CN206250406U - A kind of low impedance earthing array of aircraft 300kV electrostatic experiment - Google Patents
A kind of low impedance earthing array of aircraft 300kV electrostatic experiment Download PDFInfo
- Publication number
- CN206250406U CN206250406U CN201621387358.5U CN201621387358U CN206250406U CN 206250406 U CN206250406 U CN 206250406U CN 201621387358 U CN201621387358 U CN 201621387358U CN 206250406 U CN206250406 U CN 206250406U
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- sheath
- aircraft
- electrostatic
- plain conductor
- fixture
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Abstract
The utility model is related to a kind of low impedance earthing array of aircraft 300kV electrostatic experiment, including earth clip, the first sheath, the second sheath, plain conductor and fixture, the plain conductor two ends are fixedly connected with earth clip and fixture respectively, plain conductor is made of braiding, cover the second sheath and the first sheath successively outside plain conductor, second sheath is made up of insulating materials, and the first sheath is made up of high-abrasive material.The low impedance earthing array of aircraft 300kV electrostatic experiment of the present utility model can ensure to be less than 1 Ω with aircraft reliability electrostatic overlap joint, overlap resistance with the fixture of aircraft end in contact.Pe sheath provides the isolation of 300kV electrostatic potentials on earthing or grounding means, and the cable of earthing or grounding means can arbitrarily be put, and uncontrollable electric discharge will not occur with aircraft surfaces.Fixture possesses and quickly steps up function, can be overlapped with irregular part on wing.
Description
Technical field
The utility model belongs to aircraft testing device design field, more particularly to a kind of experiment of aircraft 300kV electrostatic
Low impedance earthing array.
Background technology
When aircraft carries out 300kV ESD tests, airframe surface is all equipotentiality body, is had with ground (ground connection)
300kV electrical potential differences.When experiment ground cable because the reasons such as arrangement and place are less than electrostatic breakdown distance with aircraft surfaces distance
When, aircraft surfaces can cause ESD test to fail, while easily causing static discharge with the uncontrollable discharging in advance of earthing or grounding means
Injury.
Utility model content
The purpose of this utility model is to provide a kind of low impedance earthing array of aircraft 300kV electrostatic experiment, solves current
Cable can not effectively carry out the problem of aircraft static experiment.
To reach above-mentioned purpose, the technical solution adopted in the utility model is：A kind of low-resistance of aircraft 300kV electrostatic experiment
Anti- earthing or grounding means, including earth clip, the first sheath, the second sheath, plain conductor and fixture, the plain conductor two ends respectively with
Earth clip is fixedly connected with fixture, and plain conductor is made of braiding, covers the second sheath and first successively outside plain conductor
Sheath, the second sheath is made up of insulating materials, and the first sheath is made up of high-abrasive material.
Further, the plain conductor is made of copper material.
Further, the insulating materials of the first sheath includes such as polythene material.
Further, the plain conductor two ends use welding manner with earth clip and fixture type of attachment.
Further, the fixture is Flexible clamp, for accommodating aircraft opposite sex surface.
The low impedance earthing array of aircraft 300kV electrostatic experiment of the present utility model can ensure with the fixture of aircraft end in contact
With aircraft reliability electrostatic overlap joint, overlap resistance is less than 1 Ω.Pe sheath provides the isolation of 300kV electrostatic potentials on earthing or grounding means,
The cable of earthing or grounding means can arbitrarily be put, and uncontrollable electric discharge will not occur with aircraft surfaces.Fixture possesses and quickly steps up function, can
Overlapped with irregular part on wing.
Brief description of the drawings
Accompanying drawing herein is merged in specification and constitutes the part of this specification, shows and meets of the present utility model
Embodiment, and be used to explain principle of the present utility model together with specification.
The low impedance earthing array front view that Fig. 1 is tested for the aircraft 300kV electrostatic of the embodiment of the utility model one.
Fig. 2 is A-A positions sectional view in Fig. 1.
The low impedance earthing array schematic diagram that Fig. 3 is tested for the aircraft 300kV electrostatic of the embodiment of the utility model one.
Description of symbols
1- earth clips, the sheaths of 2- first, the sheaths of 3- second, 4- plain conductors, 5- fixtures.
Specific embodiment
For the purpose, technical scheme and advantage for implementing the utility model are clearer, below in conjunction with the utility model
Accompanying drawing in embodiment, is further described in more detail to the technical scheme in the utility model embodiment.In the accompanying drawings, ad initio
Same or similar element or element with same or like function are represented to same or similar label eventually.Described reality
It is a part of embodiment of the utility model to apply example, rather than whole embodiments.Below with reference to the embodiment of Description of Drawings
It is exemplary type, it is intended to for explaining the utility model, and it is not intended that to limitation of the present utility model.It is new based on this practicality
Embodiment in type, the every other implementation that those of ordinary skill in the art are obtained under the premise of the work of creation type is not made
Example, belongs to the scope of the utility model protection.Embodiment of the present utility model is described in detail below in conjunction with the accompanying drawings.
In description of the present utility model, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outward " are based on accompanying drawing institute
The orientation or position relationship for showing, are for only for ease of description the utility model and simplify description, signified rather than indicating or implying
Device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to this practicality
The limitation of novel protected scope.
