CN105155986B - Compound glass for aircraft windows and method for manufacturing glass - Google Patents
Compound glass for aircraft windows and method for manufacturing glass Download PDFInfo
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- CN105155986B CN105155986B CN201510400715.0A CN201510400715A CN105155986B CN 105155986 B CN105155986 B CN 105155986B CN 201510400715 A CN201510400715 A CN 201510400715A CN 105155986 B CN105155986 B CN 105155986B
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- compound glass
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Abstract
The invention discloses compound glass for aircraft windows. The compound glass comprises an outer compound glass layer and an inner compound glass layer. A hollow cavity is formed between the outer compound glass layer and the inner compound glass layer, hollow ventilation strips are uniformly arranged in the hollow cavity at intervals, nanometer silicon dioxide is arranged on the outer compound glass layer, electrochromic glass is arranged on the inner compound glass layer, the edges of the outer compound glass layer and the edges of the inner compound glass layer respectively cling onto the inner walls of edge connecting pieces with U-shaped cross sections, the ventilation strips penetrate the middles of the edge connecting pieces, spaces among the outer compound glass layer, the inner compound glass layer, the ventilation strips and the edge connecting pieces are sealed by the nanometer silicon dioxide, the outer compound glass layer and the edge connecting pieces are made of tempered glass, and the inner compound glass layer is made of acrylic resin. The invention further discloses a method for manufacturing the compound glass for the aircraft windows. The compound glass and the method have the advantages that the compound glass is excellent in hardness, cooling can be facilitated, accordingly, mist due to heat transfer of the compound glass can be prevented, and the brightness can be adjusted.
Description
Technical field
The present invention relates to the manufacture method of a kind of aircraft windows compound glass and glass, is mainly used in aircraft transparency etc..
Background technology
Existing aircraft transparency is usually compound glass manufacture, by making it harder using double-deck or three-decker
Gu.Due in coastal navigation, easily there is salt fog in coastal air, cause glass made by existing resin easily by corruption
Erosion, causes its service life to be limited, meanwhile, easily there is fog in existing double-deck or triplex glass structure, causes sight line unclear,
Furthermore, it is desirable to using the curtain of manual control, cause crew member's workload to increase, using inconvenience.
The content of the invention
It is an object of the invention to provide the manufacture method of a kind of aircraft windows compound glass and glass, can improve existing
The defect of technology, while enabling glass that there is good hardness, convenient cooling, it is to avoid its heat transfer causes fog, while realizing
The regulation of brightness.
The present invention is achieved through the following technical solutions：
A kind of aircraft windows compound glass, including compound glass outer layer and compound glass internal layer, the compound glass outer layer
Hollow cavity is formed and compound glass internal layer between, uniform intervals are provided with hollow air duct slats in the hollow cavity,
Nano silicon is provided with the compound glass outer layer, on the compound glass internal layer electrochomeric glass is provided with,
The compound glass outer layer and compound glass internal layer edge are fitted in respectively on the inwall of the edge connector of U-shaped profile,
The air duct slats is through edge connector middle part, the compound glass outer layer, compound glass internal layer, air duct slats and edge connector
Between sealed by nano silicon, the compound glass outer layer, edge connector be safety glass and make, described compound
Glass inner layer is made up of acrylic resin.
The present invention using safety glass by making compound glass outer layer and for connecting compound glass outer layer and compound glass
The edge connector of glass internal layer, can make total more firm, it is not easy to impaired, and then effectively improve its service life；
The present invention using inside and outside two-layer by way of being arranged, it is possible to increase overall acoustical and thermal performance, meanwhile, adopt
Outer layer safety glass and the compound mode of internal layer acrylic resin, can make it not allow rapid wear while the hardness of glass is kept
It is bad, and its weight can be reduced, improve its use value；
The present invention can realize the regulation to glass brightness by adopting electrochomeric glass, without again using existing
Window curtain structure, and then window overall structure can be simplified, and can conveniently adjust；
The present invention using nano silicon by being realized to compound glass outer layer, compound glass internal layer, air duct slats and side
Sealing between edge connector, can be while sealing be realized, using the Corrosion Protection of nano silicon, it is to avoid sealing
Structural damage affects glass quality；
The present invention can make it be used for coastal grade and easily occur by arranging nano silicon on compound glass outer layer
Salt fog it is regional when be not easy to be damaged, effectively extend its service life；
The present invention, can when needed to adopting between compound glass outer layer and compound glass internal layer by arranging air duct slats
Thermal current is heated, and realizes the effect of mist elimination.
Further, to better implement the present invention, the hollow cavity is vacuum cavity.
