CN106828873B - A kind of up-front forming method of aerofoil profile with piezoelectricity deicing function - Google Patents
A kind of up-front forming method of aerofoil profile with piezoelectricity deicing function Download PDFInfo
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- CN106828873B CN106828873B CN201710081243.6A CN201710081243A CN106828873B CN 106828873 B CN106828873 B CN 106828873B CN 201710081243 A CN201710081243 A CN 201710081243A CN 106828873 B CN106828873 B CN 106828873B
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- piezoelectricity
- leading edge
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Moulds For Moulding Plastics Or The Like (AREA)
Abstract
The present invention relates to a kind of up-front forming methods of aerofoil profile with piezoelectricity deicing function, belong to superhybrid composite leading edge of a wing technical field and aircraft deicing field.This method includes：Inside and outside covering is tailored, pit is milled out on exterior skin；It is molded to the curvature needed for aerofoil profile leading edge；It cleans and carries out anodized or blasting treatment；Embedded piezoelectric vibrator, filling bonding agent solidification；Exterior skin is put into lower die and is positioned, surface is laid with first layer epoxy resin-matrix fiber prepreg material, and conducting wire passes through this layer of epoxy resin-matrix fiber prepreg material；After the completion of conducting wire arrangement, continues to be laid with second layer epoxy resin-matrix fiber prepreg material and cover inside panel；It heats, after heat-insulation pressure keeping to composite layer curing molding, takes out aerofoil profile leading edge；The resin overflowed is cleared up, ice-phobic coating is coated on the surface of exterior skin.The present invention makes aerofoil profile leading edge have very high specific strength and specific stiffness, excellent fatigue behaviour and shock resistance and high damage tolerance.
Description
Technical field
The present invention relates to superhybrid composite leading edge of a wing technical field and aircraft deicing fields, more particularly to a kind of
The up-front forming method of aerofoil profile with piezoelectricity deicing function.
Background technology
Aerofoil profile leading edge of the present invention includes the leading edge of a wing and empennage leading edge, their main function includes generating to rise
Power, manipulation direction and the balance for maintaining aircraft.Aircraft is under certain flying conditions, the aerofoil profile leading edge meeting as parts surface windward
Inevitably by two kinds of most fatal threats：When the shock of high-altitude flying bird, second is that super-cooling waterdrop shock is produced in cloud layer
Raw icing.Bird hits the deformation of generation and the covering of ice sheet can destroy the flow pattern of aerofoil and then causes point of airfoil surface air-flow
From causing aircraft pneumatic and the decline of maneuvering performance, therefore the anti-bird of aircraft hits except anti-ice problem is always interesting
Global problem.Traditional single metal layer aerofoil profile leading edge and hot-air obviously cannot meet people to aircraft peace except anti-icing
The requirement of full nargin.
It is mainly the following currently, solving above-mentioned bird and hitting the aircraft wing leading edge structures of ice formation issues：(1) before passing through
Edge reinforcing member cuts bird body, and the impact force of bird body is absorbed by being coated on internal honeycomb sandwich layer.As document number is
A kind of anti-bird described in the Chinese patent literature of CN201010554079.4 knocks machine horizontal tail leading edge structure away.(2) by by hot gas
Anti- deicing system is combined with ultrasonic wave higher-order of oscillation auxiliary device, realizes the double shield of hot deicing and ultrasonic wave deicing.Such as
Document number is that a kind of aircraft wing ultrasonic wave described in the Chinese patent literature of CN201110443826.1 assists hot gas joint anti-
Deicer.(3) by pasting fixed piezoelectric vibrator on object construction and applying certain voltage drive signal, excitation piezoelectricity shakes
Traveling wave removes ice sheet in sub- generation face or outside face.One as described in the Chinese patent literature that document number is CN201210013021.8
Kind of travelling-wave type piezoelectric material vibration de-icing device and method based on mode in face or outside face.(1) plant structure the shortcomings that be
Only to up-front tip region reinforce prevents bird from hitting and to increase the preceding edge thickness after keriotheca excessive.(2) plant method
The tangential stress generated when excessively complicated and ultrasonic vibration frequency is higher the disadvantage is that deicer remains unchanged is smaller.(3) are planted
The shortcomings that method is that piezoelectric vibrator is adhered to inner surface, and piezoelectric vibrator easily falls off and fails when object construction is impacted.
