An aviation socket with a protection function

Abstract

The application relates to the technical field of aviation sockets, and discloses an aviation socket with a protection function, which comprises a plug, a socket and a locking piece. The plug comprises a first shell and a first plug core arranged in the first shell. The first plug core is arranged in the first shell through plug-in connection of one end of the first shell. A sealing piece is arranged at the other end of the first shell. A sliding groove is arranged on the outer side wall of the first shell along the circumference of the first shell. The locking piece is arranged in the sliding groove in a sliding mode. When the plug is plugged into the socket, the locking piece is used for locking connection between the plug and the socket. Screws for fixing the first plug core are arranged on the side wall of the sliding groove. An anti-impact assembly is arranged on the inner side wall of the first shell and away from the first plug core. The anti-impact assembly is arranged in the first shell. The anti-impact assembly is used for buffering the impact force on the first shell, so that the first shell is buffered and protected, the components in the first shell are prevented from being damaged, and the service life of the aviation socket is prolonged.

Description

Technical Field

[0001] This application relates to the field of aviation socket technology, and more specifically, to an aviation socket with protective functions. Background Technology

[0002] Aviation sockets, also known as aviation plugs or connectors, are industrial-grade electrical connection components with high reliability and high protection performance. Due to their excellent stability, anti-interference and environmental adaptability, they are widely used in scenarios with high requirements for electrical connection reliability.

[0003] Traditional aviation sockets generally consist of a socket and a plug. The connection or disconnection of the circuit is achieved by plugging and unplugging the plug and socket. To prevent the plug and socket from falling out during insertion, existing technology uses a rotating cylinder threaded connection between the plug and socket to lock them in place, thus ensuring the long-term use of the aviation socket. However, in actual use, the plug and rotating cylinder lack protection, making them susceptible to external impacts during connection. The socket relies solely on the structure of the plug shell and rotating cylinder to resist impacts, making it easy for impacts to damage the plug and rotating cylinder, thereby affecting the service life of the aviation socket. Utility Model Content

[0004] The purpose of this application is to provide an aviation socket with protective functions to solve the problems mentioned in the background art.

[0005] To achieve the above objectives, this application provides the following technical solution:

[0006] An aviation socket with protective function includes a plug, a socket, and a locking member. The plug includes a first housing and a first plug inside the first housing. The first plug is inserted into the first housing through one end and installed inside the first housing. A sealing member is provided at the other end of the first housing. A sliding groove is provided on the outer side wall of the first housing along its circumference. The locking member is slidably disposed in the sliding groove. When the plug is inserted into the socket, the locking member locks the connection between the plug and the socket. A screw for fixing the first plug is provided on the side wall of the sliding groove. An impact-resistant component is provided on the inner side wall of the first housing away from the first plug.

[0007] Furthermore, the impact-resistant component includes a first energy-absorbing cavity arranged circumferentially along the first housing, the opening of the first energy-absorbing cavity being disposed facing one end of the first housing, and a plugging ring being threadedly connected to the opening end of the first energy-absorbing cavity.

[0008] Furthermore, the outer wall of the first insert has an annular groove located on both sides of the screw along its circumference, and a sealing ring is embedded in the annular groove.

[0009] Furthermore, the locking component includes a rotating cylinder fitted over the first housing, with a retaining ring at one end of the rotating cylinder that slides within a sliding groove, and an internal thread at the other end of the rotating cylinder.

[0010] Furthermore, a second energy-absorbing cavity is provided circumferentially inside the side wall of the rotating cylinder.

[0011] Furthermore, the length of the rotating cylinder is shorter than the length of the sliding groove, so as to avoid the screw when the rotating cylinder slides to the end of the sliding groove near the seal.

[0012] Furthermore, a semi-cylindrical base is provided at the other end of the first housing, with the two sides of the base protruding outward to form a bottom protrusion; the sealing element includes a top seat that is spliced ​​with the base to form a cylinder, with the two sides of the top seat protruding outward to form a top protrusion that cooperates with the bottom protrusion.

[0013] Furthermore, a bottom protrusion ring is formed by protruding outward along its circumference on the inner side wall of the base, and a top protrusion ring is formed by protruding outward along its circumference on the inner wall of the top seat to cooperate with the bottom protrusion ring.

