CN208559739U - A kind of pre-buried electric discharge brush configuration of wing tip - Google Patents
A kind of pre-buried electric discharge brush configuration of wing tip Download PDFInfo
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- CN208559739U CN208559739U CN201820994558.XU CN201820994558U CN208559739U CN 208559739 U CN208559739 U CN 208559739U CN 201820994558 U CN201820994558 U CN 201820994558U CN 208559739 U CN208559739 U CN 208559739U
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- brush
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- electric discharge
- wing tip
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Abstract
The utility model discloses a kind of pre-buried electric discharge brush configurations of wing tip, including wing tip interconnected and rib, the discharge end edge of the wing tip is provided with pre-buried groove, and electric discharge body of the brush is equipped in the pre-buried groove, and the discharge end of the electric discharge body of the brush is equipped with the discharge wire of pencil；The outer surface of the wing tip is also equipped with one layer of electric discharge copper mesh being overlapped on electric discharge body of the brush；The utility model discharges brush configuration instead of traditional structure for carrying out discharge brush installation by discharge brush mounting base by built-in type, compared to traditional discharge brush mechanism, the utility model has simple installation, discharge brush lightweight construction, effectively reduces the aerodynamic drag that aircraft is subject to, the beneficial effect reduce components consumption, reduce cost, guaranteeing aircraft surfaces flatness.
Description
Technical field
The utility model belongs to technical field of aircraft structure design, in particular to a kind of pre-buried discharge brush of wing tip
Structure.
Background technique
Aircraft or aircraft can encounter various atrocious weather situations in flight course, wherein threaten it is biggish be exactly
In thunderstorm weather, aircraft, which has, larger can suffer from being struck by lightning.Lightning stroke is aircraft when by being struck by lightning to the main harm of aircraft, high pressure
The insulating materials and partial structurtes of aircraft surfaces can be punctured, high current can make conduction on airframe discontinuously locate on fire or cause
Material corrosion causes the mechanical performance of aircraft to decline to a great extent, or even causes danger, therefore the lightning protection design of aircraft is aircraft
Indispensable component part in structural system design.For aircraft when meeting with lightning stroke, the body of aircraft is as lightning discharge access
In a component part, the inlet point an of lightning stroke and leaving a little for lightning stroke are certainly existed on the body of aircraft.Lightning stroke
To leave a little be exactly point of discharge of the aircraft to atmosphere, point of discharge is usually located at the tail portion of aircraft, it is most likely that horizontal tail, vertical fin,
On the rear of rudder or at the tail point of fuselage.Therefore, the anti-lightning strike electric discharge measure of usual aircraft be wing, horizontal tail, vertical fin,
The appropriate location installation of the wing tip rear of rudder puts a brush and carries out conductive discharge, the injury for avoiding aircraft from being struck by lightning.But
Traditional discharge brush is installed by the discharge brush support being installed on the wing tip rear of wing, horizontal tail, vertical fin, rudder
Connection, and in order to guarantee stability of the discharge brush in aircraft flight, it is also necessary to by one or more fasteners to electric discharge
It is fastened between brush support and wing tip, discharge brush and discharge brush support.This mode has resulted in assembly when installation discharge brush
It is cumbersome, while the heavier-weight of discharge brush and discharge brush support, aerodynamic drag is also increased, gas when aircraft flight is brought
Dynamic loss.Especially in unmanned plane field, traditional electric discharge brush configuration is difficult to meet the high speed of unmanned plane, high stealth is wanted
It asks.Therefore for defect existing for conventional discharge brush configuration, the utility model discloses a kind of pre-buried electric discharge brush configurations of wing tip.
Utility model content
The purpose of this utility model is to provide a kind of pre-buried electric discharge brush configurations of wing tip, and the utility model has been abandoned traditional
Mode of the tip design discharge brush support to install discharge brush in aircraft discharging structure in aircraft, passes through pre-buried discharge brush
Structure realizes discharge brush and airplane wingtip syntype, has the effect of simple installation, reduces aircraft aerodynamic drag.
The utility model is achieved through the following technical solutions:
A kind of pre-buried electric discharge brush configuration of wing tip, including wing tip interconnected and rib, the electric discharge end margin of the wing tip
Place is provided with pre-buried groove, and electric discharge body of the brush is equipped in the pre-buried groove, and the discharge end of the electric discharge body of the brush is equipped with
The discharge wire of pencil；The outer surface of the wing tip is also equipped with one layer of electric discharge copper mesh being overlapped on electric discharge body of the brush.
