CN109862637A - A kind of anti-icing electric heating structure and preparation method using graphene-carbon nanotube composite material - Google Patents
A kind of anti-icing electric heating structure and preparation method using graphene-carbon nanotube composite material Download PDFInfo
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Abstract
本发明公开了一种用石墨烯‑碳纳米管复合材料的防除冰电加热结构及制备方法，该电加热结构以聚酰亚胺膜为基底，基底上均布一层用于加热的条状或网格状石墨烯‑碳纳米管复合材料形成石墨烯‑碳纳米管复合材料层，石墨烯‑碳纳米管复合材料层两端均设置有电极，石墨烯‑碳纳米管复合材料层上铺设一层用于绝缘导热的石墨烯薄膜层。本发明采用石墨烯‑碳纳米管复合材料作为导电发热源，升温速率相比传统电加丝加热快；石墨烯薄膜层作为导热材料，表面温度分布相比传统电加热丝加热更均匀；将电加热结构布置在机翼前缘部位，工作时采用恒流或恒压源进行供电，通过改变供电功率可有效的在不同结冰条件下进行防除冰工作。
The invention discloses an anti-icing electric heating structure and a preparation method using graphene-carbon nanotube composite materials. Or a grid-like graphene-carbon nanotube composite material forms a graphene-carbon nanotube composite material layer, electrodes are provided at both ends of the graphene-carbon nanotube composite material layer, and the graphene-carbon nanotube composite material layer is laid A graphene film layer for insulating and thermal conductivity. In the present invention, the graphene-carbon nanotube composite material is used as the conductive heating source, and the heating rate is faster than that of the traditional electric heating wire; the graphene film layer is used as the thermal conductive material, and the surface temperature distribution is more uniform than that of the traditional electric heating wire; The heating structure is arranged on the leading edge of the wing, and a constant current or constant voltage source is used for power supply during operation. By changing the power supply, the anti-icing work can be effectively carried out under different icing conditions.
Description
Technical field
The present invention relates to the anti-deicing technical fields of aircraft, and in particular to a kind of with graphene-carbon nano tube composite material
Anti- deicing electric heating device and preparation method.
Background technique
Aircraft icing is always one of the chief threat of aviation safety.Aircraft table in ground shutdown status and flight course
Face can all freeze, and mainly icing position includes wing, propeller, radome, windscreen, engine lip, control surface to aircraft
Deng.The anti-deicing of aircraft wing at present mainly uses the anti-deicing system of hot gas, and heating efficiency is low, and can reduce motor power.
After electric aircraft theory proposes, there is an urgent need to develop the anti-de-icing method of more energy-efficient electric heating.
In the modern anti-deicing system of electric heating, mostly uses resistance wire as heater element, kept away by way of partition heating
Exempt to generate central hot spot.Traditional electric heating system rate of heat addition is slow, takes a long time heating wing cover, and heating region
Non-uniform temperature.
Summary of the invention
Goal of the invention: in order to overcome above-mentioned the deficiencies in the prior art, the present invention provides a kind of to be received with graphene-carbon
The anti-deicing electric heating device and preparation method of mitron composite material, make full use of graphene-carbon nano tube composite material performance
Anti- de-icing work is carried out, it is slow to solve traditional electric heating rate of heat addition, and adds for easy to operate, simple process and effect is obvious
The problem of thermal region non-uniform temperature.
Technical solution: a kind of anti-deicing electric heating device with graphene-carbon nano tube composite material of the present invention, the electricity add
Heat structure is using polyimide film as substrate, and uniformly distributed one layer of strip for heating or latticed graphene-carbon are received in the substrate
Mitron composite material forms graphene-carbon nano tube composite material layer, and graphene-carbon nano tube composite material layer both ends are equal
It is provided with electrode, one layer of graphene film layer for being used for insulating heat-conductive is laid on the graphene-carbon nano tube composite material layer,
The graphene film layer has biadhesive.