[0014] Compared with the prior art, the beneficial effects of this application are:

[0015] 1. In this application, by providing an impact-resistant component inside the first housing, the impact-resistant component buffers the impact force received on the first housing, thereby providing buffer protection for the first housing to prevent damage to the internal components, thus providing buffer protection for the plug and improving the service life of the aviation socket.

[0016] 2. In this application, by setting a second energy-absorbing chamber inside the rotating cylinder, the impact force on the rotating cylinder is buffered by the second energy-absorbing chamber to prevent damage to the plug and socket connection points, thereby improving the service life of the aviation socket. Attached Figure Description

[0017] Figure 1 This is a structural schematic diagram of an aviation socket with protective function according to this application.

[0018] Figure 2 This is a schematic diagram of the plug structure when the locking element avoids the screw in this application.

[0019] Figure 3 This is one of the exploded structural diagrams of the plug in this application.

[0020] Figure 4 This is the second schematic diagram of the plug structure in this application.

[0021] Figure 5 This is a half-sectional view of the plug in this application.

[0022] Figure 6This is a half-sectional view of the first outer shell in this application.

[0023] The meanings of the labels in the diagram are as follows:

[0024] 10. Plug; 11. First outer shell; 12. First insert; 111. Sliding groove; 112. Base; 1121. Bottom protrusion; 1122. Top protrusion; 20. Socket; 21. Second outer shell; 22. Pin; 30. Locking element; 40. Screw; 50. Top seat; 300. Socket plastic core seat; 301. Socket element; 310. Sealing ring; 321. Bottom protrusion ring; 331. Top protrusion ring; 401. First mounting hole; 410. Rotating cylinder; 501. First energy absorption chamber; 510. Plug ring; 511. Retaining ring; 512. Second energy absorption chamber. Detailed Implementation

[0025] To further understand the content of this application, a detailed description of this application will be provided in conjunction with the accompanying drawings and embodiments. It should be understood that the embodiments are merely illustrative and not intended to limit the scope of this application.

[0026] The following is in conjunction with the appendix Figures 1-6 This embodiment will be described in further detail.

[0027] like Figure 1 As shown, an aviation socket with protective function in this embodiment includes a plug 10, a socket 20 and a locking member 30. The locking member 30 is used to lock the plug 10 into the socket 20 to improve the anti-detachment effect of the two.

[0028] Combination Figure 3 and Figure 4 As shown, the plug 10 includes a first housing 11 and a first insert 12 disposed within the first housing 11, and the socket 20 includes a second housing 21 and a second insert disposed within the second housing 21. The first insert 12 includes a socket plastic core seat 300, and the socket plastic core seat 300 is provided with a plurality of first mounting holes 401 for mounting socket components 301. Specifically, in this embodiment, the number of first mounting holes 401 is set to 4, and each first mounting hole 401 is provided with a socket component 301. The second insert includes a pin plastic core seat, and the pin plastic core seat is provided with a plurality of second mounting holes for mounting pin components 22. The number of pin components 22 corresponds to the number of socket components 301. Therefore, when the plug 10 is plugged into the socket 20, the pin component 22 is plugged into the corresponding first mounting hole 401, and an electrical connection is made between the pin component 22 and the socket component 301, thereby realizing the electrical connection between the plug 10 and the socket 20.

[0029] The first plug 12 is inserted into the first housing 11 through one end. The other end of the first housing 11 is provided with a sealing element. The sealing element is used to seal the other end of the first housing 11 when the wire is connected to the first plug 12, so as to improve the waterproof and dustproof effect of the plug 10.

[0030] A sliding groove 111 is provided on the outer side wall of the first outer casing 11 along its circumference. The locking member 30 is slidably disposed in the sliding groove 111. When the plug 10 is plugged into the socket 20, the locking member 30 locks the plug 10 and the socket 20 together. A screw 40 is provided on the side wall of the sliding groove 111. When the first insert 12 is inserted into the first outer casing 11, the screw 40 passes through the first outer casing 11 and is threaded into the first insert 12, so as to realize the detachable installation of the first insert 12 in the first outer casing 11. Specifically, a through hole is provided on the side wall of the sliding groove 111 near the end of the first outer casing 11. A threaded hole is provided on the outer side wall of the insert plastic core seat 300 corresponding to the through hole. Thus, when the screw 40 is threaded into the threaded hole through the through hole, the first insert 12 inserted into the first outer casing 11 can be fixed.

