Aviation connector and chassis contact structure and assembly process method

Abstract

The application provides an aviation connector and a chassis contact structure and an assembling process method, which comprise: a chassis provided with a mounting through hole; an aviation connector arranged in the mounting through hole, and a flange part of the aviation connector arranged on the inner side of the chassis; a fixing clamp arranged on the inner side of the chassis, one end of the fixing clamp connected with the flange part of the aviation connector, and the other end of the fixing clamp connected with a printed board; and a copper sheet arranged between the one end of the fixing clamp and the flange part of the aviation connector. The aviation connector according to the embodiment of the application has the beneficial effects that the lap joint resistance between the aviation connector and the chassis is reduced to within 1 mΩ, a good discharge channel is provided for HIRF and lightning interference introduced by the aviation connector cable, and the anti-interference capability of the airborne product is improved.

Description

Technical Field

[0001] This invention relates to the field of grounding technology for airborne equipment, specifically to an aviation connector and chassis contact structure and assembly process. Background Technology

[0002] Proper grounding of airborne equipment measurement and acquisition systems is crucial for suppressing interference. During the design phase, correctly combining grounding and shielding can effectively eliminate the impact of external interference. The fundamental purpose of good grounding is to eliminate noise voltage generated when interference current flows through the common ground wire, and to protect against the effects of electromagnetic fields and ground potential differences, i.e., to prevent the formation of ground loops. GJB 1696-93, "Electromagnetic Compatibility and Grounding Requirements for Ground Facilities of Aerospace Systems," stipulates that the bridging resistance of power, signal, control, and lightning subsystems should not exceed 1mΩ.

[0003] The reference ground for the power supply circuits, signal circuits, and control circuits of airborne equipment is mostly the chassis housing. HIRF and lightning interference conduct energy to the connector through the shielding layer of the external wiring harness, flows through the chassis housing, and is guided to the aircraft frame via the chassis grounding strip / plate. The bridging resistance between the connector and the chassis housing plays a crucial role in the product's HIRF, lightning interference, and electromagnetic compatibility.

[0004] Common contact methods for aviation connectors and chassis housings:

[0005] 1. Typically, aviation connectors are connected to the chassis via conductive gaskets. These gaskets contain metal particles, with square and pure silver particles exhibiting the best conductivity. High-strength screws are used to tightly secure the connector, conductive gasket, and chassis. However, the lap resistance remains around 8 milliohms, failing to achieve proper grounding between the connector and chassis. This method places strict requirements on screw torque, hindering field maintenance and resulting in substandard lap resistance.

[0006] 2. Custom-made aviation connectors are used. The manufacturer leads a ground wire from the flange of the aviation connector, which is then connected to the chassis during assembly. However, actual measurements show that this grounding method results in a grounding resistance of approximately 3mΩ due to the long distance of the ground wire and the limited contact area between the ground wire and the chassis. Furthermore, custom-made aviation connectors are costly and time-consuming. Summary of the Invention

[0007] In view of this, embodiments of this specification provide an aviation connector and chassis contact structure and assembly process method to reduce the lap resistance between the aviation connector and the chassis housing.

[0008] This specification provides the following technical solution in its embodiments: an aviation connector and chassis contact structure, comprising: a chassis having a mounting through hole; an aviation connector passing through the mounting through hole, with the flange portion of the aviation connector located inside the chassis; a fixing clip located inside the chassis, one end of the fixing clip being connected to the flange portion of the aviation connector, and the other end of the fixing clip being connected to a printed circuit board; and a copper sheet disposed between one end of the fixing clip and the flange portion of the aviation connector.

[0009] Furthermore, the copper sheet can extend to the outside of one end of the retaining clip, and the copper sheet placed on the outside of the flange portion of the aviation connector at one end of the retaining clip contacts the inner side of the chassis.

[0010] Furthermore, the contact structure between the aviation connector and the chassis also includes a first locking assembly, which is sequentially connected to the chassis, the flange portion of the aviation connector, the copper sheet, and the retaining clip, and the first locking assembly can press the flange portion, the copper sheet, and the retaining clip of the aviation connector together.

[0011] Furthermore, a conductive sealing gasket is provided between the chassis and the flange portion of the aviation connector.

[0012] Furthermore, the copper plate placed at one end of the fixing clamp and on the outside of the flange portion of the aviation connector is fixedly connected to the chassis by bolts.

[0013] Furthermore, the pins of the aviation connector are soldered to the printed circuit board.