Further, the electrode material is the conductive silver paste containing 1%~5% Graphene powder.
Further, the substrate with a thickness of 200~500 μm.
Further, the graphene-carbon nano tube composite material is strip, and 10~30mm of width, length is less than
1000mm。
Further, the first insulation is equipped between the graphene-carbon nano tube composite material layer and graphene film layer
Layer, first thickness of insulating layer are 20~50 μm；The graphene film layer is equipped with second insulating layer, second insulation
For layer with a thickness of 30 μm, the material of first insulating layer and second insulating layer is polyimide film.
The present invention also provides a kind of preparation sides of anti-deicing electric heating device with graphene-carbon nano tube composite material
Method, comprising steps of
(1) by the way of laser cutting that graphene-carbon nano tube composite material cutting is into strips or latticed, simultaneously
Guarantee edge impulse- free robustness；
(2) strip or latticed graphene-carbon nano tube composite material are evenly distributed with as substrate using polyimide film
Graphene-carbon nano tube composite material layer is formed on the substrate；
(3) graphene-carbon nano tube composite material layer both ends are uniformly coated with conductive silver paste as electrode, to conductive silver paste
It is laid with the copper strips with connecting terminal on surface after solidification, and carries out energization test；
(4) one layer of graphene film layer for being used for insulating heat-conductive, stone will be laid on graphene-carbon nano tube composite material layer
Black alkene film layer has biadhesive；
(5) above structure marginal portion is packaged using high temperature hot pressing machine, obtains electric heating device.
Further, encapsulation carries out under vacuum conditions in the step (5), excludes air between each layer, applies pressure
Guarantee that each layer bonding is reliable.
Further, it is equipped between graphene-carbon nano tube composite material layer and graphene film layer in the step (4)
First insulating layer, graphene film layer are equipped with second insulating layer, and the material of first insulating layer and second insulating layer is
Polyimide film.
Compared with prior art, the present invention having following technical effect that
1, the present invention is using graphene-carbon nano tube composite material as conductive exothermal source, and heating rate is compared to tradition electricity
Add silk heating fast, energy consumption compares traditional electric heating low 20%~40%；
2, ground experiment is verified the heating structure and can be worked normally at -70~300 DEG C, and improving electric heating, to prevent and kill off ice environment suitable
It should be able to power；
3, the advantage for making full use of graphene-carbon nano tube composite material conductive exothermal fast is laid with one layer of graphene film
Layer is used as Heat Conduction Material, and it is thermally conductive more uniform that surface temperature distribution compares traditional electric heating wire；
It 4, is mode in parallel, more when using strip graphene-carbon nano tube composite material inside the electric heating device
Item remains to work normally in the case where damaging, and improves aircraft icing guard system safety；
5, the present invention uses layer flexible structure, can fit closely with aircraft skin, effectively improve heat transfer efficiency.
Electric heating device of the present invention is arranged in leading edge of a wing position, and when work is powered using constant current or constant pressure source, leads to
Anti- de-icing work can effectively be carried out under different ice-formation conditions by crossing change output power, have equipment it is simple, it is easy to operate and
The advantages such as effect is obvious, great prepare with scale prospect.
Detailed description of the invention
Fig. 1 is scheme of installation inside wing cover；
Fig. 2 is electric heating device schematic diagram of the present invention；
Fig. 3 is that strip graphene-carbon nano tube composite material layer is laid with schematic diagram；
Fig. 4 is that latticed graphene-carbon nano tube composite material layer is laid with schematic diagram.
Specific embodiment
The present invention is described further with reference to the accompanying drawings and examples:
As shown in Figures 1 to 4, a kind of anti-deicing electric heating device with graphene-carbon nano tube composite material of the present invention,
The electric heating device 2 is arranged in 1 leading edge position of wing, electric heating device 2 and 1 covering inner surface of aircraft wing by riveting or glues
Knot mode is combined closely, and guarantees that contact is firm.
