CN103600563B - Aircraft radome leading edge - Google Patents
Aircraft radome leading edge Download PDFInfo
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- CN103600563B CN103600563B CN201310515957.5A CN201310515957A CN103600563B CN 103600563 B CN103600563 B CN 103600563B CN 201310515957 A CN201310515957 A CN 201310515957A CN 103600563 B CN103600563 B CN 103600563B
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Abstract
An aircraft radome leading edge comprises a radome leading edge shell and an anti-icing coat positioned outside the shell, the anti-icing coat comprises a primer and a finish, the primer is an epoxy polyurethane primer, and the finish is an organosilicon modified acrylate coating; the thicknesses of the dry films of the primer and the finish are 23mum and 43mum respectively; and the organosilicon modified acrylate coating comprises 55-65wt% of an organosilicon modified acrylic resin, 20-25wt% of a color filler, 3wt% of nanometer calcium carbonate, 3wt% of nanometer magnesium oxide, 1wt% of a leveling agent, 0.8wt% of an antifoaming agent, 1.2wt% of a dispersant, 0.5wt% of a catalyst and 3-5wt% of a solvent. The radome leading edge made in the invention can effectively reduce the formation of ice layers on the leading edge of a radome, and is in favor of the shedding of formed ice layers.
Description
Technical field
The present invention relates to a kind of aircraft radome leading edge.
Background technology
The world today, aircraft becomes the vehicles of people's pay attention to day by day gradually due to its quick, safe feature.But, when aircraft flies under icing meteorology condition with the subsonic speed being less than a certain critical Mach number, some parts windward surface will because of the droplets impact its in air, gather and freeze, such as cowl lip.A large amount of accidents and research all show that even the accumulated ice of aircraft key position, a small amount of, also can cause the lift of aircraft to decline, flight resistance increase, thus cause the deterioration of the pneumatic qualities such as the maneuverability of aircraft and stability.Especially aero-engine is under ground and humiture certain in the air, and freezing easily appears in air inlet radome fairing and support plate.Inlet flow field will be caused to distort owing to freezing, make engine performance deterioration; Ice comes off and engine blade also may be caused to rupture, and even causes the major accident of fatal crass.Especially large aircraft, have the features such as high thrust, large Gross Weight Takeoff, subsonic speed, strong viability (all-weather flight) as large-scale Dakota, this just determines this class aircraft and inevitably there is aloft ice formation issues.Therefore carry out aircraft to freeze and the research of guard technology is that very important importance developed by aircraft, especially large transport airplane, significant to flight safety.
For the different parts of aircraft, current anti-/ de-icing method is as follows: the (1) hot gas anti-icing system of engine bleed air: be mainly used in the anti-icing of wing, empennage leading edge and engine inlets lip and air inlet component, make the temperature of protection coating reach the evaporating temperature of super-cooling waterdrop under ice-formation condition by the heating of hot gas, thus avoid super-cooling waterdrop to freeze to freeze at frozen surface.(2) cycle gasbag-type deicing system: utilize engine bleed to supply air bag pneumatic channel, make it periodically to expand or shrink, destroys ice sheet and surperficial adhesion, then is issued to the object of deicing in the effect of aerodynamic force.Be mainly used in the deicing of wing, empennage leading edge, the bleed of needs is much little compared with hot gas anti-icing system, when anti-icing hot gas undersupply, can be used as alternative icing safeguard procedures.(3) electric heating prevents/deicing system: both sustainable heating played anti-ice action, can heat as deicing system in the cycle again.What be mainly used in propeller blade, rectification calotte and windscreen prevents/deicing.Except above-mentioned electric heating system, the electricity of low energy consumption scold deicing, Electro-Impulse De-icing and other novel anti-/ de-icing method, as ultrasonic wave, marmem and high-frequency electronic deicing etc. also can be used as the anti-icing replacement scheme of bleed, the key technology of these schemes, still in exploitation and experimental stage, needs in use to verify its feasibility and reliability further.
