Aircraft cable connector test equipment

Abstract

The utility model relates to the technical field of aircraft accessory testing, and discloses aircraft cable connector testing equipment, which comprises a base, the top end of the base is rotatably connected with a bidirectional screw rod, two sides of the top end of the base are slidably connected with sliding tables, the sliding tables are in threaded connection with the bidirectional screw rod, the top ends of the sliding tables are fixedly provided with bearing tables, and the bearing tables are connected with the bidirectional screw rod. A clamping groove is formed in one side of the bearing platform, a groove is formed in the top of the clamping groove, a wiring terminal is connected to the interior of the clamping groove in a clamped mode, and a cable connector is connected to one side of the wiring terminal in a clamped mode; the two-way screw is driven by the driving assembly, the two-way screw can control the two sliding tables to move in opposite directions, the distance between the two bearing tables is increased, the wiring terminal can be conveniently placed between the two bearing tables, the two-way screw is reversely driven by the driving assembly, the wiring terminal can be clamped by the two bearing tables through the clamping grooves, and the wiring terminal can be conveniently placed on the two bearing tables. And the vertical displacement of the wiring terminal can be prevented through the arrangement of the groove.

Description

Technical Field

[0001] This utility model relates to the field of aircraft component testing technology, specifically to aircraft cable connector testing equipment. Background Technology

[0002] Cable connectors are mainly used for internal connections in various digital program-controlled exchanges and optoelectronic transmission equipment, as well as for signal transmission between patch panels. They are used to transmit data, audio, video, and other communication equipment. They are electrical connection devices specifically designed for use in aircraft and other high-end equipment. They are characterized by high voltage resistance, anti-interference, waterproofing, shock resistance, and corrosion resistance. They can maintain good electrical contact and signal transmission under high-intensity vibration, extreme temperatures, and harsh environments. Therefore, vibration testing is often required before use.

[0003] The "Vibration Testing Fixture and Vibration Testing Device" disclosed in application number "202021259997.X" "includes a test stage, a stage, an adjustable clamping element, and multiple fasteners. The test stage includes several mounting sides, each side having multiple fastening holes; the stage has a first through hole adapted to each fastening hole; the adjustable clamping element is placed on the stage and used to clamp the product to be tested; each fastener passes through the first through hole and the fastening hole to fix the stage to the test stage. During vibration testing, the vibration test results of electronic equipment in different directions can be observed without using different test fixtures, and multiple vibration test results in different directions can be detected on the same test stage, improving the versatility of the vibration testing fixture, reducing the number of fixtures used, and achieving the effect of reducing manufacturing costs."

[0004] However, the above method still has the following drawbacks: the adjustable clamping device can clamp the electronic product, but it requires the lead screw to drive the moving arm, which makes it difficult to achieve the self-locking of the lead screw. During vibration, the lead screw and the moving arm are prone to loosening, which will reduce the stability of the electronic product and affect the test accuracy. Utility Model Content

[0005] To address the shortcomings of existing technologies, this utility model provides an aircraft cable connector testing device, which has the advantages of good stability and high testing accuracy, and solves the problems mentioned in the background technology.

[0006] This utility model provides the following technical solution: an aircraft cable connector testing device, including a base, a bidirectional screw rotatably connected to the top of the base, slides slidably connected to both sides of the top of the base, the slides being threadedly connected to the bidirectional screw, a support fixedly provided at the top of the slides, a clamping groove provided on one side of the support, a bevel provided at the top of the clamping groove, a terminal engaged inside the clamping groove, a cable connector engaged on one side of the terminal, a drive assembly provided on one side of the top of the base, a vibration sensor fixedly installed in the middle of the top of the base, and a vibration assembly provided inside the base.

[0007] As a preferred embodiment of this utility model, the slide table has sliding grooves on both sides of its bottom end, and guide rails are fixedly provided on both sides of the top end of the base. The bottom end of the slide table is slidably connected to the guide rails through the sliding grooves, and a threaded sleeve is fixedly provided in the middle of the slide table. The threaded sleeve is threadedly connected to a bidirectional screw.

[0008] As a preferred embodiment of this utility model, the drive assembly includes a worm gear, both ends of which are rotatably connected to support plates. The bottom end of the support plate is fixedly connected to one side of the top of the base. The worm gear is meshed with a worm wheel, and the middle part of one side of the worm wheel is fixedly connected to one end of a bidirectional screw.