Electric heating device 2 is divided into three layers, first using polyimide film as substrate 5, substrate 5 with a thickness of 200~500 μ
m；Uniformly distributed one layer of graphene-carbon nano tube composite material for heating forms graphene-carbon nano tube composite material in substrate 5
Layer 4, graphene-carbon nano tube composite material layer 4 with a thickness of 20 μm, simultaneously because 1 leading edge ice sheet of wing is thick when aircraft freezes
Degree is uneven, and the shape of graphene-carbon nano tube composite material is cut into strip or latticed by laser, can be by changing between strip
Away from different zones heating power is controlled under conditions of heating power is constant with netted pore size, anti-deicing energy consumption is reduced；When
Graphene-carbon nano tube composite material is strip, and 10~30mm of width, length is less than 1000mm；
4 both ends of graphene-carbon nano tube composite material layer are provided with electrode 7, and 7 material of electrode is to contain 1%~5% stone
The conductive silver paste of black alkene powder；One layer of graphene film for being used for insulating heat-conductive is laid on graphene-carbon nano tube composite material layer 4
Layer 6, graphene film layer 6 is with a thickness of 30 μm, lateral thermal coefficient 500~1300W/mK, longitudinal 10~15W/ of thermal coefficient
MK, insulation performance is good, while graphene film layer 6 has biadhesive, and graphene-carbon nano tube composite material layer 4
The first insulating layer 8,8 material polyimide film of the first insulating layer, with a thickness of 20~50 μ are additionally provided between graphene film layer 6
m；Graphene film layer 6 is equipped with second insulating layer 9,9 material polyimide film of second insulating layer, with a thickness of 30 μm；Due to stone
The biadhesive of black alkene film layer 6 can guarantee that the first insulating layer 8 and second insulating layer 9 bond reliably.
It is powered using constant current or constant voltage source 3 by serial or parallel connection mode when work, can be had by changing output power
Effect carries out anti-de-icing work under different ice-formation conditions, measures through test: 3 size of current of constant-current supply is 10~50A, surface
Heating temperature is 60~150 DEG C, and power needed for every square meter graphene-carbon nano tube composite material layer 4 is 600~800W, required
Power is much smaller than existing electric heating system.
A kind of preparation method of the anti-deicing electric heating device with graphene-carbon nano tube composite material of the present invention, including
Step:
(1) by the way of laser cutting that graphene-carbon nano tube composite material cutting is into strips or latticed, simultaneously
Guarantee that edge impulse- free robustness, resistance error are no more than 5%；
(2) using polyimide film as substrate 5, strip or latticed graphene-carbon nano tube composite material is equal
Cloth forms graphene-carbon nano tube composite material layer 4 on substrate 5；
(3) 4 both ends of graphene-carbon nano tube composite material layer are uniformly coated with conductive silver paste as electrode 7, to conductive silver
It starches and is laid with the copper strips with connecting terminal on surface after solidifying, and carry out energization test；
(4) one layer of graphene film layer 6 for being used for insulating heat-conductive will be laid on graphene-carbon nano tube composite material layer 4,
Graphene film layer 6 has biadhesive, and the is equipped between graphene-carbon nano tube composite material layer 4 and graphene film layer 6
One insulating layer 8, graphene film layer 6 are equipped with second insulating layer 9, and the material of the first insulating layer 8 and second insulating layer 9 is poly-
Acid imide film；
(5) above structure marginal portion is packaged using high temperature hot pressing machine, encapsulation carries out under vacuum conditions, excludes
Air between each layer applies pressure and guarantees that each layer bonding is reliable, obtains electric heating device.
Wherein the present invention in graphene-carbon nano tube composite material the preparation method is as follows:
1) graphene microchip is dispersed in dehydrated alcohol and water mixed solution under ultrasonication, is configured to graphite
Alkene content is the dispersion liquid of 0.1mg/ml；
2) ferrocene and thiophene are added in the scattered dispersion liquid of step 1), ultrasound 15 minutes evenly dispersed.Two cyclopentadienyls
Iron and graphene mass ratio are 10:1, and thiophene and graphene mass ratio are 2:1.