Except the method for these initiatively deicing above-mentioned, also extensively adopt in the world at present and play the effect of passive anti-deicing in easily the freeze method of position application low-surface-energy hydrophobic coating of aircraft.The low surface energy coat being coated in body surface, except reducing the condensation degree of super-cooling waterdrop at body surface, when aircraft is by heating active deicing, can also makes body surface ice sheet melt the water droplet formed and depart from body as early as possible, thus prevent from heavily freezing.The relatively aforementioned several method of method of this application low-surface-energy hydrophobic coating have cost low, consume energy little, realize the features such as difficulty is low, be the anti-deicing supplementary means of a kind of very important aircraft surfaces.But the performance of current most of low-surface-energy hydrophobic coatings still can not meet the safety requirements of the anti-deicing of aircraft surfaces completely.
Summary of the invention
The present invention aims to provide a kind of cowl lip, and its base house skin comprises organosilicon modified crylic acid resin ice-phobic coating, therefore, it is possible to effectively reduce the formation of ice sheet on cowl lip, and is conducive to coming off of the ice sheet formed.
Particularly, a kind of cowl lip, comprise cowl lip housing and the ice-phobic coating being positioned at hull outside, this ice-phobic coating comprises priming paint and finish paint, and described priming paint is epoxy polyurethane priming paint, finish paint is organic silicone modified acrylate coating material; The build of priming paint and finish paint is respectively 23 microns and 43 microns; Described organic silicone modified acrylate coating material comprises: by weight, organosilicon modified crylic acid resin 55-65%, color filters 20-25%, nano-calcium carbonate 3%, nano magnesia 3%, levelling agent 1%, defoamer 0.8%, dispersant 1.2%, catalyst 0.5%, solvent 3-5%; Organosilicon modified crylic acid resin is wherein prepared as follows: (1) prepares raw material: by weight, organic silicon monomer 23 parts, (methyl) acrylate monomer 100 parts, hydroxy acryl acid ester 45 parts, acrylonitrile 5 parts, amido silicon oil 20 parts, solvent 55 parts, initator 5 parts; (2) solvent of total solvent amount 75wt% is joined in the four-hole boiling flask that reflux condensing tube, thermometer, agitator and dropping funel are housed, pass into nitrogen deoxygenation, put into oil bath pan, be heated to 115 DEG C, start agitator, make solvent refluxing; The mixed solution that the 15wt% of the 95wt% of whole organic silicon monomer 23 parts, (methyl) acrylate monomer 100 parts, hydroxy acryl acid ester 45 parts, acrylonitrile 5 parts, amido silicon oil 20 parts, initator total amount, solvent total amount forms was joined evenly in reactor in 2 hours, after adding, continue insulation reaction 3 hours; Remaining initator and solvent are joined in reactor, continues insulation reaction and stop for 2.5 hours, be cooled to room temperature, discharging; Organic silicon monomer comprises VTES, the methyl vinyl diethoxysilane of weight ratio 5:7.
Preferably, (methyl) acrylate monomer comprises methyl methacrylate, the butyl methacrylate of weight ratio 5:7.
Preferably, described hydroxy acryl acid ester monomer is the one in methacrylic acid-beta-hydroxy ethyl ester, methacrylic acid-β-hydroxypropyl acrylate, senecioate-hydroxyl ethyl ester or senecioate-hydroxypropyl acrylate; Described initator comprises main initator and co initiator, and described main initator is the one in azodiisobutyronitrile, benzoyl peroxide, two t-amyl peroxy compounds or di-tert-butyl peroxide; Co initiator is the one in peroxide-2-ethyl hexanoic acid tert-butyl, peroxidized t-butyl perbenzoate, two tertiary amyl peroxide.The weight ratio of main initator and co initiator is 4:1.Described solvent is the one in ethyl acetate, butyl acetate, butanols, 1-Methoxy-2-propyl acetate or acetone.
Preferably, the concrete steps preparing organic silicone modified acrylate coating material are as follows: add the acrylic resin modified and mixed organic solvents of the aforementioned organic silicon of 80% quality in a reservoir, and whole nano materials and dispersant; Carry out stirring at low speed (380 revs/min), mixing time about 6 minutes, stop mixer; Then add described color filters, (2500 revs/min) stir 15 minutes at a high speed; Grinding, reaches grain fineness≤8 μm; Add remaining organosilicon modified crylic acid resin and other various described auxiliary agents again, and with remaining described organic solvent adjusting viscosity; Stir; Filter discharging.
