CN113964557A - Installation corrosion protection structure of airplane high-current grounding wire - Google Patents
Installation corrosion protection structure of airplane high-current grounding wire Download PDFInfo
- Publication number
- CN113964557A CN113964557A CN202111121907.XA CN202111121907A CN113964557A CN 113964557 A CN113964557 A CN 113964557A CN 202111121907 A CN202111121907 A CN 202111121907A CN 113964557 A CN113964557 A CN 113964557A
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- China
- Prior art keywords
- wire
- aircraft
- corrosion protection
- sealant
- installation
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R4/00—Electrically-conductive connections between two or more conductive members in direct contact, i.e. touching one another; Means for effecting or maintaining such contact; Electrically-conductive connections having two or more spaced connecting locations for conductors and using contact members penetrating insulation
- H01R4/58—Electrically-conductive connections between two or more conductive members in direct contact, i.e. touching one another; Means for effecting or maintaining such contact; Electrically-conductive connections having two or more spaced connecting locations for conductors and using contact members penetrating insulation characterised by the form or material of the contacting members
- H01R4/64—Connections between or with conductive parts having primarily a non-electric function, e.g. frame, casing, rail
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
- H01R4/00—Electrically-conductive connections between two or more conductive members in direct contact, i.e. touching one another; Means for effecting or maintaining such contact; Electrically-conductive connections having two or more spaced connecting locations for conductors and using contact members penetrating insulation
- H01R4/28—Clamped connections, spring connections
- H01R4/30—Clamped connections, spring connections utilising a screw or nut clamping member
Abstract
The application provides an installation corrosion protection structure of aircraft heavy current ground connection electric wire, protective structure includes: an aircraft airframe structure; a wire terminal for connecting a wire; the switching bracket is used for connecting the airplane body structure and the wire connector; the switching support and the airplane body structure are made of different metal materials, the switching support is connected with the airplane body structure and/or the wire connector through a connecting piece, contact surfaces between the switching support and the airplane body structure and/or the wire connector are polished, a sealant is sprayed around contact gaps between the switching support and the wire connector and/or the airplane body structure, and the sealant uniformly permeates into the contact gaps. The installation corrosion protection structure of the large-current grounding wire of the airplane can ensure that the grounding installation work of an EWIS system on the airplane has good electrical performance in a severe environment area, and can effectively prevent the installation corrosion.
Description
Technical Field
The application belongs to the technical field of aircraft maintenance, and particularly relates to an installation corrosion protection structure of a large-current grounding wire of an aircraft.
Background
Because of the heavy load on the aircraft, a large-current grounding wire exists on the aircraft. The large-current grounding wire on the airplane is generally directly connected and installed with a main structure of the airplane, but in the design method, a wire joint of the large-current grounding wire and a main structure substrate of the airplane may have dissimilar metal contact and connection gaps, so that contact corrosion, gap corrosion and the like can be caused in a region with a severe environment.
In order to avoid the problem that the direct installation of the large-current grounding wire on the aircraft body structure causes the body structure substrate to be seriously corroded, and the integrity of the aircraft structure is damaged, so that the flight safety is caused and the service life of the aircraft is influenced, an installation corrosion structure is needed to avoid the problem.
Disclosure of Invention
It is an object of the present application to provide an installed corrosion protection structure for an aircraft high current ground wire that solves or mitigates at least one of the problems described above.
The technical scheme provided by the application is as follows: an installed corrosion protection structure for an aircraft high current ground wire, the protection structure comprising:
an aircraft airframe structure;
a wire terminal for connecting a wire; and
the switching bracket is used for connecting the airplane body structure and the wire connector;
the switching support and the airplane body structure are made of the same metal material, the switching support is connected with the airplane body structure and/or the wire connector through a connecting piece, contact surfaces between the switching support and the airplane body structure and/or the wire connector are polished, a sealant is sprayed around contact gaps between the switching support and the wire connector and/or the airplane body structure, and the sealant uniformly permeates into the contact gaps.
Further, the switching support comprises a machine body installation sheet and a wire connector installation sheet, and a preset angle is formed between the machine body installation sheet and the wire connector installation sheet.
Further, the predetermined angle is 90 degrees.
Furthermore, the polishing range of the polishing treatment of the contact surface is circular, and the polishing diameter is equal to about 1.5 times of the diameter of the excircle of the wiring joint.
Further, the sealant includes a removable sealant and a non-removable sealant.
Further, when the adapter bracket is frequently disassembled from the wire connector and/or the aircraft body structure, the removable sealant is adopted; non-removable sealants are used when the transition bracket is not frequently removed from the electrical connector and/or the aircraft airframe structure.
Further, the sealant is coated at least 10mm more in each direction.
Further, the thickness of the sealant is 0.3 mm-0.5 mm.
