CN103587202A - Wingtip's winglet leading-edge assembly - Google Patents
Wingtip's winglet leading-edge assembly Download PDFInfo
- Publication number
- CN103587202A CN103587202A CN201310520297.XA CN201310520297A CN103587202A CN 103587202 A CN103587202 A CN 103587202A CN 201310520297 A CN201310520297 A CN 201310520297A CN 103587202 A CN103587202 A CN 103587202A
- Authority
- CN
- China
- Prior art keywords
- solvent
- parts
- leading edge
- initator
- clean
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Landscapes
- Paints Or Removers (AREA)
Abstract
A wingtip's winglet leading-edge assembly comprises a wingtip's winglet leading-edge housing and an anti-icing coating positioned outside the housing. The anti-icing coating comprises a primer and a finish paint. The primer is a zinc-based epoxy zinc-rich primer. The finish paint is an organic silicon modified acrylate coating. Dry film thicknesses of the primer and the finish paint are respectively 27 micrometers and 48 micrometers. The organic silicon modified acrylate coating comprises: by weight, 55-65% of organic silicon modified acrylic resin, 20-25% of pigment and filler, 3% of nano-calcium phosphate , 3% of nanometer titanium dioxide, 1% of a levelling agent, 0.8% of an antifoaming agent, 1.2% of a dispersant, 0.5% of a catalyst and 3-5% of a solvent. According to the wingtip's winglet leading-edge assembly, formation of an ice layer on the wingtip's winglet leading edge can be minimized effectively. In addition, the wingtip's winglet leading-edge assembly is beneficial to shedding of an ice layer which has already formed.
Description
Technical field
The present invention relates to a kind of winglet leading edge assembly.
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 while flying when aircraft is freezing meteorological condition with the subsonic speed that is less than a certain critical Mach number under, the surface windward of some parts will be because of the droplets impact its in atmosphere, gather and freeze, winglet leading edge for example.A large amount of accidents and research all show, even the accumulated ice of aircraft key position, a small amount of, also can cause the lift of aircraft to decline, and flight resistance increases, thereby cause the deterioration of the pneumatic qualities such as the maneuverability of aircraft and stability.Especially aero-engine is under ground and aerial certain humiture, and air inlet radome fairing and support plate are prone to icing.Owing to freezing, will cause inlet flow field distortion, engine performance is worsened; Ice comes off and also may cause engine blade fracture, even causes fatal crass's major accident.Especially large aircraft, has the features such as high thrust, large Gross Weight Takeoff, subsonic speed, strong viability (all-weather flight) as large-scale Dakota, and this has just determined that this class aircraft inevitably exists aloft ice formation issues.Therefore carrying out aircraft research icing and guard technology is that aircraft, especially large transport airplane are developed very important importance, significant to flight safety.
Different parts for aircraft, current anti-/ de-icing method is as follows: the (1) hot air anti-icing system of engine compressor bleed: be mainly used in the anti-icing of wing, empennage leading edge and engine inlets lip and air inlet component, heating by hot gas makes the temperature of protection coating reach the evaporating temperature of super-cooling waterdrop under ice-formation condition, thereby avoids super-cooling waterdrop to freeze in icing shallow freezing.(2) cycle gasbag-type deicing system: utilize engine bleed to supply with air bag pneumatic channel, make it periodically expand or shrink, destruction ice sheet and surperficial adhesion, then in the effect of aerodynamic force, be issued to the object of deicing.Be mainly used in the deicing of wing, empennage leading edge, the bleed needing is little a lot of compared with hot air anti-icing system, when anti-icing hot gas undersupply, can be used as alternative icing safeguard procedures.Electric heating anti-/ deicing system: both sustainable heating played anti-ice action, can heat as deicing system in the cycle again.Be mainly used in the prevent/deicing of propeller blade, rectification calotte and windscreen.Except above-mentioned electric heating system, the electricity of low energy consumption is scolded deicing, Electro-Impulse De-icing and other novel prevent/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 further to verify its feasibility and reliability.