Preferably, the technique of spray-applied primer and organic silicone modified acrylate coating material formation ice-phobic coating is as follows:
Cleaning and polishing:
60 DEG C of warm water washings are adopted to remove the remaining paint stripper of shell, be stained with solvent with the brown shirting of cleaning and slightly clean removal dirt, water sand milling or solvent sand milling case surface, be stained with the cleaning agent fine purifiation of coatings system surperficial and dry with the brown shirting of cleaning, the surface processed should be clean, pollution-free, ensures that 35s moisture film does not diverge continuously;
Spray-applied primer
Within cleaning and polishing step complete 5 hours, uniformly spray one deck epoxy polyurethane priming paint at shell; Adopt airless spraying, pressure ratio 55:1, spray gun distance 650 ~ 720mm, jet angle 75 ~ 85 degree, spray voltage 28 ~ 30V, spraying current 220 ~ 240A, nozzle diameter: 0.38 ~ 0.46mm, ambient humidity: < 76%, case surface temperature, higher than dew point more than 5 DEG C, sprays one time;
Spraying organic silicone modified acrylate coating material
Being dried at priming paint can adhesive tape but be no more than within the scope of 72h and carry out primary coat process: remove the coarse of dry spray with the sand felt being moistened with flexible solvent or aqua is gently worn, clean the dust particle of primed surface with dust-binding cloth, then use flexible solvent or alcohol isoreactivity solvent to the wiping one time gently of all primary coat faces; Until its dry tack free, determine primed surface without any pollution after, can application face be coated with; Adopt airless spraying, pressure ratio 47:1, spray gun distance 570 ~ 610mm, nozzle diameter: 0.85 ~ 0.91mm, ambient humidity: < 75%, case surface temperature: higher than dew point more than 6 DEG C, jet angle 77 ~ 88 degree, spray voltage 31 ~ 35V, spraying current 220 ~ 235A;
Maintenance, bone dry to be coated can come into operation.
Preferably, in uneven thickness on leading edge housing of ice-phobic coating, thinning or first thickening thinning gradually more gradually gradually backward from radome fairing front end.
The present invention also relates to a kind of prepare organosilicon modified crylic acid resin method, prepare the method for organic silicone modified acrylate coating material and in cowl lip assembly, form the spray painting method of ice-phobic coating.
Detailed description of the invention
Cowl lip assembly according to the present invention comprises cowl lip housing and is positioned at the ice-phobic coating of hull outside, and this ice-phobic coating comprises priming paint and finish paint, and described priming paint is epoxy polyurethane priming paint, finish paint is organic silicone modified acrylate coating material.Preferably, the build of priming paint and finish paint is respectively 23 microns and 43 microns.Preferably, in the present invention, the cowl lip of indication refers to that the radome fairing being projected in 1/5 scope before chord length is anterior.More preferably, in uneven thickness on leading edge housing of ice-phobic coating, such as thinning or first thickening thinning gradually gradually gradually backward from radome fairing front end, not only can improve anti-icing characteristic so simultaneously but also the impact that can reduce for radome fairing aeroperformance.
Particularly, form ice-phobic coating in cowl lip hull outside and comprise the steps: that (1) prepares Silicone-Modified Acrylate Resin; (2) organic silicone modified acrylate coating material is prepared; (3) spray-applied primer and organic silicone modified acrylate coating material, maintenance forms ice-phobic coating.
Silicone-Modified Acrylate Resin preparation method is specific as follows: (1) prepares raw material: by weight, organic silicon monomer 23 parts, (methyl) acrylate monomer 100 parts, hydroxy acryl acid ester 45 parts, acrylonitrile 5 parts, amido silicon oil 20 parts, solvent 55 parts, initator 5 parts; (2) solvent of total solvent amount 75wt% is joined in the four-hole boiling flask that reflux condensing tube, thermometer, agitator and dropping funel are housed, pass into nitrogen deoxygenation, put into oil bath pan, be heated to 115 DEG C, start agitator, make solvent refluxing; The mixed solution that the 15wt% of the 95wt% of whole organic silicon monomer 23 parts, (methyl) acrylate monomer 100 parts, hydroxy acryl acid ester 45 parts, acrylonitrile 5 parts, amido silicon oil 20 parts, initator total amount, solvent total amount forms was joined evenly in reactor in 2 hours, after adding, continue insulation reaction 3 hours; Remaining initator and solvent are joined in reactor, continues insulation reaction and stop for 2.5 hours, be cooled to room temperature, discharging.