Working principle and usage mode:
Suitable position of the utility model in the edge of the discharge end of airplane wingtip opens up pre-buried groove, then will electric discharge
Body of the brush is pre-buried to be installed among the pre-buried groove, is made to discharge body of the brush and wing tip syntype and is become an entirety, instead of
Traditional discharge brush will carry out the structure of installation connection by special discharge brush mounting base and wing tip, have simple installation, have
Effect reduces the effect of flight resistance.Meanwhile it because being installed instead of traditional by discharge brush using built-in type electric discharge brush configuration
Seat carries out the structure of electric discharge brush configuration installation, eliminates required various fasteners in conventional discharge brush configuration, further drops
Low installation cost and the flatness that ensure that aircraft surfaces, ensure that the Stealth Fighter of aircraft to a certain extent.It is putting simultaneously
The discharge wire of the discharge end installation pencil of brush main body, and be laid with one layer on wing tip surface and be overlapped on putting on electric discharge body of the brush
Electrolytic copper net, when aircraft is by being struck by lightning, electric current can be guided to electric discharge body of the brush by the electric discharge copper mesh on wing tip surface and by putting
The discharge wire of the pencil of brush main body discharge end is discharged rapidly, and airframe is avoided to be damaged.
In order to preferably realize the utility model, further, the outer profile and wing tip of the electric discharge body of the brush installation end
The Internal periphery of pre-buried groove of discharge end edge setting fit, the installation end for the body of the brush that discharges is bonded with pre-buried groove
Conducting resinl installation is applied using fitting between face.
The Internal periphery of the pre-buried groove of the discharge end edge setting of the outer profile and wing tip of the installation end of electric discharge body of the brush
It fits, when carrying out the installation of electric discharge body of the brush, it is only necessary to the installation end for the body of the brush that discharges is snapped fits into pre-buried groove,
Make to discharge the outer profile of installation end of body of the brush and the Internal periphery of pre-buried groove fits closely that electric discharge body of the brush and pre- can be realized
Bury the connection installation of groove；Meanwhile because required various fasteners in the installation of conventional discharge brush are eliminated, in order to protect
Stability of card electric discharge body of the brush during aircraft flight is needed through conducting glue to putting a body of the brush and pre-buried groove
Between be adhesively fixed.
In order to preferably realize the utility model, further, the Internal periphery diameter of the pre-buried groove from the inside to the outside by
It is tapered small.
In order to increase electric discharge body of the brush and pre-buried groove between stable connection, by pre-buried groove be set as Internal periphery from
It is interior to being gradually reduced outside in interior big outer small shape, the body of the brush that makes to discharge is difficult to deviate from from pre-buried groove.
In order to preferably realize the utility model, further, on the outer surface of the junction of the wing tip and rib also
It is overlapped with conducting copper mesh.
It, can be when aircraft be by being struck by lightning, by what is gathered in wing box by the way that conducting copper mesh is arranged between wing tip and rib
Electric current is oriented to wing tip by the conducting copper mesh between rib and wing tip and rib, and is discharged by wing tip.
In order to preferably realize the utility model, further, the discharge end of the electric discharge body of the brush is provided with mounting hole,
Discharge wire is spirally connected or is welded in the mounting hole.
Mounting hole is set in the discharge end of electric discharge body of the brush, is spirally connected or welds the discharge wire of pencil in mounting hole, make whole
For the structure of a discharge brush in integration, structure is more compact.
In order to preferably realize the utility model, further, also cladding is pacified outside the discharge end of the electric discharge body of the brush
Equipped with protective case.
In order to preferably realize the utility model, further, the wing tip uses entirety RTM machine-shaping.
The utility model compared with prior art, have the following advantages that and the utility model has the advantages that
(1) the utility model is by the pre-buried groove of discharge end edge in wing tip, and installs and put in pre-buried groove
The structure of brush main body carries out electric discharge brush configuration by the way that special discharge brush mounting base is arranged at wing tip edge instead of traditional
Installation structure, be effectively reduced electric discharge brush configuration weight, reduce electric discharge brush configuration installation difficulty, realize electric discharge
The installation of the integrated syntypeization of brush configuration and wing tip, compared to traditional electric discharge brush configuration, the utility model has simple installation, puts
The beneficial effect for the aerodynamic drag that brush structure is light-weight, effectively reduces aircraft is subject to；
(2) the utility model is carried out instead of traditional by discharge brush mounting base using built-in type electric discharge brush configuration
The structure that the brush configuration that discharges is installed, while also just eliminating in conventional discharge brush mounting base and electric discharge brush configuration progress installation process
Required fastener, compared to traditional electric discharge brush configuration, the utility model have reduce components consumption, reduce cost,
Guarantee the beneficial effect of aircraft surfaces flatness.
Detailed description of the invention
Fig. 1 is the overall structure diagram of the utility model；
Fig. 2 is discharge brush structural schematic diagram；
Fig. 3 is that wing tip and rib overlap schematic diagram.
Wherein: 1- discharge wire；2- electric discharge body of the brush；3- wing tip；4- rib；The pre-buried groove of 01-；02A- electric discharge copper mesh；
02B- conducting copper mesh.
