CN112993688B - Electric connector for aviation - Google Patents
Electric connector for aviation Download PDFInfo
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- CN112993688B CN112993688B CN202110168984.4A CN202110168984A CN112993688B CN 112993688 B CN112993688 B CN 112993688B CN 202110168984 A CN202110168984 A CN 202110168984A CN 112993688 B CN112993688 B CN 112993688B
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- stopper
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- 210000000078 claw Anatomy 0.000 claims abstract description 47
- 230000000670 limiting effect Effects 0.000 claims description 21
- 238000009434 installation Methods 0.000 claims description 9
- 230000007246 mechanism Effects 0.000 description 6
- 230000008901 benefit Effects 0.000 description 5
- 238000000034 method Methods 0.000 description 4
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000004323 axial length Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
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Classifications
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R13/00—Details of coupling devices of the kinds covered by groups H01R12/70 or H01R24/00 - H01R33/00
- H01R13/73—Means for mounting coupling parts to apparatus or structures, e.g. to a wall
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R13/00—Details of coupling devices of the kinds covered by groups H01R12/70 or H01R24/00 - H01R33/00
- H01R13/46—Bases; Cases
- H01R13/516—Means for holding or embracing insulating body, e.g. casing, hoods
Landscapes
- Details Of Connecting Devices For Male And Female Coupling (AREA)
- Connector Housings Or Holding Contact Members (AREA)
Abstract
The invention relates to an electrical connector for aviation, which can be fixed on a mounting wall plate on an aircraft and comprises a connector body and a plurality of elastic clamping claws. Wherein the connector body is cylindrical, two end faces thereof in the axial direction are respectively provided with an interface for connecting a cable, and a flange extending outward in the radial direction is formed at one end of the connector body. A plurality of the resilient fingers are evenly arranged around the outer periphery of the connector body, are secured to the connector body adjacent the root portion of the flange, and extend from the root portion to a free end converging inwardly in the axial direction of the connector body. Wherein an inwardly recessed catch is formed between the root of the resilient catch and the flange, the catch being configured to receive and retain the mounting panel after the resilient catch has passed through the mounting panel.
Description
Technical Field
The invention relates to the technical field of electrical appliance connecting pieces, in particular to an aviation electrical connector.
Background
Known aerial electrical connector mounting means include square flange mounting and nut-clamp mounting. Both types of connectors contain set screw and nut assemblies. When the installation or the disassembly is carried out, the installer needs to use a special tool for fixing force or disassembling. Aeronautical electrical connectors have the drawback of requiring long installation times, since the installation process involves the installation of additional screw nuts.
In areas of poor reach, poor installation environments have difficulty providing sufficient space for an installer to screw the nut and screw, and thus, existing avionic connectors have difficulty installing.
In addition to this, when an installer installs the screw nuts in a small installation space, it is difficult to observe whether the screw nuts are aligned with each other, and thus the screw nuts are easily dropped by a wrong operation during the installation. In vehicles flying at high speeds, such as aircraft, the falling screw and nut fittings are prone to various risks to the aircraft.
In view of this, there is a need for improvements to existing avionic connectors.
Disclosure of Invention
In view of the above-mentioned current situation of the aviation electrical connector, an object of the present invention is to provide an aviation electrical connector, which is no longer fixed by a screw and nut assembly.
This object is achieved by the following form of the apparatus of the invention. The aviation electric connector can be fixed on a mounting wall plate on an aircraft and comprises a connector body and a plurality of elastic clamping claws. Wherein the connector body is cylindrical, interfaces for connecting cables are provided on both end surfaces thereof in the axial direction, respectively, and a flange extending outward in the radial direction is formed at one end portion of the connector body. A plurality of the resilient fingers are evenly arranged around the outer periphery of the connector body, are secured to the connector body adjacent the root portion of the flange, and extend from the root portion to a free end converging inwardly in the axial direction of the connector body.
