Aviation electric connector

Abstract

The utility model discloses an aviation electric connector, and the connector comprises a first socket sleeve which is internally provided with a first plugging structure; a second insertion structure is arranged in the second socket sleeve; the connecting threaded sleeve is in threaded connection with the first socket sleeve; the limiting grooves are formed in the first socket sleeve and the second socket sleeve at intervals; the locking elastic pieces are arranged on the first socket sleeve and the second socket sleeve and located in the limiting grooves, and first clamping faces are arranged on the locking elastic pieces. The plug comprises a plug connector and a rotation limiting part, an expansion head is arranged on the rotation limiting part, a second clamping face is formed between the expansion head and the rotation limiting part, and after the rotation limiting part is inserted, the first clamping face on the locking elastic piece abuts against the second clamping face on the rotation limiting part, so that the reliability of connection between the plug and the first plug-in structure or the second plug-in structure is ensured; and the electric connector is prevented from loosening under the action of vibration generated by the operation of the aircraft.

Description

Technical Field

[0001] This application relates to the field of electrical connector technology, and in particular to an electrical connector for aviation applications. Background Technology

[0002] Electrical connectors are indispensable products for electrical connections or signal transmission between system or complete circuit units. With the rapid development of modern science and technology, electrical connectors are needed and used extensively in communications, computers, measurement and control, and various electronic devices. Reliability and safety are important indicators in the design and production of electrical connectors, and are of great significance for the stable operation of systems and equipment. To ensure the stable operation of systems, the requirements for the reliability of electrical connectors are becoming increasingly stringent.

[0003] In the existing technology, because aircraft are prone to vibration during operation, and vibration has a great impact on the connection reliability of electrical connectors, it can easily lead to poor contact between the electrical connector and the plug, or even cause the connection between the electrical connector and the plug to fail.

[0004] Therefore, it is necessary to propose an aviation electrical connector to enhance its reliability, which has become an important technical problem that urgently needs to be solved. Utility Model Content

[0005] This application provides an electrical connector for aviation, which aims to solve the problem in the prior art that the vibration that aircraft easily generates during operation has a significant impact on the connection reliability of electrical connectors, easily leading to poor contact between the electrical connector and the plug, or even connection failure between the electrical connector and the plug.

[0006] To achieve the above objectives, this application proposes an aviation electrical connector, comprising: a first socket sleeve, wherein a first insertion structure is provided inside the first socket sleeve; a second socket sleeve, wherein a second insertion structure is provided inside the second socket sleeve; a connecting threaded sleeve, wherein the connecting threaded sleeve is screwed onto the first socket sleeve; a limiting groove, wherein both the first socket sleeve and the second socket sleeve are provided with limiting grooves at intervals; and a locking spring, wherein the locking spring is disposed on the first socket sleeve and the second socket sleeve and is located within the limiting groove, and the locking spring is provided with a first snap-fit ​​surface.

[0007] In some embodiments, the device further includes: an annular groove disposed in the second socket sleeve; and a limiting retaining ring disposed in the annular groove and abutting against the connecting threaded sleeve.

[0008] In some embodiments, it further includes: a plurality of first rotation limiting teeth, and the ends of the first socket sleeve and the second socket sleeve are each provided with a plurality of first rotation limiting teeth at intervals.

[0009] In some embodiments, the first snap-fit ​​surface is an inclined surface.

[0010] In some embodiments, it further includes: knurling, the knurling being disposed on the outer peripheral surface of the connecting threaded sleeve.

[0011] In some embodiments, the device further includes: a mounting platform disposed on the first socket sleeve, the mounting platform having mounting holes.

[0012] This application proposes an aviation electrical connector, comprising: a first socket sleeve, wherein a first insertion structure is provided inside the first socket sleeve; a second socket sleeve, wherein a second insertion structure is provided inside the second socket sleeve; a connecting screw sleeve, wherein the connecting screw sleeve is screwed onto the first socket sleeve; a limiting groove, wherein both the first socket sleeve and the second socket sleeve are provided with limiting grooves at intervals; and a locking spring, wherein the locking spring is disposed on the first socket sleeve and the second socket sleeve and is located within the limiting groove, and the locking spring is provided with a first snap-fit ​​surface. In the use of aviation electrical connectors, special plugs are required. These plugs include a connector that inserts into a first or second mating structure, and a limiting part that restricts the plug's angle. When the connector is inserted into the first or second mating structure, the limiting part simultaneously inserts into a limiting groove to restrict the angle of the plug relative to the first or second socket sleeve. The limiting part has an enlarged head, forming a second engaging surface with the limiting part. During insertion, the enlarged head pushes open a locking spring, and after the enlarged head passes the locking spring, the locking spring rebounds, and the first engaging surface on the locking spring abuts against the second engaging surface on the limiting part. Through these steps, after the plug is inserted into the first or second socket sleeve, the locking spring abuts against the enlarged head of the limiting part, thereby locking the connection between the plug and the first or second mating structure. This ensures the reliability of the connection and prevents the electrical connector from loosening due to vibrations generated during aircraft operation. Attached Figure Description

[0013] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort, wherein:

[0014] Figure 1 This is a three-dimensional structural diagram of an aviation electrical connector according to an embodiment of this application;

[0015] Figure 2 This is a magnified view of part A in section 1;

[0016] Figure 3 This is a cross-sectional view of an aviation electrical connector according to an embodiment of this application;

[0017] Figure 4 This is a magnified view of part B in section 3;

[0018] Figure 5 This is a schematic diagram of the connection between an aviation electrical connector and a plug in one embodiment of this application.

