CN103600827A - Near space airship - Google Patents
Near space airship Download PDFInfo
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- CN103600827A CN103600827A CN201310504627.6A CN201310504627A CN103600827A CN 103600827 A CN103600827 A CN 103600827A CN 201310504627 A CN201310504627 A CN 201310504627A CN 103600827 A CN103600827 A CN 103600827A
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Abstract
A near space airship comprises an airship skin. The skin comprises a weather-proof layer, a primer layer, a force bearing layer, an adhesive layer, a helium blocking layer and a thermal sealing layer sequentially from outside to inside, wherein the thermal sealing layer is a polyurethane film; the helium blocking layer is an aluminized polyester (Al-PET) film; the adhesive layer is made of polycarbonate; the force bearing layer is made of PBO plain weave fabric; the primer layer is made of double-component epoxy polyamide; the weather-proof layer is made of nanometer fluorocarbon coating. As the nanometer fluorocarbon coating is adopted, the near space airship enhances self-cleaning effect, ultraviolet resistance and environment protection ability of the weather-proof layer and greatly enhances weather resistance of the airship skin. The invention also relates to a manufacturing method of the airship skin.
Description
Technical field
The present invention relates to a kind of dirigible, relate in particular to a kind of near space dirigible.
Background technology
Near space dirigible is the multi-functional flying platform of a kind of novel near space getting up along with development in science and technology.It is different from aircraft, the low latitude dirigible of flight in aviation layer, also be different from the satellite being operated on low orbit, it has very extensively military affairs and civilian value, such as all having great using value at aspects such as missile defence, anti-terrorism, communication, remote sensing, spatial observation and aeromerric moasurenonts.But near space airship flight is highly generally near 20km, this regional air is thin, density is approximately 1/14 of earth's surface density of air, atmospheric pressure is in 5.5kPa left and right, mean wind speed is 10m/s, and maximum wind speed can reach 40m/s, and ultraviolet ray is mainly UV-B, its spectral range is 290～360nm, and ultraviolet ray, ozone and high energy particle irradiation intensity are more a lot of by force than low Altitude.Near space space environment is had higher requirement to the covering performance of dirigible, is mainly reflected in the aspects such as strength-to-density ratio, obstructing capacity, uvioresistant irradiation and ozone erosion, crease-resistant folding.High Performance covering is being undertaken near space dirigible weight-saving important task, and covering technology will be the basis of setting up near space airship platform, becomes the key that improves dirigible service ability and viability.
The covering of general non-rigid dirigible is mainly multiple-structure, generally includes weather layer, resistance heliosphere, main structure layer and adhesive layer.Between the multilayer of existing near space airship envelope, conventionally all adopt the mode of heat seeling coating technique or applicator roll or adopt the bonding mode of film to realize and be bonded to each other, but because the thickness of each layer film is generally all very thin, therefore all very high for the accuracy requirement of above-mentioned technique, but still often inevitably occur the defects such as bubble or fold therefore the performance of produced near space airship envelope also having been produced to adverse effect.
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 is selected aluminum polyester (Al-PET) film, tack coat is polycarbonate, bearing layer is selected PBO plain cloth, prime coat is two component epoxy polyamide, weathering layer is nano-fluorine carbon coating, hot sealing layer thickness is 14 microns, resistance heliosphere be take PET film as basement membrane, adopts magnetron sputtering technique to deposit the aluminium film of the thin densification of one deck thereon, and the surface density of base material PET film is 60g/m
2, institute's aluminizer thickness is 70 nanometers, and resistance heliosphere thickness is 38 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 is to comprise nano-TiO
2, nano-MgO, nanometer CaCO
3, nano-ZnO high fluorinated hydroxy acrylic resin high solid coating, wherein nano-TiO
2, nano-MgO, nanometer CaCO
3, nano-ZnO particle diameter be 40-50 nanometer, it is 1:2:1:2 that their part by weight closes, weathering layer thickness is 30 microns.