Wherein an inwardly recessed catch groove is formed between the root of the resilient catch and the flange, the catch groove being configured to receive and retain the mounting panel after the resilient catch has passed through the mounting panel.
According to the aviation electric connector, the elastic clamping claws can be radially inwards contracted under the action of the compression of the mounting holes of the mounting wall plate when penetrating into the mounting wall plate. After the elastic clamping jaw penetrates through the mounting hole, the elastic clamping jaw restores to a natural state, the clamping groove formed by the root of the elastic clamping jaw and the flange of the connector main body is clamped with the mounting wallboard, and the aviation electric connector is mounted on the mounting wallboard. Thanks to the particular arrangement, the aeronautical electrical connector can be mounted on the mounting panel without a threaded structure, thus having the characteristic of being simple to operate.
According to a preferred embodiment of the present invention, the aircraft electrical connector further includes a pressing sleeve configured to be movable on an outer surface of the plurality of elastic claws in an axial direction of the connector body toward the flange of the connector body, thereby causing the plurality of elastic claws to contract radially. By means of the pressing sleeve, an installer can very conveniently detach the aviation electric connector from the installation wall plate.
According to a preferred embodiment of the present invention, a front end surface of the connector body is axially projected forward from a front end surface of the elastic claw. The connector main body protruding from the front end face of the elastic claw enables a user to easily observe the interface of the aviation electric connector, and the user can conveniently plug in a cable.
According to a preferred embodiment of the invention, the press sleeve is a cylindrical piece closed at one end and open at the other end, the closed end of which is fixed to the end of the connector body remote from the flange, the open end receiving the free end of the resilient catch, the connector body forming a connector step for abutting against the closed end. The push sleeve can thereby be secured to the connector body without the user having to spend time looking for a removal tool before the aeronautical electrical connector body needs to be removed.
According to a preferred embodiment of the present invention, the aeronautical electrical connector further comprises an elastic member capable of being placed in the cavity formed between the inner surface of the elastic claw and the outer surface of the connector body, the elastic member being in a natural stretched state or in a compressed state when the closed end abuts against the connector step, and both ends abutting against the closed end and the root of the elastic claw, respectively. Under this condition, the elastic component can avoid pressing the sleeve pipe and appear moving towards the elasticity jack catch and oppress elasticity jack catch radial contraction under the condition of violent vibrations in service environment, consequently, the condition that the aviation electric connector can avoid droing because of aircraft vibrations takes place.
According to a preferred embodiment of the present invention, the elastic member is a spring capable of being fitted over the connector body.
According to a preferred embodiment of the present invention, a plurality of limit grooves or limit protrusions are formed on an end surface of the flange facing the elastic claw, the limit grooves or limit protrusions being uniformly arranged around a circumferential direction of the connector body, and the mounting wall plate is formed with limit protrusions or limit grooves matching the corresponding limit grooves or limit protrusions in shape.
According to a preferred embodiment of the present invention, the plurality of stopper grooves are connected by a stopper annular groove, and the plurality of stopper protrusions are connected by a stopper annular protrusion.
According to a preferred embodiment of the present invention, a plurality of retaining grooves or retaining protrusions are formed on an end surface of the elastic claw facing the flange, the retaining grooves or the retaining protrusions being uniformly arranged around a circumferential direction of the connector body, and the mounting wall plate is formed with retaining protrusions or retaining grooves matching the corresponding retaining grooves or retaining protrusions in shape.
According to a preferred embodiment of the present invention, the plurality of stopper grooves are connected by a stopper annular groove, and the plurality of stopper protrusions are connected by a stopper annular protrusion.
Through the combination of the multiple limiting grooves and the limiting protrusions, the aviation electric connector cannot rotate relative to the installation wall plate.
According to a preferred embodiment of the present invention, the taper of the external tapered surface of the root portion of the elastic claw is greater than the taper of the external tapered surface of the body portion of the elastic claw.