[0009] As a preferred embodiment of this utility model, a connecting shaft is fixedly provided at one end of the worm gear, a turntable is fixedly provided at one end of the connecting shaft, an eccentric shaft is fixedly provided on one side of the turntable, and a bushing is sleeved on the surface of the eccentric shaft.

[0010] As a preferred technical solution of this utility model, the base is fixedly provided with supports on both sides of the top end, and a stiffening plate is welded to one side of the support. The two ends of the bidirectional screw are respectively rotatably connected to the middle of one side of the two supports, and one side of the support plate is fixedly connected to the other side of one of the supports.

[0011] As a preferred embodiment of this utility model, a base plate is fixedly provided at the bottom end of the base, and mounting holes are provided at the four corners of the base plate. Two upright plates are fixedly provided at the top end of the base plate, and the top ends of the upright plates are fixedly connected to the base.

[0012] As a preferred embodiment of this utility model, the vibration assembly includes a vibration motor, a mounting plate is fixedly provided at the top of the vibration motor, a mounting base is fixedly connected to the top of the mounting plate by bolts, and the top of the mounting base is welded to the inner wall of the top of the base.

[0013] As a preferred embodiment of this utility model, a slot is provided in the middle of the top of the mounting plate, and a block is fixedly provided in the middle of the bottom of the mounting base, the block engaging with the inside of the slot.

[0014] Compared with the prior art, the present invention has the following beneficial effects:

[0015] 1. The bidirectional screw is driven by a drive assembly. The bidirectional screw can control the two slides to move in opposite directions, increasing the distance between the two supports. This makes it easier to place the terminal block between the two supports. The bidirectional screw is driven in the opposite direction by the drive assembly. The two supports can hold the terminal block through the clamping groove. The bevel design can prevent the vertical displacement of the terminal block and is suitable for terminal blocks of different heights. The operation is simple and convenient. After the cable connector is engaged with the terminal block, the drive assembly can achieve self-locking of the bidirectional screw, preventing displacement of the supports and loosening of the terminal block, thus ensuring test accuracy.

[0016] 2. By installing a vibration component inside the base, the vibration component can vibrate the base. The base can transmit the vibration to the aircraft cable connector through the support and terminal block, thus enabling vibration testing of the cable connector. By connecting the vibration sensor at the top of the base to a vibration meter, the amplitude and frequency environment of the cable connector can be monitored. Attached Figure Description

[0017] Figure 1 This is one of the structural schematic diagrams of this utility model;

[0018] Figure 2 This is the second structural schematic diagram of the present invention;

[0019] Figure 3 This is a schematic diagram of the structure of the foundation of this utility model;

[0020] Figure 4 This is a schematic diagram of the structure of the drive component of this utility model;

[0021] Figure 5 This is a schematic diagram of the structure of the vibration component of this utility model.

[0022] In the diagram: 1. Base; 2. Bidirectional screw; 3. Support; 4. Rib plate; 5. Drive assembly; 501. Worm gear; 502. Worm wheel; 503. Support plate; 504. Connecting shaft; 505. Turntable; 506. Eccentric shaft; 507. Bushing; 6. Slide table; 7. Threaded sleeve; 8. Bearing platform; 9. Gutter; 10. Bevel; 11. Slide groove; 12. Guide rail; 13. Vibration sensor; 14. Terminal block; 15. Base plate; 16. Vertical plate; 17. Vibration assembly; 1701. Vibration motor; 1702. Mounting plate; 1703. Mounting base; 1704. Slot; 1705. Locking block. Detailed Implementation

[0023] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0024] Please see Figures 1-5 The aircraft cable connector testing equipment includes a base 1, a bidirectional screw 2 rotatably connected to the top of the base 1, and slides 6 slidably connected to both sides of the top of the base 1. The slides 6 are threadedly connected to the bidirectional screw 2. A support 8 is fixedly provided on the top of the slides 6. A clamping groove 9 is provided on one side of the support 8. A bevel 10 is provided on the top of the clamping groove 9. A terminal block 14 is engaged inside the clamping groove 9. A cable connector is engaged on one side of the terminal block 14. A drive assembly 5 is provided on one side of the top of the base 1 to drive the bidirectional screw 2. The bidirectional screw 2 is driven by the drive assembly 5. The screw 2, a bidirectional screw 2, can control the two slides 6 to move in opposite directions, increasing the distance between the two supports 8, making it easier to place the terminal 14 between the two supports 8. The bidirectional screw 2 is driven in the opposite direction by the drive assembly 5. The two supports 8 can hold the terminal 14 through the clamping groove 9. The bevel 10 can prevent the vertical displacement of the terminal 14 and is suitable for use with terminal 14 of different heights. A vibration sensor 13 is fixedly installed in the middle of the top of the base 1. The base 1 is equipped with a vibration assembly 17 that vibrates the terminal 14.