Further, the connecting piece comprises a rivet and a bolt, the switching support is connected with the airplane body structure through the rivet, and the switching support is connected with the wire terminal through the bolt.
The installation corrosion protection structure of the large-current grounding wire of the airplane can ensure that the grounding installation work of an EWIS system on the airplane has good electrical performance in a severe environment area, and can effectively prevent the installation corrosion.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
Fig. 1 is a schematic view of a corrosion protection structure of a high-current grounding wire of an aircraft according to the present application.
Fig. 2 is a schematic view of an adapter bracket according to the present application.
Fig. 3 is a schematic view of the distribution of sealant in the bolt or rivet of the present application.
Fig. 4a and 4b are schematic views of the contact surface polishing process in two embodiments.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
In order to prevent the large-current grounding wire of the airplane from corroding the main body structure of the airplane and influencing the safety and the service life of the airplane, an indirect grounding mode is adopted. Namely, the wire joint 7 of the large-current grounding wire is installed on the switching bracket 1 which is made of the same material as the installation base material of the wire joint 7, and the switching bracket 1 is connected with the airplane main body structure 4 in a sealing riveting mode.
Specifically, as shown in fig. 1, the installation corrosion protection structure provided in the present application mainly includes: aircraft major structure 4, the adapter bracket 1 of aircraft major structure 4 and wire joint 7 is connected respectively at wire joint 7 and the both ends of connecting wire 2, wherein, adapter bracket 1 and aircraft body structure 4 are different metal material, adapter bracket 1 all passes through the connecting piece with arbitrary structure or two structures in aircraft body structure 4 and wire joint 7 and is connected, and adapter bracket 1 all polishes with arbitrary structure or the contact surface between two structures in aircraft body structure 4 and the wire joint 7 and handles, it has sealant 5 to spray around the contact gap of arbitrary structure or two structures in adapter bracket 1 and wire joint 7 and aircraft body structure 4, inside this sealant 5 infiltration contact gap that can be even.
As shown in fig. 2, which is a schematic structural diagram of the adaptor bracket in the preferred embodiment of the present invention, the adaptor bracket (1) includes a body mounting plate 11 and a wire terminal mounting plate 12, the body mounting plate 11 and the wire terminal mounting plate 12 both have a connecting hole for a bolt to pass through, and a predetermined angle is formed between the body mounting plate 11 and the wire terminal mounting plate 12, and the height is preferably 90 degrees.
In an embodiment of the application, the switching bracket 1 is connected with the main body structure 4 of the airplane through riveting 6, and the riveting part is sealed and protected after the riveting is completed. And the adapter bracket 1 and the terminal fitting 7 are connected by a bolt 3.
In the preferred embodiment of the present application, the base contact surface between the adapting bracket 1 and the wiring connector 7 is polished to ensure good conductivity of the wiring connector 7. Wherein, the scope of polishing is circular, and the diameter of polishing approximately equals 1.5 times of wiring joint 7 excircle diameter to guarantee that wiring joint 7 and aircraft body structure 4's contact surface is smooth. The wiring connector 7 at the cleaning and polishing position is connected with the switching bracket 1 by using a fastening screw. In addition, an electrical special corrosion inhibitor (insulation) is sprayed around the contact gap between the wire joint 7 and the adapter bracket 1, so that the corrosion inhibitor can uniformly permeate into the gap.
In the present application, the sealant 5 includes removable sealant and non-removable sealant, and the removable sealant may be used for filling when the adaptor bracket 1 is frequently disassembled from either or both of the wire connector 7 and the aircraft airframe structure 4; when the adaptor bracket 1 is not frequently disassembled from either or both of the terminal fitting 7 and the aircraft airframe structure 4, it may be filled with a non-removable sealant. For example, the fastener can be subjected to wet assembly for fasteners which are not frequently disassembled, the sealant which needs to be frequently disassembled can be replaced by sealing putty, the sealing putty is coated in a connecting hole or a bolt and a screw rod part are screwed into the connecting hole, the sealant has no maintainability, and the sealing putty can be used in places which are not frequently disassembled; the sealing putty has repairability and can be used in places needing frequent disassembly, as shown in figure 3.
And polishing redundant parts of the contact edges of the wire connectors 7 and the switching bracket 1 to perform insulation and sealing paint repairing treatment.
In addition, in the present application, a sealant is applied between the contact surfaces of the adapter bracket 1 and the aircraft airframe structure 4. Preferably, as shown in fig. 4a and 4b, the sealant is coated at least 10mm more in each direction when in use, and the sealant thickness is 0.3mm to 0.5 mm.