Except above-mentioned these initiatively the method for deicing, also extensively adopt in the world at present in easily the freeze method of position application low-surface-energy hydrophobic coating of aircraft and play the effect of passive anti-deicing.Be coated in the low surface energy coat of body surface except reducing super-cooling waterdrop in the degree of condensing of body surface, when aircraft passes through heating active deicing, can also make body surface ice sheet melt the water droplet forming and depart from as early as possible body, thereby 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
Therefore the present invention aims to provide a kind of winglet leading edge assembly, and its base house skin comprises organosilicon modified crylic acid resin ice-phobic coating, can effectively reduce the formation of ice sheet in winglet leading edge, and the coming off of the ice sheet that is conducive to form.
Particularly, a kind of winglet leading edge assembly, comprises winglet leading edge housing and the ice-phobic coating that is positioned at hull outside, and this ice-phobic coating comprises priming paint and finish paint, and described priming paint is that zinc-base epoxy zinc rich primer, finish paint are organic silicone modified acrylate coating material; The build of priming paint and finish paint is respectively 27 microns and 48 microns; Described organic silicone modified acrylate coating material comprises: by weight, and organosilicon modified crylic acid resin 55-65%, color filler 20-25%, nano-calcium phosphate 3%, nano titanium oxide 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, and 28 parts of organic silicon monomers, 100 parts of (methyl) acrylate monomers, 45 parts of hydroxy acryl acid esters, 5 parts of acrylonitrile, 20 parts of amido silicon oils, 55 parts of solvents, 5 parts of initators; (2) solvent of total solvent amount 75 wt% 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 ℃, start agitator, make solvent refluxing; The mixed solution that 15 wt% of 95 wt% of 28 parts of whole organic silicon monomers, 100 parts of (methyl) acrylate monomers, 45 parts of hydroxy acryl acid esters, 5 parts of acrylonitrile, 20 parts of amido silicon oils, initator total amount, solvent total amount are formed joined evenly in reactor in 2 hours, after adding, continue insulation reaction 3 hours; Remaining initator and solvent are joined in reactor, continue insulation reaction and stop for 2.5 hours, be cooled to room temperature, discharging; Organic silicon monomer comprises that weight ratio is γ methyl ethylene diethoxy silane, the tetramethyl divinyl disiloxane of 7:8.
Preferably, methyl) acrylate monomer comprises that weight ratio is 7:8 methacrylic acid-2-Octyl Nitrite, methyl acrylate.
Preferably, described hydroxy acryl acid ester monomer is a kind of 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 auxiliary initator, and described main initator is a kind of in azodiisobutyronitrile, benzoyl peroxide, two t-amyl peroxy things or di-tert-butyl peroxide; Auxiliary initator is a kind of in peroxide-2-ethyl hexanoic acid tert-butyl, peroxidized t-butyl perbenzoate, two tertiary amyl peroxide.The weight ratio of main initator and auxiliary initator is 4:1.Described solvent is a kind of in ethyl acetate, butyl acetate, butanols, 1-Methoxy-2-propyl acetate or acetone.
Preferably, the concrete steps of preparing organic silicone modified acrylate coating material are as follows: in container, add aforementioned organosilicon modified crylic acid resin and the mixed organic solvents of 80% quality, and whole nano materials and dispersant; Carry out stirring at low speed (380 revs/min), mixing time approximately 6 minutes, stops mixer; Then add described color filler, (2500 revs/min) stir 15 minutes at a high speed; Grind, reach grain fineness≤8 μ m; Add again remaining organosilicon modified crylic acid resin and other various described auxiliary agents, and with remaining described organic solvent adjusting viscosity; Stir; Filter discharging.