[0019] In the figure: First socket sleeve 1, connecting threaded sleeve 2, straight knurled 3, limiting retaining ring 5, mounting platform 6, first rotation limiting tooth 7, limiting groove 8, locking spring 9, first locking surface 91, ring groove 10, first insertion structure 11, rotation limiting part 12, enlarged head 121, tapered part 122, second socket sleeve 13. Detailed Implementation

[0020] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of the embodiments. Based on the embodiments of this application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of this application.

[0021] It should be noted that all directional indicators (such as up, down, left, right, front, back, etc.) in the embodiments of this application are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indicator will also change accordingly.

[0022] It should also be noted that when a component is described as "fixed to" or "set on" another component, it can be directly on the other component or there may be an intervening component present. When a component is described as "connected to" another component, it can be directly connected to the other component or there may be an intervening component present.

[0023] Furthermore, the use of terms such as "first" and "second" in this application is for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. Additionally, the technical solutions of the various embodiments can be combined with each other, but only on the basis of being achievable by those skilled in the art. When the combination of technical solutions is contradictory or impossible to implement, such a combination of technical solutions should be considered non-existent and not within the scope of protection claimed in this application.

[0024] See Figure 1 , Figure 2 , Figure 3 , Figure 4 and Figure 5As shown, this application proposes an aviation electrical connector, comprising: a first socket sleeve 1, wherein a first insertion structure 11 is provided inside the first socket sleeve 1; a second socket sleeve 13, wherein a second insertion structure is provided inside the second socket sleeve 13; a connecting screw sleeve 2, wherein the connecting screw sleeve 2 is screwed to the first socket sleeve 1; a limiting groove 8, wherein the first socket sleeve 1 and the second socket sleeve 13 are provided with limiting grooves 8 at intervals; and a locking spring 9, wherein the locking spring 9 is disposed in the first socket sleeve 1 and the second socket sleeve 13 and is located in the limiting groove 8, and the locking spring 9 is provided with a first snap-fit ​​surface 91.

[0025] The first socket sleeve 1 is the structural basis of an aviation electrical connector, and other structures in the aviation electrical connector are directly or indirectly mounted on the first socket sleeve 1. The first insertion structure 11 on the first socket sleeve 1 is used for inserting one plug, and the second insertion structure on the second socket sleeve 13 is used for inserting another plug. The connecting threaded sleeve 2 is used to install the second socket sleeve 13 onto the first socket sleeve 1. The connecting threaded sleeve 2 has an internal thread, and the first socket sleeve 1 has an external thread that matches the internal thread of the connecting threaded sleeve 2. In addition to the connector that inserts into the first or second plug structure, the plug also has a limiting part 12 for limiting the angle of the plug. The limiting part 12 is inserted into the limiting groove 8, thereby limiting the angle of the plug relative to the first or second socket sleeve 13. The limiting part 12 is provided with an enlarged head 121, and a second locking surface is formed between the enlarged head 121 and the limiting part 12. During the insertion of the limiting part 12, the enlarged head 121 pushes open the locking spring 9, and after the enlarged head 121 passes the locking spring 9, the locking spring 9 rebounds, and the first locking surface 91 on the locking spring 9 abuts against the second locking surface on the limiting part 12.

[0026] Specifically, in the use of aviation electrical connectors, special plugs are required. These plugs include a connector that inserts into a first or second mating structure 11, and a limiting portion 12 that restricts the plug angle. When the connector is inserted into the first or second mating structure, the limiting portion 12 simultaneously inserts into the limiting groove 8 to limit the angle of the plug relative to the first or second socket sleeve 13. The limiting portion 12 is equipped with an enlarged head 121, forming a second locking surface with the limiting portion 12. During the insertion of the limiting portion 12, the enlarged head 121... After the locking spring 9 is released and the expanding head 121 passes over the locking spring 9, the locking spring 9 rebounds, and the first snap-fit ​​surface 91 on the locking spring 9 abuts against the second snap-fit ​​surface on the rotation limiting part 12. Through the above steps, after the plug is inserted into the first socket sleeve 1 or the second socket sleeve 13, the locking spring 9 abuts against the expanding head 121 of the rotation limiting part 12, thereby locking the connection state between the plug and the first plug-in structure 11 or the second plug-in structure, ensuring the reliability of the connection between the plug and the first plug-in structure 11 or the second plug-in structure, and preventing the electrical connector from loosening under the vibration generated by the operation of the aircraft.

[0027] Preferably, the end of the enlarged head 121 away from the rotation limit part 12 is provided with a tapered part 122. The tapered part 122 allows the enlarged head 121 to smoothly extend into the gap between the locking spring 9 and the limiting groove 8, thereby pushing the locking spring 9 open.

