Electric connector for aviation aircraft

Abstract

The utility model discloses an electric connector for an aviation aircraft, which belongs to the field of electric connectors and comprises a socket, a plug is plugged on the socket, a locking structure is mounted on the socket and comprises a vertical column and a movable plate slidably mounted on the outer wall of the vertical column, and the movable plate is mounted on the outer wall of the vertical column. A spring is mounted on the side wall of the moving plate and located outside the stand column; according to the electric connector, the locking structure is arranged, and a movable plate, a spring, a clamping block, a connecting plate, a circular ring and the like are matched, so that the locking function after the socket and the plug are plugged is realized, the socket and the plug are prevented from loosening under vibration, and the situation that most of existing electric connectors adopt a connection mode that the plug and the socket are plugged together is avoided; the problem that the connection between the plug and the socket is loosened after the electric connector is vibrated for a long time is solved, so that a guarantee is provided for stable transmission of electric signals of an aviation aircraft.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of electric connector, specifically an electric connector for an aircraft. BACKGROUND

[0002] An aircraft refers to an appliance flying in the earth's atmosphere. There are various types of aircrafts, and the family is complete. From the height of 10 centimeters above the ground to the height of dozens of kilometers that cannot be seen by the naked eye, there are our flying brothers showing their skills. Due to the complex internal structure of the aircraft, various electrical signals need to be transmitted through the circuit of each component inside the aircraft, and the electric connector is used to connect different wire lines.

[0003] Most of the existing electric connectors adopt the connection mode that the plug and the socket are plugged together. The aircraft will be subjected to a large impact force and vibrate when flying at high speed, turbulent flow or landing. The plug and the socket connection will be loose after the electric connector is subjected to vibration for a long time, thereby affecting the electrical signal transmission of the aircraft.

[0004] Therefore, the utility model provides an electric connector for an aircraft to solve the above problems. UTILITY MODEL CONTENT

[0005] The utility model provides an electric connector for an aircraft, which aims to solve the problems of the existing electric connector that most of the existing electric connectors adopt the connection mode that the plug and the socket are plugged together, the aircraft will be subjected to a large impact force and vibrate when flying at high speed, turbulent flow or landing, and the plug and the socket connection will be loose after the electric connector is subjected to vibration for a long time.

[0006] In order to achieve the above purpose, the utility model provides the following technical scheme: an electric connector for an aircraft, comprising a socket, the socket is plugged with a plug, and the socket is provided with a locking structure;

[0007] The locking structure comprises a column and a moving plate slidingly installed on the outer wall of the column, a spring is installed on the side wall of the moving plate and outside the column, a clamping block is installed on the side wall of the moving plate, the locking structure further comprises two symmetrical connecting plates installed on the outer wall of the plug, and the ends of the two connecting plates away from the plug are connected through a circular ring. By setting the locking structure, the locking function of the socket and the plug after plugging is realized, so that the socket and the plug will not be loose under vibration, and the problems that most of the existing electric connectors adopt the connection mode that the plug and the socket are plugged together, and the plug and the socket connection will be loose after the electric connector is subjected to vibration for a long time are avoided, thereby providing protection for the stable transmission of the electrical signal of the aircraft.

[0008] Preferably, the outer wall of the plug is provided with a protection structure;

[0009] The protection structure comprises a sleeve plate mounted on the outer wall of the plug, a bellows mounted on the sleeve plate, and an externally threaded cylinder mounted on the other end of the bellows, and the protection structure further comprises a sleeve rotatably mounted on the socket, and an internally threaded hole formed in the inner wall of the sleeve.

[0010] Preferably, a first wire is connected to the socket, a second wire is mounted on the plug, a plurality of insertion holes are formed in the socket, and a plurality of insertion pins are mounted on the plug and correspond to the insertion holes.

[0011] Preferably, two groups of columns are provided, a mounting groove is symmetrically formed in the socket, the socket is connected to the two ends of the columns through the mounting groove, and the socket is slidably connected to the moving plate through the mounting groove.

[0012] Preferably, a button is mounted on the side wall of the moving plate, the clamping block and the button extend to the outside of the socket through the mounting groove, and an inclined groove is symmetrically formed in the inner wall of the ring, and an inclined surface is formed in the clamping block and corresponds to the inclined groove.

[0013] Preferably, a positioning plate is mounted on the outer wall of the plug, and a positioning groove is formed in the socket and corresponds to the positioning plate.

[0014] Preferably, the sleeve is threadedly connected to the externally threaded cylinder through the internally threaded hole, a water-proof ring groove is formed in the outer wall of the socket, and the socket is rotatably connected to the sleeve through the water-proof ring groove.