Preferably, the technique of spraying priming paint and organic silicone modified acrylate coating material formation ice-phobic coating is as follows:
Clean and polishing:
Adopt 60 ℃ of warm water washings to remove the remaining paint stripper of shell, with clean brown shirting, be stained with solvent and slightly clean removal dirt, water sand milling or solvent sand milling case surface, with clean brown shirting, be stained with the cleaning agent fine purifiation surface of coatings system also dry, the surface of processing should be clean, pollution-free, guarantees that 35s moisture film does not diverge continuously;
Spraying priming paint
Cleaning and polishing step completes within 5 hours, shell surface uniform spray one deck zinc-base epoxy zinc rich primer; 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 more than 5 ℃, sprays one time higher than dew point;
Spraying organic silicone modified acrylate coating material
At priming paint, being dried to can adhesive tape but be no more than and within the scope of 72h, carry out primary coat processing: with light worn the coarse of dry spray that go of the sand felt that is moistened with flexible solvent or aqua, with the dust particle on the clean primary coat of dust-binding cloth surface, 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 primary coat 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: more than 6 ℃, jet angle 77～88 is spent higher than dew point, spray voltage 31～35V, spraying current 220～235A;
Maintenance, treats that coating bone dry can come into operation.
Preferably, in uneven thickness on leading edge housing of ice-phobic coating, from attenuation or the first thickening attenuation gradually more gradually gradually backward of winglet front end.
The present invention also relates to a kind of method of preparing organosilicon modified crylic acid resin, prepare the method for organic silicone modified acrylate coating material and in winglet leading edge assembly, form the spray painting method of ice-phobic coating.
The specific embodiment
Winglet leading edge assembly according to the present invention comprises winglet leading edge housing and the ice-phobic coating that is positioned at hull outside, and this ice-phobic coating comprises priming paint and finish paint, and described priming paint is that zinc-base epoxy zinc rich primer, finish paint are organic silicone modified acrylate coating material.Preferably, the build of priming paint and finish paint is respectively 27 microns and 48 microns.Preferably, in the present invention, the winglet leading edge of indication refers to the winglet front portion that is projected in front 1/5 scope of chord length.More preferably, in uneven thickness on leading edge housing of ice-phobic coating, for example from winglet front end, attenuation or first thickening gradually, in attenuation gradually, can not only improve anti-icing characteristic simultaneously but also can reduce the impact for winglet aeroperformance so gradually backward.
Particularly, in winglet leading edge hull outside, form ice-phobic coating and comprise the steps: that (1) prepare Silicone-Modified Acrylate Resin; (2) prepare organic silicone modified acrylate coating material; (3) spraying priming paint 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, and 28 parts of organic silicon monomers, 100 parts of (methyl) acrylate monomers, 45 parts of hydroxy acryl acid esters, 5 parts of acrylonitrile, 20 parts of amido silicon oils, 55 parts of solvents, 5 parts of initators; (2) solvent of total solvent amount 75 wt% 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 ℃, start agitator, make solvent refluxing; The mixed solution that 15 wt% of 95 wt% of 28 parts of whole organic silicon monomers, 100 parts of (methyl) acrylate monomers, 45 parts of hydroxy acryl acid esters, 5 parts of acrylonitrile, 20 parts of amido silicon oils, initator total amount, solvent total amount are formed joined evenly in reactor in 2 hours, after adding, continue insulation reaction 3 hours; Remaining initator and solvent are joined in reactor, continue insulation reaction and stop for 2.5 hours, be cooled to room temperature, discharging.
Preferably, organic silicon monomer comprises that weight ratio is γ methyl ethylene diethoxy silane, the tetramethyl divinyl disiloxane of 7:8; (methyl) acrylate monomer comprises that weight ratio is 7:8 methacrylic acid-2-Octyl Nitrite, methyl acrylate.
Described hydroxy acryl acid ester monomer is a kind of 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 auxiliary initator, and described main initator is a kind of in azodiisobutyronitrile, benzoyl peroxide, two t-amyl peroxy things or di-tert-butyl peroxide; Auxiliary initator is a kind of in peroxide-2-ethyl hexanoic acid tert-butyl, peroxidized t-butyl perbenzoate, two tertiary amyl peroxide.The weight ratio of main initator and auxiliary initator is 4:1.
