CN103600833B - A kind of ultraviolet resistant near space airship - Google Patents
A kind of ultraviolet resistant near space airship Download PDFInfo
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- CN103600833B CN103600833B CN201310515617.2A CN201310515617A CN103600833B CN 103600833 B CN103600833 B CN 103600833B CN 201310515617 A CN201310515617 A CN 201310515617A CN 103600833 B CN103600833 B CN 103600833B
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Abstract
A kind of ultraviolet resistant near space airship, comprise airship envelope, this covering comprises weathering layer, prime coat, bearing layer, tack coat, resistance heliosphere and hot sealing layer from outside to inside successively, hot sealing layer is polyurethane film, resistance heliosphere selects aluminum polyester (Al-PET) film, and tack coat is polycarbonate, and bearing layer selects PBO plain cloth, prime coat is two component epoxy polyamide, and weathering layer is nano-fluorine carbon coating.Present invention employs nano-fluorine carbon coating, enhance the self_cleaning effect of weathering layer, uvioresistant and capability of environmental protection, greatly enhance the weather resisting property of airship envelope.The invention still further relates to a kind of manufacture method of airship envelope.
Description
Technical field
The present invention relates to a kind of dirigible, particularly relate to a kind of ultraviolet resistant near space airship.
Background technology
Near space dirigible is the multi-functional flying platform of the novel near space of one got up along with development in science and technology.It is different from aircraft, the low-altitude airship of flight in aviation layer, also the satellite be operated on low orbit is different from, it has widely military and civilian value, such as, in missile defence, anti-terrorism, communication, remote sensing, spatial observation and aeromerric moasurenont etc., all have great using value.But near space airship flight is highly general near 20km, this regional air is thin, density is approximately 1/14 of earth's surface density of air, atmospheric pressure is at about 5.5kPa, mean wind speed is 10m/s, and maximum wind speed can reach 40m/s, and ultraviolet is UV-B mainly, its spectral range is 290 ~ 360nm, and ultraviolet, ozone and high energy particle irradiation intensity are more a lot of by force than low Altitude.The covering performance of near space space environment to dirigible is had higher requirement, and is mainly reflected in strength-to-density ratio, obstructing capacity, uvioresistant irradiation and the aspect such as ozone attack, crease-resistant folding.High Performance covering is responsible near space dirigible weight-saving important task, and covering technology will be the basis setting up near space airship platform, becomes the key improving dirigible service ability and viability.
The covering of general non-rigid dirigible is mainly multiple-structure, generally includes weathering layer, resistance heliosphere, main structural and adhesive layer.Usually all adopt the mode of melt coating processes or applicator roll between the multilayer of existing near space airship envelope or adopt the mode of film bonding to realize being bonded to each other, but because the thickness of each layer film is general all very thin, therefore the accuracy requirement for above-mentioned technique is all very high, but still often inevitably there is the defect such as bubble or fold, therefore also adverse effect is created to the performance of produced near space airship envelope.
Summary of the invention
The present invention is intended to overcome above-mentioned defect, a kind of near space dirigible is provided, the manufacture method of airship envelope and this covering, particularly, a kind of near space dirigible, comprise airship envelope, this covering comprises weathering layer from outside to inside successively, prime coat, bearing layer, tack coat, resistance heliosphere and hot sealing layer, it is characterized in that hot sealing layer is polyurethane film, resistance heliosphere selects aluminum polyester (Al-PET) film, tack coat is polycarbonate, bearing layer selects PBO plain cloth, prime coat is two component epoxy polyamide, weathering layer is nano-fluorine carbon coating, hot sealing layer thickness is 18 microns, resistance heliosphere take PET film as basement membrane, and adopt magnetron sputtering technique to deposit the aluminium film of the thin densification of one deck thereon, the surface density of base material PET film is 60g/m
2, institute's aluminizer thickness is 70 nanometers, and resistance heliosphere thickness is 34 microns, and adhesive layer thickness is 15 microns, and the tabby surface density of PBO that bearing layer is selected is 80g/m
2, bearing layer thickness is 150 microns, and the build of prime coat is 15 microns, and the nano-fluorine carbon coating that weathering layer is selected comprises nano-TiO
2, nano-MgO, Nano-meter CaCO3
3, nano-ZnO high fluorinated hydroxy acrylic resin height solid coating, wherein nano-TiO
2, nano-MgO, Nano-meter CaCO3
3, nano-ZnO particle diameter be 40-50 nanometer, it is 3:3:2:2 that their part by weight closes, and weathering layer thickness is 30 microns.