[0031] In this embodiment, in order to improve the sealing effect at the connection of the screw 40, an annular groove is provided on the outer side wall of the first insert 12 along its circumference, located on both sides of the screw 40. That is, the annular groove is provided on the outer side wall of the insert plastic core seat 300. A sealing ring 310 is embedded in the annular groove. The sealing ring 310 is made of rubber. The sealing ring 310 abuts against the inner side wall of the first outer shell 11 to improve the sealing performance of the first insert 12 in the first outer shell 11.

[0032] An impact-resistant component is provided on the inner side wall of the first housing 11 away from the first plug 12. The impact-resistant component buffers the impact force on the first housing 11, so as to protect the first housing 11 from damage to the internal components and thus improve the service life of the aviation socket.

[0033] Combination Figure 5 and Figure 6As shown, in this embodiment, the first outer shell 11 is made of plastic to improve the corrosion resistance of the plug 10. The impact-resistant component includes a first energy-absorbing cavity 501 arranged circumferentially along the first outer shell 11. The opening of the first energy-absorbing cavity 501 faces one end of the first outer shell 11. A plugging ring 510 is threadedly connected to the opening end of the first energy-absorbing cavity 501. In actual use, when the plugging ring 510 is installed at the opening of the first energy-absorbing cavity 501, the first energy-absorbing cavity 501 is formed, and the side wall of the plugging ring 510 can support the side wall of the sliding groove 111 to improve the strength of the first outer shell 11. At the same time, the detachable installation of the plugging ring 510 allows the opening of the first energy-absorbing cavity 501 to be opened and closed. In actual use, sound-absorbing material (such as polyurethane foam) or cushioning material (such as polyurethane foam) can be filled into the first energy-absorbing cavity 501, thereby giving the first outer shell 11 the effect of silencing the sound generated by the impact or improving the effect of cushioning the impact force received by the first outer shell 11.

[0034] In this embodiment, the locking member 30 includes a rotating cylinder 410 fitted over the first outer shell 11. One end of the rotating cylinder 410 is provided with a retaining ring 511 that slides within the sliding groove 111. Both the rotating cylinder 410 and the retaining ring 511 are made of plastic. The retaining ring 511 and the side walls at both ends of the sliding groove 111 limit the rotation of the rotating cylinder 410 from detaching from the first outer shell 11. The rotating cylinder 410 has an internal thread at the other end, and the outer wall of the second outer shell 21 has an external thread. Therefore, when the plug 10 is inserted into the socket 20, the rotating cylinder 410 slides along the sliding groove 111 and rotates. The engagement of the external and internal threads enables the rotating cylinder 410 to be threaded onto the second outer shell 21 until the retaining ring 511 abuts against the side wall of the sliding groove 111 near the socket 20, thereby locking the plug 10 and socket 20 that are inserted into each other.

[0035] Specifically, in order to facilitate the user to rotate the rotating cylinder 410, friction textures (not shown in the figure) are provided on the outer wall of the rotating cylinder 410.

[0036] In order to provide buffer protection for the insertion positions of the plug 10 and the socket 20, in this embodiment, a second energy-absorbing cavity 512 is provided in the circumferential direction of the inner side wall of the rotating cylinder 410. The second energy-absorbing cavity 512 is used to buffer the impact force on the rotating cylinder 410, so as to prevent damage to the insertion positions of the plug 10 and the socket 20, thereby improving the service life of the aviation socket.

[0037] Combination Figure 2As shown, in actual use, the length of the rotating cylinder 410 is shorter than the length of the sliding groove 111. When the rotating cylinder 410 slides to the sliding groove 111 near the end of the seal, it avoids the screw 40, thereby allowing the screw 40 to be installed and removed at the through hole and the threaded hole, so as to install and remove the first insert 12 in the first housing 11.

[0038] In practical use, the wire is inserted through the other end of the first housing 11 and the wire core is soldered to the corresponding socket 301. At this time, the first plug 12 is installed in the first housing 11 to realize the electrical connection between the wire and the plug 10. In order to improve the sealing at the wire insertion point, in this embodiment, a semi-cylindrical base 112 is provided at the other end of the first housing 11. The base 112 is integrally formed on the other end of the first housing 11, and the two sides of the base 112 protrude outward to form bottom protrusions 1121.