[0015] Beneficial effects: By setting the locking structure, the moving plate, the spring, the clamping block, the connecting plate, and the ring are cooperated to realize the locking function after the socket and the plug are inserted, so that the socket and the plug will not be loose due to vibration, and the problem that the existing electric connector is mostly connected by inserting the plug and the socket together, and the connection between the plug and the socket will be loose after the electric connector is subjected to vibration for a long time is avoided, thereby providing protection for stable transmission of electrical signals of the aircraft. BRIEF DESCRIPTION OF DRAWINGS

[0016] Figure 1 It is a perspective cut structure schematic view of an electric connector for an aircraft;

[0017] Figure 2 It is a perspective structure schematic view of an electric connector for an aircraft;

[0018] Figure 3 It is a partial cut and disassembly structure schematic view of an electric connector for an aircraft;

[0019] Figure 4 It is an enlarged structure schematic view of A of an electric connector for an aircraft;

[0020] Figure 5 It is a schematic view of a socket structure of an electrical connector for an aerial vehicle.

[0021] In the figure: 1, socket; 11, mounting groove; 12, positioning groove; 13, jack; 14, water-proof ring groove; 2, plug; 21, pin; 3, locking structure; 31, column; 32, moving plate; 33, spring; 34, clamping block; 341, inclined surface; 35, connecting plate; 36, ring; 361, inclined groove; 37, button; 4, first wire; 5, second wire; 6, positioning plate; 7, protection structure; 71, cover plate; 72, bellows; 73, externally threaded cylinder; 74, sleeve; 741, internal thread. DETAILED DESCRIPTION

[0022] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application.

[0023] Embodiment 1

[0024] The present embodiment provides an electrical connector for an aerial vehicle, as shown in the figure, the electrical connector comprises a socket 1, a plug 2 is inserted into the socket 1, and a locking structure 3 is mounted on the socket 1. Figures 1-5

[0025] The locking structure 3 comprises a column 31 and a moving plate 32 slidingly mounted on the outer wall of the column 31, a spring 33 is mounted on the side wall of the moving plate 32 and located outside the column 31, a clamping block 34 is mounted on the side wall of the moving plate 32, the locking structure 3 further comprises two connecting plates 35 symmetrically mounted on the outer wall of the plug 2, and the two connecting plates 35 are connected through a ring 36 at the end away from the plug 2.

[0026] ​In use, the installer drives the plug 2 to move close to the socket 1, aligns each pin 21 with the corresponding socket 13, and continues to drive the pin 21 into the socket 13, at the same time, the plug 2 moves close to the socket 1 with the two side connecting plates 35, the two sides move close to the clamping block 34 with the ring 36, when the inclined groove 361 contacts the inclined surface 341, continue to push the plug 2 to move close to the socket 1, the ring 36 drives the two side clamping blocks 34 to move to the inside of the mounting groove 11, the clamping block 34 drives the moving plate 32 to slide on the outer wall of the column 31 and compresses the spring 33, when the ring 36 slides through the clamping block 34, the clamping block 34 loses force, under the reset action of the spring 33, the moving plate 32 is pushed to move, the moving plate 32 pushes the clamping block 34 to clamp the ring 36, thereby realizing the locking function after the socket 1 and the plug 2 are plugged together, so that the socket 1 and the plug 2 will not be loose under vibration, avoiding the problem that the existing electrical connector mostly adopts the connection mode that the plug 2 and the socket 1 are plugged together, and the electrical connector will be loose after being subjected to vibration for a long time, thereby providing protection for stable transmission of electrical signals of an aircraft.

[0027] Among them, through the setting of the button 37, pressing the button 37, the button 37 moves close to the mounting groove 11 with the moving plate 32, the moving plate 32 moves to the inside of the mounting groove 11 with the clamping block 34, the clamping block 34 no longer limits the ring 36, and the plug 2 is pulled out in the direction away from the socket 1, so as to realize the unlocking function of the locking structure 3.

[0028] In the embodiment, the socket 1 is connected with the first wire 4, the plug 2 is installed with the second wire 5, the socket 1 is provided with a plurality of sockets 13, and the plug 2 is installed with pins 21 corresponding to the sockets 13;

[0029] Among them, through the cooperation of the positioning plate 6 and the positioning groove 12, when the socket 1 and the plug 2 are connected, the positioning plate 6 and the positioning groove 12 are aligned, the plurality of pins 21 and the plurality of sockets 13 can be quickly aligned, which is beneficial to improve the connection effect of the socket 1 and the plug 2;

[0030] In the embodiment, the side wall of the moving plate 32 is installed with the button 37, the clamping block 34 and the button 37 penetrate the mounting groove 11 and extend to the outside of the socket 1, the inner wall of the ring 36 is symmetrically provided with the inclined groove 361, and the clamping block 34 is provided with the inclined surface 341 corresponding to the inclined groove 361.