3) dispersion liquid prepared in step 2) is put into the stainless steel water thermal response of polytetrafluoroethyllining lining under stiring
In kettle.12h, after reaction, cooled to room temperature are reacted at 200 DEG C.Reaction product separating, washing, drying, for use.
4) reaction product dried in step 3) is added in corundum crucible, is deposited by chemical vapour deposition technique
Carbon source, deposition reaction area include three humidity provinces, respectively gasification zone, the first flat-temperature zone and the second flat-temperature zone, deposition reaction area
Vacuumize, gasification zone temperature then risen to 600 DEG C, the first flat-temperature zone and the second flat-temperature zone temperature rise to 1400 DEG C, then to
Deposition reaction area is passed through the argon gas and hydrogen of 1L/mim, and it is 1:1 that argon gas and hydrogen, which are passed through volume ratio,.It is being passed through argon gas and hydrogen
It is full of entire reaction compartment after 4min, dehydrated alcohol is then passed through to reaction zone by syringe pump, charge velocity 20ml/min,
React 60min.After the reaction was completed, stop heating, close hydrogen, when the temperature in the furnace chamber all drops to room temperature, close
Argon gas.It opens furnace chamber and takes out reaction product, obtain graphene-carbon nano tube composite material.
Claims (8)
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110481795A (en) * | 2019-09-11 | 2019-11-22 | 山东大学 | A kind of graphene composite material ice preventing and removing device for helicopter rotors and production method |
| CN110481793A (en) * | 2019-07-12 | 2019-11-22 | 中国人民解放军空军工程大学 | A kind of new electrically heating ice shape regulation method and anti-freeze type aircraft |
| CN111105895A (en) * | 2019-10-21 | 2020-05-05 | 珠海烯蟀科技有限公司 | Method and device for supplying power by using silver paste as high borosilicate graphene layer |
| CN111204063A (en) * | 2020-03-23 | 2020-05-29 | 中国民用航空飞行学院 | Curing method and curing system of glass fiber reinforced resin matrix composite |
| CN111231376A (en) * | 2019-12-03 | 2020-06-05 | 惠阳航空螺旋桨有限责任公司 | Electric heating unit die and method for preparing electric heating unit assembly by using same |
| CN112124600A (en) * | 2020-09-30 | 2020-12-25 | 中航(成都)无人机系统股份有限公司 | Anti-icing and deicing coating of composite wing |
| CN112629093A (en) * | 2021-03-09 | 2021-04-09 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for removing ice growing on surface of film hot knife and model |
| CN112920704A (en) * | 2019-12-05 | 2021-06-08 | 中车唐山机车车辆有限公司 | Electric heating coating paint, electric heating skin and ice and snow prevention system |
| CN113597032A (en) * | 2021-08-10 | 2021-11-02 | 北京航空航天大学 | Compatible stealth anti-icing material and preparation method and application thereof |
| CN114524080A (en) * | 2022-02-18 | 2022-05-24 | 中国航发北京航空材料研究院 | Carbon nanotube film electrothermal composite material skin structure for preventing and removing ice and preparation method thereof |
| CN115513567A (en) * | 2022-09-22 | 2022-12-23 | 上海卫星工程研究所 | Integral composite heating sheet and lithium battery pack thereof |
| US20220411076A1 (en) * | 2021-06-24 | 2022-12-29 | Goodrich Corporation | Aircraft feature with heating system formed of laser-induced graphene |
| CN116061459A (en) * | 2021-12-02 | 2023-05-05 | 江西九由航空装备有限公司 | A method of paving electric heating sheet on quadratic surface |
| CN119418838A (en) * | 2025-01-03 | 2025-02-11 | 中国航空工业集团公司沈阳空气动力研究所 | A configuration optimization design method for improving the anti-icing performance of graphene electric heating film |