The installation corrosion protection structure of the airplane high-current grounding wire provided by the invention can ensure that the grounding installation work of an EWIS system on an airplane, for example, has good electrical performance in a severe environment area, and can be suitable for the grounding installation of the airplane high-current grounding wire with the wire joint of which the specification is larger than 8AWG and the airplane body are made of different materials.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (9)
1. An aircraft high current grounding wire installation corrosion protection structure, said protection structure comprising:
an aircraft airframe structure (4);
a wire terminal (7) for connecting the wire (2); and
a switching bracket (1) for connecting the aircraft body structure (4) with the wire connector (7);
the switching support (1) and the airplane body structure (4) are made of the same metal material, the switching support (1) is connected with the airplane body structure (4) and/or the wire connector (7) through a connecting piece, the contact surface between the switching support (1) and the airplane body structure (4) and/or the wire connector (7) is polished, a sealant is sprayed around the contact gap between the switching support (1) and the wire connector (7) and/or the airplane body structure (4), and the sealant uniformly permeates into the contact gap.
2. An installation corrosion protection structure for aircraft high-current grounding wire according to claim 1, wherein the adapter bracket (1) comprises a machine body installation sheet and a wire connector installation sheet, and a predetermined angle is formed between the machine body installation sheet and the wire connector installation sheet.
3. An aircraft high current grounding wire installation corrosion protection structure as claimed in claim 2, wherein said predetermined angle is 90 degrees.
4. An aircraft high current grounding wire installation corrosion protection structure as claimed in claim 1, wherein the contact surface grinding process has a grinding range of a circular shape and a grinding diameter approximately equal to 1.5 times the diameter of the outer circle of the terminal fitting.
5. An aircraft high current grounding wire installation corrosion protection structure according to claim 1, wherein said sealant comprises a removable sealant and a non-removable sealant.
6. Installation corrosion protection structure for aircraft high current ground wires according to claim 5, characterized in that removable sealant is used when frequent disassembly between the adapter bracket (1) and the wiring connector (7) and/or the aircraft airframe structure (4); when the adapter carrier (1) is not frequently detached from the connection terminal (7) and/or the aircraft fuselage structure (4), a non-removable sealant is used.
7. An aircraft high current grounding wire installation corrosion protection structure as claimed in claim 1, wherein said sealant is over-applied by at least 10mm in each direction.
8. An aircraft high current grounding wire installation corrosion protection structure as claimed in claim 7, wherein said sealant thickness is 0.3mm to 0.5 mm.
9. An installation corrosion protection structure for aircraft high current grounding wire according to claim 1, wherein said connecting member comprises a rivet and a bolt, said adaptor bracket (1) is connected with the aircraft body structure (4) through the rivet, and said adaptor bracket (1) is connected with the connecting terminal (7) through the bolt.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111121907.XA CN113964557A (en) | 2021-09-24 | 2021-09-24 | Installation corrosion protection structure of airplane high-current grounding wire |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111121907.XA CN113964557A (en) | 2021-09-24 | 2021-09-24 | Installation corrosion protection structure of airplane high-current grounding wire |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113964557A true CN113964557A (en) | 2022-01-21 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111121907.XA Pending CN113964557A (en) | 2021-09-24 | 2021-09-24 | Installation corrosion protection structure of airplane high-current grounding wire |
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| CN (1) | CN113964557A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2620274A1 (en) * | 1987-09-04 | 1989-03-10 | Aerospatiale | System for electrically connecting two conducting elements |
| CN101867098A (en) * | 2009-04-14 | 2010-10-20 | 株式会社电装 | Aluminium conductor terminal device and manufacture method thereof |
| CN106063039A (en) * | 2014-01-28 | 2016-10-26 | 住友电装株式会社 | Terminal and aluminum wire connection structure of terminal |
| CN107743667A (en) * | 2015-09-11 | 2018-02-27 | 宝马股份公司 | Ground terminal for al member |
| CN110462936A (en) * | 2017-03-27 | 2019-11-15 | 古河电气工业株式会社 | Connection structural bodies |
| CN211789571U (en) * | 2020-01-19 | 2020-10-27 | 郑州宇通重工有限公司 | Transition type grounding fixing piece |
-
2021
- 2021-09-24 CN CN202111121907.XA patent/CN113964557A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2620274A1 (en) * | 1987-09-04 | 1989-03-10 | Aerospatiale | System for electrically connecting two conducting elements |
| CN101867098A (en) * | 2009-04-14 | 2010-10-20 | 株式会社电装 | Aluminium conductor terminal device and manufacture method thereof |
| CN106063039A (en) * | 2014-01-28 | 2016-10-26 | 住友电装株式会社 | Terminal and aluminum wire connection structure of terminal |
| CN107743667A (en) * | 2015-09-11 | 2018-02-27 | 宝马股份公司 | Ground terminal for al member |
| CN110462936A (en) * | 2017-03-27 | 2019-11-15 | 古河电气工业株式会社 | Connection structural bodies |
| CN211789571U (en) * | 2020-01-19 | 2020-10-27 | 郑州宇通重工有限公司 | Transition type grounding fixing piece |
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