Rapid verification device based on aviation line on-off fault and detection method thereof

Abstract

The invention relates to the technical field of equipment line fault detection, and provides an aviation line on-off fault rapid verification device and a detection method thereof.The aviation line on-off fault rapid verification device comprises a host main body, an extension main body and a socket, a T-shaped plate is fixedly installed on the host main body, and a T-shaped groove matched with the T-shaped plate for use is formed in the extension main body; the host machine body is provided with two groups of slots, and the extension machine body is provided with a group of slots. According to the invention, the socket is inserted into the slot, two groups of arc-shaped plates on the annular knob respectively enter two groups of positioning grooves, the annular knob is moved to drive the arc-shaped plates and the annular plate to move on the socket and enter the connecting groove, and the annular knob is rotated to drive the arc-shaped plates to enter the arc-shaped grooves, so that the installation of the socket is completed. And the condition that the detection efficiency of the aviation wire harness is reduced due to different interfaces of the wires is avoided.

Description

Technical Field

[0001] This invention relates to the field of equipment line fault detection technology, specifically to a rapid verification device for aviation line continuity faults and a detection method for the device. Background Technology

[0002] Aviation wiring harnesses often contain hundreds or even thousands of wires, with complex structures, multiple branches, and cross connections. Traditional multimeters require individual point-by-point measurement of each wire, necessitating manual insertion and removal of probes and switching of measurement points, making the process cumbersome. For avionics system wiring harnesses and engine wiring harnesses of large aircraft, testing a single harness can often take hours or even days, significantly reducing maintenance time and extending aircraft downtime.

[0003] Aircraft wiring harnesses, such as engine wiring harnesses and avionics system wiring harnesses, typically contain dozens to hundreds of wires. Because these wires have different interfaces, a multimeter is needed to connect different contacts when testing the wiring harness. This is not only time-consuming, but may also lead to missed or incorrect tests due to operator fatigue, thus reducing the efficiency of aviation wiring harness testing. Summary of the Invention

[0004] To address the shortcomings of existing technologies, this invention provides a rapid verification device for aviation line continuity faults, which solves the problem of reduced detection efficiency of aviation wiring harnesses due to different wire interfaces.

[0005] To achieve the above objectives, the present invention provides the following technical solution:

[0006] A rapid verification device for aviation line continuity faults includes a main body, a sub-body, and a socket. A T-shaped plate is fixedly installed on the main body, and a T-shaped groove for cooperating with the T-shaped plate is opened on the sub-body. Two sets of slots are opened on the main body, and one set of slots is opened on the sub-body.

[0007] The socket is equipped with a replacement device for easy replacement;

[0008] The main unit is equipped with a connecting device that facilitates the connection of the extension unit. After inserting the T-shaped plate into the T-shaped slot, the socket is inserted into the slot. As the socket moves, the connecting device limits the extension unit. Then, the moving and replacing device limits the socket.

[0009] Preferably, the replacement device includes an annular sliding groove formed on the socket, and four sets of No. 1 fixing rods are fixedly installed on the annular sliding groove, with a No. 1 spring sleeved on each set of No. 1 fixing rods.

[0010] Preferably, the replacement device further includes an annular plate slidably mounted on an annular sliding groove and slidably connected to a first fixing rod, an annular knob rotatably mounted on the annular plate, and two sets of arc-shaped plates fixedly mounted on the annular knob.

[0011] Preferably, the replacement device further includes a connecting groove formed on the main body and communicating with the slot, wherein the connecting groove is provided with two sets of positioning grooves, and each set of positioning grooves is provided with an arc-shaped groove.

[0012] Preferably, the connecting device includes a limiting groove formed on the main body of the host, two sets of second fixing rods are fixedly installed on the limiting groove, each set of second fixing rods is sleeved with a second spring, and a limiting plate that is slidably connected to the second fixing rod is slidably installed on the limiting groove.

[0013] Preferably, the connecting device further includes a limiting rod fixedly installed on the main body of the host, a No. 3 spring sleeved on the limiting rod, a positioning block slidably installed on the limiting rod and slidably connected to the main body of the host and the T-shaped plate, a connecting plate rotatably installed between the positioning block and the limiting plate, and an insertion hole for cooperating with the positioning block is opened on the T-shaped groove.