Invention content
It is an object of the invention in view of the above-mentioned problems, provide a kind of aerofoil profile with piezoelectricity deicing function it is up-front at
Type method has very high specific strength and specific stiffness, excellent fatigue behaviour and shock resistance and high damage tolerance.
The object of the present invention is achieved like this：
A kind of aerofoil profile leading edge with piezoelectricity deicing function, which is characterized in that including inside and outside two layers of covering and be placed in inside and outside
Composite layer between two layers of covering is equipped with several pits on exterior skin, is embedded with piezoelectric vibrator in pit, shakes in piezoelectricity
It is filled with bonding agent in gap between son and pit, fluorinated polyurethane ice-phobic coating is also coated on the surface of exterior skin.
Wherein, the composite layer is fiber reinforced epoxy resin based composites layer, and inside and outside two layers of covering is equal
For metal skin, the piezoelectric vibrator is rectangular piezoelectric ceramic piece, and the pit is rectangle, and several pits are with two different rows
Mode for cloth carries out regularly arranged.
A kind of up-front forming method of aerofoil profile with piezoelectricity deicing function, which is characterized in that include the following steps：
S1, the rectangular metal panels of two pieces of same sizes is tailored respectively as inside panel and exterior skin, and in exterior skin
Specific position on one side, which is milled out, carries out regularly arranged pit with two different arrangement modes；
S2, the exterior skin after inside panel and milling is separately formed to the curvature needed for aerofoil profile leading edge；
S3, inside panel after molding and exterior skin are cleaned successively and carry out anodized or blasting treatment；
S4, the piezoelectric vibrator that upper and lower surface is coated with to metal electrode are embedded in the pit centres of exterior skin, in piezoelectric vibrator
With fill bonding agent in the gap of pit surrounding, and it is by the bonding agent that one end of conducting wire is Nian Jie with piezoelectric vibrator upper surface solid
Calmly, drying box internal heating curing is put into after；
S5, the exterior skin that would be embedded with piezoelectric vibrator are put into the lower die of compacting tool set and position, and are spread on the surface of exterior skin
If first layer epoxy resin-matrix fiber prepreg material, and the conducting wire of connection piezoelectric vibrator upper surface is made to pass through this layer of epoxy resin-matrix fibre
Tie up prepreg；
S6, conducting wire is waited for after the completion of first layer epoxy resin-matrix fiber prepreg material surface is arranged, continue to be laid with second layer ring
Thickness required by epoxy resin-based fiber prepreg material to composite layer, and cover inside panel；
S7, upper mold downlink, and it is heated to required temperature, after heat-insulation pressure keeping to composite layer curing molding, upper mold uplink,
Take out aerofoil profile leading edge；
A small amount of resin that S8, cleaning aerofoil profile leading edge are overflowed in mold process, and coat anti-icing painting on the surface of exterior skin
Layer.
Wherein, in the S1, exterior skin uses thickness for the aluminium alloy plate of 0.6-1mm or titanium alloy sheet, exterior skin fovea superior
The depth in hole is 0.3mm, and planar dimension is slightly larger than the planar dimension of piezoelectric vibrator, and pit regular array is leaned in exterior skin both sides
At proximal edge, inside panel uses thickness for the aluminium alloy plate of 0.3mm, titanium alloy sheet or aluminium sheet.
Wherein, it when the inside panel is aluminium alloy plate or titanium alloy sheet, needs by die forming, progressive molding or ball blast
Forming carries out preform.
Wherein, it in the S3, when inside panel or exterior skin are aluminium alloy plate, needs to pass through oil removing, alkali cleaning and pickling successively
It is cleaned, and anodized is carried out using acid solution；When inside panel or exterior skin are titanium alloy sheet, then need successively
It is cleaned by oil removing and pickling, and anodized is carried out using alkaline solution.
Wherein, in the S4, piezoelectric vibrator uses rectangular piezoelectric ceramic piece, and metal electrode is silver electrode, and bonding agent is ring
Oxygen resin glue.
Wherein, in the S5, when exterior skin is aluminium alloy plate, the positioning pin by lower mould surface is needed to be positioned；Outside
When covering is titanium alloy sheet, then needs the curved surface obtained by preform to be closed with drag face paste and position；The epoxy resin-matrix
Fiber prepreg material is positioned by oneself viscosity, specially the unidirectionally glass fiber reinforced epoxy resin of arrangement or twill weave preimpregnation
Material or carbon-fibre reinforced epoxy resin prepreg,
Wherein, in the S6, conducting wire is arranged by the way of ensureing that same type piezoelectric vibrator is connected in parallel.
