Airplane wire harness joint fixing device

Abstract

The utility model provides an aircraft wire harness joint fixing device, and relates to the technical field of wire harness joint fixation, the aircraft wire harness joint fixing device comprises a fixing block body, two installation auxiliary block bodies are slidably installed on the outer circumferential surface of the fixing block body, and by means of four limiting abutting blocks, an aircraft wire harness joint inserted into an insertion hole site is accurately limited and clamped, and the installation auxiliary block bodies are installed on the outer circumferential surface of the fixing block body. When the position of the fixed block body needs to be fixed, the positions of the two installation auxiliary block bodies can be rotationally adjusted along the peripheral surface of the fixed block body by virtue of a sliding installation cooperation mechanism between the limiting sliding block and the limiting sliding groove according to the actual position condition of a specific area for fixed installation in the installed end surface; therefore, the two installation auxiliary block bodies are respectively and accurately rotated to the area which is provided by the current installation end face and can be used for fixed installation, the individual requirement of a specific fixed installation area is effectively met, and the problem that when an existing wiring harness connector with the movable characteristic is fixedly installed, a special fixing structure matched with the wiring harness connector is lacked is solved.

Description

Technical Field

[0001] This utility model relates to the field of wire harness connector fixing technology, and in particular to an aircraft wire harness connector fixing device. Background Technology

[0002] Within the complex and sophisticated electrical architecture of aircraft, there exists a unique requirement: certain wiring harness connectors must be able to flexibly and precisely change their positions according to changes in actual application scenarios. This is because various systems within an aircraft are interconnected and operate in diverse modes. For example, in the integrated cabling of avionics equipment, some wiring harness connectors need to change positions when switching between different equipment modules or adjusting functions to ensure the efficiency and stability of signal transmission.

[0003] However, for these movable wire harness connectors, a thorny problem arises when they are located in specific positions and require secure fixing: the lack of a dedicated fixing structure. This deficiency makes it difficult for installers to find suitable means to ensure the reliable fixing of the wire harness connectors in specific positions, potentially affecting the safety and stability of the entire electrical system.

[0004] Furthermore, due to the diversity of internal aircraft equipment and the variability of mission requirements, the installation locations of these wiring harness connectors often need to be changed frequently. Currently used fasteners, because their locking holes are fixed in the initial design, cannot be dynamically adjusted according to the specific requirements of different installation locations. This means that when moving them from one installation location to another, the locking holes may not be compatible with the installation reference or structure of that location, potentially failing to effectively secure them. This not only increases the difficulty and time cost of installation but may also lead to electrical connection failures due to insecure fixing, posing a potential threat to aircraft flight safety. Utility Model Content

[0005] This utility model relates to an aircraft wire harness connector fixing device, which at least partially solves the problem of the lack of a special fixing structure adapted to the fixing and installation of wire harness connectors with movable characteristics.

[0006] This utility model provides an aircraft wire harness connector fixing device, specifically including: a fixing block, the fixing block having a circular block structure, and a plug-in hole for the wire harness connector to be inserted through the central part of the fixing block; a limiting groove having a ring groove structure on the outer peripheral surface of the fixing block, and the limiting groove having an isosceles trapezoidal longitudinal cross-section; two mounting auxiliary blocks having an arc-shaped block structure slidably mounted on the outer peripheral surface of the fixing block, and each mounting auxiliary block having a limiting slider having an arc-shaped block structure and an isosceles trapezoidal longitudinal cross-section, the limiting slider slidingly engaging with the limiting groove; and a mounting notch having a mounting notch having a countersunk through hole penetrating the rear end face of each mounting auxiliary block having an inner rear side of the mounting notch.

[0007] Furthermore, the inner side of the mounting notch facing the limiting slider has a receiving groove b, which is circular in shape. A threaded through hole b penetrating the inner circumference of the limiting slider is provided at the axial center of the receiving groove b. A set of locking bolts a is installed in the threaded through hole b, with the head of the locking bolts a located inside the receiving groove b. When the locking bolts a are locked along the threaded through hole b, the stud end of the locking bolts a is in close contact with the inner end face of the limiting slider groove.