[0014] Preferably, one set of the sockets is equipped with a main unit plug, one set of the sockets is equipped with a sub-unit plug, and one set of the sockets is equipped with a power supply plug. Both the main unit and the sub-unit are equipped with multiple sets of indicator lights, and the sub-unit is equipped with multiple sets of fault lights.

[0015] A detection method based on a rapid verification device for continuity and disconnection faults in aviation lines, the method comprising the following steps:

[0016] Step 1: Connect the compatible battery to power on the device and observe the status of the fault light and wireless signal indicator light on the device panel. If the indicator lights show abnormalities, make a preliminary judgment on the possible fault types.

[0017] Step 2: Connect the main unit plug and the extension plug in sequence, turn on the corresponding switch of the line, and observe the indicator lights of the main and extension lines. If the indicator light goes out, turn on the switch again and judge whether there is a fault in the line based on the subsequent status of the indicator light.

[0018] Step 3: Wait for 3S to upload the test results to the system to complete one test process.

[0019] Compared with the prior art, the beneficial effects of the present invention are:

[0020] 1. This invention, through the setting of a replacement device, allows the socket to be inserted into the slot, and the two sets of arc-shaped plates on the ring knob to enter the two sets of positioning grooves respectively. Moving the ring knob causes the arc-shaped plates and the ring plate to move on the socket and enter the connecting groove. Rotating the ring knob causes the arc-shaped plates to enter the arc groove, thereby completing the installation of the socket. This avoids the situation where different wire interfaces reduce the detection efficiency of aviation wire harnesses.

[0021] 2. The present invention, through the setting of the connecting device, aligns the T-shaped slot on the main body of the sub-unit with the T-shaped plate on the main body of the host unit for insertion. When the socket is pulled out, the positioning block moves, causing it to move out of the main body of the host unit and into the socket, thereby completing the connection between the main and sub-units. This avoids the situation where the main and sub-units are easily separated after being placed in the testing box, which is time-consuming to find. Attached Figure Description

[0022] The accompanying drawings, which are included to provide a further understanding of this application and form part of this application, illustrate exemplary embodiments and are used to explain this application, but do not constitute an undue limitation of this application. In the drawings:

[0023] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0024] Figure 2 This is a schematic diagram showing the positional relationship between the socket and the annular knob of the present invention;

[0025] Figure 3 This is a schematic diagram showing the positional relationship between the annular knob and the annular plate of the present invention;

[0026] Figure 4 This is a schematic diagram of the overall structure of the internal parts of the host body of the present invention;

[0027] Figure 5 This is a schematic diagram showing the positional relationship between the T-slot and the insertion hole of the present invention;

[0028] Figure 6 This is a schematic diagram of the process framework of the present invention.

[0029] In the diagram: 1. Main unit body; 2. Sub-unit body; 3. Socket; 11. T-shaped plate; 21. T-shaped groove; 31. Slot; 4. Replacement device; 41. Annular sliding groove; 42. Fixed rod No. 1; 43. Spring No. 1; 44. Annular plate; 45. Annular knob; 46. Arc plate; 47. Connecting groove; 48. Positioning groove; 49. Arc groove; 5. Connecting device; 51. Limiting groove; 52. Fixed rod No. 2; 53. Spring No. 2; 54. Limiting plate; 55. Limiting rod; 56. Spring No. 3; 57. Positioning block; 58. Connecting plate; 59. Socket; 6. Main unit plug; 61. Sub-unit plug; 7. Power supply plug; 8. Indicator light; 81. Fault light. Detailed Implementation

[0030] The following will describe in detail the implementation of this application with reference to the accompanying drawings and embodiments, so that the implementation process of how this application uses technical means to solve technical problems and achieve technical effects can be fully understood and implemented accordingly.

[0031] Example 1

[0032] The different interfaces of the wires reduce the detection efficiency of aviation wire harnesses. To solve this problem, refer to... Figures 1-5 This embodiment proposes a rapid verification device for aviation line continuity faults, including a main unit 1, a sub-unit 2, and a socket 3. A plug for detecting wiring harnesses is installed on the socket 3. A T-shaped plate 11 is fixedly installed on the main unit 1. A T-shaped groove 21 that mates with the T-shaped plate 11 is opened on the sub-unit 2. Two sets of slots 31 are opened on the main unit, and one set of slots 31 is opened on the sub-unit 2. A main unit plug 6 is installed on one set of sockets 3 for connecting one end of the wiring harness. A sub-unit plug 61 is installed on one set of sockets 3 for connecting the other end of the wiring harness. A power supply plug 7 is installed on one set of sockets 3 for connecting an external power source. Multiple sets of indicator lights 8 are installed on both the main unit 1 and the sub-unit 2. Multiple sets of fault lights 81 are installed on the sub-unit 2.