On the basis of the common general knowledge in the field, the preferred embodiments can be combined randomly to obtain the preferred examples of the invention. Other systems, methods, features and advantages of the invention will be or will become apparent to one with skill in the art upon examination of the following figures and detailed description. It is intended that all such additional systems, methods, features and advantages be included within this description and this summary, be within the scope of the invention, and be protected by the accompanying claims.
Drawings
For a better understanding of the above and other objects, features, advantages and functions of the present invention, reference should be made to the preferred embodiments illustrated in the accompanying drawings. Like reference numerals in the drawings refer to like parts. It will be appreciated by persons skilled in the art that the drawings are intended to illustrate preferred embodiments of the invention without any limiting effect on the scope of the invention, and that the various components in the drawings are not drawn to scale.
Fig. 1 is a schematic structural view of an avionic connector according to a preferred embodiment of the present disclosure.
Fig. 2 is a longitudinal sectional view of the aerospace electrical connector shown in fig. 1.
Fig. 3 is a schematic view of the structure of an avionic connector, with the push sleeve hidden.
Fig. 4 is a schematic structural view of a mounting panel of an avionic connector suitable for use in a preferred embodiment of the present disclosure.
Detailed Description
The inventive concept of the present invention will be described in detail below with reference to the accompanying drawings. What has been described herein is merely a preferred embodiment in accordance with the present invention and other ways of practicing the invention will occur to those skilled in the art and are within the scope of the invention. In the following detailed description, directional terms, such as "upper", "lower", "inner", "outer", "longitudinal", "lateral", and the like, are used with reference to the orientation depicted in the accompanying drawings. Components of embodiments of the present invention can be positioned in a number of different orientations and the directional terminology is used for purposes of illustration and is in no way limiting.
In the present disclosure, "front-rear direction" refers to a direction along an axial direction of the aircraft electrical connector, where "front" indicates a side of the aircraft electrical connector at a leading position during the process of passing through the mounting panel, and "rear" indicates a side of the aircraft electrical connector at a trailing position during the process of passing through the mounting panel.
Referring to fig. 1-2, a perspective view, a longitudinal cross-sectional view, respectively, of an aerospace electrical connector is shown. The avionic connector 100 according to the present disclosure can be fixed to a mounting panel 200 on an aircraft. The aircraft electrical connector 100 includes a connector body 10, a plurality of elastic claws 20, a push sleeve 30, and the like.
Referring to fig. 1 and 2 in conjunction with fig. 3, wherein, to facilitate illustrating the inventive concepts of the present disclosure, fig. 3 does not illustrate the push sleeve 30 of the aerospace electrical connector 100. The connector body 10 is a member for realizing an electrical connection or a communication connection of a two-terminal cable, and has a cylindrical shape. Ports 11 for connecting cables are formed on both end surfaces of the connector body 10 in the axial direction. The interface 11 is of a pin-and-socket type in the embodiment shown in fig. 1 and 3, but the form of the interface 11 is not limited thereto. The interface 11 is for example in the form of a component comprising a shielding collar, a central guide pin, etc. It should be understood that other interface forms capable of making electrical or communication connections may be used as the interface form for the avionic connector 100 of the present disclosure.
A flange 12 extending radially outward is formed at the rear end of the connector body 10. The flange 12 is optionally formed to have a circular cross section with an outer edge having a diameter R of not less than 1.5 times the diameter R of the connector body 10, for example, a flange outer diameter R of 1.8 times, 2 times the diameter R of the connector body.
A plurality of resilient fingers 20 are evenly arranged around the outer periphery of the connector body 10, having a root portion 24 adjacent the flange 12 and a body portion 22 remote from the flange 12. The resilient latch 20 is secured to the connector body 10 by a heel 24. The resilient claws 20 are extended from the root portions 24 to free ends while contracting inward in the axial direction of the connector body 10, so that the outer surfaces of the body portions 22 of the resilient claws 20 are formed as tapered surfaces S1, S2 that are inclined radially inward from the rear ends toward the front ends.
