Search

CN-122000735-A - Aviation electric connector assembly

CN122000735ACN 122000735 ACN122000735 ACN 122000735ACN-122000735-A

Abstract

The invention relates to the field of electric connectors, in particular to an aviation electric connector assembly, which comprises a male connector and a female connector, wherein the end part of the male connector is fixedly connected with a mounting seat, the bottom end of the mounting seat is in annular array sealing sliding connection with a plurality of arc-shaped clamping blocks, a first spring is fixedly connected between the arc-shaped clamping blocks and the mounting seat, and an annular groove is formed in the inner wall of the female connector corresponding to the position of the arc-shaped clamping blocks. According to the invention, the arc-shaped clamping block, the first spring and the annular groove are arranged, when the arc-shaped clamping block is connected, the arc-shaped clamping block can be contracted only by pressing the button, the button is released after the arc-shaped clamping block is inserted into the groove to complete locking, when the arc-shaped clamping block is separated, the button is pressed again, the clamping block is contracted and withdrawn from the groove, and the whole operation action is simple and labor-saving, so that the time and the physical strength are saved.

Inventors

  • HUANG SHUANGWU
  • Gong Jiongwei

Assignees

  • 宁波宏武航空科技有限公司

Dates

Publication Date
20260508
Application Date
20260407

Claims (10)

  1. 1. An avionic electrical connector assembly, comprising: The novel connecting structure comprises a male connector (1) and a female connector (12), wherein the end part of the male connector (1) is fixedly connected with a mounting seat (2), a plurality of arc-shaped clamping blocks (3) are hermetically and slidably connected with an annular array at the bottom end of the mounting seat (2), a first spring (4) is fixedly connected between each arc-shaped clamping block (3) and the mounting seat (2), and an annular groove (1301) is formed in the inner wall of the female connector (12) at a position corresponding to each arc-shaped clamping block (3); The air groove (102) is formed in the male connector (1), the air groove (102) is communicated with the mounting seat (2) in an air flow mode, an annular sliding seat (5) is connected in a sliding mode in the air groove (102), a first piston (6) is fixedly connected to the end portion of the annular sliding seat (5), and the first piston (6) is connected in the air groove (102) in a sealing sliding mode; the two driving plates (7), the two driving plates (7) are symmetrically and fixedly connected to the side wall of the annular sliding seat (5), and a driving chute (701) is formed in the side wall of the driving plate (7); The two buttons (8), the position sliding connection that two buttons (8) correspond drive plate (7) is on male joint (1) lateral wall, fixedly connected with second spring (9) between button (8) and the male joint (1) lateral wall, button (8) bottom fixedly connected with link frame (10), link frame (10) bottom fixedly connected with slide pin (11), slide pin (11) sliding connection is in drive chute (701).
  2. 2. An avionics connector assembly according to claim 1, further comprising: The annular clamping seat (13), the annular clamping seat (13) is connected in the female connector (12) in a sliding manner, and the annular groove (1301) is formed in the annular clamping seat (13); When the temperature is increased, the driving assembly drives the annular clamping seat (13) to move reversely, the male connector (1) is pushed to move away from the female connector (12) through the arc-shaped clamping block (3), and when the temperature is reduced, the driving assembly drives the annular clamping seat (13) to move forward, and the male connector (1) is pulled to be close to the female connector (12) through the arc-shaped clamping block (3).
  3. 3. An avionic electrical connector assembly as defined in claim 2, wherein said drive assembly comprises: The heat conduction barrels (14) are fixedly connected in the female connector (12) in an annular array mode, inert gas is filled in the heat conduction barrels (14), a second piston (15) is connected in the heat conduction barrels (14) in a sealing sliding mode, and a first rack (16) is fixedly connected to the end portion of the second piston (15); The plurality of second racks (17) are connected in the female joint (12) in an annular array sliding manner, and a third spring (18) is fixedly connected between the second racks (17) and the annular clamping seat (13); and the transmission gear sets are respectively meshed with the first rack (16) and the second rack (17).
  4. 4. An avionic electrical connector assembly as claimed in claim 3, characterised in that the transmission gear set comprises a support (19), the support (19) is fixedly connected in the female connector (12), a first gear (20) is rotatably connected to the support (19), the first gear (20) is meshed with the bottom surface of the first rack (16), a second gear (21) is fixedly connected to the shaft of the first gear (20), the second gear (21) is meshed with the second rack (17), and the radius of the first gear (20) is larger than that of the second gear (21).
  5. 5. An avionics connector assembly according to claim 3, further comprising: The connecting shells (22) are fixedly connected in the female connector (12) in an annular array, a pushing plate (23) is connected in a sliding mode in the connecting shells (22), and a fourth spring (24) is fixedly connected between the pushing plate (23) and the connecting shells (22); And the limiting assembly is used for limiting the pushing plate (23), and when the joint temperature exceeds a threshold value, the limiting assembly releases the limit of the pushing plate (23).
  6. 6. The avionics connector assembly of claim 5, wherein the spacing assembly comprises: The clamping groove (2302) is formed in the side wall of the pushing plate (23), and a first pushing inclined plane is formed in the side wall of the pushing plate (23); the clamping block (25), clamping block (25) sliding connection is on connecting shell (22) lateral wall, fixedly connected with fifth spring (26) between clamping block (25) and connecting shell (22), clamping block (25) joint is in draw-in groove (2302), clamping block (25) set up the second promotion inclined plane with first promotion inclined plane looks adaptation.
  7. 7. The avionics connector assembly of claim 6, further comprising: The L-shaped pushing seat (27), the L-shaped pushing seat (27) is fixedly connected to the end part of the clamping block (25), and the side wall of the L-shaped pushing seat (27) is fixedly connected with a driving inclined seat (28); the L-shaped connecting frame (29), one end of the L-shaped connecting frame (29) is fixedly connected with the first rack (16), and a pushing roller (30) is fixedly connected with the other end of the L-shaped connecting frame (29) at a position corresponding to the driving inclined seat (28).
  8. 8. An avionic electrical connector assembly according to claim 1, wherein the male connector (1) end is fixedly connected with a first spacer (101) and the female connector (12) end is fixedly connected with a second spacer (1201).
  9. 9. An avionic electrical connector assembly according to claim 5, wherein the pushing plate (23) is fixedly connected at its end to a bumper pad (2301).
  10. 10. An avionic electrical connector assembly as claimed in claim 2, wherein the annular array of inner side walls of the female connector (12) defines a limit chute (1202), and the annular cartridge (13) is slidably connected to the limit chute (1202).

