CN214100075U - Connection structure of aviation connector - Google Patents

Abstract

The application discloses a connecting structure of an aviation connector, which comprises an aviation male connector, wherein the aviation male connector is provided with a connecting end with an external thread, and the end surface of the connecting end is provided with a jack; the aviation female head comprises a pipe body, a screw cap sleeved on the outer wall of the pipe body and a plug-in connector extending out of one end of the pipe body; a first convex ring is formed on the outer wall of the other end of the pipe body; the nut is used for being in threaded connection with the external thread of the connecting end, the threaded end of the nut is a first end, and the second end of the nut faces the annular wall of the first convex ring; the plug connector crosses over the first end of the screw cap when the screw cap is not screwed, so as to be in plug fit with the jack to form electric connection; when the screw cap is inserted in place, the screw cap axially moves along the direction deviating from the first convex ring to be in threaded connection with the connecting end, and a gap is formed between the second end of the screw cap and the ring wall of the first convex ring; and the limiting piece is detachably embedded in the interval so as to limit the nut to rotate in opposite phases. By adopting the connecting structure, the stability of the threaded connection of the aviation connector is ensured.

Description

Connection structure of aviation connector

Technical Field

The application relates to the field of data lines, in particular to a connection structure of an aviation connector.

Background

The aviation connector can also be called a plug seat, is widely applied to various electric circuits, plays a role in connecting or disconnecting a circuit, and has obvious influence on the performance of the aviation connector due to the environment in the using, storing and transporting processes. For example, in the aviation connector data line for vehicle-mounted sound equipment, when a vehicle runs, the vehicle is influenced by vibration or bump, and how to ensure stable connection of the connectors is one of main consideration factors, the connection is generally carried out in a circular screw connector mode in the current market, but the connection cannot be automatically separated under the condition of vibration or bump, so that the application is developed.

SUMMERY OF THE UTILITY MODEL

The utility model provides an aim at overcomes the above-mentioned defect or the problem that exist among the background art, provides a connection structure of aviation connector, adopts this connection structure, guarantees the firm of aviation connector spiro union to avoid in the use, the nut leads to producing the risk of automatic back of a position by factors such as vibration.

In order to achieve the purpose, the following technical scheme is adopted:

connection structure of aviation joint, it includes: the aviation male head is provided with a connecting end with an external thread, and the end face of the connecting end is provided with a jack; the aviation female head comprises a pipe body, a screw cap sleeved on the outer wall of the pipe body and a plug-in connector extending out of one end of the pipe body; a first convex ring is formed on the outer wall of the other end of the pipe body; the nut is used for being in threaded connection with the external thread of the connecting end, the threaded end of the nut is a first end, and the second end of the nut faces the annular wall of the first convex ring; the plug connector crosses over the first end of the screw cap when the screw cap is not screwed, so as to be in plug fit with the jack to form electric connection; when the screw cap is inserted in place, the screw cap axially moves along the direction deviating from the first convex ring to be in threaded connection with the connecting end, and a gap is formed between the second end of the screw cap and the ring wall of the first convex ring; and the limiting piece is detachably embedded in the interval so as to limit the nut to rotate in opposite phases.

Furthermore, the limiting part is an elastic ring which is sleeved on the pipe body and axially limited in the gap.

Further, the diameter of the pipe body in the interval is larger than the inner diameter of the elastic ring.

Further, the axial thickness of the elastic ring is greater than the length of the gap.

Further, the section of the elastic ring is circular or elliptical.

Further, the aviation female head also comprises a rubber core; the rubber core is sleeved in the pipe body, one end of the rubber core extends out of the pipe body, and the part of the rubber core extending out of the pipe body forms the plug-in connector; the pipe body is provided with a butting surface so as to limit the second end of the nut to axially separate from the pipe body in the direction deviating from the first convex ring; the diameter of the first convex ring is larger than the aperture of the second end of the screw cap.