[0025] In this embodiment, preferably, the drive assembly 5 includes a worm gear 501, with support plates 503 rotatably connected to both ends of the worm gear 501. The bottom end of the support plate 503 is fixedly connected to one side of the top of the base 1. A worm wheel 502 is meshed with the worm gear 501, and the middle part of one side of the worm wheel 502 is fixedly connected to one end of the bidirectional screw 2. A connecting shaft 504 is fixedly provided at one end of the worm gear 501, and a turntable 505 is fixedly provided at one end of the connecting shaft 504. An eccentric shaft 506 is fixedly provided on one side of the turntable 505, and a sleeve is provided on the surface of the eccentric shaft 506. The base 1 has a bushing 507, and supports 3 are fixedly provided on both sides of the top. A stiffening plate 4 is welded to one side of the support 3. The two ends of the double screw 2 are rotatably connected to the middle of one side of the two supports 3 respectively. One side of the support plate 503 is fixedly connected to the other side of one of the supports 3. By rotating the eccentric shaft 506 through the bushing 507, the turntable 505 can be driven to rotate. The turntable 505 can drive the worm gear 501 to rotate. The worm gear 501 can drive the double screw 2 to rotate through the worm wheel 502, so that the distance between the two slides 6 can be adjusted in the center.

[0026] In this embodiment, preferably, the vibration assembly 17 includes a vibration motor 1701. A mounting plate 1702 is fixedly provided at the top of the vibration motor 1701. A mounting base 1703 is fixedly connected to the top of the mounting plate 1702 by bolts. The top of the mounting base 1703 is welded to the inner wall of the top of the base 1. A slot 1704 is provided in the middle of the top of the mounting plate 1702. A locking block 1705 is fixed in the middle of the bottom of the mounting base 1703. The locking block 1705 is engaged with the inside of the slot 1704. The vibration motor 1701 can be fixed by the mounting base 1703 and the mounting plate 1702. The vibration motor 1701 can vibrate the base 1. The base 1 can transmit the vibration to the aircraft cable connector. By engaging the locking block 1705 with the slot 1704, the firmness and stability between the mounting plate 1702 and the mounting base 1703 can be improved.

[0027] In this embodiment, preferably, the slide table 6 has slide grooves 11 on both sides of its bottom end, and guide rails 12 are fixed on both sides of the top end of the base 1. The bottom end of the slide table 6 is slidably connected to the guide rails 12 through the slide grooves 11. A threaded sleeve 7 is fixedly provided in the middle of the slide table 6. The threaded sleeve 7 is threadedly connected to the bidirectional screw 2. The rotational motion of the bidirectional screw 2 can be converted into the linear motion of the slide table 6 through the threaded sleeve 7. The slide grooves 11 and guide rails 12 can guide the slide table 6 and prevent the slide table 6 from tilting.

[0028] In this embodiment, preferably, a base plate 15 is fixedly provided at the bottom end of the base 1, and mounting holes are provided at the four corners of the base plate 15. Two upright plates 16 are fixedly provided at the top end of the base plate 15, and the top ends of the upright plates 16 are fixedly connected to the base 1. The base 1 can be fixedly installed through the base plate 15, and the base 1 and the base plate 15 can be reinforced through the upright plates 16.

[0029] In use, the base plate 15 is first fixedly installed through the mounting holes. The base plate 15 can limit the position of the base 1. When vibration testing of the aircraft cable connector is required, the eccentric shaft 506 is rotated through the bushing 507 of the drive assembly 5. The eccentric shaft 506 can drive the turntable 505 to rotate. The turntable 505 can drive the worm gear 501 to rotate. The worm gear 501 can drive the double screw 2 to rotate through the worm wheel 502. The double screw 2 can control the two slides 6 to move in opposite directions, increasing the distance between the two supports 8. Then, the terminal 14 is placed between the two supports 8, and the double screw 2 is rotated in the opposite direction. The two supports 8 can clamp the terminal 14 through the clamping groove 9. The loosening bevel 10 can prevent the vertical displacement of the terminal 14 and is suitable for use with terminal 14 of different heights.