Further, to better implement the present invention, it is fixed between the compound glass outer layer and compound glass internal layer
Intermediate connector is connected with, the intermediate connector is located at the opposite side wall in compound glass outer layer and compound glass internal layer edge
On.
The present invention discloses a kind of manufacture method of aircraft windows compound glass, comprises the following steps：
S1：By compound glass outer layer and compound glass internal layer respectively by adhesives on edge connector inwall,
Make to form hollow cavity between compound glass outer layer and compound glass internal layer；
S2：Through hole is set on the edge connector, the diameter of through hole is made equal to the external diameter of air duct slats, by air duct slats
It is embedded in respective through hole；
S3：In compound glass outer layer and edge connector inwall joint place, compound glass internal layer and edge connector inwall
The joint place of the through hole on joint place, air duct slats and edge connector sprays respectively nanosilica solution；
S4：Nanosilica solution is sprayed on compound glass outer layer outer wall；
S5：The compound glass that nanosilica solution is coated with step S4 is put into after electric baker is toasted natural
Cooling；
S6：Again electrochomeric glass is bonded on compound glass internal layer by binding agent.
Further, to better implement the present invention, electric baker baking temperature is not higher than 100 DEG C in step S5.
Further, to better implement the present invention, electric baker baking time is 30-60s in step S5.
Further, to better implement the present invention, after step S2 is completed, by hollow cavity evacuation, middle cavity is made
In vivo vacuum is not more than 10Pa.
Description of the drawings
In order to be illustrated more clearly that the technical scheme of the embodiment of the present invention, below will be attached to what is used needed for embodiment
Figure is briefly described, it will be appreciated that the following drawings illustrate only certain embodiments of the present invention, thus be not construed as it is right
The restriction of scope, for those of ordinary skill in the art, on the premise of not paying creative work, can be with according to this
A little accompanying drawings obtain other related accompanying drawings.
Fig. 1 is overall structure cross-sectional view of the present invention.
Wherein：101. compound glass outer layers, 102. compound glass internal layers, 103. air duct slats, 104. hollow cavities, 105. is electric
Cause photo chromic glass, 106. edge connectors, 107. intermediate connectors.
Specific embodiment
The present invention is described in further detail with reference to specific embodiment, but embodiments of the present invention are not limited to
This.
Embodiment 1：
As shown in figure 1, a kind of aircraft windows compound glass, including compound glass outer layer 101 and compound glass internal layer 102,
Hollow cavity 104 is formed between the compound glass outer layer 101 and compound glass internal layer 102, in the hollow cavity 104
It is even to be arranged at intervals with hollow air duct slats 103, nano silicon is provided with the compound glass outer layer 101, described
Electrochomeric glass 105, the compound glass outer layer 101 and the side of compound glass internal layer 102 are provided with compound glass internal layer 102
Edge is fitted in respectively on the inwall of edge connector 106 of U-shaped profile, and the air duct slats 103 runs through edge connector 106
Middle part, the compound glass outer layer 101, between compound glass internal layer 102, air duct slats 103 and edge connector 106 pass through nanometer
Silicon dioxide is sealed, and the compound glass outer layer 101, edge connector 106 are safety glass and make, in the compound glass
Layer 102 is by acrylic resin.
By the way that edge connector 106 is fixed on airframe.Due to making edge connection using safety glass
Part 106, it is possible to increase the intensity of edge joins position, it is to avoid its damage, while using the edge connector 106 of U-shaped structure,
Compound glass outer layer 101 and compound glass internal layer 102 can be conveniently installed, conveniently realize the sealing of structure.
Due to making compound glass outer layer 101 using safety glass, overall intensity can be effectively improved so as to be not easy
Damage, and cover nano silicon on compound glass outer layer 101, can utilize nano silicon it is superpower it is acidproof,
Alkaline-resisting, resistance to elevated temperatures, makes compound glass outer layer 101 be not easy to be damaged, and effectively extends its service life.
In the present invention, electrochomeric glass 105 can be connected with power supply by wire, when needed, electricity can be made
Cause photo chromic glass to be powered, principle of discoloration can occur in the energized state using it, the overall brightness of window is adjusted, from
And the drawbacks of can avoid that existing Window curtain structure is complicated, need manual operation, facilitate crew member's unification adjustment window brightness, together
When simplify window overall structure.
In flight course, can be by way of being aerated to air duct slats 103, to carrying out adding in hollow cavity 104
Heat, makes that fog will not be produced in hollow cavity 104, keeps the visuality of window.
Because glass easily conducts heat, the present invention is set to the hollow cavity 104 for vacuum cavity.By arranging vacuum
Cavity, can realize insulation and the effect of heat insulation of window, and making the radiance of window effectively reduces, meanwhile, advantageously in avoiding
The formation of fog.