Described solvent is a kind of in ethyl acetate, butyl acetate, butanols, 1-Methoxy-2-propyl acetate or acetone.
The concrete steps of preparing organic silicone modified acrylate coating material are as follows:
The aforementioned organosilicon modified crylic acid resin and the mixed organic solvents that in container, add 80% quality, and whole nano materials and dispersant; Carry out stirring at low speed (380 revs/min), mixing time approximately 6 minutes, stops mixer; Then add described color filler, (2500 revs/min) stir 15 minutes at a high speed; Grind, reach grain fineness≤8 μ m; Add again remaining organosilicon modified crylic acid resin and other various described auxiliary agents, and with remaining described organic solvent adjusting viscosity; Stir; Filter discharging.
Preferably, color filler used can be selected multiple pigment, for example 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 contain the environment-friendly type catalyst of organotin, for example K-KAT4205 zirconium complex.Defoamer, composition is polysiloxane solution, for example BYK-066N or BYK-141; Dispersant, composition is for 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 filler 20-25%, nano-calcium phosphate 3%, nano titanium oxide 3%, levelling agent 1%, defoamer 0.8%, dispersant 1.2%, catalyst 0.5%, solvent 3-5%.
The technique that spraying priming paint and organic silicone modified acrylate coating material form ice-phobic coating is as follows:
Clean and polishing:
Adopt 60 ℃ of warm water washings to remove the remaining paint stripper of shell, with clean brown shirting, be stained with solvent and slightly clean removal dirt, water sand milling or solvent sand milling case surface, with clean brown shirting, be stained with the cleaning agent fine purifiation surface of coatings system also dry, the surface of processing should be clean, pollution-free, guarantees that 35s moisture film does not diverge continuously;
Spraying priming paint
Cleaning and polishing step completes within 5 hours, shell surface uniform spray one deck zinc-base epoxy zinc rich primer; 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 more than 5 ℃, sprays one time higher than dew point;
Spraying organic silicone modified acrylate coating material
At priming paint, being dried to can adhesive tape but be no more than and within the scope of 72h, carry out primary coat processing: with light worn the coarse of dry spray that go of the sand felt that is moistened with flexible solvent or aqua, with the dust particle on the clean primary coat of dust-binding cloth surface, 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 primary coat 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: more than 6 ℃, jet angle 77～88 is spent higher than dew point, spray voltage 31～35V, spraying current 220～235A;
Maintenance, treats that coating bone dry can come into operation.
Ice-phobic coating according to the present invention have lower surface can, can effectively prevent from that winglet leading edge from freezing and being conducive to established ice cube to come off.Meanwhile, this ice-phobic coating meets national standard, as GB6379, GB1725, GB1720, GB1732, the GB1728 requirement about coating hardness, viscosity, adhesive force, impact strength and drying time.
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 (9)
1. a winglet leading edge assembly, comprises winglet leading edge housing and the ice-phobic coating that is positioned at hull outside, and this ice-phobic coating comprises priming paint and finish paint, and described priming paint is that zinc-base epoxy zinc rich primer, finish paint are organic silicone modified acrylate coating material; The build of priming paint and finish paint is respectively 27 microns and 48 microns; Described organic silicone modified acrylate coating material comprises: by weight, and organosilicon modified crylic acid resin 55-65%, color filler 20-25%, nano-calcium phosphate 3%, nano titanium oxide 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, and 28 parts of organic silicon monomers, 100 parts of (methyl) acrylate monomers, 45 parts of hydroxy acryl acid esters, 5 parts of acrylonitrile, 20 parts of amido silicon oils, 55 parts of solvents, 5 parts of initators; (2) solvent of total solvent amount 75 wt% 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 ℃, start agitator, make solvent refluxing; The mixed solution that 15 wt% of 95 wt% of 28 parts of whole organic silicon monomers, 100 parts of (methyl) acrylate monomers, 45 parts of hydroxy acryl acid esters, 5 parts of acrylonitrile, 20 parts of amido silicon oils, initator total amount, solvent total amount are formed joined evenly in reactor in 2 hours, after adding, continue insulation reaction 3 hours; Remaining initator and solvent are joined in reactor, continue insulation reaction and stop for 2.5 hours, be cooled to room temperature, discharging; Organic silicon monomer comprises that weight ratio is γ methyl ethylene diethoxy silane, the tetramethyl divinyl disiloxane of 7:8.