Specific embodiment
Embodiment 1:
A kind of pre-buried electric discharge brush configuration of wing tip, as shown in Figure 1, including wing tip 3 interconnected and rib 4, the wing tip 3
Discharge end edge be provided with pre-buried groove 01, be equipped in the pre-buried groove 01 electric discharge body of the brush 2, the discharge brush master
The discharge end of body 2 is equipped with the discharge wire 1 of pencil；The outer surface of the wing tip 3 is also equipped with one layer and is overlapped on electric discharge body of the brush 2
On electric discharge copper mesh 02A.
Suitable position of the utility model in the edge of the discharge end of airplane wingtip 3 opens up pre-buried groove 01, then will
Body of the brush 2 is pre-buried installs among the pre-buried groove 01 for electric discharge, make to discharge body of the brush 2 and 3 syntype of wing tip and become one it is whole
Body will be carried out the structure of installation connection by special discharge brush mounting base and wing tip 3 instead of traditional discharge brush, have peace
Dress is easy, effectively reduces the effect of flight resistance；Meanwhile because using built-in type electric discharge brush configuration instead of traditional by putting
Brush mounting base carries out the structure of electric discharge brush configuration installation, eliminates required various fasteners in conventional discharge brush configuration,
It further reduced installation cost and ensure that the flatness of aircraft surfaces, ensure that the Stealth Fighter of aircraft to a certain extent；
Simultaneously in the discharge wire 1 of the discharge end installation pencil of electric discharge body of the brush 2, and one layer is laid on the surface of wing tip 3 and is overlapped on and puts
Electric discharge copper mesh 02A in brush main body 2, when aircraft is by being struck by lightning, electric current can be led by the electric discharge copper mesh 02A on 3 surface of wing tip
It flow to electric discharge body of the brush 2 and is discharged rapidly by the discharge wire 1 of the pencil of the discharge end of electric discharge body of the brush 2, avoid aircraft
Body is damaged.
Embodiment 2:
The present embodiment advanced optimizes on the basis of embodiment 1, as shown in Fig. 2, 2 installation end of electric discharge body of the brush
Outer profile and the Internal periphery of pre-buried groove 01 of discharge end edge setting of wing tip 3 fit, the installation for the body of the brush 2 that discharges
End between the binding face of pre-buried groove 01 using be bonded apply conducting resinl install；The diameter of the Internal periphery of the pre-buried groove 01 from
Interior to outer to be gradually reduced, pre-buried groove 01 is in interior big outer small shape；The discharge end of the electric discharge body of the brush 2 is provided with installation
Hole is spirally connected or is welded with discharge wire 1 in the mounting hole；Also cladding is equipped with guarantor outside the discharge end of the electric discharge body of the brush 2
Sheath.
Discharge body of the brush 2 installation end outer profile and wing tip 3 discharge end edge setting pre-buried groove 01 it is interior
Profile fits, when carrying out the installation of electric discharge body of the brush 2, it is only necessary to snap fits into the installation end for the body of the brush 2 that discharges pre-buried
In groove 01, the outer profile of installation end of electric discharge body of the brush 2 and the Internal periphery of pre-buried groove 01 is made to fit closely can be realized and put
The connection of brush main body 2 and pre-buried groove 01 is installed；Meanwhile it because eliminating required various tight in the installation of conventional discharge brush
Firmware, therefore in order to guarantee stability of the body of the brush 2 during aircraft flight of discharging is needed through conducting glue to putting a little
It is adhesively fixed between body of the brush 2 and the binding face of pre-buried groove 01.By it is above-mentioned will electric discharge body of the brush 2 is pre-buried installs into pre-
The structure in groove 01 is buried, makes discharge body of the brush 2 and the integrated syntype of wing tip 3, not only makes the installation of electric discharge body of the brush 2 more easy
Fast, it ensure that the flatness of aircraft outer surface, while effectively reducing the air drag being subject in aircraft flight, especially
It is for unmanned plane, the electric discharge brush configuration of built-in type meets the requirement of unmanned plane high speed, high stealth very well.It is put to increase
Stable connection between brush main body 2 and pre-buried groove 01, it is in interior big for setting Internal periphery from the inside to the outside for pre-buried groove 01
Outer small shape makes electric discharge body of the brush 2 be difficult to deviate from from pre-buried groove 01.In the discharge end of electric discharge body of the brush 2, installation is set
Hole is spirally connected or welds the discharge wire 1 of pencil in mounting hole, makes the structure of entire discharge brush in integration, and structure is more compact.
Cladding is equipped with protective case outside the discharge end of electric discharge body of the brush 2 simultaneously, is to protect electric discharge in aircraft flight
Body of the brush 2 and discharge wire 1 extend it and use the time.
The other parts of the present embodiment are same as Example 1, and so it will not be repeated.