Preferably, organic silicon monomer comprises VTES, the methyl vinyl diethoxysilane of weight ratio 5:7.
Preferably, (methyl) acrylate monomer comprises methyl methacrylate, the butyl methacrylate of weight ratio 5:7.
Described hydroxy acryl acid ester monomer is the one in methacrylic acid-beta-hydroxy ethyl ester, methacrylic acid-β-hydroxypropyl acrylate, senecioate-hydroxyl ethyl ester or senecioate-hydroxypropyl acrylate;
Described initator comprises main initator and co initiator, and described main initator is the one in azodiisobutyronitrile, benzoyl peroxide, two t-amyl peroxy compounds or di-tert-butyl peroxide; Co initiator is the one in peroxide-2-ethyl hexanoic acid tert-butyl, peroxidized t-butyl perbenzoate, two tertiary amyl peroxide.The weight ratio of main initator and co initiator is 4:1.
Described solvent is the one in ethyl acetate, butyl acetate, butanols, 1-Methoxy-2-propyl acetate or acetone.
The concrete steps preparing organic silicone modified acrylate coating material are as follows:
Add the acrylic resin modified and mixed organic solvents of the aforementioned organic silicon of 80% quality in a reservoir, and whole nano materials and dispersant; Carry out stirring at low speed (380 revs/min), mixing time about 6 minutes, stop mixer; Then add described color filters, (2500 revs/min) stir 15 minutes at a high speed; Grinding, reaches grain fineness≤8 μm; Add remaining organosilicon modified crylic acid resin and other various described auxiliary agents again, and with remaining described organic solvent adjusting viscosity; Stir; Filter discharging.
Preferably, color filters used can select multiple pigment, such as white, red, yellow, black or blueness, wherein said Chinese white is rutile type titanium white, described redness and yellow uitramarine are azo pigment, described black pigment is middle colour carbon black, and described blue pigment is the blue or green series of phthalein.Described levelling agent is the surfactant of esters of acrylic acid, ester fourth cellulose family and long-chain silicones class; Described catalyst is not containing the environment-friendly type catalyst of organotin, such as K-KAT4205 zirconium complex.Defoamer, composition is polysiloxane solution, such as BYK-066N or BYK-141; Dispersant, composition is the high molecular weight block copolymer solution containing affine pigment group, as BYK-161 or BYK-163; Described mixed solvent is the mixture of methyl iso-butyl ketone (MIBK), 1-Methoxy-2-propyl acetate and butyl acetate, and mixed proportion is 1:2:3.Preferably, by weight, organosilicon modified crylic acid resin 55-65%, color filters 20-25%, nano-calcium carbonate 3%, nano magnesia 3%, levelling agent 1%, defoamer 0.8%, dispersant 1.2%, catalyst 0.5%, solvent 3-5%.
The technique that spray-applied primer and organic silicone modified acrylate coating material form ice-phobic coating is as follows:
Cleaning and polishing:
60 DEG C of warm water washings are adopted to remove the remaining paint stripper of shell, be stained with solvent with the brown shirting of cleaning and slightly clean removal dirt, water sand milling or solvent sand milling case surface, be stained with the cleaning agent fine purifiation of coatings system surperficial and dry with the brown shirting of cleaning, the surface processed should be clean, pollution-free, ensures that 35s moisture film does not diverge continuously;
Spray-applied primer
Within cleaning and polishing step complete 5 hours, uniformly spray one deck epoxy polyurethane priming paint at shell; Adopt airless spraying, pressure ratio 55:1, spray gun distance 650 ~ 720mm, jet angle 75 ~ 85 degree, spray voltage 28 ~ 30V, spraying current 220 ~ 240A, nozzle diameter: 0.38 ~ 0.46mm, ambient humidity: < 76%, case surface temperature, higher than dew point more than 5 DEG C, sprays one time;
Spraying organic silicone modified acrylate coating material
Being dried at priming paint can adhesive tape but be no more than within the scope of 72h and carry out primary coat process: remove the coarse of dry spray with the sand felt being moistened with flexible solvent or aqua is gently worn, clean the dust particle of primed surface with dust-binding cloth, then use flexible solvent or alcohol isoreactivity solvent to the wiping one time gently of all primary coat faces; Until its dry tack free, determine primed surface without any pollution after, can application face be coated with; Adopt airless spraying, pressure ratio 47:1, spray gun distance 570 ~ 610mm, nozzle diameter: 0.85 ~ 0.91mm, ambient humidity: < 75%, case surface temperature: higher than dew point more than 6 DEG C, jet angle 77 ~ 88 degree, spray voltage 31 ~ 35V, spraying current 220 ~ 235A;
Maintenance, bone dry to be coated can come into operation.