Wherein, in the S8, ice-phobic coating is that the polyurethane coating layer that thickness is 20 μm -100 μm or fluorinated polyurethane apply
The bed of material.
Beneficial effects of the present invention are：
1) it uses superhybrid composite substitution single metal material to manufacture aerofoil profile leading edge, so that aerofoil profile leading edge is had very high
Specific strength and specific stiffness, excellent fatigue behaviour and shock resistance and high damage tolerance.
2) it uses the piezoelectric vibrator of two class difference arrangement modes to inspire two different mode of oscillations, reaches most after superposition
Good piezoelectricity deicing effect, which have low energy consumption, deicing is thorough, advantages of simple structure and simple.
3) piezoelectric vibrator ensure that the rigid contact of piezoelectric vibrator and exterior skin, have in the pit of metal exterior skin
Conducive to the transmission of vibration and the saving of energy, while using pit and constraint of the composite material to piezoelectric vibrator degree of freedom, avoiding
Piezoelectric vibrator obscission caused by when leading edge is impacted, improves service life；Piezoelectric vibrator is buried with conducting wire simultaneously
It is overlying on inside material system, realizes the simplification of lengthy and jumbled structure.
Description of the drawings
Fig. 1 is the internal structure schematic diagram of the present invention.
Fig. 2 is the cross section partial schematic diagram of the present invention.
Fig. 3 is arrangement and the wire connection diagram of piezoelectric vibrator.
Wherein：1- exterior skins, 2- composite layers, 3- inside panels, 4- piezoelectric vibrators, 5- bonding agents.
Specific implementation mode
With reference to specific embodiments and the drawings, the present invention is further explained.
As shown in Figs. 1-2, a kind of aerofoil profile leading edge with piezoelectricity deicing function, including inside and outside two layers of covering 1,3 and be placed in
Composite layer 2 between inside and outside two layers of covering 1,3 is equipped with several pits on exterior skin 1, piezoelectric vibrator is embedded in pit
4, it is filled with bonding agent 5 in the gap between piezoelectric vibrator 4 and pit, the poly- ammonia of fluorination is also coated on the surface of exterior skin 1
Ester ice-phobic coating.
Wherein, composite layer 2 is specially fiber reinforced epoxy resin based composites layer；Inside and outside two layers of covering 1,3 is equal
Can be specially aluminium alloy plate or titanium alloy sheet for metal skin；Piezoelectric vibrator 4 is specially rectangular piezoelectric ceramic piece, and pit is
The rectangle pit to match with rectangular piezoelectric ceramic piece, several pits are carried out regularly arranged with two different arrangement modes.
Below in conjunction with specific embodiment, molding up-front to aforementioned aerofoil profile is described further.
Embodiment one
The first step tailors out two pieces and leading edge of a wing developed dimension phase according to the result of calculation of leading edge of a wing developed dimension
The TA2 plates answered, the TA2 plates that one of thickness is 0.3mm are as inside panel, the TA2 plates then conduct that another piece of thickness is 0.6mm
Exterior skin；Then it is 0.3mm that depth is milled out on exterior skin, and planar dimension is slightly larger than several squares of piezoelectric ceramics planar dimension
Shape pit, and several rectangle pits are regularly arranged with two different arrangement modes progress as shown in Figure 1；
Two blocks of TA2 plates are respectively put into the diel with leading edge of a wing curvature shapes type face, strike out by second step
Curve form needed for shape to inside and outside two pieces of coverings；
Third walks, and two pieces of coverings inside and outside after forming are carried out oil removing, pickling and sodium hydroxide anodized successively；
4th step, the piezoelectric ceramic piece that the thickness that upper and lower surface is coated with to silver electrode is 0.3mm are placed in rectangle pit,
Epoxide-resin glue is filled in the gap of piezoelectric ceramic piece and pit surrounding, and conducting wire one end and piezoelectricity are made pottery by epoxide-resin glue
Tile upper surface is adhesively fixed, after to be put into temperature setting be 130 DEG C of drying box internal heating curing；
Exterior skin is put into the lower die of compacting tool set and closes and position with drag face paste, spread on its surface by the 5th step