Further, the aperture of the second end of the nut is radially constricted; the outer wall of the pipe body close to the plug connector is provided with a second convex ring, the second convex ring is suitable for being sleeved in the screw cap, a gap exists between the outer wall of the second convex ring and the inner wall of the screw cap, the annular wall of the second convex ring facing the first convex ring forms the abutting surface, and the abutting surface abuts against the hole edge on the inner side of the second end.

Further, the aviation male head comprises a cylinder body and a third convex ring, the third convex ring is formed on the outer wall of the cylinder body so as to separate the outer wall of the cylinder body into a first section close to the opening of the cylinder body and a second section close to the bottom of the cylinder, and the first section is the connecting end.

Further, the cable fixing device also comprises a first cable and a second cable extending from the other end of the pipe body; a plurality of contact pins extending along the axial direction are arranged in the barrel, and one end of each contact pin penetrates out of the barrel bottom to be connected with a core wire corresponding to the first cable; glue the core be equipped with contact pin quantity the same and run through length direction's wear groove, each wear the inslot and be equipped with the inserted sheet, inserted sheet one end supplies the contact pin butt forms the electricity connect, the other end stretch out wear the groove in order to meet with the heart yearn of second cable.

Further, a first cable head is injection-molded on the second section and the periphery intersected with the first cable; a second cable head is formed on the periphery of the first convex ring intersected with the second cable in an injection molding mode; the inner diameter of the elastic ring is larger than the diameter of the second cable, and the elastic ring is sleeved on the second cable before the aviation male head and the aviation female head are not spliced.

Compared with the prior art, the scheme has the following beneficial effects:

1. in the application, the aviation female joint is provided with a pipe body for sleeving the nut, and the plug-in connector extending out of one end of the pipe body needs to go beyond the screw-in end of the nut, so that the plug-in connector can extend into the jack before the nut is not connected with the external thread, and the structure provides a abdicating stroke for plugging; when the aviation male head and the aviation female head are inserted in place, the screw cap is just connected with the external thread of the connecting end and can be in threaded connection; after the screw joint, an interval for the screw nut to retreat is inevitably formed between the second end of the screw nut and the annular wall of the first convex ring on the pipe body, so that the detachable screw joint of the aviation male head and the aviation female head is realized; through setting up the locating part, be for the reverse phase rotation of restriction nut, guarantee the firm of aviation joint spiro union to avoid in the use, the nut leads to producing the risk of automatic back of a position by factors such as vibration.

2. In this application, the locating part adopts the elastic ring, utilizes its elastic deformation's performance, can not only overlap on locating the body in the interval conveniently, and can also drop it from the body, plays demountable assembly, and the simple easy manufacturing of structure of elastic ring is with low costs in addition.

3. In this application, the body diameter in the interval is greater than the internal diameter of elastic ring, increases frictional force between the two, cup joints more firmly.

4. In this application, the axial thickness of elasticity circle describes the spaced length greatly, when it is located the interval, its both ends must push up respectively and hold in the second end and the first bulge loop of nut to form end face seal, reach dustproof, waterproof, antifog effect.

5. In this application, the cross-section of elasticity circle is circular or oval to the circular appearance of aviation male head and aviation female head is harmonious, and pleasing to the eye degree is better.

6. In the application, the abutting surface is arranged on the pipe body to limit the second end of the nut to axially separate from the pipe body in a direction deviating from the direction of the first convex ring; the diameter through first bulge loop is greater than the aperture of the second end of nut to the second end that the restriction nut deviates from the butt face direction axial and breaks away from the body, consequently, first bulge loop and butt face realize spacing the second end axial of nut on the body, but can make the nut along deviating from first bulge loop direction axial motion with the link spiro union, this structure avoids losing of spare part.

7. In this application, before public head of aviation and the female head of aviation do not form grafting, the elastic ring can overlap earlier and locate on the second cable, not only can avoid losing of spare part, and after aforementioned grafting, to its application of force, utilizes its elastic deformation ground to overlap earlier the outer wall at second cable head, and progressively orientation the interval direction removes, until it falls into in the interval, this mode simple operation.