Ice-phobic coating according to the present invention has lower surface energy, effectively can prevent cowl lip from freezing and being conducive to established ice cube and come off.Meanwhile, this ice-phobic coating meets national standard, if GB6379, GB1725, GB1720, GB1732, GB1728 are about coating hardness, viscosity, adhesive force, impact strength and the requirement of drying time.
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. an aircraft radome leading edge, comprise cowl lip housing and the ice-phobic coating being positioned at hull outside, this ice-phobic coating comprises priming paint and finish paint, and described priming paint is epoxy polyurethane priming paint, finish paint is organic silicone modified acrylate coating material; The build of priming paint and finish paint is respectively 23 microns and 43 microns; Described organic silicone modified acrylate coating material comprises: by weight, organosilicon modified crylic acid resin 55-65%, color filters 20-25%, nano-calcium carbonate 3%, nano magnesia 3%, levelling agent 1%, defoamer 0.8%, dispersant 1.2%, catalyst 0.5%, the first solvent 3-5%; Organosilicon modified crylic acid resin is wherein prepared as follows: (1) prepares raw material: by weight, organic silicon monomer 23 parts, (methyl) acrylate monomer 100 parts, hydroxy acryl acid ester 45 parts, acrylonitrile 5 parts, amido silicon oil 20 parts, the second solvent 55 parts, initator 5 parts; (2) second solvent of total second quantity of solvent 75wt% is joined in the four-hole boiling flask that reflux condensing tube, thermometer, agitator and dropping funel are housed, pass into nitrogen deoxygenation, put into oil bath pan, be heated to 115 DEG C, start agitator, make the second solvent refluxing; The mixed solution that the 15wt% of the 95wt% of whole organic silicon monomer 23 parts, (methyl) acrylate monomer 100 parts, hydroxy acryl acid ester 45 parts, acrylonitrile 5 parts, amido silicon oil 20 parts, initator total amount, the second solvent total amount forms was joined evenly in reactor in 2 hours, after adding, continue insulation reaction 3 hours; Remaining initator and the second solvent are joined in reactor, continues insulation reaction and stop for 2.5 hours, be cooled to room temperature, discharging; Organic silicon monomer comprises VTES, the methyl vinyl diethoxysilane of weight ratio 5:7.
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| CN201310515957.5A CN103600563B (en) | 2013-10-26 | 2013-10-26 | Aircraft radome leading edge |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4797325A (en) * | 1984-12-13 | 1989-01-10 | United Kingdom Atomic Energy Authority | Spacecraft materials |
| CN102382536A (en) * | 2011-08-11 | 2012-03-21 | 天津大学 | Super-hydrophobic ice-covering-proof coating having slowly-releasing function and preparation method thereof |
| CN103305112A (en) * | 2013-06-27 | 2013-09-18 | 浙江大学 | Environment-friendly coating with anti-icing function and preparation method thereof |
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2013
- 2013-10-26 CN CN201310515957.5A patent/CN103600563B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4797325A (en) * | 1984-12-13 | 1989-01-10 | United Kingdom Atomic Energy Authority | Spacecraft materials |
| CN102382536A (en) * | 2011-08-11 | 2012-03-21 | 天津大学 | Super-hydrophobic ice-covering-proof coating having slowly-releasing function and preparation method thereof |
| CN103305112A (en) * | 2013-06-27 | 2013-09-18 | 浙江大学 | Environment-friendly coating with anti-icing function and preparation method thereof |
Non-Patent Citations (1)
| Title |
|---|
| 王毅,元辛等.飞机机翼防除冰系统研究进展.《河南科学》.2012,第30卷(第9期),第1246-1250页. * |
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Effective date of registration: 20170731 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. |