[0031] Embodiment 2

[0032] Different from the embodiment 1, the existing electric connector lacks waterproof and dustproof device, the plug 2 and the socket 1 are plugged together, water vapor and dust can enter the electric connector from the connection, which affects the use stability of the electric connector, therefore, the outer wall of the plug 2 is provided with the protection structure 7;

[0033] The protection structure 7 comprises a sleeve plate 71 installed on the outer wall of the plug 2, the sleeve plate 71 is provided with a bellows 72, the other end of the bellows 72 is provided with an external thread cylinder 73, the protection structure 7 further comprises a sleeve 74 rotatably installed on the socket 1, the inner wall of the sleeve 74 is provided with an internal thread 741;

[0034] In use, when the socket 1 and the plug 2 are plugged together and locked by the locking structure 3, the bellows 72 is stretched towards the socket 1, the bellows 72 drives the external thread cylinder 73 to the position of the internal thread 741 of the sleeve 74, the sleeve 74 is rotated to be screwed with the external thread cylinder 73, so that the connection of the socket 1 and the plug 2 is sealed in the protection structure 7, the water vapor and dust in the air are prevented from entering the outside of the protection structure 7, the problem that the existing electric connector lacks waterproof and dustproof device and the water vapor and dust enter the electric connector from the connection when the plug 2 and the socket 1 are plugged together is solved, the waterproof and dustproof function of the electric connector is realized, and the use stability of the electric connector is improved.

[0035] In the embodiment, the sleeve 74 is screwed with the external thread cylinder 73 through the internal thread 741, the outer wall of the socket 1 is provided with a water isolation ring groove 14, and the socket 1 is rotatably connected with the sleeve 74 through the water isolation ring groove 14.

[0036] The above is only the preferred embodiment of the present application, but the protection scope of the present application is not limited to this, any skilled person in the art can make equivalent replacement or change according to the technical scheme and concept of the present application within the technical range disclosed by the present application, which should be covered in the protection scope of the present application.

Claims

1. An electrical connector for an aircraft, comprising a socket (1), characterized in that: The plug (2) is inserted into the socket (1), and the locking structure (3) is installed on the socket (1); The locking structure (3) comprises a stand (31) and a moving plate (32) slidably installed on the outer wall of the stand (31), a spring (33) is installed on the side wall of the moving plate (32) and located outside the stand (31), a clamping block (34) is installed on the side wall of the moving plate (32), the locking structure (3) further comprises two connecting plates (35) symmetrically installed on the outer wall of the plug (2), and the two connecting plates (35) are connected through a ring (36) away from the plug (2).

2. The electrical connector for an aerospace vehicle of claim 1, wherein: The outer wall of the plug (2) is provided with a protection structure (7); The protection structure (7) comprises a sleeve plate (71) installed on the outer wall of the plug (2), a bellows (72) installed on the sleeve plate (71), an externally threaded cylinder (73) installed at the other end of the bellows (72), and a sleeve (74) rotatably installed on the socket (1), wherein an internally threaded hole (741) is formed in the inner wall of the sleeve (74).

3. The electrical connector for aerospace vehicles as recited in claim 1, wherein: The first wire (4) is connected to the socket (1), the second wire (5) is installed on the plug (2), a plurality of insertion holes (13) are formed in the socket (1), and a plug pin (21) is installed on the plug (2) corresponding to the insertion hole (13).

4. The electrical connector for aerospace vehicles of claim 1, wherein: The stand (31) is provided with two groups, the socket (1) is symmetrically provided with an installation groove (11), and the socket (1) is connected to the two ends of the stand (31) through the installation groove (11).

5. The electrical connector for aerospace vehicles of claim 1, wherein: The side wall of the moving plate (32) is provided with a button (37), the clamping block (34) and the button (37) penetrate through the installation groove (11) and extend to the outside of the socket (1), and the inner wall of the ring (36) is symmetrically provided with an inclined groove (361), and the clamping block (34) is provided with an inclined surface (341) corresponding to the inclined groove (361).

6. The electrical connector for aerospace vehicles of claim 1, wherein: The outer wall of the plug (2) is provided with a positioning plate (6), and the socket (1) is provided with a positioning groove (12) corresponding to the positioning plate (6).

7. The electrical connector for aerospace vehicles of claim 2, wherein: The sleeve (74) is threadedly connected with the externally threaded cylinder (73) through the internally threaded hole (741), the outer wall of the socket (1) is provided with a water-proof ring groove (14), and the socket (1) is rotatably connected with the sleeve (74) through the water-proof ring groove (14).

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