If the carbon fiber reinforced epoxy resin-based prepreg of first layer, and the conducting wire of connection piezoelectric ceramic piece upper surface is made to be presoaked across this layer
Material；
6th step ensures the piezoelectric ceramics of same row in the circuit configuration conducting wire of first layer prepreg surface as shown in Figure 3
Piece is connected to same driving source by parallel way, then proceedes to lay the carbon fiber reinforced epoxy resin-based prepreg of the second layer to again
Thickness required by condensation material layer, and cover inside panel；
7th step, upper mold downlink after mold is preheated to 60 DEG C continue to be heated to 130 DEG C and are gradually forced into 1MPa, heat preservation
After pressurize 2h (i.e. after composite layer curing molding), upper mold uplink takes out aerofoil profile leading edge；
8th step, a small amount of epoxy resin that cleaning aerofoil profile leading edge is overflowed in mold process, and it is equal on the surface of exterior skin
The fluorinated polyurethane coating that even coating thickness is 20 μm -100 μm, it is dry；
Exterior skin is made grounding, connection signal generator and power amplifier by the 9th step, and by power amplifier
Output end is connected with extraction wire inside aerofoil profile leading edge to convey driving voltage, be arranged after suitable output parameter can be realized it is excellent
Different deicing and anti-icing effect.
Embodiment two
The first step tailors out two pieces and leading edge of a wing developed dimension phase according to the result of calculation of leading edge of a wing developed dimension
2024 duralumin plates answered, 2024 duralumin plates that one of thickness is 0.3mm are 0.6mm's as inside panel, another piece of thickness
2024 duralumin plates are then used as exterior skin；Then it is 0.3mm that depth is milled out on exterior skin, and planar dimension is slightly larger than piezoelectric ceramics
Several rectangle pits of planar dimension, and several rectangle pits with two different arrangement modes as shown in Figure 1 into professional etiquette
Then arrange；
Inside and outside two pieces of coverings are carried out oil removing, alkali cleaning, pickling and phosphoric acid anodizing and handled by second step successively；
Third walks, and the piezoelectric ceramic piece that the thickness that upper and lower surface is coated with to silver electrode is 0.3mm is placed in rectangle pit,
Epoxide-resin glue is filled in the gap of piezoelectric ceramic piece and pit surrounding, and conducting wire one end and piezoelectricity are made pottery by epoxide-resin glue
Tile upper surface is adhesively fixed, after to be put into temperature setting be 130 DEG C of drying box internal heating curing；
Exterior skin is put into the lower mould surface of compacting tool set and by positioning finger setting, first is laid on its surface by the 4th step
Layer glass fiber reinforced epoxy resin base prepreg, and the conducting wire of connection piezoelectric ceramic piece upper surface is made to pass through this layer of prepreg；
5th step ensures the piezoelectric ceramics of same row in the circuit configuration conducting wire of first layer prepreg surface as shown in Figure 3
Piece is connected to same driving source by parallel way, then proceedes to lay second layer glass fiber reinforced epoxy resin base prepreg extremely
Thickness required by composite layer, and cover inside panel；
6th step, upper mold downlink after mold is preheated to 60 DEG C continue to be heated to 130 DEG C and are gradually forced into 1MPa, heat preservation
After pressurize 2h (i.e. after composite layer curing molding), upper mold uplink takes out aerofoil profile leading edge；
7th step, a small amount of epoxy resin that cleaning aerofoil profile leading edge is overflowed in mold process, and it is equal on the surface of exterior skin
The fluorinated polyurethane coating that even coating thickness is 20 μm -100 μm, it is dry；
Exterior skin is made grounding, connection signal generator and power amplifier by the 8th step, and by power amplifier
Output end is connected with extraction wire inside aerofoil profile leading edge to convey driving voltage, be arranged after suitable output parameter can be realized it is excellent
Different deicing and anti-icing effect.
In embodiment two, since inside and outside two pieces of coverings use 2024 duralumin plates, second in embodiment one is eliminated
It walks preforming.
