CN205770190U - A kind of aircraft fuselage lights cover structure and there is its aircraft - Google Patents
A kind of aircraft fuselage lights cover structure and there is its aircraft Download PDFInfo
- Publication number
- CN205770190U CN205770190U CN201620517673.9U CN201620517673U CN205770190U CN 205770190 U CN205770190 U CN 205770190U CN 201620517673 U CN201620517673 U CN 201620517673U CN 205770190 U CN205770190 U CN 205770190U
- Authority
- CN
- China
- Prior art keywords
- aircraft
- glass lamp
- lamp shade
- cover structure
- mounting ring
- Prior art date
- 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.)
- Active
Links
Abstract
The utility model discloses a kind of aircraft fuselage lights cover structure and there is its aircraft.It is provided with opening in the fuselage wall plate structure of described aircraft, it is characterized in that, described aircraft fuselage lights cover structure includes: mounting ring, described mounting ring is connected with the inwall of the aperture position of fuselage wall plate structure, being at least partially disposed in described opening of described mounting ring, this part is referred to as glass lamp shade connecting portion；Airtight lampshade, described airtight lampshade is tightly connected with described mounting ring；Glass lamp shade, described glass lamp shade is tightly connected with described glass lamp shade connecting portion, and closes described opening.Aircraft in this utility model fuselage lights cover structure, structural shape is simple and reliable, and in view of airtight and water proofing property, technical maturity, easy to assembly, it is simple to examination and maintenance, be applicable to solving problem prior art, in order to observing leading edge of a wing ice condition, take measures deicing as early as possible.
Description
Technical field
This utility model relates to aircraft technology field, particularly relate to a kind of aircraft fuselage lights cover structure and
There is its aircraft.
Background technology
The accumulated ice that during aircraft flight, aerofoil surface moisture accumulation is formed in leading edge can the air of badly damaged aircraft
Power performance, increases flight resistance, reduces lift, has a strong impact on full machine maneuverability, stability, test
Showing, if memory leading edge accumulates the thick ice sheet of 1.2cm, airplane ascensional force is by minimizing about 50%, aircraft
Resistance, by increase about 60%, has a strong impact on aircraft safety flight.
Thus, it is desirable to have a kind of technical scheme overcomes or at least to alleviate at least one of prior art above-mentioned
Defect.
Utility model content
The purpose of this utility model is to provide a kind of aircraft fuselage lights cover structure overcome or at least alleviate
At least one drawbacks described above of prior art.
For achieving the above object, this utility model provides a kind of aircraft fuselage lights cover structure, described in fly
It is provided with opening, it is characterised in that described aircraft fuselage lights cover structure includes in the fuselage wall plate structure of machine:
Mounting ring, described mounting ring is connected with the inwall of the aperture position of fuselage wall plate structure, and described mounting ring is extremely
Small part is arranged in said opening, and this part is referred to as glass lamp shade connecting portion；Airtight lampshade, described airtight
Lampshade is tightly connected with described mounting ring；Glass lamp shade, described glass lamp shade and described glass lamp shade connecting portion
It is tightly connected, and closes described opening.
Preferably, described airtight lampshade and described mounting ring junction are carried out at fillet and binding face sealing
Reason.
Preferably, it is filled with sealant between described glass lamp shade and described glass lamp shade connecting portion.
Preferably, described glass lamp shade is bolted with described glass lamp shade connecting portion.
Preferably, in described airtight lampshade with glass lamp shade, it is provided with heater, described heater bag
Including heater, the temperature sensor being connected with heater, described temperature sensor is used for detecting temperature, described
Heater, for receiving the temperature that described temperature sensor is transmitted, adds when temperature is less than the threshold value of heater
Heat.
Preferably, described airtight lampshade wall scribbles ice-phobic coating and waterproof coating.
Present invention also provides a kind of aircraft, the leading edge of a wing position of described aircraft is installed just like described in business
Aircraft fuselage lights cover structure, for the leading edge of a wing position of hunter.
Aircraft in this utility model fuselage lights cover structure, structural shape is simple and reliable, and in view of gas
Close and water proofing property, technical maturity, easy to assembly, it is simple to examination and maintenance, it is adaptable to solve prior art
Middle problem, in order to observing leading edge of a wing ice condition, take measures deicing as early as possible.
Accompanying drawing explanation
Fig. 1 is the structural representation of the aircraft fuselage lights cover structure according to this utility model one embodiment.