Drawings

In order to more clearly illustrate the technical solution of the embodiments, the drawings needed to be used are briefly described as follows:

FIG. 1 is a schematic view of an embodiment of an aircraft joint being unconnected;

FIG. 2 is a schematic view of an embodiment of an aircraft joint connection;

FIG. 3 is a schematic structural diagram of an aircraft female head in an embodiment;

FIG. 4 is a schematic view of the second end of the nut being axially retained by the first collar according to one embodiment;

FIG. 5 is a schematic view of the second end of the nut being axially retained by the second collar according to one embodiment;

FIG. 6 is a cross-sectional view of FIG. 5;

FIG. 7 is a cross-sectional view of an exemplary embodiment of an aeronautical male;

FIG. 8 is a schematic structural diagram of an embodiment of a position limiting member;

FIG. 9 is a cross-sectional view A-A of FIG. 8;

FIG. 10 is a schematic illustration of an embodiment of an aviation male connector and an aviation female connector being plugged together;

FIG. 11 is a schematic partial cross-sectional view of FIG. 10;

FIG. 12 is a schematic view illustrating a bolt connection between an aviation male head and an aviation female head in the embodiment;

FIG. 13 is a schematic partial cross-sectional view of FIG. 12;

fig. 14 is a schematic diagram of the track of the step-by-step movement of the limiting member.

Description of the main reference numerals:

the aviation male head 1, the cylinder 11 and the connecting end 111; a third collar 12; a jack 13; a pin 14;

a first cable 2, a core wire 21, a first cable head 22;

the aircraft female head 3, the pipe body 31, the first convex ring 32, the second convex ring 33 and the abutting surface 331; a nut 34, a first end 341, a second end 342; plug 35, insert 351;

the second cable 4, the core wire 41, the second cable head 42;

and a stopper 5.

Detailed Description

In the claims and specification, unless otherwise specified the terms "first", "second" or "third", etc., are used to distinguish between different items and are not used to describe a particular order.

In the claims and specification, unless otherwise specified, the terms "central," "lateral," "longitudinal," "horizontal," "vertical," "top," "bottom," "inner," "outer," "upper," "lower," "front," "rear," "left," "right," "clockwise," "counterclockwise," and the like are used in the orientation and positional relationship indicated in the drawings and are used for ease of description only and do not imply that the referenced device or element must have a particular orientation or be constructed and operated in a particular orientation.

In the claims and the specification, unless otherwise defined, the terms "fixedly" or "fixedly connected" are to be understood in a broad sense as meaning any connection which is not in a relative rotational or translational relationship, i.e. including non-detachably fixed connection, integrally connected and fixedly connected by other means or elements.

In the claims and specification, unless otherwise defined, the terms "comprising", "having" and variations thereof mean "including but not limited to".

The technical solution in the embodiments will be clearly and completely described below with reference to the accompanying drawings.

Referring to fig. 1 and 2, fig. 1 and 2 show a connection structure of an aviation connector in an embodiment, which includes an aviation male connector 1, a first cable 2, an aviation female connector 3, a second cable 4 and a limiting member 5.

As shown in fig. 7, 10 and 11, the aeronautical male 1 comprises a cylinder 11 and a third convex ring 12 which are integrally formed; the opening of the barrel 11 forms a jack 13, 3 pins 13 extending along the axial direction are arranged in the barrel 11, one end of each pin 13 penetrates out of the barrel bottom to be connected with a core wire 21 corresponding to the first cable 2, and the other end is positioned in the barrel 11 and close to the opening of the barrel; a third convex ring 12 is formed on the outer wall of the cylinder body to divide the outer wall of the cylinder body into a first section close to the opening of the cylinder body and a second section close to the bottom of the cylinder body; the first section is a connection end 111, the outer wall of which is provided with external threads.

A first cable 2, in this embodiment, the first cable 2 has 3 core wires 21 connected to 3 pins 14; the first cable head 22 is formed on the second section of the aviation male head 1 and the periphery intersected with the first cable 2 in an injection molding mode, so that the aviation male head 1 and the first cable 2 are fixedly connected and electrically connected.