Embodiment three
The first step tailors out two pieces and leading edge of a wing developed dimension phase according to the result of calculation of leading edge of a wing developed dimension
The TA2 plates answered, the TA2 plates that one of thickness is 0.3mm are as inside panel, the TA2 plates then conduct that another piece of thickness is 0.6mm
Exterior skin；Then it is 0.3mm that depth is milled out on exterior skin, and planar dimension is slightly larger than several squares of piezoelectric ceramics planar dimension
Shape pit, and several rectangle pits are regularly arranged with two different arrangement modes progress as shown in Figure 1；
Two blocks of TA2 plates are respectively put into the former with leading edge of a wing curvature shapes type face, pass through shot-blasting machine by second step
TA2 plates are forced to be shaped to curvature shapes needed for inside and outside two pieces of coverings to plank High-velocity Projectiles of dishing out；
Third walks, and two pieces of coverings inside and outside after forming are carried out oil removing, pickling and sodium hydroxide anodized successively；
4th step, the piezoelectric ceramic piece that the thickness that upper and lower surface is coated with to silver electrode is 0.3mm are placed in rectangle pit,
Fill epoxide-resin glue in the gap of piezoelectric ceramic piece and pit surrounding, after be put into the drying box that temperature setting is 130 DEG C plus
Heat cure；
Exterior skin is put into the lower die of compacting tool set and closes and position with drag face paste, spread on its surface by the 5th step
If the thickness required by carbon fiber reinforced epoxy resin-based prepreg to composite layer, and cover inside panel；
6th step, upper mold downlink after mold is preheated to 60 DEG C continue to be heated to 130 DEG C and are gradually forced into 1MPa, heat preservation
After pressurize 2h (i.e. after composite layer curing molding), upper mold uplink takes out aerofoil profile leading edge；
7th step, a small amount of epoxy resin that cleaning aerofoil profile leading edge is overflowed in mold process, and it is equal on the surface of exterior skin
The fluorinated polyurethane coating that even coating thickness is 20 μm -100 μm, it is dry；
Exterior skin is made grounding, connection signal generator and power amplifier by the 8th step, and by power amplifier
Output end is connected with the up-front inside panel of aerofoil profile to convey driving voltage, be arranged after suitable output parameter can be realized it is excellent
Deicing and anti-icing effect.
The step of in embodiment three, driving voltage is fed directly to inside panel, and there is no need to the arrangement conducting wires of embodiment one.
Example IV
The first step tailors out two pieces and leading edge of a wing developed dimension phase according to the result of calculation of leading edge of a wing developed dimension
2024 duralumin plates answered, 2024 duralumin plates that one of thickness is 0.3mm are 0.6mm's as inside panel, another piece of thickness
2024 duralumin plates are then used as exterior skin；Then it is 0.3mm that depth is milled out on exterior skin, and planar dimension is slightly larger than piezoelectric ceramics
Several rectangle pits of planar dimension, and several rectangle pits with two different arrangement modes as shown in Figure 1 into professional etiquette
Then arrange；
Inside and outside two pieces of coverings are carried out oil removing, alkali cleaning, pickling and phosphoric acid anodizing and handled by second step successively；
Third walks, and the piezoelectric ceramic piece that the thickness that upper and lower surface is coated with to silver electrode is 0.3mm is placed in rectangle pit,
Fill epoxide-resin glue in the gap of piezoelectric ceramic piece and pit surrounding, after be put into the drying box that temperature setting is 130 DEG C plus
Heat cure；
Exterior skin is put into the lower die of compacting tool set and closes and position with drag face paste, spread on its surface by the 4th step
If the thickness required by glass fiber reinforced epoxy resin base prepreg to composite layer, and cover inside panel；
5th step, upper mold downlink after mold is preheated to 60 DEG C continue to be heated to 130 DEG C and are gradually forced into 1MPa, heat preservation
After pressurize 2h (i.e. after composite layer curing molding), upper mold uplink takes out aerofoil profile leading edge；
6th step, a small amount of epoxy resin that cleaning aerofoil profile leading edge is overflowed in mold process, and it is equal on the surface of exterior skin
The fluorinated polyurethane coating that even coating thickness is 20 μm -100 μm, it is dry；
Exterior skin is made grounding, connection signal generator and power amplifier by the 7th step, and by power amplifier
Output end is connected with the up-front inside panel of aerofoil profile to convey driving voltage, be arranged after suitable output parameter can be realized it is excellent
Deicing and anti-icing effect.
In example IV, inside and outside two pieces of coverings use 2024 duralumin plates, while driving voltage is fed directly to Inner Mongol
Skin, therefore the step of eliminating preforming in embodiment one and arrangement conducting wire.