In the embodiment of fig. 1-3, the number of resilient jaws 20 of the aviation electrical connector 100 shown is 4, and the shape of each resilient jaw 20 is the same. In fact, the number of resilient claws 20 can also be any suitable number, 2, 3, 5, etc. The angle at which each resilient latch 20 extends in the circumferential direction may be different. For example, in the embodiment in which 4 elastic claws 20 are provided, the radians of the 4 elastic claws 20 may be set to 1/3, 1/3, 1/3, pi, or the like, respectively, in addition to approximately 1/2.
Referring to fig. 2 and 3, an inwardly recessed notch 13 is formed between the root 24 of the resilient latch 20 and the flange 12, the notch 13 being configured to receive and retain the mounting wall 200 after the resilient latch 20 has passed through the mounting wall 200. The depth of the card slot 13 is set to any size in the range of 3mm to 20mm, for example, 8mm, 12mm, etc., depending on the overall size of the avionic connector 100.
In one embodiment, the resilient jaws 20 are formed with a root taper S2 on the outer surface of their root 24 that is slightly greater than the taper of the main taper S1 of their body portion 22, e.g., 2 °, 3 °, 5 °, etc. When the installer pushes the aviation electrical connector 100 from the front end to the rear end, when the contact position between the mounting hole of the mounting wall plate 200 and the outer conical surface of the elastic claw 20 is changed from the main conical surface S1 to the root conical surface S2, the speed of the installer pushing the aviation electrical connector 100 is obviously slowed down, which is beneficial to the installer to avoid pushing the aviation electrical connector 100 at an excessively fast speed, so that the flange 12 is deformed or even falls off when receiving a large impact load of the mounting wall plate 200. Furthermore, with this form of root taper S2 and primary taper S1, the installer experiences a significant jamming effect when pushing the aerospace electrical connector 100 into the root 24, thereby alerting the installer to push the electrical connector at a relatively slow speed during subsequent operation. This arrangement is particularly suitable for use in situations where the operating space is so small that the installer cannot observe the avionic connector 100 in real time.
According to the present disclosure, the overall length of the aerospace electrical connector 100 is defined by the axial length of the connector body 10. Specifically, the front end face of the connector body 10 projects axially forward from the front end faces of the elastic claws 20, and the rear end face of the connector body 10 projects axially rearward from the rear end face of the flange 12. Because the two end faces of the connector body 10 are located at the axially outermost ends of the aviation electrical connector 100, the interfaces 11 on the two ends of the aviation electrical connector 100 are in an exposed state, and therefore, the plugging of cables by users is facilitated.
Anti-rotation mechanisms for limiting rotation of the aerospace electrical connector 100 relative to the mounting wall plate 200 relative to each other are also disclosed according to the present disclosure. Specifically, in the embodiment of fig. 3 and 4, the anti-rotation mechanism includes a plurality of retaining grooves 15 on the flange 12 and a plurality of retaining protrusions 21 on the mounting wall plate 200. It is understood that the "plurality" here may be 4 as shown in fig. 3 and 4, and may be any number of 2, 3, 5, and so on.
The respective limit grooves 15 on the flange 12 are formed on the end surface of the flange 12 facing the resilient claws 20. The respective stopper grooves 15 are uniformly arranged around the circumference of the connector body 10. Correspondingly, the stopper protrusion 21 of the mounting wall plate 200 is formed on the surface of the mounting wall plate 200 facing the flange 12 side. In the embodiment of fig. 3 and 4, the stop projections 21 and the stop grooves 15 have a substantially rectangular shape in the axial direction, so that the different radial sections of the stop projections 21 and the stop grooves 15 have a relatively large circumferential extension (arc length), and the stop projections 21 and the stop grooves 15 therefore have a relatively good impact resistance.