In order that structure is more consolidated, it is preferable that the present invention is in the compound glass outer layer 101 and compound glass internal layer
Intermediate connector 107 is fixedly connected between 102, the intermediate connector 107 is located at compound glass outer layer 101 and compound glass
On the opposite side wall in the edge of internal layer 102.In the present invention, the diameter of the intermediate connector 107 between the mm of 0.3mm-0.5, its
Height, by above-mentioned setting, can be being realized in connection compound glass outer layer 101 and compound glass between 0.1mm-0.2mm
While layer 102, the heat transfer efficiency for making intermediate connector 107 is kept low.
Embodiment 2：
Present embodiment discloses a kind of manufacture method of aircraft windows compound glass, comprises the following steps：
S1：By compound glass outer layer 101 and compound glass internal layer 102 respectively by adhesives in edge connector
On 106 inwalls, make to form hollow cavity 104 between compound glass outer layer 101 and compound glass internal layer 102；
S2：Through hole is set on the edge connector, makes the diameter of through hole equal to the external diameter of air duct slats 103, will divulge information
Bar 103 is embedded in respective through hole；
S3：At compound glass outer layer 101 and the inwall joint place of edge connector 106, compound glass internal layer 102 and edge
The joint place of the through hole on the inwall joint place of connector 106, air duct slats 103 and edge connector 106 sprays respectively nano-silica
SiClx solution；
S4：Nanosilica solution is sprayed on the outer wall of compound glass outer layer 101；
S5：The compound glass that nanosilica solution is coated with step S4 is put into after electric baker is toasted natural
Cooling；
S6：Again electrochomeric glass is bonded on compound glass internal layer 102 by binding agent.
By step S1, compound glass outer layer 101 and compound glass internal layer 102 are glued respectively to using acrylic resin
On the inwall of edge connector 106, compound glass internal layer 102 and compound glass outer layer 101 is set fully to be fitted in edge connector
Inwall on, between compound glass outer layer 101 and compound glass internal layer 102 formed 0.1mm-0.2mm space；
Air duct slats 103 is arranged on edge connector by step S2, can be adopted in the through hole of edge connector
Mode with acrylic resin is arranged on the outer wall of air duct slats 103, makes air duct slats be firmly fixed on edge connector 106；
Realize connecting compound glass internal layer 102, compound glass outer layer 101, air duct slats 103 and edge by step S3, S4
Sealing between fitting 106, makes nano silicon be completely filled in the space between edge connector 106 and said structure
In, fully sealing for structure is realized, meanwhile, by arranging nano-silica on the outer wall of compound glass outer layer 101 in step S4
SiClx, realizes the anti-corrosion treatment of compound glass outer layer 101, improves the Corrosion Protection of compound glass outer layer so as to use the longevity
Life is longer；
Overall structure is toasted by step S5, nano silicon is fitted in completely on said structure, made whole
Individual structure is more stable, it is not easy to impaired；
By step S6, electrochomeric glass 105 is bonded on compound glass internal layer 102 using acrylic resin, will
It passes through circuit and is connected with the on and off switch and cabin total power switch of single window, facilitates single brightness regulation and entirety
Brightness regulation.
Preferably, in the present invention, electric baker baking temperature is not higher than 100 DEG C in step S5, and the heated baking time is
30-60s。
Have in hollow cavity air and enter due in the step S3-S5 course of processing, may result in, in order to keep it
Internal certain vacuum, the present invention is being carried out in vacuum to hollow cavity, after step S2 is completed, by hollow cavity
104 evacuation, make vacuum in hollow cavity 104 be not more than 10Pa.In step S3-S5, make to keep 10- in hollow cavity
In the range of 15Pa.
The preferred embodiments of the present invention are the foregoing is only, the present invention is not limited to, for the skill of this area
For art personnel, the present invention can have various modifications and variations.It is all within the spirit and principles in the present invention, made any repair
Change, equivalent, improvement etc., should be included within the scope of the present invention.
Claims (7)
1. a kind of aircraft windows compound glass, it is characterised in that：Including compound glass outer layer（101）With compound glass internal layer
（102）, the compound glass outer layer（101）With compound glass internal layer（102）Between form hollow cavity（104）, in described
Cavity body（104）Interior uniform intervals are provided with hollow air duct slats（103）, in the compound glass outer layer（101）On be provided with
Nano silicon, in the compound glass internal layer（102）On be provided with electrochomeric glass（105）, outside the compound glass
Layer（101）With compound glass internal layer（102）Edge is fitted in respectively the edge connector of U-shaped profile（106）Inwall on,
The air duct slats（103）Through edge connector（106）Middle part, the compound glass outer layer（101）, compound glass internal layer
（102）, air duct slats（103）With edge connector（106）Between by nano silicon seal, the compound glass outer layer
（101）, edge connector（106）It is safety glass to make, the compound glass internal layer（102）It is made up of acrylic resin.
2. a kind of aircraft windows compound glass according to claim 1, it is characterised in that：The hollow cavity（104）For
Vacuum cavity.
3. a kind of aircraft windows compound glass according to claim 1 and 2, it is characterised in that：Outside the compound glass
Layer（101）With compound glass internal layer（102）Between be fixedly connected with intermediate connector（107）, the intermediate connector（107）Position
In compound glass outer layer（101）With compound glass internal layer（102）On the opposite side wall in edge.
4. the manufacture method of a kind of aircraft windows compound glass according to any one of claim 1-3, it is characterised in that：Bag
Include following steps：
S1：By compound glass outer layer（101）With compound glass internal layer（102）Respectively by adhesives in edge connector
（106）On inwall, compound glass outer layer is made（101）With compound glass internal layer（102）Between form hollow cavity（104）；
S2：Through hole is set on the edge connector, the diameter for making through hole is equal to air duct slats（103）External diameter, by air duct slats
（103）It is embedded in respective through hole；
S3：In compound glass outer layer（101）With edge connector（106）Inwall joint place, compound glass internal layer（102）With edge
Connector（106）Inwall joint place, air duct slats（103）With edge connector（106）On the joint place of through hole spray receive respectively
Rice silicon dioxde solution；
S4：In compound glass outer layer（101）Nanosilica solution is sprayed on outer wall；
S5：The compound glass that nanosilica solution is coated with step S4 is put into naturally cold after electric baker is toasted
But；
S6：Again electrochomeric glass is bonded in by compound glass internal layer by binding agent（102）On.
5. the manufacture method of a kind of aircraft windows compound glass according to claim 4, it is characterised in that：Step S5
Middle electric baker baking temperature is not higher than 100 DEG C.
6. the manufacture method of a kind of aircraft windows compound glass according to claim 4, it is characterised in that：Step S5
Middle electric baker baking time is 30-60s.
7. the manufacture method of a kind of aircraft windows compound glass according to claim 4, it is characterised in that：Complete step
After S2, by hollow cavity（104）Evacuation, makes hollow cavity（104）Interior vacuum is not more than 10Pa.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510400715.0A CN105155986B (en) | 2015-07-10 | 2015-07-10 | Compound glass for aircraft windows and method for manufacturing glass |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510400715.0A CN105155986B (en) | 2015-07-10 | 2015-07-10 | Compound glass for aircraft windows and method for manufacturing glass |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105155986A CN105155986A (en) | 2015-12-16 |
| CN105155986B true CN105155986B (en) | 2017-04-12 |
Family
ID=54796991
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510400715.0A Expired - Fee Related CN105155986B (en) | 2015-07-10 | 2015-07-10 | Compound glass for aircraft windows and method for manufacturing glass |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105155986B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112960102B (en) * | 2021-03-18 | 2022-12-13 | 上海机电工程研究所 | Aircraft conical cabin integrated equipment installation opening cover and installation method |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2656491B1 (en) * | 1989-12-21 | 1996-06-07 | Saint Gobain Vitrage Int | HEATED GLAZING. |
| FR2766651B1 (en) * | 1997-07-23 | 1999-09-03 | Saint Gobain Vitrage | SHEET HEATED GLAZING, ESPECIALLY FOR AIRCRAFT COCKPIT |
| CN2386159Y (en) * | 1999-08-20 | 2000-07-05 | 林绍坤 | Heating double glazing |
| US6561460B2 (en) * | 2000-08-03 | 2003-05-13 | Ppg Industries Ohio, Inc. | Switchable electrochromic devices for use in aircraft transparency windows |
| RU2602125C2 (en) * | 2012-08-01 | 2016-11-10 | Ппг Индастриз Огайо, Инк. | Smart window system for aerospace application |
| KR101326192B1 (en) * | 2012-12-28 | 2013-11-07 | 정민상 | Multi-layer glass with heating unit |
| CN104251094A (en) * | 2013-06-25 | 2014-12-31 | 江苏中恒铝业有限公司 | Hydrophobic type aluminum alloy door/window |
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2015
- 2015-07-10 CN CN201510400715.0A patent/CN105155986B/en not_active Expired - Fee Related
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| Publication number | Publication date |
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| CN105155986A (en) | 2015-12-16 |
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