[0028] See Figure 1 , Figure 2 and Figure 3 As shown, in some embodiments, it further includes: an annular groove 10, which is disposed in the second socket sleeve 13. The annular groove 10 is an annular groove disposed in the second socket sleeve 13, and its cross-sectional shape is rectangular; a limiting retaining ring 5, which is disposed in the annular groove 10 and abuts against the connecting threaded sleeve 2. The limiting retaining ring 5 is a C-shaped retaining ring with an opening at one end. The limiting retaining ring 5 can deform to increase its inner diameter, thereby fitting onto the annular groove 10 of the second socket sleeve 13. After fitting onto the annular groove 10, the limiting retaining ring 5 returns to its original shape under the action of its own elasticity, thereby locking into the annular groove 10.

[0029] In this embodiment, a limiting protrusion is provided inside the second socket sleeve 13. The limiting protrusion is used to abut against the connecting threaded sleeve 2, but the connecting threaded sleeve 2 can rotate relative to the limiting protrusion. When the second socket sleeve 13 is connected to the first socket sleeve 1, the connecting threaded sleeve 2 is put on the second socket sleeve 13 and abuts against the limiting protrusion. Then, the connecting threaded sleeve 2 is screwed onto the outer circumferential surface of the first socket sleeve 1. Finally, the limiting retaining ring 5 is installed on the annular groove 10, so that both the limiting retaining ring 5 and the limiting protrusion abut against the connecting threaded sleeve 2, thus completing the installation of the second socket sleeve 13.

[0030] See Figure 1 and Figure 2 As shown, in some embodiments, it further includes: a plurality of first rotation limiting teeth 7, and the ends of the first socket sleeve 1 and the second socket sleeve 13 are each provided with a plurality of first rotation limiting teeth 7 at intervals. The plug is provided with second rotation limiting teeth adapted to the first rotation limiting teeth 7. When the first rotation limiting teeth 7 and the second rotation limiting teeth are engaged, the rotation of the plug can be effectively limited, and it is beneficial to increase the contact surface between the plug and the first socket sleeve 1 or the second socket sleeve 13, thereby increasing the stability of the connection between the two.

[0031] In some embodiments, the first snap-fit ​​surface 91 is an inclined surface, and the angle formed between the first snap-fit ​​surface 91 and the locking spring 9 is an acute angle. Through the above structural design, when the plug tends to be pulled out of the first socket sleeve 1 or the second socket sleeve 13, the snap-fit ​​between the locking spring 9 and the rotation limiting part 12 becomes tighter and tighter, further ensuring the reliability of the connection between the plug and the first socket sleeve 1 or the second socket sleeve 13.

[0032] See Figure 1 As shown, in some embodiments, it further includes: knurled surface 3, which is disposed on the outer peripheral surface of the connecting threaded sleeve 2. The knurled surface 3 makes it easier for workers to tighten the connecting threaded sleeve 2.

[0033] See Figure 1 As shown, in some embodiments, it further includes: a mounting platform 6, which is disposed on the first socket sleeve 1, and the mounting platform 6 is provided with mounting holes. The design of the mounting platform 6 and the mounting holes on the mounting platform 6 is conducive to installing the first socket sleeve 1 onto external components, thereby fixing the first socket sleeve 1 and ensuring its stability on the aircraft.

[0034] The above description is only a part or preferred embodiment of this application. Neither the text nor the drawings should limit the scope of protection of this application. All equivalent structural transformations made using the content of this application's specification and drawings under the overall concept of this application, or direct / indirect applications in other related technical fields, are included within the scope of protection of this application.

Claims

1. An electrical connector for use in aviation, characterized in that, The utility model relates to a first socket sleeve (1) is provided with first plug structure (11) in, second socket sleeve (13) is provided with second plug structure in, connecting screw sleeve (2) is screwed in first socket sleeve (1), spacing is provided with limit groove (8) to first socket sleeve (1) and second socket sleeve (13), locking elastic sheet (9) is arranged in first socket sleeve (1) and second socket sleeve (13), and is located in limit groove (8), and first clamping surface (91) is provided on locking elastic sheet (9). Further comprising: Annular groove (10) is arranged in second socket sleeve (13), limit baffle ring (5) is arranged in annular groove (10) and abuts against connecting screw sleeve (2). Further comprising: A plurality of first rotation limiting teeth (7) are arranged at the ends of the first socket sleeve (1) and the second socket sleeve (13). The first clamping surface (91) is an inclined surface.

2. An electrical connector for use in an aircraft as claimed in claim 1, wherein Further comprising: Straight grain knurl (3) is arranged on the outer circumferential surface of the connecting screw sleeve (2). Further comprising:

3. An electrical connector for use in an aircraft as defined in claim 1, wherein Mounting table (6) is arranged on the first socket sleeve (1), and mounting holes are arranged on the mounting table (6). ​ 4. An electrical connector for use in an aircraft as defined in claim 1, wherein ​ 5. An electrical connector for use in an aircraft as defined in claim 1, wherein, ​ ​ 6. An electrical connector for use in an aircraft as claimed in claim 5, wherein ​ ​

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