[0014] The present invention also provides an assembly process for assembling the above-mentioned aerospace connector and chassis contact structure, comprising the following steps:

[0015] Step 1: Tighten the aviation connector, conductive gasket, copper sheet and fixing clip to the chassis, and the torque of the connecting bolts should be greater than or equal to 0.68 Nm;

[0016] Step 2: Secure the copper plate, which is placed on the outside of the flange portion of the aviation connector, to the chassis using bolts.

[0017] Step 3: Solder the pins of the aviation connector to the printed circuit board;

[0018] Step 4: Tighten the fixing clip to the printed circuit board to secure it.

[0019] Compared with the prior art, the beneficial effects that can be achieved by at least one of the above-mentioned technical solutions adopted in the embodiments of this specification include: reducing the lap resistance between the aviation connector and the chassis to less than 1mΩ, providing a good discharge channel for HIRF and lightning interference introduced by aviation connector cables, and improving the anti-interference capability of airborne products. Attached Figure Description

[0020] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0021] Figure 1 This is a schematic diagram of the overall structure of an embodiment of the present invention;

[0022] Figure 2 This is a schematic diagram of the aviation connector structure according to an embodiment of the present invention.

[0023] The attached figures are labeled as follows: 10, chassis; 20, aviation connector; 30, fixing clip; 40, copper sheet; 50, conductive sealing gasket. Detailed Implementation

[0024] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0025] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0026] like Figure 1 and Figure 2 As shown, this embodiment of the invention provides an aviation connector and chassis contact structure, including a chassis 10, a conductive sealing gasket 50, an aviation connector 20, a fixing clip 30, and a copper sheet 40. The chassis 10 has a mounting through hole; the aviation connector 20 passes through the mounting through hole, and the flange portion of the aviation connector 20 is located inside the chassis 10; the conductive sealing gasket 50 is placed between the chassis and the flange of the aviation connector 20; the fixing clip 30 is located inside the chassis 10, one end of the fixing clip 30 is connected to the flange portion of the aviation connector 20, and the other end of the fixing clip 30 is connected to a printed circuit board; the copper sheet 40 is disposed between one end of the fixing clip 30 and the flange portion of the aviation connector 20.

[0027] By reducing the lap resistance between the aviation connector and the chassis to less than 1mΩ, a good discharge path is provided for HIRF and lightning interference introduced by aviation connector cables, thereby improving the anti-interference capability of airborne products.

[0028] It should be noted that the copper sheet 40 is made of a highly conductive material, enabling surface contact conductivity with the chassis and aviation connector. The retaining clip 30 is used to secure the aviation connector 20 to the printed circuit board, reducing the risk of breakage or reduced lifespan of the aviation connector 20 pins due to stress during module transfer.

[0029] The copper sheet 40 can extend to the outside of one end of the fixing clip 30, and the copper sheet 40 placed on the outside of the flange portion of the aviation connector 20 at one end of the fixing clip 30 contacts the inner side of the chassis 10, effectively reducing the resistance between the aviation connector 20 and the chassis.

[0030] This invention enables the integration of an aviation connector, copper plate, fixing clip, and printed circuit board into a single unit, allowing for rapid assembly and disassembly. Even after multiple disassemblies and reassemblies during module replacement or system assembly, the structure ensures that the copper plate maintains good contact with the connector housing, guaranteeing low impedance between the chassis and the connector housing.

[0031] Preferably, the contact structure between the aviation connector and the chassis further includes a first locking assembly, which sequentially connects the chassis 10, the flange portion of the aviation connector 20, the copper sheet 40, and the fixing clip 30, and the first locking assembly can press the flange portion of the aviation connector 20, the copper sheet 40, and the fixing clip 30 together.

[0032] Furthermore, a conductive sealing gasket 50 is provided between the chassis 10 and the flange portion of the aviation connector 20. The conductive sealing gasket 50, made of a highly malleable, low-resistance conductive sealing material, ensures tight contact between the aviation connector and the chassis, eliminating the influence of structural component machining tolerances on the chassis's sealing performance. It effectively shields against internal electromagnetic interference and external electromagnetic radiation, while also protecting against salt spray and mold corrosion.

[0033] One end of the fixing clip 30 is fixed to the outer side of the flange portion of the aviation connector 20 and the chassis 10 by bolts. The pins of the aviation connector 20 are soldered to the printed circuit board. The aviation connector 20 serves as a communication bridge between external signals and airborne equipment. The flange of the aviation connector 20 increases the contact area with the copper plate 40 while simultaneously securing it to the chassis housing.