2. winglet leading edge assembly according to claim 1, is characterized in that: (methyl) acrylate monomer comprises that weight ratio is 7:8 methacrylic acid-2-Octyl Nitrite, methyl acrylate.
3. according to the winglet leading edge assembly described in aforementioned arbitrary claim, it is characterized in that: described hydroxy acryl acid ester monomer is a kind of 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 auxiliary initator, and described main initator is a kind of in azodiisobutyronitrile, benzoyl peroxide, two t-amyl peroxy things or di-tert-butyl peroxide; Auxiliary initator is a kind of in peroxide-2-ethyl hexanoic acid tert-butyl, peroxidized t-butyl perbenzoate, two tertiary amyl peroxide; The weight ratio of main initator and auxiliary initator is 4:1; Described solvent is a kind of in ethyl acetate, butyl acetate, butanols, 1-Methoxy-2-propyl acetate or acetone.
4. according to the winglet leading edge assembly described in aforementioned arbitrary claim, it is characterized in that: the concrete steps of preparing organic silicone modified acrylate coating material are as follows: in container, add aforementioned organosilicon modified crylic acid resin and the mixed organic solvents of 80% quality, and whole nano materials and dispersant; Carry out stirring at low speed (380 revs/min), mixing time approximately 6 minutes, stops mixer; Then add described color filler, (2500 revs/min) stir 15 minutes at a high speed; Grind, reach grain fineness≤8 μ m; Add again remaining organosilicon modified crylic acid resin and other various described auxiliary agents, and with remaining described organic solvent adjusting viscosity; Stir; Filter discharging.
5. according to the winglet leading edge assembly described in aforementioned arbitrary claim, it is characterized in that: the technique that spraying priming paint and organic silicone modified acrylate coating material form ice-phobic coating is as follows:
Clean and polishing:
Adopt 60 ℃ of warm water washings to remove the remaining paint stripper of shell, with clean brown shirting, be stained with solvent and slightly clean removal dirt, water sand milling or solvent sand milling case surface, with clean brown shirting, be stained with the cleaning agent fine purifiation surface of coatings system also dry, the surface of processing should be clean, pollution-free, guarantees that 35s moisture film does not diverge continuously;
Spraying priming paint
Cleaning and polishing step completes within 5 hours, shell surface uniform spray one deck zinc-base epoxy zinc rich primer; 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 more than 5 ℃, sprays one time higher than dew point;
Spraying organic silicone modified acrylate coating material
At priming paint, being dried to can adhesive tape but be no more than and within the scope of 72h, carry out primary coat processing: with light worn the coarse of dry spray that go of the sand felt that is moistened with flexible solvent or aqua, with the dust particle on the clean primary coat of dust-binding cloth surface, 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 primary coat 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: more than 6 ℃, jet angle 77～88 is spent higher than dew point, spray voltage 31～35V, spraying current 220～235A;
Maintenance, treats that coating bone dry can come into operation.
6. according to the winglet leading edge assembly described in aforementioned arbitrary claim, it is characterized in that: in uneven thickness on leading edge housing of ice-phobic coating, from attenuation or the first thickening attenuation gradually more gradually gradually backward of winglet front end.