Description

Aviation electric connector assembly Technical Field The invention relates to the field of electric connectors, in particular to an aviation electric connector assembly. Background The aviation electric connector is an indispensable key element in the electric system of the aircraft, bears important tasks of signal transmission and electric power distribution, and the contact reliability of the aviation electric connector is directly related to the safety and success and failure of the flight task. For example, the invention patent with the application number of CN202410652230.X discloses an aerospace electric connector, which comprises a female plug structure and a male plug structure, wherein a female plug core head is arranged at the end of the female plug structure, a male plug core head is arranged at the end of the male plug structure, a first opening is formed at the end of the female plug structure, a second opening is formed at the end of the male plug structure, external threads are arranged on the surfaces of the outer walls of the female plug structure and the male plug structure, and a second thread sleeve is arranged on the surfaces of the outer walls of the female plug structure and the male plug structure. For the case, the defects that, for example, in the out-of-cabin activities, a astronaut needs to wear heavy out-of-cabin space suit gloves, the flexibility of fingers is greatly limited, the connection or the disassembly can be completed by repeatedly rotating for a plurality of circles in a threaded connection mode, the operation is laborious and time-consuming, the quick installation and separation are inconvenient, and the workload and the operation risk of the astronaut are increased. Accordingly, the present invention provides an avionic electrical connector assembly to solve the above-mentioned problems. Disclosure of Invention In order to achieve the purpose, the aviation electric connector component comprises a male connector and a female connector, wherein the end part of the male connector is fixedly connected with a mounting seat, a plurality of arc-shaped clamping blocks are hermetically and slidably connected with an annular array at the bottom end of the mounting seat, a first spring is fixedly connected between the arc-shaped clamping blocks and the mounting seat, and an annular groove is formed in the inner wall of the female connector at the position corresponding to the arc-shaped clamping blocks; The air groove is formed in the male connector, the air groove is communicated with the mounting seat in an air flow mode, an annular sliding seat is connected in a sliding mode in the air groove, a first piston is fixedly connected to the end portion of the annular sliding seat, and the first piston is connected in the air groove in a sealing sliding mode; the two driving plates are symmetrically and fixedly connected to the side wall of the annular sliding seat, and the side wall of each driving plate is provided with a driving chute; the two buttons are correspondingly connected to the outer side wall of the male connector in a sliding mode, a second spring is fixedly connected between the buttons and the outer side wall of the male connector, a linkage frame is fixedly connected to the bottom end of each button, a sliding pin is fixedly connected to the bottom end of each linkage frame, and the sliding pins are connected to the driving chute in a sliding mode. Preferably, the method further comprises: The annular clamping seat is connected in the female connector in a sliding manner, and the annular groove is formed in the annular clamping seat; When the temperature is reduced, the driving assembly drives the annular clamping seat to move forward, and the male connector is pulled to be close to the female connector through the arc-shaped clamping block. Preferably, the driving assembly includes: the heat conduction barrels are fixedly connected in the female connector in an annular array manner, inert gas is filled in the heat conduction barrels, a second piston is connected in a sealing sliding manner in the heat conduction barrels, and a first rack is fixedly connected to the end part of the second piston; the plurality of second racks are connected in the female joint in a sliding manner in an annular array manner, and a third spring is fixedly connected between the second racks and the annular clamping seat; And the transmission gear set is meshed with the first rack and the second rack respectively. Preferably, the transmission gear set comprises a support, the support is fixedly connected in the female joint, a first gear is rotationally connected to the support and meshed with the bottom surface of the first rack, a second gear is fixedly connected to the shaft of the first gear and meshed with the second rack, and the radius of the first gear is larger than that of the second gear. Preferably, the method further comprises: The plurality of connecting shells are fixe