In the embodiments of this application, refer to Figure 4As shown, a protrusion 204 is further provided in the middle of the PIN needle 201, and one side of the protrusion 204 is a slope, and the slope faces the head end 102 of the rubber core 101, so that the protrusion 204 is similar to a barb; when the above-mentioned PIN needle 201 is inserted into the through hole 105, the PIN needle 201 can be smoothly inserted because the slope faces the above-mentioned head end 102. After insertion, since the other side of the slope of the above-mentioned protrusion 204 is perpendicular to the PIN needle 201 itself or has an inward slope, when the above-mentioned PIN needle 201 is withdrawn from the through hole 105 from the rear end 103 in the reverse direction, the above-mentioned protrusion 204 can be similar to a barb to prevent it from withdrawing.

[0048] In the embodiment of the present application, the PIN needle 201 is located at the head end 102 of the rubber core 101 and is also provided with a six-petal structure 203; the end of the six-petal structure 203 is provided with an extension port with the same diameter as the head end 102. Through the above-mentioned extension port, when the male needle is inserted into the PIN needle 201, the above-mentioned six-petal structure 203 is prevented from being directly at the outermost side, which makes it easy for the petals to age, thereby making it easy for the electrical connection with the male needle to be unstable. At the same time, the six-petal structure 203 can have a contact area with the male needle, thereby enhancing the stability of the connection.

[0049] In the embodiment of the present application, the PIN pin 201 is provided with an oblique groove 205 at the tail end of the plastic core 101, and a plug 206 is provided at the position where the oblique groove 205 is connected to the PIN pin 201. This prevents the oblique groove 205 from flowing into the hollow of the PIN pin 201 when welding with the wire, thereby preventing the welding from being weak or consuming too much solder during welding, causing waste.

[0050] It should be noted that each embodiment in this specification is described in a progressive manner, and each embodiment focuses on the differences from other embodiments, and the same or similar parts between the various embodiments can be referred to each other. Although optional embodiments of the utility model embodiments have been described, once those skilled in the art know the basic creative concept, they can make additional changes and modifications to these embodiments. Therefore, the attached claims are intended to be interpreted as including optional embodiments and all changes and modifications that fall within the scope of the utility model embodiments.

[0051] Finally, it should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity from another entity, and do not necessarily require or imply any such actual relationship or order between these entities. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that an article or terminal device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such article or terminal device. In the absence of further restrictions, the elements defined by the sentence "including one..." do not exclude the existence of other identical elements in the article or terminal device including the elements.

[0052] The technical solution provided by the present invention is introduced in detail above. Specific examples are used in this article to illustrate the principle and implementation method of the present invention. At the same time, for those skilled in the art, according to the principle and implementation method of the present invention, there will be changes in the specific implementation method and application scope. In summary, the content of this specification should not be understood as a limitation on the present invention.

Claims

1. An aviation plug inner core, characterized in that: include: A plastic core (101) and a PIN needle (201); The rubber core (101) is provided with a plurality of through holes (105); The PIN pin (201) is a metal stamping round structure, on which a slit (202) is radially provided, so as to form a non-closed column; A bracket metal sheet (301) is provided with a plurality of breakable openings (302), wherein the breakable openings (302) are connected to the tail ends of the PIN pins (201); the number of PIN pins (201) connected to each bracket metal sheet (301) is the same as the number of perforations (105) on each rubber core (101); When the PIN needle (201) is inserted into the through hole (105), the two are interference-fitted, wherein the PIN needle (201) passes through the breakable opening (302) and is disconnected from the bracket hardware sheet (301).

2. The aviation plug inner core according to claim 1, characterized in that: The head end (102) of the rubber core (101) is radially provided with an anti-fool groove (104); The diameter of the through hole (105) located on one side of the head end (102) is smaller than the diameter of the end located on the tail end (103), and the PIN needle (201) is arranged accordingly.

3. The aviation plug inner core according to claim 1, characterized in that: At the tail end (103) of the rubber core (101), a partition (106) is provided between every two of the through holes (105).

4. The aviation plug inner core according to claim 3, characterized in that: There are four perforations (105), and the orthographic projection of the partition (106) is a cross; The length of the partition (106) is the same as the length of the PIN needle (201) exposed at the tail end (103).

5. The aviation plug inner core according to claim 3, characterized in that: The tail end (103) is also provided with a sealing groove (107).

6. The aviation plug inner core according to any one of claims 1 to 5, characterized in that: A protrusion (204) is also provided in the middle of the PIN needle (201), one side of the protrusion (204) is a slope, and the slope faces the head end (102) of the rubber core (101).

7. The aviation plug inner core according to any one of claims 1 to 5, characterized in that: The PIN needle (201) is located at the head end (102) of the rubber core (101) and is also provided with a six-petal structure (203); the end of the six-petal structure (203) is provided with an extension opening with the same caliber as the head end (102).

8. The aviation plug inner core according to claim 7, characterized in that: The PIN needle (201) is provided with an oblique groove (205) at the tail end of the rubber core (101), and a seal (206) is provided at the position where the oblique groove (205) and the PIN needle (201) are connected.

9. The aviation plug inner core according to claim 7, characterized in that: The PIN needle (201) is made of copper alloy.

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