The invention still further relates to a kind of method of manufacturing near space airship envelope, comprise the steps:
(1) at bearing layer inside face, apply successively tack coat, resistance heliosphere and hot sealing layer; Adhesive layer thickness is 15 microns, and resistance heliosphere thickness is 38 microns, and hot sealing layer thickness is 14 microns;
(2) at bearing layer outside face spraying two component epoxy polyamide priming paint, adopt airless spraying, pressure ratio 37:1 preferably, 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 more than 5 ℃, sprays one time higher than dew point, dry film thickness 15 μ m;
(3) spray two component epoxy polyamide priming paint and within 60 minutes, sprayed fluorocarbon coating afterwards, adopt airless spraying, pressure ratio 60:1 preferably, 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, while preferably filming together lower 27 degrees Celsius of standard thickness, surface drying time is 50 minutes, application twice; Per pass build 15 μ m.
Owing to having adopted nano-fluorine carbon coating; the enough protective coats of C-F bond energy are not subject to ultraviolet destruction; strengthened the self_cleaning effect of coating simultaneously; and the nano material wherein comprising also all possesses good uvioresistant and capability of environmental protection, so the use of nano-fluorine carbon coating has strengthened the weather resisting property of airship envelope widely.In addition, because the outer membrane of bearing layer has adopted the mode of spraying, can make film uniform and delicate more, reduce the appearance of bubble and fold.
The specific embodiment
According near space airship envelope of the present invention, comprise successively from outside to inside weathering layer, prime coat, bearing layer, tack coat, resistance heliosphere and hot sealing layer.Hot sealing layer is polyurethane film, and resistance heliosphere is selected aluminum polyester (Al-PET) film, and tack coat is polycarbonate, and bearing layer is selected 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 14 microns; Resistance heliosphere be take PET film as basement membrane, adopts magnetron sputtering technique to deposit the aluminium film of the thin densification of one deck thereon, and the surface density of base material PET film is 60g/m
2, institute's aluminizer thickness is 70 nanometers, and resistance heliosphere thickness is 38 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 is to comprise nano-TiO
2, nano-MgO, nanometer CaCO
3, nano-ZnO high fluorinated hydroxy acrylic resin high solid coating, wherein nano-TiO
2, nano-MgO, nanometer CaCO
3, nano-ZnO is 40-50 nanometer, it is 1:2:1:2 that their part by weight closes, 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, at bearing layer inside face, apply successively tack coat, resistance heliosphere and hot sealing layer; Adhesive layer thickness is 15 microns, and resistance heliosphere thickness is 38 microns, and hot sealing layer thickness is 14 microns;
The second, at bearing layer outside face spraying two component epoxy polyamide priming paint, adopt airless spraying, pressure ratio 37:1 preferably, 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 ℃, spray dry film thickness 15 μ m one time;
The 3rd, spray two component epoxy polyamide priming paint and within 60 minutes, sprayed fluorocarbon coating afterwards, adopted 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, while preferably filming together lower 27 degrees Celsius of standard thickness, surface drying time is 50 minutes, application twice; Per pass build 15 μ m.
Owing to having adopted nano-fluorine carbon coating; the enough protective coats of C-F bond energy are not subject to ultraviolet destruction; strengthened the self_cleaning effect of coating simultaneously; and the nano material wherein comprising also all possesses good uvioresistant and capability of environmental protection, so the use of nano-fluorine carbon coating has strengthened the weather resisting property of airship envelope widely.In addition, because the outer membrane of bearing layer has adopted 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 and replacing or modification content of the present invention according to content disclosed by the invention and the art technology of grasping; but these replacements or modification should not be considered as departing from the present invention's design, and these replacements or modification are all in the claimed interest field of the present invention.
Claims (3)
1. a near space dirigible, 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 is selected aluminum polyester (Al-PET) film, and tack coat is polycarbonate, bearing layer is selected PBO plain cloth, prime coat is two component epoxy polyamide, and weathering layer is nano-fluorine carbon coating, and hot sealing layer thickness is 14 microns; Resistance heliosphere be take PET film as basement membrane, adopts magnetron sputtering technique to deposit the aluminium film of the thin densification of one deck thereon, and the surface density of base material PET film is 60g/m
2, institute's aluminizer thickness is 70 nanometers, and resistance heliosphere thickness is 38 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 is to comprise nano-TiO
2, nano-MgO, nanometer CaCO
3, nano-ZnO high fluorinated hydroxy acrylic resin high solid coating, wherein nano-TiO
2, nano-MgO, nanometer CaCO
3, nano-ZnO particle diameter be 40-50 nanometer, it is 1:2:1:2 that their part by weight closes, weathering layer thickness is 30 microns.