With continued reference to fig. 3 and 4, the respective retaining grooves 15 on the flanges 12 are preferably connected by a retaining annular groove 16. The respective catching protrusions 21 of the mounting wall plate 200 are connected by a catching annular protrusion 23. In this case, the stopper projection 21 is formed as a projection projecting radially outward from the stopper annular projection 23. The integral structure of the retainer annular projections 23 and the respective retainer projections 21, and the integral structure of the retainer annular grooves 16 and the respective retainer grooves 15 further improve the impact resistance of the retainer projections 21 (retainer grooves 15), which is particularly advantageous in an environment of high-frequency vibration such as an aircraft.
It should be understood that although the above-described embodiment shows only the rotation preventing mechanism in which the limit projection 21 (limit annular projection 23) is formed on the mounting wall plate 200 and the limit groove 15 (limit annular groove 16) is provided on the flange 12, according to the present disclosure, the limit projection 21 (limit annular projection 23) and the limit groove 15 (limit annular groove 16) may be interchanged in position, that is, the limit projection 21 (limit annular projection 23) is provided on the flange 12 and the rotation preventing mechanism of the limit groove 15 (limit annular groove 16) is provided on the mounting wall plate 200. The solution described above is easily implemented by those skilled in the art based on the concepts of fig. 3 and 4.
Otherwise, similar mechanisms may be disposed on the end surface of the elastic claw 20 facing the mounting wall plate 200 and the end surface of the mounting wall plate 200 facing the elastic claw 20, and for the same reason, those skilled in the art can form such rotation-preventing mechanisms under the guidance of the illustrations and the corresponding descriptions in fig. 3 and 4, and therefore, the details are not repeated herein.
According to the above description, the aviation electrical connector 100 achieves the effect of simply and firmly attaching to the mounting panel 200 without using a screw or nut member. The present disclosure further relates to a solution for easily detaching the aviation electrical connector 100 from the mounting panel 200, which will be described below.
Removal of the aerospace electrical connector 100 is accomplished by the push sleeve 30 shown in fig. 1-2 according to the present disclosure. Wherein the pressing sleeve 30 is configured to be movable on the outer surface of the plurality of elastic claws 20 toward the flange 12 of the connector body 10 in the axial direction of the connector body 10, thereby causing the plurality of elastic claws 20 to contract radially.
Specifically, the pressing sleeve 30 is a cylindrical member having one end closed and the other end opened, the closed end of which is fixed to the end of the connector body 10 remote from the flange 12, and the open end of which receives the free end of the elastic claw 20. The connector body 10 forms a connector step 14 for abutting the closed end. Note that although one end of the pressing sleeve 30 is a closed end, in fact, as shown in fig. 2, the closed end of the pressing sleeve 30 is not completely closed, and is an end wall having a through hole matching the shape of the connector body 10. When it is necessary to disassemble the aeronautical electrical connector 100, the user pushes the pressing sleeve 30 towards the rear end in the axial direction, so that pressing the sleeve 30 radially contracts the elastic jaws 20. Another advantage of this form of aeronautical electric connector 100 is that the direction of the required thrust force for radially contracting the elastic jaws 20 and deforming the electric connector 100 in the condition of being disassembled is the same as the direction of the required thrust force for pushing the electric connector 100 away from the mounting wall plate 200, and therefore the electric connector 100 is easy to disassemble.
According to the present disclosure, the aeronautical electrical connector 100 further comprises an elastic member 40 that can be placed in the cavity formed between the inner surface of the elastic claw 20 and the outer surface of the connector body 10. When the closed end abuts the connector step 14, the resilient member 40 is in a natural stretched or compressed state, and the two ends abut the closed end and the root 24 of the resilient pawl 20, respectively. In this case, the elastic member 40 can prevent the pressing sleeve 30 from moving toward the elastic claws 20 to press the elastic claws 20 to radially contract when severe vibration occurs in the use environment, and thus the aviation electrical connector 100 can prevent the aviation electrical connector from falling off due to aircraft vibration.
According to the present disclosure, the pressing sleeve 30 may be a member formed by a plurality of arc-shaped wall-shaped structural members butt-jointed to each other in the circumferential direction. The wall-like structures may be joined together by conventional snap-fit or bolted connections to form the compression sleeve 30.