It is as shown in Figure 1 to Figure 3 the low impedance earthing array of aircraft 300kV electrostatic of the present utility model experiment, it includes
Earth clip 1, the first sheath 2, the second sheath 3, plain conductor 4 and fixture 5.The two ends of plain conductor 4 are equal with earth clip 1 and fixture 5
It is fixedly linked using welding manner, the outside of plain conductor 4 is wrapped up being protected using the first sheath 2 and the second sheath 3 successively.The
One sheath 2 is made up of high-abrasive material, and the second sheath 3 is made up of insulating materials.
In figure, earth clip 1 is weldingly connected with plain conductor 4, and the first sheath 2 is coated on the second sheath 3, the second sheath
Sheath 3 is enclosed within plain conductor 4, and the other end of plain conductor 4 is connected using welding with fixture 5, and fixture 5 uses Flexible clamp,
Aircraft opposite sex face can be accommodated.
Specifically, fixture 5 is overlapped by spring force and ground contact point, plain conductor 4 is naturally drooped, earth clip 1 and examination
The ground earth point for testing scene is fixed with bolt.
In the utility model, to solve grounding resistance of transmission problems of too, plain conductor 4 is made up of copper material,
And using the copper conductive strips of braiding as ground cable.
In the utility model, to solve the problems, such as outer surface and the airframe surface-discharge of plain conductor 4, led to metal
Line 4 install additional the first sheath 2 and with the second sheath 3, there are the first sheath 2 wear resistance properties, the second sheath 3 to have insulation attribute；The
One sheath 2 and the covering cable part of plain conductor 4 of the second sheath 3, it is ensured that cable does not in test occur electrostatic with aircraft surfaces
Electric discharge.
In the utility model, to solve the problems, such as that earthing or grounding means is connected with aircraft special-shaped surfaces, fixture 5 uses elastic clip
Tight device.
The low impedance earthing array of aircraft 300kV electrostatic experiment of the present utility model can ensure with the fixture of aircraft end in contact
With aircraft reliability electrostatic overlap joint, overlap resistance is less than 1 Ω.Pe sheath provides the isolation of 300kV electrostatic potentials on earthing or grounding means,
The cable of earthing or grounding means can arbitrarily be put, and uncontrollable electric discharge will not occur with aircraft surfaces.Fixture possesses and quickly steps up function, can
Overlapped with irregular part on wing.
The above, optimal specific embodiment only of the present utility model, but protection domain of the present utility model is not
This is confined to, any one skilled in the art can readily occur in the technical scope that the utility model is disclosed
Change or replacement, should all cover within protection domain of the present utility model.Therefore, protection domain of the present utility model should be with
The scope of the claims is defined.
Claims (5)
1. the low impedance earthing array that a kind of aircraft 300kV electrostatic is tested, it is characterised in that including earth clip (1), the first sheath
(2), the second sheath (3), plain conductor (4) and fixture (5), plain conductor (4) two ends respectively with earth clip (1) and fixture
(5) it is fixedly connected, plain conductor (4) is made of braiding, the second sheath (3) and first is covered successively outward in plain conductor (4)
Sheath (2), the second sheath (3) is made up of insulating materials, and the first sheath (2) is made up of high-abrasive material.
2. the low impedance earthing array that aircraft 300kV electrostatic according to claim 1 is tested, it is characterised in that the gold
Category wire (4) is made of copper material.
3. the low impedance earthing array that aircraft 300kV electrostatic according to claim 1 is tested, it is characterised in that the first shield
The insulating materials for covering (2) includes such as polythene material.
4. the low impedance earthing array that aircraft 300kV electrostatic according to claim 1 is tested, it is characterised in that the gold
Category wire (4) two ends use welding manner with earth clip (1) and fixture (5) type of attachment.
5. the low impedance earthing array that aircraft 300kV electrostatic according to claim 1 is tested, it is characterised in that the folder
Tool (5) is Flexible clamp, for clamping aircraft special-shaped surfaces.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621387358.5U CN206250406U (en) | 2016-12-16 | 2016-12-16 | A kind of low impedance earthing array of aircraft 300kV electrostatic experiment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621387358.5U CN206250406U (en) | 2016-12-16 | 2016-12-16 | A kind of low impedance earthing array of aircraft 300kV electrostatic experiment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206250406U true CN206250406U (en) | 2017-06-13 |
Family
ID=59008278
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621387358.5U Active CN206250406U (en) | 2016-12-16 | 2016-12-16 | A kind of low impedance earthing array of aircraft 300kV electrostatic experiment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206250406U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111263500A (en) * | 2019-10-12 | 2020-06-09 | 中航通飞研究院有限公司 | Airplane lap joint system and construction method |
-
2016
- 2016-12-16 CN CN201621387358.5U patent/CN206250406U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111263500A (en) * | 2019-10-12 | 2020-06-09 | 中航通飞研究院有限公司 | Airplane lap joint system and construction method |
| CN111263500B (en) * | 2019-10-12 | 2024-01-19 | 中航通飞华南飞机工业有限公司 | Aircraft lap joint system and construction method |
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| GR01 | Patent grant |