Reference:
| 1 | Fuselage wall plate structure | 3 | Airtight lampshade |
| 2 | Mounting ring | 4 | Glass lamp shade |
| 21 | Glass lamp shade connecting portion |
Detailed description of the invention
Clearer for the purpose making this utility model implement, technical scheme and advantage, below in conjunction with this
Accompanying drawing in utility model embodiment, is carried out in further detail the technical scheme in this utility model embodiment
Description.In the accompanying drawings, the most same or similar label represents same or similar element or tool
There is the element of same or like function.Described embodiment is a part of embodiment of this utility model, and
It is not all, of embodiment.The embodiment described below with reference to accompanying drawing is exemplary, it is intended to be used for
Explain this utility model, and it is not intended that to restriction of the present utility model.Based in this utility model
Embodiment, those of ordinary skill in the art obtained under not making creative work premise all its
His embodiment, broadly falls into the scope of this utility model protection.Below in conjunction with the accompanying drawings to reality of the present utility model
Execute example to be described in detail.
In description of the present utility model, it is to be understood that term " " center ", " longitudinally ", " horizontal stroke
To ", "front", "rear", "left", "right", " vertically ", " level ", " top ", " end " " interior ", " outward " etc.
Orientation or the position relationship of instruction are based on orientation shown in the drawings or position relationship, are for only for ease of and retouch
State this utility model and simplify description rather than instruction or imply that the device of indication or element must have spy
Fixed orientation, with specific azimuth configuration and operation, therefore it is not intended that this utility model is protected model
The restriction enclosed.
Fig. 1 is the structural representation of the aircraft fuselage lights cover structure according to this utility model one embodiment.
In the present embodiment, the fuselage wall plate structure 1 of aircraft is provided with opening.
The fuselage lights cover structure of aircraft as shown in Figure 1, aircraft fuselage lights cover structure include mounting ring 2,
Airtight lampshade 3 and glass lamp shade 4, mounting ring 2 connects with the inwall of the aperture position of fuselage wall plate structure 1
Connecing, being at least partially disposed in opening of mounting ring 2, this part is referred to as glass lamp shade connecting portion 21；Gas
Close lampshade 3 is tightly connected with mounting ring 2；Glass lamp shade 4 is tightly connected with glass lamp shade connecting portion 21,
And close opening.
It is understood that the aircraft fuselage lights cover structure of the application needs also to be able to make under freezing environment
With, therefore, penetrate into after dissolving for anti-stagnant ice, it is advantageous to airtight lampshade 3 and mounting ring 2 junction
Carry out fillet and binding face encapsulation process.It is filled with between glass lamp shade 4 and glass lamp shade connecting portion 21
Sealant.
Advantageously, in the present embodiment, glass lamp shade 4 is with glass lamp shade connecting portion 21 by bolt even
Connect.Use this structure, it is possible to facilitate replacing and its internal dress of whole aircraft fuselage lights cover structure
Put or the replacing of part.
Advantageously, (not shown) in the present embodiment, in airtight lampshade 3 and glass lamp shade 4
Being provided with heater, heater includes heater, the temperature sensor being connected with heater, and temperature passes
Sensor is used for detecting temperature, and heater is for receiving the temperature that temperature sensor is transmitted, when temperature is less than adding
The heating during threshold value of hot device.
So, when running into weather of extremely trembling with fear and causing freezing, ice-melt measure can be carried out by heater.
Advantageously, in the present embodiment, airtight lampshade 3 wall scribbles ice-phobic coating and waterproof coating.
Use this measure, it is possible to prevent airtight lampshade from freezing further or infiltration.
Present invention also provides a kind of aircraft, the leading edge of a wing position of aircraft is provided with aircraft as above and uses
Fuselage lights cover structure, for the leading edge of a wing position of hunter.
Last it is noted that above example is only in order to illustrate the technical solution of the utility model, rather than
It is limited.Although this utility model being described in detail with reference to previous embodiment, this area general
Lead to and skilled artisans appreciate that the technical scheme described in foregoing embodiments still can be repaiied by it
Change, or wherein portion of techniques feature is carried out equivalent；And these amendments or replacement, do not make phase
The essence answering technical scheme departs from the spirit and scope of this utility model each embodiment technical scheme.
Claims (7)
1. an aircraft fuselage lights cover structure, the fuselage wall plate structure (1) of described aircraft is provided with out
Mouthful, it is characterised in that described aircraft fuselage lights cover structure includes:
Mounting ring (2), described mounting ring (2) connects with the inwall of the aperture position of fuselage wall plate structure (1)
Connecing, being at least partially disposed in described opening of described mounting ring (2), this part is referred to as glass lamp shade even
Meet portion (21)；
Airtight lampshade (3), described airtight lampshade (3) is tightly connected with described mounting ring (2)；
Glass lamp shade (4), described glass lamp shade (4) seals even with described glass lamp shade connecting portion (21)
Connect, and close described opening.