The invention still further relates to a kind of method manufacturing near space airship envelope, comprise the steps:
(1) tack coat, resistance heliosphere and hot sealing layer is applied successively at bearing layer inside face; Adhesive layer thickness is 15 microns, and resistance heliosphere thickness is 34 microns, and hot sealing layer thickness is 18 microns;
(2) at bearing layer outside face spraying two component epoxy polyamide priming paint, adopt airless spraying, preferably pressure ratio 37:1, spray gun distance 450 ~ 620mm, angle of spray 75 ~ 80 degree, spray voltage 27 ~ 30V, spraying current 210 ~ 230A, nozzle diameter: 0.58 ~ 0.76mm, ambient humidity: < 76%, bearing layer surface temperature, higher than dew point more than 5 DEG C, sprays one time, dry film thickness 15 μm;
(3) spray two component epoxy polyamide priming paint and spray fluorocarbon coating afterwards in 60 minutes, adopt airless spraying, preferably pressure ratio 60:1, spray gun distance 400 ~ 550mm, nozzle diameter: 0.68 ~ 0.80mm, ambient humidity: < 80%, angle of spray 86 ~ 90 degree, spray voltage 29 ~ 32V, spraying current 235 ~ 240A, preferably surface drying time 50 minutes during lower 27 degrees Celsius of one film standard thickness, application twice; Per pass build 15 μm.
Owing to have employed nano-fluorine carbon coating; the enough protective coats of C-F bond energy are not subject to ultraviolet destruction; enhance the self_cleaning effect of coating simultaneously; and the nano material wherein comprised also all possesses good uvioresistant and capability of environmental protection, therefore the use of nano-fluorine carbon coating greatly enhances the weather resisting property of airship envelope.In addition, the outer membrane due to bearing layer have employed the mode of spraying, can make film uniform and delicate more, reduce the appearance of bubble and fold.
Detailed description of the invention
Weathering layer, prime coat, bearing layer, tack coat, resistance heliosphere and hot sealing layer is comprised from outside to inside successively according near space airship envelope of the present invention.Hot sealing layer is polyurethane film, and resistance heliosphere selects aluminum polyester (Al-PET) film, and tack coat is polycarbonate, and bearing layer selects PBO plain cloth, and prime coat is two component epoxy polyamide, and weathering layer is nano-fluorine carbon coating.Preferably, hot sealing layer thickness is 18 microns; Resistance heliosphere take PET film as basement membrane, and adopt magnetron sputtering technique to deposit the aluminium film of the thin densification of one deck thereon, the surface density of base material PET film is 60g/m
2, institute's aluminizer thickness is 70 nanometers, and resistance heliosphere thickness is 34 microns, and adhesive layer thickness is 15 microns, and the tabby surface density of PBO that bearing layer is selected is 80g/m
2, bearing layer thickness is 150 microns, and the build of prime coat is 15 microns, and the nano-fluorine carbon coating that weathering layer is selected comprises nano-TiO
2, nano-MgO, Nano-meter CaCO3
3, nano-ZnO high fluorinated hydroxy acrylic resin height solid coating, wherein nano-TiO
2, nano-MgO, Nano-meter CaCO3
3, nano-ZnO is 40-50 nanometer, it is 3:3:2:2 that their part by weight closes, and weathering layer thickness is 30 microns.
The present invention also provides a kind of manufacture method of near space airship envelope, specifically comprises the steps:
The first, apply tack coat, resistance heliosphere and hot sealing layer successively at bearing layer inside face; Adhesive layer thickness is 15 microns, and resistance heliosphere thickness is 34 microns, and hot sealing layer thickness is 18 microns;
The second, at bearing layer outside face spraying two component epoxy polyamide priming paint, adopt airless spraying, preferably pressure ratio 37:1, spray gun distance 450 ~ 620mm, angle of spray 75 ~ 80 degree, spray voltage 27 ~ 30V, spraying current 210 ~ 230A, nozzle diameter: 0.58 ~ 0.76mm, ambient humidity: < 76%, bearing layer surface temperature is higher than dew point more than 5 DEG C, spray one time, dry film thickness 15 μm;
3rd, spray two component epoxy polyamide priming paint and sprayed fluorocarbon coating afterwards in 60 minutes, adopt airless spraying, preferably pressure ratio 60:1, spray gun distance 400 ~ 550mm, nozzle diameter: 0.68 ~ 0.80mm, ambient humidity: < 80%, angle of spray 86 ~ 90 degree, spray voltage 29 ~ 32V, spraying current 235 ~ 240A, preferably surface drying time 50 minutes during lower 27 degrees Celsius of one film standard thickness, application twice; Per pass build 15 μm.
Owing to have employed nano-fluorine carbon coating; the enough protective coats of C-F bond energy are not subject to ultraviolet destruction; enhance the self_cleaning effect of coating simultaneously; and the nano material wherein comprised also all possesses good uvioresistant and capability of environmental protection, therefore the use of nano-fluorine carbon coating greatly enhances the weather resisting property of airship envelope.In addition, the outer membrane due to bearing layer have employed the mode of spraying, can make film uniform and delicate more, reduce the appearance of bubble and fold.
Those skilled in the art can make replacement or modification according to content disclosed by the invention and the art technology grasped to content of the present invention; but these replacements or modification should not be considered as disengaging the present invention design, and these replacements or modification are all in the interest field of application claims protection.