7. one kind for the preparation of according to forming the method for the organic silicone modified acrylate coating material of ice-phobic coating in the winglet leading edge assembly described in any one in claim 1-6, it is characterized in that concrete steps are as follows: in container, add aforementioned organosilicon modified crylic acid resin and the mixed organic solvents of 80% quality, and whole nano materials and dispersant; Carry out stirring at low speed (380 revs/min), mixing time approximately 6 minutes, stops mixer; Then add described color filler, (2500 revs/min) stir 15 minutes at a high speed; Grind, reach grain fineness≤8 μ m; Add again remaining organosilicon modified crylic acid resin and other various described auxiliary agents, and with remaining described organic solvent adjusting viscosity; Stir; Filter discharging; This coating comprises: by weight, and organosilicon modified crylic acid resin 55-65%, color filler 20-25%, nano-calcium phosphate 3%, nano titanium oxide 3%, levelling agent 1%, defoamer 0.8%, dispersant 1.2%, catalyst 0.5%, solvent 3-5%.
8. one kind for the preparation of according to the method that forms the organosilicon modified crylic acid resin in the organic silicone modified acrylate coating material of ice-phobic coating in the winglet leading edge assembly described in any one in claim 1-6, it is characterized in that specific as follows: (1) prepares raw material: by weight, 28 parts of organic silicon monomers, 100 parts of (methyl) acrylate monomers, 45 parts of hydroxy acryl acid esters, 5 parts of acrylonitrile, 20 parts of amido silicon oils, 55 parts of solvents, 5 parts of initators; (2) solvent of total solvent amount 75 wt% 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 ℃, start agitator, make solvent refluxing; The mixed solution that 15 wt% of 95 wt% of 28 parts of whole organic silicon monomers, 100 parts of (methyl) acrylate monomers, 45 parts of hydroxy acryl acid esters, 5 parts of acrylonitrile, 20 parts of amido silicon oils, initator total amount, solvent total amount are formed joined evenly in reactor in 2 hours, after adding, continue insulation reaction 3 hours; Remaining initator and solvent are joined in reactor, continue insulation reaction and stop for 2.5 hours, be cooled to room temperature, discharging.
9. according to forming a spray painting method for ice-phobic coating in the winglet leading edge assembly described in any one in claim 1-6, it is characterized in that concrete technology is as follows:
Clean and polishing:
Adopt 60 ℃ of warm water washings to remove the remaining paint stripper of shell, with clean brown shirting, be stained with solvent and slightly clean removal dirt, water sand milling or solvent sand milling case surface, with clean brown shirting, be stained with the cleaning agent fine purifiation surface of coatings system also dry, the surface of processing should be clean, pollution-free, guarantees that 35s moisture film does not diverge continuously;
Spraying priming paint
Cleaning and polishing step completes within 5 hours, shell surface uniform spray one deck zinc-base epoxy zinc rich primer; 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 more than 5 ℃, sprays one time higher than dew point;
Spraying organic silicone modified acrylate coating material
At priming paint, being dried to can adhesive tape but be no more than and within the scope of 72h, carry out primary coat processing: with light worn the coarse of dry spray that go of the sand felt that is moistened with flexible solvent or aqua, with the dust particle on the clean primary coat of dust-binding cloth surface, 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 primary coat 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: more than 6 ℃, jet angle 77～88 is spent higher than dew point, spray voltage 31～35V, spraying current 220～235A;
Maintenance, treats that coating bone dry can come into operation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310520297.XA CN103587202B (en) | 2013-10-30 | 2013-10-30 | A kind of winglet leading edge assemblies |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310520297.XA CN103587202B (en) | 2013-10-30 | 2013-10-30 | A kind of winglet leading edge assemblies |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103587202A true CN103587202A (en) | 2014-02-19 |