[0033] The socket 3 is equipped with a replacement device 4 for easy replacement, and the main unit 1 is equipped with a connection device 5 for easy connection of the extension unit. After inserting the T-shaped plate 11 into the T-shaped groove 21, the socket 3 is inserted into the slot 31. As the socket 3 moves, the connection device 5 limits the extension unit 2. Then, the replacement device 4 is moved to limit the socket 3, so that the main unit and the extension unit are limited together.

[0034] The replacement device 4 includes an annular sliding groove 41 formed on the socket 3. Four sets of first-order fixing rods 42 are fixedly installed on the annular sliding groove 41 to make the movement of the annular plate 44 more stable. Each set of first-order fixing rods 42 is fitted with a first-order spring 43, allowing the annular plate 44 to quickly return to its original position. The replacement device 4 also includes an annular plate 44 slidably mounted on the annular sliding groove 41 and slidably connected to the first-order fixing rods 42. An annular knob 45 is rotatably mounted on the annular plate 44. Two sets of arc-shaped plates 46 are fixedly installed on the annular knob 45. The replacement device 4 also includes a... The connecting groove 47, which communicates with the slot 31, has two sets of positioning grooves 48. Each set of positioning grooves 48 has an arc-shaped groove 49. When the socket 3 is inserted into the slot 31, the two sets of arc-shaped plates 46 on the ring knob 45 enter the two sets of positioning grooves 48 respectively. Moving the ring knob 45 causes the arc-shaped plates 46 and the ring plate 44 to move on the socket 3 and enter the connecting groove 47. Rotating the ring knob 45 causes the arc-shaped plates 46 to enter the arc-shaped groove 49, thereby completing the installation of the socket 3. This avoids the situation where different wire interfaces reduce the detection efficiency of aviation wire harnesses.

[0035] Example 2

[0036] Because the main and sub-units tend to separate after being placed in the testing box, locating them is time-consuming. To solve this problem, refer to... Figures 1-5 The connecting device 5 includes a limiting groove 51 formed on the main body 1. Two sets of second-order fixing rods 52 are fixedly installed on the limiting groove 51 to make the movement of the limiting plate 54 more stable. A second-order spring 53 is sleeved on each set of second-order fixing rods 52 to enable the limiting plate 54 to quickly return to its original position. A limiting plate 54 that is slidably connected to the second-order fixing rods 52 is slidably installed on the limiting groove 51. The connecting device 5 also includes a limiting rod 55 fixedly installed on the main body 1. A third-order spring 56 is sleeved on the limiting rod 55 to enable the positioning block 57 to quickly return to its original position. A positioning block that is slidably connected to the main body 1 and the T-shaped plate 11 is slidably installed on the limiting rod 55. A connecting plate 58 is rotatably installed between block 57, positioning block 57 and limiting plate 54. The T-slot 21 has a socket 59 for use with positioning block 57. After the equipment is used, the T-slot 21 on the sub-unit body 2 is aligned with the T-plate 11 on the main unit body 1 and inserted. When the socket 3 is pulled out, the second spring 53 resets and drives the limiting plate 54 to move. Under the action of connecting plate 58 and third spring 56, the limiting plate 54 moves and drives the positioning block 57 to move, so that it moves out of the main unit body 1 and into the socket 59, thereby completing the connection between the main and sub-units. This avoids the situation where the main and sub-units are easily separated after being put into the test box, and it is time-consuming to find them.

[0037] Working principle: Insert the socket 3 into the slot 31. The two sets of arc plates 46 on the ring knob 45 enter the two sets of positioning slots 48 respectively. Move the ring knob 45 to make the arc plates 46 and the ring plate 44 move on the socket 3 and enter the connecting slot 47. Rotate the ring knob 45 to make the arc plates 46 enter the arc slot 49, thereby completing the installation of the socket 3. After the equipment is used, align the T-shaped slot 21 on the main body 2 with the T-shaped plate 11 on the main body 1 and insert it. When the socket 3 is pulled out, the second spring 53 resets and drives the limit plate 54 to move. Under the action of the connecting plate 58 and the third spring 56, the limit plate 54 moves and drives the positioning block 57 to move out of the main body 1 and into the socket 59, thereby completing the connection between the main and sub-units.