2. a near space 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 is selected aluminum polyester (Al-PET) film, tack coat is polycarbonate, and bearing layer is selected PBO plain cloth, and prime coat is two component epoxy polyamide, weathering layer is nano-fluorine carbon coating, and hot sealing layer thickness is 14 microns; Resistance heliosphere be take PET film as basement membrane, adopts magnetron sputtering technique to deposit the aluminium film of the thin densification of one deck thereon, and the surface density of base material PET film is 60g/m
2, institute's aluminizer thickness is 70 nanometers, and resistance heliosphere thickness is 38 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 is to comprise nano-TiO
2, nano-MgO, nanometer CaCO
3, nano-ZnO high fluorinated hydroxy acrylic resin high solid coating, wherein nano-TiO
2, nano-MgO, nanometer CaCO
3, nano-ZnO particle diameter be 40-50 nanometer, it is 1:2:1:2 that their part by weight closes, weathering layer thickness is 30 microns.
3. manufacture a method near space airship envelope according to claim 2, comprise the steps:
(1) at bearing layer inside face, apply successively tack coat, resistance heliosphere and hot sealing layer; Adhesive layer thickness is 15 microns, and resistance heliosphere thickness is 38 microns, and hot sealing layer thickness is 14 microns;
(2) at bearing layer outside face spraying two component epoxy polyamide priming paint, adopt airless spraying, pressure ratio 37:1 preferably, 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 more than 5 ℃, sprays one time higher than dew point, dry film thickness 15 μ m;
(3) spray two component epoxy polyamide priming paint and within 60 minutes, sprayed fluorocarbon coating afterwards, adopt airless spraying, pressure ratio 60:1 preferably, 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, while preferably filming together lower 27 degrees Celsius of standard thickness, surface drying time is 50 minutes, application twice; Per pass build 15 μ m.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310504627.6A CN103600827B (en) | 2013-10-23 | 2013-10-23 | A kind of near space dirigible |
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| CN201310504627.6A CN103600827B (en) | 2013-10-23 | 2013-10-23 | A kind of near space dirigible |
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| CN103600827A true CN103600827A (en) | 2014-02-26 |
| CN103600827B CN103600827B (en) | 2015-09-23 |
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Citations (6)
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|---|---|---|---|---|
| JP2001039396A (en) * | 1999-07-27 | 2001-02-13 | Agency Of Ind Science & Technol | Gas cell film of stratosphere staying airship |
| JP2002036409A (en) * | 2000-07-27 | 2002-02-05 | Taiyo Kogyo Corp | Sheet material, its manufacturing method and flying object using sheet |
| JP2002200684A (en) * | 2000-10-31 | 2002-07-16 | Fuji Heavy Ind Ltd | Composite film |
| US20070281570A1 (en) * | 2006-05-30 | 2007-12-06 | Liggett Paul E | Reduced weight flexible laminate material for lighter-than-air vehicles |
| 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 |
-
2013
- 2013-10-23 CN CN201310504627.6A patent/CN103600827B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001039396A (en) * | 1999-07-27 | 2001-02-13 | Agency Of Ind Science & Technol | Gas cell film of stratosphere staying airship |
| JP2002036409A (en) * | 2000-07-27 | 2002-02-05 | Taiyo Kogyo Corp | Sheet material, its manufacturing method and flying object using sheet |
| JP2002200684A (en) * | 2000-10-31 | 2002-07-16 | Fuji Heavy Ind Ltd | Composite film |
| US20070281570A1 (en) * | 2006-05-30 | 2007-12-06 | Liggett Paul E | Reduced weight flexible laminate material for lighter-than-air vehicles |
| 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 |
|---|
| 曹旭等: "PBO基质平流层飞艇蒙皮材料的制备研究", 《高科技纤维与应用》 * |
| 杨景花: "纳米二氧化钛改性氟碳涂料及涂装工艺的研究", 《中国优秀硕士学位论文全文数据库》 * |
| 王博赟等: "纳米氟碳涂料研究进展", 《化工进展》 * |
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Effective date of registration: 20170725 Address after: Licheng Town East Street Liyang city 213300 Jiangsu city of Changzhou province 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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