| CN119767453A (en) * | 2024-12-12 | 2025-04-04 | 北京航空航天大学 | Electric heating material for wing with integrated anti-icing structure and function, preparation method and application thereof |
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Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110481793A (en) * | 2019-07-12 | 2019-11-22 | 中国人民解放军空军工程大学 | A kind of new electrically heating ice shape regulation method and anti-freeze type aircraft |
| CN110481795A (en) * | 2019-09-11 | 2019-11-22 | 山东大学 | A kind of graphene composite material ice preventing and removing device for helicopter rotors and production method |
| CN111105895A (en) * | 2019-10-21 | 2020-05-05 | 珠海烯蟀科技有限公司 | Method and device for supplying power by using silver paste as high borosilicate graphene layer |
| CN111231376A (en) * | 2019-12-03 | 2020-06-05 | 惠阳航空螺旋桨有限责任公司 | Electric heating unit die and method for preparing electric heating unit assembly by using same |
| CN112920704A (en) * | 2019-12-05 | 2021-06-08 | 中车唐山机车车辆有限公司 | Electric heating coating paint, electric heating skin and ice and snow prevention system |
| CN111204063A (en) * | 2020-03-23 | 2020-05-29 | 中国民用航空飞行学院 | Curing method and curing system of glass fiber reinforced resin matrix composite |
| CN112124600A (en) * | 2020-09-30 | 2020-12-25 | 中航(成都)无人机系统股份有限公司 | Anti-icing and deicing coating of composite wing |
| CN112629093B (en) * | 2021-03-09 | 2021-07-02 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for removing ice growing on surface of film hot knife and model |
| CN112629093A (en) * | 2021-03-09 | 2021-04-09 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for removing ice growing on surface of film hot knife and model |
| US20220411076A1 (en) * | 2021-06-24 | 2022-12-29 | Goodrich Corporation | Aircraft feature with heating system formed of laser-induced graphene |
| CN113597032A (en) * | 2021-08-10 | 2021-11-02 | 北京航空航天大学 | Compatible stealth anti-icing material and preparation method and application thereof |
| CN116061459A (en) * | 2021-12-02 | 2023-05-05 | 江西九由航空装备有限公司 | A method of paving electric heating sheet on quadratic surface |
| CN114524080A (en) * | 2022-02-18 | 2022-05-24 | 中国航发北京航空材料研究院 | Carbon nanotube film electrothermal composite material skin structure for preventing and removing ice and preparation method thereof |
| CN114524080B (en) * | 2022-02-18 | 2024-04-09 | 中国航发北京航空材料研究院 | Composite material skin structure with carbon nano tube film for electrothermal ice prevention and deicing and preparation method thereof |
| CN115513567A (en) * | 2022-09-22 | 2022-12-23 | 上海卫星工程研究所 | Integral composite heating sheet and lithium battery pack thereof |
| CN119767453A (en) * | 2024-12-12 | 2025-04-04 | 北京航空航天大学 | Electric heating material for wing with integrated anti-icing structure and function, preparation method and application thereof |
| CN119418838A (en) * | 2025-01-03 | 2025-02-11 | 中国航空工业集团公司沈阳空气动力研究所 | A configuration optimization design method for improving the anti-icing performance of graphene electric heating film |
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Effective date of registration: 20200413 Address after: Yudaojie Qinhuai District of Nanjing City, Jiangsu Province, No. 29 210016 Applicant after: Nanjing University of Aeronautics and Astronautics Applicant after: JIANGSU XFNANO MATERIALS TECH Co.,Ltd. Address before: Yudaojie Qinhuai District of Nanjing City, Jiangsu Province, No. 29 210016 Applicant before: Nanjing University of Aeronautics and Astronautics |
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Application publication date: 20190607 |