The above is only a preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, several transformation or improvement can also be made, under the premise of not departing from the present invention total design, these are improved or transformation
It should also be as belonging within the scope of protection of present invention.
Claims (8)
1. a kind of up-front forming method of aerofoil profile with piezoelectricity deicing function, which is characterized in that include the following steps：
S1, the rectangular metal panels of two pieces of same sizes is tailored respectively as inside panel and exterior skin, and in the one side of exterior skin
On specific position mill out and carry out regularly arranged pit with two different arrangement modes；
S2, the exterior skin after inside panel and milling is separately formed to the curvature needed for aerofoil profile leading edge；
S3, inside panel after molding and exterior skin are cleaned successively and carry out anodized or blasting treatment；
S4, upper and lower surface is coated with metal electrode piezoelectric vibrator insertion exterior skin pit centres, piezoelectric vibrator with it is recessed
It cheats in the gap of surrounding and fills bonding agent, and one end of conducting wire and piezoelectric vibrator upper surface are adhesively fixed by the bonding agent,
After be put into drying box internal heating curing；
S5, the exterior skin that would be embedded with piezoelectric vibrator are put into the lower die of compacting tool set and position, and the is laid on the surface of exterior skin
One layer of epoxy resin-matrix fiber prepreg material, and the conducting wire of connection piezoelectric vibrator upper surface is made to pass through this layer of epoxy resin-matrix fiber pre-
Leaching material；
S6, conducting wire is waited for after the completion of first layer epoxy resin-matrix fiber prepreg material surface is arranged, continue to be laid with second layer asphalt mixtures modified by epoxy resin
Thickness required by aliphatic radical fiber prepreg material to composite layer, and cover inside panel；
S7, upper mold downlink, and it is heated to required temperature, after heat-insulation pressure keeping to composite layer curing molding, upper mold uplink is taken out
Aerofoil profile leading edge；
A small amount of resin that S8, cleaning aerofoil profile leading edge are overflowed in mold process, and coat ice-phobic coating on the surface of exterior skin.
2. a kind of up-front forming method of aerofoil profile with piezoelectricity deicing function according to claim 1, which is characterized in that
In the S1, exterior skin uses thickness for the aluminium alloy plate of 0.6-1mm or titanium alloy sheet, and the depth of pit is on exterior skin
0.3mm, planar dimension are slightly larger than the planar dimension of piezoelectric vibrator, and pit regular array in exterior skin both sides close to edge,
Inside panel uses thickness for the aluminium alloy plate of 0.3mm, titanium alloy sheet or aluminium sheet.
3. a kind of up-front forming method of aerofoil profile with piezoelectricity deicing function according to claim 2, which is characterized in that
The inside panel be aluminium alloy plate or titanium alloy sheet when, need by die forming, progressive molding or peen forming carry out in advance at
Shape.
4. a kind of up-front forming method of aerofoil profile with piezoelectricity deicing function according to claim 2, which is characterized in that
In the S3, when inside panel or exterior skin are aluminium alloy plate, need to be cleaned by oil removing, alkali cleaning and pickling successively, and adopt
Anodized is carried out with acid solution；When inside panel or exterior skin are titanium alloy sheet, then need to pass through oil removing and acid successively
It washes and is cleaned, and anodized is carried out using alkaline solution.
5. a kind of up-front forming method of aerofoil profile with piezoelectricity deicing function according to claim 1, which is characterized in that
In the S4, piezoelectric vibrator uses rectangular piezoelectric ceramic piece, and metal electrode is silver electrode, and bonding agent is epoxide-resin glue.
6. a kind of up-front forming method of aerofoil profile with piezoelectricity deicing function according to claim 2, which is characterized in that
In the S5, when exterior skin is aluminium alloy plate, the positioning pin by lower mould surface is needed to be positioned；Exterior skin is titanium alloy sheet
When, then it needs the curved surface obtained by preform to be closed with drag face paste and positions；The first layer epoxy resin-matrix fiber prepreg
Material is positioned by oneself viscosity, the glass fiber reinforced epoxy resin prepreg or carbon fiber of specially unidirectional arrangement or twill weave
Tie up reinforced epoxy prepreg.
7. a kind of up-front forming method of aerofoil profile with piezoelectricity deicing function according to claim 1, which is characterized in that
In the S6, conducting wire is arranged by the way of ensureing that same type piezoelectric vibrator is connected in parallel.