[0034] The aviation connector 20 is positioned by using a fixing clip 30, a copper sheet 40, and a conductive sealing gasket 50 to weld the pins of the aviation connector 20. This effectively reduces the stress between the pins of the aviation connector 20 and the printed circuit board, while greatly increasing the ease of assembly and disassembly of the module.

[0035] In the embodiments of the present invention

[0036] The present invention also provides an assembly process for assembling the above-mentioned aviation connector and chassis contact structure, ensuring that the lap resistance between the aviation connector and the chassis is reduced to less than 1mΩ, comprising the following steps:

[0037] Step 1: Tighten the aviation connector, conductive sealing gasket 50, copper sheet 40 and fixing clip 30 to the chassis 10, and the torque of the connecting bolts is greater than or equal to 0.68 Nm;

[0038] Step 2: Secure the copper sheet 40, which is placed on the outside of the flange portion of the aviation connector 20, to the chassis 10 with bolts.

[0039] Step 3: Solder the pins of the aviation connector 20 to the printed circuit board;

[0040] Step 4: Tighten the fixing clip 30 to the printed circuit board.

[0041] After installing the aviation connector 20, conductive sealing gasket 50, copper sheet 40 and fixing clamp 30 into the chassis fixture, the PCB and aviation connector 20 are positioned and then soldered. This electrical assembly process sequence and method can effectively eliminate the elastic stress between the pins of the aviation connector 20 and the PCB, meeting the various harsh operating conditions of aviation airborne equipment.

[0042] Meanwhile, the malleability of the conductive sealing gasket 50 effectively solves the errors caused by chassis manufacturing tolerances and grounding installation methods. It also ensures tight contact between the aviation connector 20, copper sheet 40, structural components, and the chassis, effectively shielding internal electromagnetic interference and external electromagnetic radiation, while also protecting against salt spray and mold corrosion.

[0043] The above description is merely a specific embodiment of the present invention and should not be construed as limiting the scope of the invention. Therefore, any substitution of equivalent components or equivalent changes and modifications made within the scope of protection of this patent should still fall within the scope of this patent. Furthermore, the technical features, technical features and technical solutions, and technical solutions in this invention can be freely combined and used.

Claims

1. A contact structure between an aviation connector and a chassis, characterized in that, include: The chassis (10) is provided with mounting through holes; An aviation connector (20) is inserted into the mounting through hole, and the flange portion of the aviation connector (20) is located inside the housing (10); The fixing clip (30) is placed inside the chassis (10). One end of the fixing clip (30) is connected to the flange part of the aviation connector (20), and the other end of the fixing clip (30) is connected to the printed circuit board. A copper sheet (40) is disposed between one end of the fixing clamp (30) and the flange portion of the aviation connector (20); the copper sheet (40) can extend to the outside of one end of the fixing clamp (30), and the copper sheet (40) disposed between one end of the fixing clamp (30) and the flange portion of the aviation connector (20) contacts the inner side of the chassis (10); The contact structure between the aviation connector and the chassis also includes a first locking assembly, which sequentially connects the chassis (10), the flange portion of the aviation connector (20), the copper sheet (40), and the fixing clip (30), and the first locking assembly can press the flange portion of the aviation connector (20), the copper sheet (40), and the fixing clip (30) together; a conductive sealing gasket (50) is provided between the chassis (10) and the flange portion of the aviation connector (20).

2. The aviation connector and chassis contact structure according to claim 1, characterized in that, One end of the fixing clamp (30) is fixedly connected to the outer side of the flange portion of the aviation connector (20) and the chassis (10) by bolts.

3. The aviation connector and chassis contact structure according to claim 1, characterized in that, The pins of the aviation connector (20) are soldered to the printed circuit board.

4. An assembly process method for assembling the aviation connector and chassis contact structure as described in any one of claims 1 to 3, characterized in that, Includes the following steps: Step 1: Tighten the aviation connector, conductive sealing gasket (50), copper sheet (40) and fixing clip (30) to the chassis (10), and the torque of the connecting bolts shall be greater than or equal to 0.68 Nm; Step 2: Secure the copper sheet (40) placed on the outside of the flange portion of the aviation connector (20) and the chassis (10) with bolts. Step 3: Solder the pins of the aviation connector (20) to the printed circuit board; Step 4: Tighten the fixing clip (30) to the printed circuit board.

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