[0038] It should be noted that, in this document, the terms “comprising,” “including,” or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0039] Although embodiments of the 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 invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A rapid verification device for aviation line continuity faults, comprising a main unit (1), a sub-unit (2), and a socket (3), characterized in that, A T-shaped plate (11) is fixedly installed on the main body (1), and a T-shaped groove (21) for use with the T-shaped plate (11) is opened on the sub-unit body (2). Two sets of slots (31) are opened on the main body, and one set of slots (31) is opened on the sub-unit body (2). The socket (3) is equipped with a replacement device (4) for easy replacement; The main body (1) is equipped with a connecting device (5) for connecting the extension unit. After inserting the T-shaped plate (11) into the T-shaped groove (21), the socket (3) is inserted into the slot (31). As the socket (3) moves, the connecting device (5) limits the extension unit body (2). Then the moving replacement device (4) limits the socket (3).

2. The rapid verification device for aviation line continuity faults according to claim 1, characterized in that, The replacement device (4) includes an annular sliding groove (41) opened on the socket (3), and four sets of No. 1 fixing rods (42) are fixedly installed on the annular sliding groove (41), and a No. 1 spring (43) is sleeved on each set of No. 1 fixing rods (42).

3. The rapid verification device for aviation line continuity faults according to claim 2, characterized in that, The replacement device (4) further includes an annular plate (44) that is slidably mounted on the annular sliding groove (41) and slidably connected to the first fixing rod (42). An annular knob (45) is rotatably mounted on the annular plate (44), and two sets of arc plates (46) are fixedly mounted on the annular knob (45).

4. The rapid verification device for aviation line continuity faults according to claim 3, characterized in that, The replacement device (4) also includes a connecting groove (47) opened on the main body and communicating with the slot (31). Two sets of positioning grooves (48) are opened on the connecting groove (47), and each set of positioning grooves (48) is provided with an arc groove (49).

5. The rapid verification device for aviation line continuity faults according to claim 1, characterized in that, The connecting device (5) includes a limiting groove (51) opened on the main body (1). Two sets of second fixing rods (52) are fixedly installed on the limiting groove (51). A second spring (53) is sleeved on each set of second fixing rods (52). A limiting plate (54) that is slidably connected to the second fixing rod (52) is slidably installed on the limiting groove (51).

6. The rapid verification device for aviation line continuity faults according to claim 5, characterized in that, The connecting device (5) further includes a limiting rod (55) fixedly installed on the main body (1). A No. 3 spring (56) is sleeved on the limiting rod (55). A positioning block (57) that is slidably connected to the main body (1) and the T-shaped plate (11) is slidably installed on the limiting rod (55). A connecting plate (58) is rotatably installed between the positioning block (57) and the limiting plate (54). An insertion hole (59) that cooperates with the positioning block (57) is opened on the T-shaped groove (21).

7. The rapid verification device for aviation line continuity faults according to claim 1, characterized in that, One set of sockets (3) is equipped with a main unit plug (6), one set of sockets (3) is equipped with a sub-unit plug (61), one set of sockets (3) is equipped with a power supply plug (7), the main unit (1) and the sub-unit (2) are each equipped with multiple sets of indicator lights (8), and the sub-unit (2) is equipped with multiple sets of fault lights (81).

8. A detection method based on a rapid verification device for aviation line continuity faults, characterized in that: Step 1: Connect the compatible battery to power on the device and observe the status of the fault light (81) and wireless signal indicator (8) on the device panel. If the indicator (8) shows an abnormality, make a preliminary judgment on the possible fault type. Step 2: Connect the main unit plug (6) and the extension plug (61) in sequence, turn on the corresponding switch of the line, and observe the status of the main and extension line indicator lights (8). If the indicator light goes out, turn on the switch again and judge whether there is a fault in the line based on the subsequent status of the indicator light (8). Step 3: Wait for 3S to upload the test results to the system to complete one test process.

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