As shown in fig. 3, the aircraft female head 3 includes a pipe body 31, a first convex ring 32, a second convex ring 33, a nut 34, and a rubber core. The first protruding ring 32 and the second protruding ring 33 are respectively formed on the outer walls of the two ends of the tube 31, wherein the second protruding ring 33 forms an abutting surface 331 facing the annular wall of the first protruding ring 32. The nut 34 is sleeved on the outer wall of the tube body 31 and is used for being in threaded fit with the external thread of the connecting end 111, the threaded end is a first end 341, and a second end 342 faces the annular wall of the first convex ring 32; specifically, the inner diameter of the nut 34 is larger than the diameters of the tube 31 and the second collar 33, so that a gap exists between the inner wall of the nut 34 and the outer wall of the second collar 33, so that the nut 34 can slide axially on the tube 31 and the second collar 33; as shown in fig. 5 and 6, the aperture of the second end 342 of the nut 34 is radially contracted, and is larger than the diameter of the tube 31 but smaller than the diameter of the second collar 33, so that when the abutting surface 331 of the second collar abuts against the hole edge inside the second end 342, the second end 342 of the nut 34 is restricted from axially separating from the tube 31 in a direction away from the first collar 32, and, as shown in fig. 4, the diameter of the first collar 32 is also larger than the aperture of the second end 342 of the nut, so as to restrict the second end 342 of the nut from axially separating from the tube 31 in a direction away from the second collar 33. Thus, the first collar 32 and the second collar 33 achieve the axial retention of the second end 342 of the nut on the tubular body 31, but enable the axial movement of the nut 34 in a direction away from the first collar 32 to be screwed with said connection end 111. The rubber core is sleeved in the tube body 31, one end of the rubber core extends out of the tube body 31, the extending end forms a plug-in connector 35, and the plug-in connector 35 goes beyond the first end 341 of the screw cap when the screw cap 34 is not screwed so as to be in plug-in fit with the jack 13; glue the core and be equipped with the wearing groove the same with contact pin 14 quantity and run through length direction, wear to be equipped with inserted sheet 351 in the groove, inserted sheet 351 one end supplies contact pin 14 butt forms the electricity and connects, and the other end stretches out the wearing groove and is located body 31 and meets with the corresponding heart yearn 41 of second cable 4.

As shown in fig. 11, 12 and 13, the second cable 4 extends into the tube 31 from the other end of the rubber core, and in this embodiment, the second cable 4 contains 3 strands of core wires connected to 3 blades 351; the second cable head 42 is formed on the periphery of the first convex ring 32 of the aviation female head and the periphery of the second cable 4 in an injection molding mode, so that the fixed connection and the electric connection relation of the aviation female head 3 and the second cable 4 are achieved.

As shown in fig. 2, the limiting member 5 is detachably embedded in the gap to limit the nut 34 from rotating in opposite directions, so as to ensure the stability of the aviation connector screw joint, and avoid the risk of automatic retreat of the nut 34 caused by vibration and other factors during use. Specifically, as shown in fig. 8 and 9, the limiting member 5 is an elastic ring, which is sleeved on the pipe body 31 and axially limited in the gap, and by using the elastic deformation performance of the elastic ring, not only can the elastic ring be conveniently sleeved on the pipe body 31 in the gap, but also the elastic ring can fall off from the pipe body 31, so as to achieve detachable assembly; in addition, the structure of the elastic ring is simple and easy to manufacture, and the cost is low; preferably, the diameter of the tube body 31 is greater than the inner diameter of the elastic ring; preferably, the axial thickness of the elastic ring is greater than the length of the space; preferably, the cross section of the elastic ring is circular or elliptical. As shown in fig. 14, in this embodiment, the inner diameter of the elastic ring is larger than the diameter of the second cable 4, before the male aircraft head 1 and the female aircraft head 3 are not plugged, the elastic ring can be firstly sleeved on the second cable 4, which not only can prevent the loss of the components, but also can apply force to the second cable head 42 after the plugging, and the elastic ring is firstly sleeved on the outer wall of the second cable head 42 by utilizing the elastic deformation of the elastic ring and gradually moves towards the spacing direction until the second cable head falls into the spacing, so that the operation is convenient.