8. a kind of up-front forming method of aerofoil profile with piezoelectricity deicing function according to claim 1, which is characterized in that
In the S8, ice-phobic coating is the polyurethane coating layer or fluorinated polyurethane dope layer that thickness is 20 μm -100 μm.
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| CN108248824B (en) * | 2017-12-29 | 2021-12-21 | 南京航空航天大学 | Wing surface leading edge structure of micro unmanned aerial vehicle, forming die and preparation method of wing surface leading edge structure |
| CN109051636A (en) * | 2018-08-14 | 2018-12-21 | 上海理工大学 | A kind of transmission belt |
| CN109436338B (en) * | 2018-10-31 | 2022-05-06 | 浙江清华柔性电子技术研究院 | Anti-icing and deicing device and anti-icing and deicing control method based on same |
| CN109228375B (en) * | 2018-11-01 | 2023-08-18 | 成都纵横大鹏无人机科技有限公司 | Skin forming method |
| CN111196048B (en) * | 2018-11-19 | 2022-03-04 | 航天特种材料及工艺技术研究所 | Forming method of large-size special-shaped structure/heat-proof integrated component and integrated component |
| CN111579199B (en) * | 2020-05-27 | 2022-05-17 | 中国空气动力研究与发展中心低速空气动力研究所 | Electromagnetic force deicing device for front edge ice hull of test model in icing wind tunnel |
| CN113071163B (en) * | 2021-04-23 | 2022-10-18 | 北京机电工程研究所 | Bionic aircraft control surface preparation method |
| CN112918685B (en) * | 2021-05-11 | 2021-12-07 | 中国空气动力研究与发展中心低速空气动力研究所 | Engine air inlet protection device with deicing capability |
| CN115260990B (en) * | 2022-07-26 | 2023-12-26 | 南京航空航天大学 | Low energy consumption deicing material relying on low interface toughness coating and preparation method thereof |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3809341A (en) * | 1972-11-14 | 1974-05-07 | I Levin | Device for removing ice from surfaces of thin-walled structures |
| CN1113475A (en) * | 1993-10-01 | 1995-12-20 | B·F·谷德里奇公司 | Polyurethane deicer |
| US5547150A (en) * | 1994-03-22 | 1996-08-20 | The B.F. Goodrich Company | Mechanical deicer having decoupled skin segments |
| US6129314A (en) * | 1997-01-21 | 2000-10-10 | The B. F. Goodrich Company | Hybrid deicer with element sequence |
| CN102431650A (en) * | 2011-12-27 | 2012-05-02 | 东南大学 | Airplane airfoil ultrasonic-assistant hot air combined ice preventing and removing device |
| CN102941924A (en) * | 2012-11-20 | 2013-02-27 | 南京航空航天大学 | Piezoelectric elastic wave deicing method |
| CN103600845A (en) * | 2013-08-23 | 2014-02-26 | 中国航空工业集团公司西安飞机设计研究所 | Heat channel area adjustable slat anti-icing design method |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2718026A1 (en) * | 2010-10-19 | 2012-04-19 | Universite Du Quebec A Chicoutimi | Vibration-based ice protection sleeve |
-
2017
- 2017-02-15 CN CN201710081243.6A patent/CN106828873B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3809341A (en) * | 1972-11-14 | 1974-05-07 | I Levin | Device for removing ice from surfaces of thin-walled structures |
| CN1113475A (en) * | 1993-10-01 | 1995-12-20 | B·F·谷德里奇公司 | Polyurethane deicer |
| US5547150A (en) * | 1994-03-22 | 1996-08-20 | The B.F. Goodrich Company | Mechanical deicer having decoupled skin segments |
| US6129314A (en) * | 1997-01-21 | 2000-10-10 | The B. F. Goodrich Company | Hybrid deicer with element sequence |
| CN102431650A (en) * | 2011-12-27 | 2012-05-02 | 东南大学 | Airplane airfoil ultrasonic-assistant hot air combined ice preventing and removing device |
| CN102941924A (en) * | 2012-11-20 | 2013-02-27 | 南京航空航天大学 | Piezoelectric elastic wave deicing method |
| CN103600845A (en) * | 2013-08-23 | 2014-02-26 | 中国航空工业集团公司西安飞机设计研究所 | Heat channel area adjustable slat anti-icing design method |
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