2. aircraft fuselage lights cover structure as claimed in claim 1, it is characterised in that described gas-tight lamp
Cover (3) and described mounting ring (2) junction carry out fillet and binding face encapsulation process.
3. aircraft fuselage lights cover structure as claimed in claim 2, it is characterised in that described Glass lamp
It is filled with sealant between cover (4) and described glass lamp shade connecting portion (21).
4. aircraft fuselage lights cover structure as claimed in claim 3, it is characterised in that described Glass lamp
Cover (4) is bolted with described glass lamp shade connecting portion (21).
5. aircraft fuselage lights cover structure as claimed in claim 4, it is characterised in that described airtight
Be provided with heater in lampshade (3) and glass lamp shade (4), described heater include heater and
The temperature sensor that heater is connected, described temperature sensor is used for detecting temperature, and described heater is used for connecing
Receive the temperature that described temperature sensor is transmitted, the heating when temperature is less than the threshold value of heater.
6. aircraft fuselage lights cover structure as claimed in claim 5, it is characterised in that described gas-tight lamp
Ice-phobic coating and waterproof coating is scribbled on cover (3) wall.
7. an aircraft, it is characterised in that the leading edge of a wing position of described aircraft is installed just like claim
Aircraft fuselage lights cover structure described in any one in 1 to 6, for the leading edge of a wing position of hunter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620517673.9U CN205770190U (en) | 2016-05-31 | 2016-05-31 | A kind of aircraft fuselage lights cover structure and there is its aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620517673.9U CN205770190U (en) | 2016-05-31 | 2016-05-31 | A kind of aircraft fuselage lights cover structure and there is its aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205770190U true CN205770190U (en) | 2016-12-07 |
Family
ID=58138263
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620517673.9U Active CN205770190U (en) | 2016-05-31 | 2016-05-31 | A kind of aircraft fuselage lights cover structure and there is its aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205770190U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112937870A (en) * | 2021-03-24 | 2021-06-11 | 北京安达维尔航空设备有限公司 | Sealing baffle structure and top plate structure |
-
2016
- 2016-05-31 CN CN201620517673.9U patent/CN205770190U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112937870A (en) * | 2021-03-24 | 2021-06-11 | 北京安达维尔航空设备有限公司 | Sealing baffle structure and top plate structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN207106876U (en) | A kind of rain-proof unmanned plane | |
| CN107543649B (en) | Hot air deicing total pressure sensor | |
| CN208134635U (en) | A kind of anti-deicing system for medium-and-large-sized fixed-wing unmanned plane | |
| CN205770190U (en) | A kind of aircraft fuselage lights cover structure and there is its aircraft | |
| Krawczyk et al. | Infrared building inspection with unmanned aerial vehicles | |
| CN205940856U (en) | Pick -up is always pressed in steam deicing | |
| CN104129504A (en) | Flute-shaped tube structure with adjustable angle for hot air anti-icing | |
| CN204758300U (en) | Engine plateau environmental test case | |
| CN203996904U (en) | A kind of bourdon's tube structure of the angle adjustable for hot air anti-icing | |
| CN204130699U (en) | The anti-electric multifunction radar cover of a kind of waterproof | |
| CN104754892A (en) | Outdoor integrated cabinet of base station and assembling method thereof | |
| CN204669742U (en) | A kind of base station outdoor integrated cabinet | |
| CN108872302A (en) | A kind of building doors and windows curtain wall thermal insulation property detection system | |
| CN205034346U (en) | Equipment nacelle heat abstractor | |
| CN204979251U (en) | Novel spray rinsing unmanned aerial vehicle device | |
| CN105947174A (en) | Airplane | |
| CN206292028U (en) | A kind of fusiformis model in wind tunnel radome fairing | |
| CN204880502U (en) | Water sweat cooling structure and refrigerating plant | |
| CN204758297U (en) | Multi -parameter engine plateau environmental test device | |
| CN107458604A (en) | A kind of telecontrolled aircraft with function of cold | |
| CN208813521U (en) | Canard configuration airplane modular shelter coat | |
| CN208402316U (en) | A kind of intelligent communication equipment rain-proof control cabinet | |
| CN206358376U (en) | A kind of airborne light photoelectric nacelle fast assembling-disassembling bindiny mechanism | |
| CN206546953U (en) | A kind of automatic recloser controlling machine box | |
| CN206734640U (en) | A kind of aircraft auxiliary power plant cabin formula punching press inlet duct |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |