CN105155986A - 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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- CN105155986A CN105155986A CN201510400715.0A CN201510400715A CN105155986A CN 105155986 A CN105155986 A CN 105155986A CN 201510400715 A CN201510400715 A CN 201510400715A CN 105155986 A CN105155986 A CN 105155986A
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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 preparation method of a kind of aircraft windows compound glass and glass, be mainly used in aircraft transparency etc.
Background technology
Existing aircraft transparency is generally compound glass manufacture, makes it firmer by adopting bilayer or three layer construction.Due to when coastal navigation, easily salt fog is there is in coastal air, the glass causing existing resin to be made holds corrosion-vulnerable, causes its application life limited, simultaneously, easily there is fog in existing bilayer or triplex glass structure, cause sight line unclear, and, need the curtain adopting Non-follow control, cause crew member's workload to increase, use inconvenience.
Summary of the invention
The object of the present invention is to provide the preparation method of a kind of aircraft windows compound glass and glass, can improve the defect of prior art, while enabling glass have good hardness, convenient cooling, avoids its heat transfer to cause fog, realizes the adjustment of brightness simultaneously.
The present invention is achieved through the following technical solutions:
A kind of aircraft windows compound glass, comprise compound glass skin and compound glass internal layer, hollow cavity is formed between described compound glass skin and compound glass internal layer, in described hollow cavity, uniform intervals is provided with the air duct slats of hollow, described compound glass skin is provided with nano silicon, described compound glass internal layer is provided with electrochomeric glass, described compound glass skin and compound glass internal layer edge are fitted on the inwall of the edge connector of U-shaped profile respectively, described air duct slats runs through in the middle part of edge connector, described compound glass is outer, compound glass internal layer, sealed by nano silicon between air duct slats and edge connector, described compound glass is outer, edge connector is tempered glass and makes, described compound glass internal layer is made up of acrylic resin.
The present invention is outer and for being connected the outer edge connector with compound glass internal layer of compound glass by adopting tempered glass to make compound glass, total can be made more firm, be not easy impaired, and then effectively improve its application life;
The present invention is by adopting the mode of inside and outside two-layer setting, overall acoustical and thermal performance can be improved, simultaneously, adopt the combination of outer tempered glass and internal layer acrylic resin, it can be made while the hardness keeping glass to be not easy to damage, and its weight can be reduced, improve its use value;
The present invention, by adopting electrochomeric glass, can realize the adjustment to glass brightness, need not adopt existing Window curtain structure again, and then can simplify window overall structure, and can conveniently regulate;
The present invention by adopt nano silicon realize to compound glass skin, compound glass internal layer, between air duct slats and edge connector between sealing, can while realization sealing, utilize the Corrosion Protection of nano silicon, avoid that hermetically-sealed construction is impaired affects glass quality;
The present invention by arranging nano silicon on compound glass skin, is not easy impaired, effectively extends its application life when it can be made easily to occur salt fog regional for coastal grade;
The present invention, by arranging air duct slats, can adopt thermal current to heat between compound glass skin and compound glass internal layer when needed, realize the effect of mist elimination.
Further, to better implement the present invention, described hollow cavity is vacuum cavity.
Further, to better implement the present invention, between described compound glass skin and compound glass internal layer, be fixedly connected with intermediate connector, described intermediate connector is positioned on compound glass skin and compound glass internal layer edge sidewall in opposite directions.
The present invention discloses a kind of preparation method of aircraft windows compound glass, comprise the following steps:
S1: outer and compound glass internal layer is respectively by adhesives on edge connector inwall by compound glass, makes compound glass skin and meet between glass inner layer to form hollow cavity;
S2: arrange through hole on described edge connector, makes the diameter of through hole equal the external diameter of air duct slats, is embedded in by air duct slats in respective through hole;
S3: spray nanosilica solution respectively with the joint place of the through hole on edge connector inwall joint place, compound glass internal layer and edge connector inwall joint place, air duct slats and edge connector at compound glass skin;
S4: spray nanosilica solution on the outer outer wall of compound glass;
S5: the compound glass being coated with nanosilica solution in step S4 is put into electric oven and carry out toasting rear cooling naturally;
S6: electrochomeric glass is being bonded on compound glass internal layer by cementing agent.
Further, to better implement the present invention, in described step S5 electric oven baking temperature not higher than 100 DEG C.
Further, to better implement the present invention, in described step S5, electric oven baking time is 30-60s.
Further, to better implement the present invention, after completing steps S2, hollow cavity is vacuumized, make vacuum in hollow cavity be not more than 10Pa.
Accompanying drawing explanation
In order to be illustrated more clearly in the technical scheme of the embodiment of the present invention, be briefly described to the accompanying drawing used required in embodiment below, be to be understood that, the following drawings illustrate only some embodiment of the present invention, therefore the restriction to scope should be counted as, for those of ordinary skill in the art, under the prerequisite not paying creative work, other relevant accompanying drawings can also be obtained according to these accompanying drawings.
Fig. 1 is overall structure cross sectional representation of the present invention.
Wherein: 101. compound glasses are outer, 102. compound glass internal layers, 103. air duct slats, 104. hollow cavities, 105. electrochomeric glass, 106. edge connector, 107. intermediate connectors.
Detailed description of the invention
Below in conjunction with specific embodiment, the present invention is described in further detail, but embodiments of the present invention are not limited thereto.
Embodiment 1:
As shown in Figure 1, a kind of aircraft windows compound glass, comprise compound glass outer 101 and compound glass internal layer 102, hollow cavity 104 is formed between described compound glass outer 101 and compound glass internal layer 102, in described hollow cavity 104, uniform intervals is provided with the air duct slats 103 of hollow, described compound glass skin 101 is provided with nano silicon, described compound glass internal layer 102 is provided with electrochomeric glass 105, described compound glass outer 101 and compound glass internal layer 102 edge are fitted on the inwall of edge connector 106 of U-shaped profile respectively, described air duct slats 103 runs through in the middle part of edge connector 106, described compound glass skin 101, compound glass internal layer 102, sealed by nano silicon between air duct slats 103 and edge connector 106, described compound glass skin 101, edge connector 106 is tempered glass and makes, described compound glass internal layer 102 is by acrylic resin.
By by airframe fixing for edge connector 106.Edge connector 106 is made owing to adopting tempered glass, the intensity at edge conjunction position can be improved, avoid it to damage, adopt the edge connector 106 of U-shaped structure simultaneously, compound glass outer 101 and compound glass internal layer 102 conveniently can be installed, conveniently realize the sealing of structure.
Compound glass skin 101 is made owing to adopting tempered glass, effectively can improve overall intensity, it is made to be not easy to damage, and on compound glass skin 101, cover nano silicon, acidproof, alkaline-resisting, the resistance to elevated temperatures that nano silicon is superpower can be utilized, compound glass skin 101 is not easy impaired, effectively extends its application life.
In the present invention, by wire, electrochomeric glass 105 can be connected with power supply, when needed, electrochomeric glass can be made to be energized, utilize it that principle of variable color can occur in the energized state, the brightness of window entirety is regulated, thus existing Window curtain structure complexity, the manually operated drawback of need can be avoided, facilitate the brightness of crew member's unified adjustment window, simplify window overall structure simultaneously.
In flight course, by the mode of ventilating to air duct slats 103, can heat in hollow cavity 104, make can not produce fog in hollow cavity 104, keep the visuality of window.
Because glass easily conducts heat, described hollow cavity 104 is set to as vacuum cavity by the present invention.By arranging vacuum cavity, insulation and the effect of heat insulation of window can be realized, the emissivity of window is effectively reduced, meanwhile, advantageously in the formation avoiding fog.
In order to make structure more firm, preferably, the present invention is fixedly connected with intermediate connector 107 between described compound glass outer 101 and compound glass internal layer 102, and described intermediate connector 107 is positioned on compound glass outer 101 and compound glass internal layer 102 edge sidewall in opposite directions.In the present invention, the diameter of described intermediate connector 107 is between the mm of 0.3mm-0.5, its height is between 0.1mm-0.2mm, by above-mentioned setting, can, while realization connects compound glass outer 101 and compound glass internal layer 102, the heat transfer efficiency of intermediate connector 107 be made to remain on reduced levels.
Embodiment 2:
Present embodiment discloses a kind of preparation method of aircraft windows compound glass, comprise the following steps:
S1: by outer for compound glass 101 and compound glass internal layer 102 respectively by adhesives on edge connector 106 inwall, make compound glass outer 101 and meet between glass inner layer 102 to form hollow cavity 104;
S2: arrange through hole on described edge connector, makes the diameter of through hole equal the external diameter of air duct slats 103, is embedded in respective through hole by air duct slats 103;
S3: spray nanosilica solution with edge connector 106 inwall joint place, air duct slats 103 respectively with the joint place of the through hole on edge connector 106 at compound glass outer 101 and edge connector 106 inwall joint place, compound glass internal layer 102;
S4: spray nanosilica solution on outer 101 outer walls of compound glass;
S5: the compound glass being coated with nanosilica solution in step S4 is put into electric oven and carry out toasting rear cooling naturally;
S6: electrochomeric glass is being bonded on compound glass internal layer 102 by cementing agent.
By step S1, acrylic resin is adopted to be bonded on the inwall of edge connector 106 respectively by compound glass outer 101 and compound glass internal layer 102, compound glass internal layer 102 and compound glass skin 102 are fully fitted on the inwall of edge connector, between compound glass outer 101 and compound glass internal layer 102, form the space of 0.1mm-0.2mm;
By step S2, air duct slats 103 is arranged on edge connector, can to adopt in the through hole of edge connector and air duct slats 103 outer wall on the mode of acrylic resin is set, make air duct slats firmly be fixed on edge connector 106;
Realize compound glass internal layer 101, compound glass skin 102, sealing between air duct slats 103 and edge connector 106 by step S3, S4, in the space that nano silicon is filled between edge connector 106 and said structure completely, realize the sealing completely of structure, simultaneously, by arranging nano silicon in step S4 on the outer wall of compound glass skin 101, realize the anti-corrosion treatment of compound glass skin 101, improve the outer field Corrosion Protection of compound glass, make its longer service life;
By step S5, overall structure is toasted, nano silicon is fitted on said structure completely, makes total more stable, be not easy impaired;
By step S6, adopt acrylic resin to be bonded on compound glass internal layer 102 by point to photo chromic glass 105, its power switch by circuit and single window and cabin total power switch are connected, facilitate single brightness regulation and overall brightness adjustment.
Preferably, in the present invention, in described step S5, electric oven baking temperature is not higher than 100 DEG C, and the heated baking time is 30-60s.
Due in step S3-S5 process, may cause having air to enter in hollow cavity, in order to keep its inner certain vacuum, the present invention is carrying out in vacuum to hollow cavity, after completing steps S2, hollow cavity 104 is vacuumized, makes vacuum in hollow cavity 104 be not more than 10Pa.In step S3-S5, make to keep within the scope of 10-15Pa in hollow cavity.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (7)
1. an aircraft windows compound glass, it is characterized in that: comprise compound glass skin (101) and compound glass internal layer (102), hollow cavity (104) is formed between described compound glass skin (101) and compound glass internal layer (102), in described hollow cavity (104), uniform intervals is provided with the air duct slats (103) of hollow, described compound glass skin (101) is provided with nano silicon, described compound glass internal layer (102) is provided with electrochomeric glass (105), described compound glass skin (101) and compound glass internal layer (102) edge are fitted on the inwall of edge connector (106) of U-shaped profile respectively, described air duct slats (103) runs through edge connector (106) middle part, described compound glass skin (101), compound glass internal layer (102), sealed by nano silicon between air duct slats (103) and edge connector (106), described compound glass skin (101), edge connector (106) is tempered glass and makes, described compound glass internal layer (102) is made up of acrylic resin.
2. a kind of aircraft windows compound glass according to claim 1, is characterized in that: described hollow cavity (104) is vacuum cavity.
3. a kind of aircraft windows compound glass according to claim 1 and 2, it is characterized in that: between described compound glass skin (101) and compound glass internal layer (102), be fixedly connected with intermediate connector (107), described intermediate connector (107) is positioned on compound glass skin (101) and compound glass internal layer (102) edge sidewall in opposite directions.
4. the preparation method of a kind of aircraft windows compound glass according to any one of claim 1-3, is characterized in that: comprise the following steps:
S1: by compound glass skin (101) and compound glass internal layer (102) respectively by adhesives on edge connector (106) inwall, make compound glass skin (101) and meet between glass inner layer (102) to form hollow cavity (104);
S2: arrange through hole on described edge connector, makes the diameter of through hole equal the external diameter of air duct slats (103), is embedded in respective through hole by air duct slats (103);
S3: spray nanosilica solution with edge connector (106) inwall joint place, air duct slats (103) respectively with the joint place of the through hole on edge connector (106) at compound glass skin (101) and edge connector (106) inwall joint place, compound glass internal layer (102);
S4: spray nanosilica solution on compound glass skin (101) outer wall;
S5: the compound glass being coated with nanosilica solution in step S4 is put into electric oven and carry out toasting rear cooling naturally;
S6: electrochomeric glass is being bonded on compound glass internal layer (102) by cementing agent.
5. the preparation method of a kind of aircraft windows compound glass according to claim 4, is characterized in that: in described step S5, electric oven baking temperature is not higher than 100 DEG C.
6. the preparation method of a kind of aircraft windows compound glass according to claim 4, is characterized in that: in described step S5, electric oven baking time is 30-60s.
7. the preparation method of a kind of aircraft windows compound glass according to claim 4, is characterized in that: after completing steps S2, is vacuumized by hollow cavity (104), makes hollow cavity (104) interior vacuum be 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 true CN105155986A (en) | 2015-12-16 |
| CN105155986B CN105155986B (en) | 2017-04-12 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510400715.0A Expired - Fee Related CN105155986B (en) | 2015-07-10 | 2015-07-10 | Compound glass for aircraft windows and method for manufacturing glass |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112960102A (en) * | 2021-03-18 | 2021-06-15 | 上海机电工程研究所 | Aircraft conical cabin integrated equipment installation opening cover and installation method |
Citations (7)
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| EP0434537A1 (en) * | 1989-12-21 | 1991-06-26 | Saint-Gobain Vitrage International | Heated windscreen |
| US6034353A (en) * | 1997-07-23 | 2000-03-07 | Saint-Gobain Vitrage | Laminated heated plate glass, especially for an airplane cockpit |
| CN2386159Y (en) * | 1999-08-20 | 2000-07-05 | 林绍坤 | Heating double glazing |
| CN1659080A (en) * | 2001-07-31 | 2005-08-24 | Ppg工业俄亥俄公司 | Switchable electrochromic devices for use in aircraft transparency windows |
| 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 |
| CN104507796A (en) * | 2012-08-01 | 2015-04-08 | Ppg工业俄亥俄公司 | Aerospace intelligent window system |
-
2015
- 2015-07-10 CN CN201510400715.0A patent/CN105155986B/en not_active Expired - Fee Related
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0434537A1 (en) * | 1989-12-21 | 1991-06-26 | Saint-Gobain Vitrage International | Heated windscreen |
| US6034353A (en) * | 1997-07-23 | 2000-03-07 | Saint-Gobain Vitrage | Laminated heated plate glass, especially for an airplane cockpit |
| CN2386159Y (en) * | 1999-08-20 | 2000-07-05 | 林绍坤 | Heating double glazing |
| CN1659080A (en) * | 2001-07-31 | 2005-08-24 | Ppg工业俄亥俄公司 | Switchable electrochromic devices for use in aircraft transparency windows |
| CN104507796A (en) * | 2012-08-01 | 2015-04-08 | Ppg工业俄亥俄公司 | Aerospace intelligent window system |
| 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 |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112960102A (en) * | 2021-03-18 | 2021-06-15 | 上海机电工程研究所 | Aircraft conical cabin integrated equipment installation opening cover and installation method |
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| CN105155986B (en) | 2017-04-12 |
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