Claims (1)
1. a ultraviolet resistant near space airship, comprise airship envelope, this covering comprises weathering layer, prime coat, bearing layer, tack coat, resistance heliosphere and hot sealing layer from outside to inside successively, it is characterized in that hot sealing layer is polyurethane film, resistance heliosphere selects aluminized mylar, and tack coat is polycarbonate, bearing layer selects PBO plain cloth, prime coat is two component epoxy polyamide, and weathering layer is nano-fluorine carbon coating, and hot sealing layer thickness is 18 microns; Resistance heliosphere take PET film as basement membrane, and adopt magnetron sputtering technique to deposit the aluminium film of the thin densification of one deck thereon, the surface density of base material PET film is 60g/m
2, institute's aluminizer thickness is 70 nanometers, and resistance heliosphere thickness is 34 microns, and adhesive layer thickness is 15 microns, and the tabby surface density of PBO that bearing layer is selected is 80g/m
2, bearing layer thickness is 150 microns, and the build of prime coat is 15 microns, and the nano-fluorine carbon coating that weathering layer is selected comprises nano-TiO
2, nano-MgO, Nano-meter CaCO3
3, nano-ZnO high fluorinated hydroxy acrylic resin height solid coating, wherein nano-TiO
2, nano-MgO, Nano-meter CaCO3
3, nano-ZnO particle diameter be 40-50 nanometer, it is 3:3:2:2 that their part by weight closes, weathering layer thickness is 30 microns, and the manufacture method of this near space airship envelope comprises the steps: that (1) applies tack coat, resistance heliosphere and hot sealing layer successively at bearing layer inside face; Adhesive layer thickness is 15 microns, and resistance heliosphere thickness is 34 microns, and hot sealing layer thickness is 18 microns; (2) at bearing layer outside face spraying two component epoxy polyamide priming paint, adopt airless spraying, pressure ratio 37:1, spray gun distance 450 ~ 620mm, angle of spray 75 ~ 80 degree, spray voltage 27 ~ 30V, spraying current 210 ~ 230A, nozzle diameter: 0.58 ~ 0.76mm, ambient humidity: < 76%, bearing layer surface temperature, higher than dew point more than 5 DEG C, sprays one time, dry film thickness 15 μm; (3) spray two component epoxy polyamide priming paint and spray fluorocarbon coating afterwards in 60 minutes, adopt airless spraying, pressure ratio 60:1, spray gun distance 400 ~ 550mm, nozzle diameter: 0.68 ~ 0.80mm, ambient humidity: < 80%, angle of spray 86 ~ 90 degree, spray voltage 29 ~ 32V, spraying current 235 ~ 240A, surface drying time 50 minutes during lower 27 degrees Celsius of one film standard thickness, application twice; Per pass build 15 μm.
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| CN201310515617.2A CN103600833B (en) | 2013-10-26 | 2013-10-26 | A kind of ultraviolet resistant near space airship |
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| CN103600833B true CN103600833B (en) | 2015-09-23 |
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| CN104742442B (en) * | 2015-03-25 | 2017-06-16 | 东莞前沿技术研究院 | Stratosphere aerostatics covering and preparation method thereof |
Citations (3)
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| CN101711200A (en) * | 2007-04-28 | 2010-05-19 | 卡马尔·阿拉维 | Flexible multi-layer material, preferably for an inflatable balloon casing, and method for the production of an inflatable casing |
| CN102416739A (en) * | 2011-08-19 | 2012-04-18 | 北京航空航天大学 | Airship sheath material and preparation method thereof |
| EP2471651A1 (en) * | 2008-12-22 | 2012-07-04 | Anagram International, Inc. | Low conductivity balloons and methods for producing same |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002036409A (en) * | 2000-07-27 | 2002-02-05 | Taiyo Kogyo Corp | Sheet material, its manufacturing method and flying object using sheet |
| JP3698666B2 (en) * | 2000-10-31 | 2005-09-21 | 東レ・デュポン株式会社 | Composite membrane |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101711200A (en) * | 2007-04-28 | 2010-05-19 | 卡马尔·阿拉维 | Flexible multi-layer material, preferably for an inflatable balloon casing, and method for the production of an inflatable casing |
| EP2471651A1 (en) * | 2008-12-22 | 2012-07-04 | Anagram International, Inc. | Low conductivity balloons and methods for producing same |
| CN102416739A (en) * | 2011-08-19 | 2012-04-18 | 北京航空航天大学 | Airship sheath material and preparation method thereof |
Non-Patent Citations (3)
| Title |
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| PBO基质平流层飞艇蒙皮材料的制备研究;曹旭等;《高科技纤维与应用》;20090815;第34卷(第4期);第37-42页 * |
| 纳米二氧化钛改性氟碳涂料及涂装工艺的研究;杨景花;《中国优秀硕士学位论文全文数据库》;20061115;第39页 * |
| 纳米氟碳涂料研究进展;王博赟等;《化工进展》;20080805;第27卷(第8期);第1192-1197页 * |
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Effective date of registration: 20170731 Address after: 213300 Liyang City, Jiangsu Province Li Cheng Zhen Dong Street No. 182 Patentee after: Liyang Technology Development Center Address before: Li Town of Liyang City, Jiangsu province 213300 Changzhou City Dongmen Street No. 67 Patentee before: LIYANG HADA ACHIEVEMENT TRANSFORMATION CENTER CO., LTD. |
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