Embodiment 3:
The present embodiment advanced optimizes on the basis of above-described embodiment 1 or 2, as shown in figure 3, the wing tip 3 uses
Whole RTM machine-shaping；Conducting copper mesh 02B is also overlapped on the wing tip 3 and the outer surface of the junction of rib 4.
Because wing tip 3 is influenced in aircraft flight by air stream and ascending eddy, it is desirable that wing tip 3 has
While high-intensitive, also to have the effect of any surface finish.Therefore wing tip 3 is prepared by the way of entirety RTM machine-shaping, had
Have the advantages that high production efficiency, lower production costs, product intensity are high, finished surface is highly polished, ensure that electric discharge brush configuration
It carries out convenient integrally installing on wing tip 3.It, can be in aircraft by the way that conducting copper mesh 02B is arranged between wing tip 3 and rib 4
When by being struck by lightning, the electric current gathered in wing box is passed through into the conducting copper mesh 02B guide vane between rib 4 and wing tip 3 and rib 4
Point, and discharged by wing tip 3.
The other parts of the present embodiment are identical as above-described embodiment 1 or 2, and so it will not be repeated.
The above is only the preferred embodiment of the utility model, not does limit in any form to the utility model
System, any simple modification made by the above technical examples according to the technical essence of the present invention, equivalent variations, each falls within
Within the protection scope of the utility model.
Claims (7)
1. a kind of pre-buried electric discharge brush configuration of wing tip, the wing tip (3) including being connected to rib (4) side, which is characterized in that the wing
The discharge end edge of sharp (3) is provided with pre-buried groove (01), and electric discharge body of the brush (2) is equipped in the pre-buried groove (01),
The discharge end of electric discharge body of the brush (2) is equipped with the discharge wire (1) of pencil；The outer surface of the wing tip (3) is also equipped with one
Layer is overlapped on the electric discharge copper mesh (02A) in electric discharge body of the brush (2).
2. the pre-buried electric discharge brush configuration of a kind of wing tip according to claim 1, which is characterized in that the electric discharge body of the brush (2)
The Internal periphery for the pre-buried groove (01) that the discharge end edge of the outer profile of installation end and wing tip (3) is arranged fits, discharge brush
It uses to be bonded between the installation end of main body (2) and the binding face of pre-buried groove (01) and applies conducting resinl installation.
3. the pre-buried electric discharge brush configuration of a kind of wing tip according to claim 2, which is characterized in that the pre-buried groove (01)
Internal periphery diameter is gradually reduced from the inside to the outside.
4. the pre-buried electric discharge brush configuration of a kind of wing tip according to claim 2, which is characterized in that the wing tip (3) and rib
(4) it is also overlapped on the surface of junction conducting copper mesh (02B).
5. the pre-buried electric discharge brush configuration of a kind of wing tip according to claim 1-4, which is characterized in that the discharge brush
Also cladding is equipped with protective case outside the discharge end of main body (2).
6. the pre-buried electric discharge brush configuration of a kind of wing tip according to claim 1, which is characterized in that the electric discharge body of the brush (2)
Discharge end be provided with mounting hole, be spirally connected or be welded with discharge wire (1) in the mounting hole.
7. the pre-buried electric discharge brush configuration of a kind of wing tip according to claim 1, which is characterized in that the wing tip (3) is using whole
Body RTM machine-shaping.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820994558.XU CN208559739U (en) | 2018-06-27 | 2018-06-27 | A kind of pre-buried electric discharge brush configuration of wing tip |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820994558.XU CN208559739U (en) | 2018-06-27 | 2018-06-27 | A kind of pre-buried electric discharge brush configuration of wing tip |
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| Publication Number | Publication Date |
|---|---|
| CN208559739U true CN208559739U (en) | 2019-03-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820994558.XU Active CN208559739U (en) | 2018-06-27 | 2018-06-27 | A kind of pre-buried electric discharge brush configuration of wing tip |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110979705A (en) * | 2019-12-25 | 2020-04-10 | 中国航空工业集团公司沈阳飞机设计研究所 | Stealth aircraft electrostatic discharge device |
| CN112027063A (en) * | 2020-09-11 | 2020-12-04 | 中国商用飞机有限责任公司 | Flexible wing of airplane test model |
-
2018
- 2018-06-27 CN CN201820994558.XU patent/CN208559739U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110979705A (en) * | 2019-12-25 | 2020-04-10 | 中国航空工业集团公司沈阳飞机设计研究所 | Stealth aircraft electrostatic discharge device |
| CN112027063A (en) * | 2020-09-11 | 2020-12-04 | 中国商用飞机有限责任公司 | Flexible wing of airplane test model |
| CN112027063B (en) * | 2020-09-11 | 2022-02-22 | 中国商用飞机有限责任公司 | Flexible wing of airplane test model |
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