The elastic member 40 is a spring 40 capable of fitting over the connector body 10. Preferably, the inner surface of the elastic claw 20 is formed in parallel with the outer surface of the connector body 10. In this case, the cavity formed between the inner surface of the resilient latch 20 and the outer surface of the connector body 10 exactly matches the shape of the spring 40, preventing the spring 40 from deflecting about the central axis of the connector body 10.
According to the aviation electrical connector 100, the elastic claws 20 are pressed radially inward by the mounting holes of the mounting wall plate 200 when the elastic claws penetrate into the mounting wall plate 200. After the elastic claws 20 pass through the mounting holes, the elastic claws 20 return to their natural state, and the fastening grooves 13 formed by the root portions of the elastic claws 20 and the flange 12 of the connector body 10 are fastened to the mounting wall plate 200, whereby the aircraft electrical connector 100 is mounted on the mounting wall plate 200. Thanks to the particular arrangement, the avionic connector 100 can be mounted on the mounting panel 200 without a screw structure, thus featuring an easy operation.
The scope of the invention is limited only by the claims. Persons of ordinary skill in the art, having benefit of the teachings of the present disclosure, will readily appreciate that alternative structures to the disclosed structures can be substituted for the possible embodiments and that the disclosed embodiments can be combined to create new embodiments that also fall within the scope of the appended claims.
Description of reference numerals:
aviation electric connector: 100.
installing a wallboard: 200.
a connector main body: 10.
elastic claw: 20.
pressing the sleeve: 30.
elastic member, spring 40: 40.
interface: 11.
flange: 12.
a clamping groove: 13.
connector step: 14.
limiting groove: 15.
limiting the annular groove: 16.
main conical surface of the elastic claw: and S1.
Root conical surface of the elastic claw: and S2.
Limiting and protruding: 21.
limiting the annular protrusion: 23.
main body portion of elastic claw: 22.
root of elastic jaw: 24.
Claims (10)
1. an electrical aviation connector fixable to a mounting panel (200) on an aircraft, the electrical aviation connector comprising:
a connector body (10), the connector body (10) being cylindrical, being provided with ports (11) for connecting cables on both end faces thereof in the axial direction, respectively, and being formed with a flange (12) extending radially outward at one end of the connector body (10); and
a plurality of resilient fingers (20), a plurality of said resilient fingers (20) being evenly arranged around the outer periphery of said connector body (10), being secured to said connector body (10) adjacent a root portion (24) of said flange (12) and extending from said root portion (24) to a free end converging inwardly in the axial direction of said connector body (10),
wherein an inwardly recessed catch groove (13) is formed between the root portion (24) of the resilient catch (20) and the flange (12), the catch groove (13) being configured to receive and retain the mounting wall plate (200) after the resilient catch (20) has passed through the mounting wall plate (200), the taper of the root portion tapered surface (S2) of the resilient catch (20) being greater than the taper of the body portion tapered surface (S1) of the resilient catch (20).
2. The aeronautical electrical connector according to claim 1, further comprising a pressing sleeve (30), wherein the pressing sleeve (30) is configured to be movable on an outer surface of the plurality of elastic claws (20) in an axial direction of the connector body (10) toward the flange (12) of the connector body (10) so that the plurality of elastic claws (20) are radially contracted.
3. The airborne electrical connector of claim 2,
the front end face of the connector body (10) is axially projected forward by the front end face of the elastic claw (20).
4. The airborne electrical connector of claim 3,
the press sleeve (30) is a cylindrical piece closed at one end and open at the other end, the closed end of which is fixed at the end of the connector body (10) remote from the flange (12), the open end receiving the free end of the resilient catch (20), the connector body (10) forming a connector step (14) for abutting against the closed end.