[0030] After the terminal 14 is fixed, the worm 501 can achieve self-locking of the bidirectional screw 2 through the worm wheel 502, which prevents the terminal 14 from loosening and falling off. After the tester engages the cable connector with the terminal 14, the vibration motor 1701 of the vibration assembly 17 vibrates the base 1. The base 1 can transmit the vibration to the aircraft cable connector through the support 8 and the terminal 14, so that the vibration test of the cable connector can be carried out. The tester connects the vibration sensor 13 to the existing vibration meter, which can monitor the amplitude and frequency environment of the cable connector. After the test, the cable connector is unplugged and the bidirectional screw 2 is rotated again to remove the terminal 14.

[0031] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. An aircraft cable connector testing device, comprising a base (1), characterized in that: The top of the base (1) is rotatably connected to a bidirectional screw (2). Both sides of the top of the base (1) are slidably connected to a slide (6). The slide (6) is threadedly connected to the bidirectional screw (2). The top of the slide (6) is fixedly provided with a support (8). A clamping groove (9) is provided on one side of the support (8). A bevel (10) is provided on the top of the clamping groove (9). A terminal block (14) is engaged inside the clamping groove (9). A cable connector is engaged on one side of the terminal block (14). A drive assembly (5) is provided on one side of the top of the base (1). A vibration sensor (13) is fixedly installed in the middle of the top of the base (1). A vibration assembly (17) is provided inside the base (1).

2. The aircraft cable connector testing equipment according to claim 1, characterized in that: The slide table (6) has sliding grooves (11) on both sides of its bottom end, and guide rails (12) are fixed on both sides of the top end of the base (1). The bottom end of the slide table (6) is slidably connected to the guide rails (12) through the sliding grooves (11). A threaded sleeve (7) is fixed in the middle of the slide table (6), and the threaded sleeve (7) is threadedly connected to the bidirectional screw (2).

3. The aircraft cable connector testing equipment according to claim 1, characterized in that: The drive assembly (5) includes a worm gear (501), both ends of which are rotatably connected to a support plate (503). The bottom end of the support plate (503) is fixedly connected to one side of the top of the base (1). The worm gear (501) is meshed with a worm wheel (502), and the middle part of one side of the worm wheel (502) is fixedly connected to one end of a bidirectional screw (2).

4. The aircraft cable connector testing equipment according to claim 3, characterized in that: One end of the worm gear (501) is fixedly provided with a connecting shaft (504), one end of the connecting shaft (504) is fixedly provided with a turntable (505), one side of the turntable (505) is fixedly provided with an eccentric shaft (506), and a bushing (507) is sleeved on the surface of the eccentric shaft (506).

5. The aircraft cable connector testing equipment according to claim 3, characterized in that: The base (1) has two fixed supports (3) on both sides of its top end. A stiffening plate (4) is welded to one side of the support (3). The two ends of the bidirectional screw (2) are rotatably connected to the middle of one side of the two supports (3). One side of the support plate (503) is fixedly connected to the other side of one of the supports (3).

6. The aircraft cable connector testing equipment according to claim 1, characterized in that: The bottom end of the base (1) is fixedly provided with a base plate (15), and the four corners of the base plate (15) are provided with mounting holes. The top end of the base plate (15) is fixedly provided with two upright plates (16), and the top end of the upright plates (16) is fixedly connected to the base (1).

7. The aircraft cable connector testing equipment according to claim 1, characterized in that: The vibration assembly (17) includes a vibration motor (1701), and a mounting plate (1702) is fixedly provided at the top of the vibration motor (1701). A mounting base (1703) is fixedly connected to the top of the mounting plate (1702) by bolts. The top of the mounting base (1703) is welded to the inner wall of the top of the base (1).

8. The aircraft cable connector testing equipment according to claim 7, characterized in that: The mounting plate (1702) has a slot (1704) at the center of its top end, and a locking block (1705) is fixedly provided at the center of the bottom end of the mounting base (1703). The locking block (1705) is engaged with the slot (1704).

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