[0008] Furthermore, the inner end face of the limiting slide groove is provided with four storage slots a in a ring array. The storage slots a are circular slot structures. Each of the four storage slots a has a threaded through hole a connected to the insertion hole at its axial center. A set of locking bolts b is installed in the threaded through hole a, and the head of the locking bolts b is located inside the storage slot a.

[0009] Furthermore, a limiting and pressing block is provided on the inner circumferential surface of the insertion hole relative to the four threaded through holes b. The limiting and pressing block has an arc-shaped block structure, and the outer circumferential surface of the limiting and pressing block has the same diameter as the inner circumferential surface of the insertion hole. A groove is opened at the top center of the outer circumferential surface of each of the four limiting and pressing blocks. The groove has a circular groove structure.

[0010] Furthermore, an extension post is fixedly installed at the bottom of the stud end of the locking bolt b; the extension post is located inside the groove and is rotatably connected to the groove through a set of bearings.

[0011] This utility model provides an aircraft wire harness connector fixing device, which has the following beneficial effects:

[0012] This utility device utilizes four limiting and pressing blocks to precisely clamp and limit the aircraft wiring harness connector inserted into the insertion hole, thereby achieving a temporary and stable connection between the aircraft wiring harness connector and the fixing block. When it is necessary to fix the position of the fixing block, the two mounting auxiliary blocks can be flexibly rotated and adjusted along the outer circumference of the fixing block according to the actual position of the specific area available for fixing on the mounting end face, thanks to the sliding installation cooperation mechanism between the limiting slider and the limiting groove. In this way, the two mounting auxiliary blocks can be precisely rotated to the area available for fixing on the current mounting end face, effectively meeting the personalized needs of specific fixing installation areas and successfully locking the position of the fixing block. Based on the reliable fixing installation of the fixing block and the aircraft wiring harness connector, and combined with the stable fixing installation process of the fixing block itself, this application comprehensively and efficiently realizes the overall fixing installation of the aircraft wiring harness connector, providing great convenience for its subsequent connection applications and effectively ensuring the stable operation and efficient work of related systems. Attached Figure Description

[0013] To more clearly illustrate the technical solutions of the embodiments of this utility model, the accompanying drawings of the embodiments will be briefly described below.

[0014] The accompanying drawings described below are only related to some embodiments of the present invention and are not intended to limit the scope of the invention.

[0015] In the attached diagram:

[0016] Figure 1 A schematic diagram of the isometric structure of this application is shown;

[0017] Figure 2 This paper shows a schematic diagram of the isometric structure in the split state of this application;

[0018] Figure 3 A cross-sectional structural schematic diagram of this application is shown;

[0019] Figure 4 This application shows Figure 3 A magnified view of the structure at point A in the middle;

[0020] Figure 5 This application shows Figure 4 Schematic diagram of the structure with the middle limit block removed;

[0021] Figure 6 This application shows Figure 3 A magnified schematic diagram of the structure at point B in the middle;

[0022] Figure 7 This application shows Figure 6 Schematic diagram of the structure with the locking bolt a removed;

[0023] List of reference numerals

[0024] 1. Fixed block; 101. Insertion hole; 102. Limiting groove; 103. Storage groove a; 104. Threaded through hole a;

[0025] 2. Install auxiliary blocks; 201. Install mating notch; 202. Limiting slider; 203. Countersunk through hole; 204. Locking bolt a; 205. Storage groove b; 206. Threaded through hole b;

[0026] 3. Limiting and pressing block; 301. Locking bolt b; 302. Groove; 303. Bearing; 304. Extension column. Detailed Implementation

[0027] To make the objectives, technical solutions, and advantages of this utility model clearer, the technical solutions of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this utility model. All other embodiments obtained by those skilled in the art based on the described embodiments of this utility model without creative effort are within the scope of protection of this utility model.