5. The airborne electrical connector of claim 4,
the aviation electrical connector further comprises an elastic piece (40) capable of being placed in a cavity formed between the inner surface of the elastic claw (20) and the outer surface of the connector body (10), wherein when the closed end abuts against the connector step (14), the elastic piece (40) is in a natural stretching state or a pressed state, and two ends of the elastic piece abut against the closed end and a root part (24) of the elastic claw (20).
6. Electrical aeronautical connector according to claim 5, characterized in that the elastic element (40) is a spring able to be fitted over the connector body (10).
7. The airborne electrical connector of any of claims 1-6,
a plurality of limiting grooves (15) or limiting protrusions (21) which are uniformly distributed around the circumference of the connector main body (10) are formed on the end face, facing the elastic claw (20), of the flange (12), and the limiting protrusions (21) or the limiting grooves (15) which are matched with the corresponding limiting grooves (15) or the corresponding limiting protrusions (21) in shape are formed on the installation wall plate (200).
8. The airborne electrical connector of claim 7,
the plurality of stopper grooves (15) are connected by a stopper annular groove (16), and the plurality of stopper projections (21) are connected by a stopper annular projection (23).
9. The electrical aviation connector according to any one of claims 1 to 6,
the end face, facing the flange (12), of the elastic claw (20) is provided with a plurality of limiting grooves (15) or limiting protrusions (21) which are uniformly distributed around the circumference of the connector main body (10), and the mounting wall plate (200) is provided with limiting protrusions (21) or limiting grooves (15) which are matched with the corresponding limiting grooves (15) or limiting protrusions (21) in shape.
10. The avionic connector according to claim 9,
the plurality of stopper grooves (15) are connected by a stopper annular groove (16), and the plurality of stopper protrusions (21) are connected by a stopper annular protrusion (23).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110168984.4A CN112993688B (en) | 2021-02-07 | 2021-02-07 | Electric connector for aviation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110168984.4A CN112993688B (en) | 2021-02-07 | 2021-02-07 | Electric connector for aviation |
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| Publication Number | Publication Date |
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| CN112993688A CN112993688A (en) | 2021-06-18 |
| CN112993688B true CN112993688B (en) | 2022-06-17 |
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| CN202110168984.4A Active CN112993688B (en) | 2021-02-07 | 2021-02-07 | Electric connector for aviation |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114204355B (en) * | 2021-12-14 | 2025-05-02 | 宁波公牛电器有限公司 | Connectors and mounting devices |
| CN115117695B (en) * | 2022-08-24 | 2022-11-15 | 中航机载系统共性技术有限公司 | Connector for airborne equipment of civil aircraft |
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| JP2005302582A (en) * | 2004-04-14 | 2005-10-27 | Furukawa Electric Co Ltd:The | Connector with lock |
| CN201038507Y (en) * | 2007-04-02 | 2008-03-19 | 许正升 | Connector with easy detaching and assembling function |
| CN102623837A (en) * | 2012-04-24 | 2012-08-01 | 宁波海曙区西尚电子有限公司 | Socket of data connector and plug |
| CN206498047U (en) * | 2016-08-30 | 2017-09-15 | 广东通宇通讯股份有限公司 | A base station antenna joint installation structure |
| CN109923737A (en) * | 2016-11-17 | 2019-06-21 | 莫列斯有限公司 | floating socket connector |
| JP3216720U (en) * | 2018-01-25 | 2018-06-21 | 正▲わい▼精密工業股▲ふん▼有限公司 | Socket connector |
| CN111742448A (en) * | 2018-02-28 | 2020-10-02 | 罗伯特·博世有限公司 | Plug connector system and method for producing a plug connector system |
| CN110630671A (en) * | 2019-10-25 | 2019-12-31 | 高密同创气门芯有限公司 | Valve inside and nitrogen spring |
| CN111009789A (en) * | 2019-12-25 | 2020-04-14 | 珠海沃顿电气有限公司 | Bus connecting device and switch cabinet with same |
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| CN112993688A (en) | 2021-06-18 |
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