[0039] The sealing element includes a top seat 50 that is spliced ​​with the base 112 to form a cylinder. The two sides of the top seat 50 protrude outward to form a top outward protrusion 1122 that mates with the bottom outward protrusion 1121. There are corresponding mounting holes between the bottom outward protrusion 1121 and the top outward protrusion 1122. The mounting holes are connected by bolts to achieve the fixed installation of the top seat 50 on the base 112.

[0040] In order to improve the sealing of the top seat 50, the outer wall of the top seat 50 is provided with a sealing protrusion that fits against the side wall of the base 112.

[0041] The inner wall of the base 112 protrudes outward along its circumference to form a bottom protrusion ring 321, and the inner wall of the top seat 50 protrudes outward along its circumference to form a top protrusion ring 331 that cooperates with the bottom protrusion ring 321. When the top seat 50 is installed on the base 112, the bottom protrusion ring 321 and the top protrusion ring 331 cooperate to form a protrusion ring strip that compresses the outer wall of the wire, so as to improve the waterproof and dustproof effect of the connection.

[0042] In summary, the above description is only a preferred embodiment of this application. All equivalent changes and modifications made within the scope of this application should be covered by this application.

Claims

1. An aviation socket with protection function, comprising a plug (10), a socket (20) and a locking member (30), characterized in that: The plug (10) comprises a first shell (11) and a first plug core (12) arranged in the first shell (11), the first plug core (12) is arranged in the first shell (11) through plug-in installation of one end of the first shell (11), a sealing element is arranged at the other end of the first shell (11), a sliding groove (111) is arranged on the outer side wall of the first shell (11) along the circumference thereof, a locking element (30) is arranged in the sliding groove (111) in a sliding manner, when the plug (10) is plugged into the socket (20), the locking element (30) is used for locking connection between the plug (10) and the socket (20), a screw (40) for fixing the first plug core (12) is arranged on the side wall of the sliding groove (111), and an anti-impact assembly is arranged on the inner side wall of the first shell (11) away from the first plug core (12).

2. The aircraft socket with protection function according to claim 1, characterized in that: The anti-impact assembly comprises a first energy absorption cavity (501) arranged along the circumference of the first shell (11), the opening of the first energy absorption cavity (501) is arranged towards one end of the first shell (11), and a plug ring (510) is threadedly connected to the opening end of the first energy absorption cavity (501).

3. The aircraft socket with protection function according to claim 1, characterized in that: An annular groove is arranged on the outer side wall of the first plug core (12) along the circumference thereof and located at both sides of the screw (40), and a sealing ring (310) is embedded in the annular groove.

4. The aircraft socket with protection function according to claim 1, characterized in that: The locking element (30) comprises a rotating cylinder (410) sleeved on the outside of the first shell (11), a blocking ring portion (511) is arranged at one end of the rotating cylinder (410) and arranged in the sliding groove (111) in a sliding manner, and an internal thread is arranged in the rotating cylinder (410) and located at the other end.

5. The aircraft socket with protection function according to claim 4, characterized in that: A second energy absorption cavity (512) is arranged on the side wall of the rotating cylinder (410) along the circumference thereof.

6. The aircraft socket with protection function according to claim 5, characterized in that: The length of the rotating cylinder (410) is shorter than the length of the sliding groove (111), and the rotating cylinder (410) is avoided from the screw (40) when the rotating cylinder (410) is slid to the end of the sliding groove (111) close to the sealing element.

7. The aircraft socket with protection function according to claim 1, characterized in that: A base (112) in the shape of a semi-cylinder is arranged at the other end of the first shell (11), the two sides of the base (112) are outwardly protruded to form a bottom outer protruding portion (1121); the sealing element comprises a top base (50) which is spliced with the base (112) to form a cylinder, the two sides of the top base (50) are outwardly protruded to form a top outer protruding portion (1122) matched with the bottom outer protruding portion (1121).

8. The aircraft socket with protection function according to claim 7, characterized in that: A bottom protruding ring (321) is outwardly protruded on the inner side wall of the base (112) along the circumference thereof, and a top protruding ring (331) is outwardly protruded on the inner wall of the top base (50) along the circumference thereof and matched with the bottom protruding ring (321).

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