[0028] Example: Please refer to Figures 1 to 7 :

[0029] This embodiment proposes an aircraft wire harness connector fixing device, comprising: a fixing block 1, which is a circular block structure, and a plug-in hole 101 for the wire harness connector to be inserted through the central part of the fixing block 1; a limiting groove 102 is formed on the outer peripheral surface of the fixing block 1, which is an annular groove structure and has an isosceles trapezoidal longitudinal section; two mounting auxiliary blocks 2 are slidably mounted on the outer peripheral surface of the fixing block 1, which are arc-shaped blocks, and a limiting slider 202 is fixedly mounted on the inner peripheral surface of each of the two mounting auxiliary blocks 2, which are arc-shaped blocks. The limiting slider 202 has an isosceles trapezoidal longitudinal cross-section and slides with the limiting groove 102. Each of the two mounting auxiliary blocks 2 has a mounting notch 201 on its front end face, and a countersunk through hole 203 penetrating the rear end face of each of the two mounting notches 201. A receiving groove b205 is formed on the inner side of the mounting notch 201 facing the limiting slider 202. The receiving groove b205 is circular, and a threaded through hole b206 penetrating the inner circumference of the limiting slider 202 is formed at the axial center of the receiving groove b205. A set of locking bolts a204 are installed on the internal thread of b206, with the head of the locking bolts a204 located inside the receiving groove b205. When the locking bolts a204 are locked along the threaded through hole b206, the stud end of the locking bolts a204 is in close contact with the inner end face of the limiting slide groove 102. The inner end face of the limiting slide groove 102 has four receiving grooves a103 arranged in a circular array. The receiving grooves a103 have a circular groove structure, and each of the four receiving grooves a103 has a threaded through hole a104 connected to the insertion hole 101 at its axial center. A set of locking bolts b301 are installed on the internal thread of the threaded through hole a104. Furthermore, the head of the locking bolt b301 is located inside the receiving groove a103; a limiting pressure block 3 is provided on the inner circumferential surface of the insertion hole 101 relative to the four threaded through holes b206. The limiting pressure block 3 has an arc-shaped block structure, and the outer circumferential surface of the limiting pressure block 3 has the same diameter as the inner circumferential surface of the insertion hole 101. A groove 302 is opened at the top center of the outer circumferential surface of each of the four limiting pressure blocks 3. The groove 302 has a circular groove structure; an extension post 304 is fixedly installed at the bottom of the stud end of the locking bolt b301; the extension post 304 is located inside the groove 302 and is rotatably connected to the groove 302 through a set of bearings 303.

[0030] The working principle of this embodiment:

[0031] First, insert the aircraft wiring harness connector, whose position needs to be moved according to actual requirements, into the insertion hole 101, leaving its rear half inside the insertion hole 101. Then, the operator uses a tool to rotate the locking bolt b301 downwards along the threaded through hole a104. As the locking bolt b301 rotates downwards along the threaded through hole a104, it simultaneously moves the limiting pressure block 3 closer to the center area of ​​the insertion hole 101 until the inner circumferential surface of the limiting pressure block 3 is in contact with the aircraft wiring harness connector inserted through the insertion hole 101. When the outer end faces of the half-sections come into contact, the threaded through hole a104 continues to rotate the locking bolt b301 downwards. With the cooperation of the bearing 303, the rotational motion of the locking bolt b301 is converted into linear motion, thereby pushing the limiting pressure block 3 to continue moving until the limiting pressure block 3 is tightly attached to the outer end face of the rear half-section of the aircraft wiring harness connector. When all four limiting pressure blocks 3 are tightly attached to the outer end face of the rear half-section of the aircraft wiring harness connector, the aircraft wiring harness connector is fixedly installed inside the insertion hole 101.