| CN103587202B CN103587202B (en) | 2015-11-25 |
Family
ID=50077619
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310520297.XA Active CN103587202B (en) | 2013-10-30 | 2013-10-30 | A kind of winglet leading edge assemblies |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103587202B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030235696A1 (en) * | 2002-06-07 | 2003-12-25 | The Boeing Company | Polysiloxane(amide-ureide) anti-ice coating |
| CN1478801A (en) * | 2003-07-11 | 2004-03-03 | 中国科学院广州化学研究所 | Method of modifying acrylate using organic silicone |
| CN102321415A (en) * | 2011-08-11 | 2012-01-18 | 天津大学 | Fluorine-silicon acrylic resin nano composite anti-icing coating and preparation method thereof |
| CN102660182A (en) * | 2012-03-07 | 2012-09-12 | 中国科学院化学研究所 | Nanocomposite ice-coating-proof paint having properties of superhydrophobicity and low adhesive strength |
| CN103203938A (en) * | 2013-04-12 | 2013-07-17 | 大连交通大学 | Spontaneous heating coating for substrate surface and preparation method of spontaneous heating coating |
-
2013
- 2013-10-30 CN CN201310520297.XA patent/CN103587202B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030235696A1 (en) * | 2002-06-07 | 2003-12-25 | The Boeing Company | Polysiloxane(amide-ureide) anti-ice coating |
| CN1478801A (en) * | 2003-07-11 | 2004-03-03 | 中国科学院广州化学研究所 | Method of modifying acrylate using organic silicone |
| CN102321415A (en) * | 2011-08-11 | 2012-01-18 | 天津大学 | Fluorine-silicon acrylic resin nano composite anti-icing coating and preparation method thereof |
| CN102660182A (en) * | 2012-03-07 | 2012-09-12 | 中国科学院化学研究所 | Nanocomposite ice-coating-proof paint having properties of superhydrophobicity and low adhesive strength |
| CN103203938A (en) * | 2013-04-12 | 2013-07-17 | 大连交通大学 | Spontaneous heating coating for substrate surface and preparation method of spontaneous heating coating |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103587202B (en) | 2015-11-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103589263A (en) | Coating-containing anti-icing propeller blade leading-edge assembly | |
| CN103587206B (en) | Wing's leading edge with anti-icing coating | |
| CN103587208A (en) | Nose leading edge containing anti-icing coating | |
| CN103600562B (en) | Propeller blade leading edge assembly | |
| CN103587204B (en) | Tailplane leading edge assembly | |
| CN103587209A (en) | Anti-icing aircraft fairing leading edge | |
| CN103587192A (en) | Fairing leading-edge assembly with anti-icing coating | |
| CN103722850A (en) | Engine hanging bracket front edge component of aircraft | |
| CN103587201B (en) | Anti-icing propeller blade leading-edge assembly | |
| CN103587203A (en) | Ice protection tailplane leading-edge assembly | |
| CN103587191A (en) | Anti-icing vertical tail leading-edge assembly | |
| CN103625070A (en) | Coating-containing wing leading edge component | |
| CN103600559B (en) | Anti-icing wing leading edge | |
| CN103587199B (en) | Wingtip's winglet leading edge | |
| CN103587205B (en) | Anti-icing aircraft engine lifting bracket leading-edge | |
| CN103600550B (en) | A kind of Aircraft engine hanger leading edge | |
| CN103587189B (en) | A kind of leading edge of a wing assembly | |
| CN103625069B (en) | Front edge of engine air inlet duct of aircraft | |
| CN103587188B (en) | Ice-proof vertical tail leading edge assembly | |
| CN103587200B (en) | A kind of ice protection engine inlets leading edge | |
| CN103600541B (en) | A kind of front edge of engine air inlet duct of aircraft assembly | |
| CN103600549B (en) | A kind of aircraft radome leading edge assemblies | |
| CN103625056B (en) | Front-edge component of engine air inlet duct of anti-icing aircraft | |
| CN103587202A (en) | Wingtip's winglet leading-edge assembly | |
| CN103587190A (en) | Anti-icing wingtip's winglet leading-edge assembly |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20170724 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. |
|
| TR01 | Transfer of patent right |