The description of the above specification and examples is intended to be illustrative of the scope of the present application and is not intended to be limiting.

Claims (10)

1. A connection structure of an aviation connector is characterized by comprising:

the aviation male head is provided with a connecting end with an external thread, and the end face of the connecting end is provided with a jack;

the aviation female head comprises a pipe body, a screw cap sleeved on the outer wall of the pipe body and a plug-in connector extending out of one end of the pipe body; a first convex ring is formed on the outer wall of the other end of the pipe body; the nut is used for being in threaded connection with the external thread of the connecting end, the threaded end of the nut is a first end, and the second end of the nut faces the annular wall of the first convex ring; the plug connector crosses over the first end of the screw cap when the screw cap is not screwed, so as to be in plug fit with the jack to form electric connection; when the screw cap is inserted in place, the screw cap axially moves along the direction deviating from the first convex ring to be in threaded connection with the connecting end, and a gap is formed between the second end of the screw cap and the ring wall of the first convex ring;

and the limiting piece is detachably embedded in the interval so as to limit the nut to rotate in opposite phases.

2. The connecting structure of an aircraft joint according to claim 1, wherein the limiting member is an elastic ring which is sleeved on the pipe body and axially limits the spacing.

3. A coupling structure for an aircraft connector as claimed in claim 2, wherein the diameter of the tubular body in said space is greater than the inner diameter of said resilient ring.

4. A coupling structure for an aircraft joint according to claim 3, wherein said resilient ring has an axial thickness greater than the length of said gap.

5. The connecting structure of an aircraft joint according to claim 4, wherein the cross section of the elastic ring is circular or elliptical.

6. The connecting structure of an aircraft joint according to claim 5, wherein the aircraft female joint further comprises a rubber core, wherein the rubber core is sleeved in the pipe body, one end of the rubber core extends out of the pipe body, and the part of the rubber core, which extends out of the pipe body, forms the plug-in joint; the pipe body is provided with a butting surface so as to limit the second end of the nut to axially separate from the pipe body in the direction deviating from the first convex ring; the diameter of the first convex ring is larger than the aperture of the second end of the screw cap.

7. A coupling structure for an aircraft connector as claimed in claim 6, wherein the bore of the second end of the nut is radially constricted; the outer wall of the pipe body close to the plug connector is provided with a second convex ring, the second convex ring is suitable for being sleeved in the screw cap, a gap exists between the outer wall of the second convex ring and the inner wall of the screw cap, the annular wall of the second convex ring facing the first convex ring forms the abutting surface, and the abutting surface abuts against the hole edge on the inner side of the second end.

8. The aircraft connector connection structure according to claim 7, wherein the aircraft male connector comprises a barrel and a third collar, the third collar being formed on the outer wall of the barrel to separate the outer wall of the barrel into a first section adjacent to the opening of the barrel and a second section adjacent to the bottom of the barrel, the first section being the connection end.

9. The aircraft connector connecting structure according to claim 8, further comprising a first cable and a second cable extending from the other end of the pipe body; a plurality of contact pins extending along the axial direction are arranged in the barrel, and one end of each contact pin penetrates out of the barrel bottom to be connected with a core wire corresponding to the first cable; glue the core be equipped with contact pin quantity the same and run through length direction's wear groove, each wear the inslot and be equipped with the inserted sheet, inserted sheet one end supplies the contact pin butt forms the electricity connect, the other end stretch out wear the groove in order to meet with the heart yearn of second cable.

10. A connecting structure of an aircraft joint according to claim 9, wherein the second section and the outer periphery intersecting the first cable are injection-molded with a first cable head; a second cable head is formed on the periphery of the first convex ring intersected with the second cable in an injection molding mode; the inner diameter of the elastic ring is larger than the diameter of the second cable, and the elastic ring is sleeved on the second cable before the aviation male head and the aviation female head are not spliced.

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