[0032] Once the location of the aircraft wiring harness connector is determined, and its position needs to be fixed, the two mounting auxiliary blocks 2 are adjusted by rotating along the outer circumference of the fixing block 1, based on the area available for fixing on the current mounting end face. This is achieved through the sliding engagement of the limiting slider 202 and the limiting groove 102. The two mounting auxiliary blocks 2 are then rotated to the area available for fixing on the current mounting end face. At this point, the operator can use a tool to rotate the locking bolt a204 along the threaded through hole b206, thus tightening the screw of the locking bolt a204. The column end is in close contact with the inner end face of the limiting slide groove 102, thereby limiting and fixing the position of the two mounting auxiliary blocks 2. After the position of the two mounting auxiliary blocks 2 is fixed, screws and other fasteners can be inserted through the countersunk through hole 203 and fixedly connected to the mounting end face to fix the position of the fixing block 1. Based on the above-mentioned fixed installation of the fixing block 1 and the aircraft wiring harness connector and the fixed installation of the fixing block 1 itself, the fixed installation operation of the aircraft wiring harness connector is realized, which facilitates its subsequent connection and application.

[0033] The following points should be noted in this article:

[0034] 1. The accompanying drawings of the embodiments disclosed herein only relate to the structures involved in the embodiments disclosed herein; other structures can be referred to in general design.

[0035] 2. Where there is no conflict, the embodiments of this disclosure and the features in the embodiments can be combined with each other to obtain new embodiments.

[0036] The above are merely specific embodiments of this disclosure, but the scope of protection of this disclosure is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in this disclosure should be included within the scope of protection of this disclosure.

Claims

1. An aircraft wire harness connector securing device, comprising: Include: Fixed block (1), the fixed block (1) axial part is provided with a plug hole (101) for wire harness connector insertion; The outer peripheral surface of the fixed block (1) is provided with a limiting sliding groove (102), and the outer peripheral surface of the fixed block (1) is slidably provided with two installation auxiliary blocks (2), the inner peripheral surface of the two installation auxiliary blocks (2) is fixedly provided with a limiting sliding block (202), the limiting sliding block (202) is arc block structure, and the limiting sliding block (202) is slidably installed with the limiting sliding groove (102); The front end surface of the two installation auxiliary blocks (2) is provided with a mounting matching slot (201), and the inner end rear surface of the two mounting matching slots (201) is provided with a countersunk through hole (203) penetrating through the rear end surface of the installation auxiliary block (2).

2. An aircraft wire harness junction fixture as defined in claim 1, wherein, The inner end side of the mounting matching slot (201) is provided with a receiving groove b (205) towards the limiting sliding block (202), and the axial part of the receiving groove b (205) is provided with a threaded hole b (206) penetrating through the inner peripheral surface of the limiting sliding block (202); A group of locking bolts a (204) are screwed in the threaded hole b (206), and the head end of the locking bolt a (204) is located in the receiving groove b (205); When the locking bolt a (204) is in the threaded locking state along the threaded hole b (206), the threaded end of the locking bolt a (204) is closely attached to the inner end surface of the limiting sliding groove (102).

3. An aircraft wire harness junction fixture as defined in claim 2, wherein, The inner end surface of the limiting sliding groove (102) is annular array and is provided with four receiving grooves a (103), and the axial part of the four receiving grooves a (103) is provided with a threaded hole a (104) communicated with the plug hole (101); A group of locking bolts b (301) are screwed in the threaded hole a (104), and the head end of the locking bolt b (301) is located in the receiving groove a (103).

4. An aircraft wire harness junction fixture as defined in claim 3, wherein, The inner peripheral surface of the plug hole (101) is provided with a limiting pressing block (3) relative to the four threaded holes b (206), the outer peripheral surface of the limiting pressing block (3) is consistent with the diameter of the inner peripheral surface of the plug hole (101), and the outer peripheral surface of the four limiting pressing blocks (3) is provided with a groove (302) at the top center.

5. An aircraft wire harness junction fixture as defined in claim 4, wherein, The threaded end of the locking bolt b (301) is fixedly provided with an extension column (304); The extension column (304) is located in the groove (302) and is rotatably connected with the groove (302) through a group of bearings (303).

6. An aircraft wire harness junction fixture as defined in any one of claims 1-5, wherein, The limiting sliding groove (102) is annular groove structure, and the longitudinal section of the limiting sliding groove (102) is isosceles trapezoidal structure; The longitudinal section of the limiting sliding block (202) is isosceles trapezoidal structure.

Images