CN114007288A - PTC flexible heating film and heating assembly for helicopter tail blade anti-icing - Google Patents
PTC flexible heating film and heating assembly for helicopter tail blade anti-icing Download PDFInfo
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- CN114007288A CN114007288A CN202111381928.5A CN202111381928A CN114007288A CN 114007288 A CN114007288 A CN 114007288A CN 202111381928 A CN202111381928 A CN 202111381928A CN 114007288 A CN114007288 A CN 114007288A
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
- H05B3/00—Ohmic-resistance heating
- H05B3/20—Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater
- H05B3/34—Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater flexible, e.g. heating nets or webs
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
- H05B3/00—Ohmic-resistance heating
- H05B3/02—Details
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
- H05B3/00—Ohmic-resistance heating
- H05B3/02—Details
- H05B3/03—Electrodes
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
- H05B3/00—Ohmic-resistance heating
- H05B3/02—Details
- H05B3/06—Heater elements structurally combined with coupling elements or holders
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- Control Of Resistance Heating (AREA)
Abstract
The invention belongs to the technical field of blade anti-icing design, and particularly relates to a PTC flexible heating film for preventing the blade at the tail of a helicopter from being iced. The PTC flexible heating film has flexibility and sequentially comprises a flexible rubber layer (1), a PTC coating (2), a comb electrode layer (3) and a high-temperature-resistant supporting layer from outside to inside; the PTC coating (2) generates heat under the power supply condition of the comb electrode layer (3) and has PTC effect. The PTC material is applied to helicopter tail blade anti-icing, a controller and a complex control law are not needed, and the weight of the whole tail blade anti-icing system can be reduced.
Description
Technical Field
The invention belongs to the technical field of blade anti-icing design, and particularly relates to a PTC flexible heating film for preventing the blade at the tail of a helicopter from being iced.
Background
When the helicopter flies in the air, under the icing condition, supercooled water drops in the air collide with the front edge part of the rotor wing profile, and the water drops are continuously collected and can be frozen at the front edge part of the helicopter to damage the flow field of the profile, so that the lift force is suddenly reduced. The rotor tail rotor blade anti-icing system can prevent the tail rotor blade from icing. The anti-icing system is a system which does not allow the anti-icing part to generate the icing phenomenon, and in the icing environment, the anti-icing system needs to be started to work all the time to ensure that the anti-icing part cannot generate the icing phenomenon. Through research and development of a plurality of years, a tail rotor blade anti-icing system applied to a helicopter can be divided into the following types according to different energy consumption: liquid anti-icing system, gas heat anti-icing system and electric heating anti-icing system. At present, the electric heating anti-icing system is widely applied, and the anti-icing mode is adopted on various types of helicopters, such AS helicopters in America, CH-47, CH-53, UH-60 and S-92, French AS332 and NH-90, Russian Mi-8, Mi-17 and Mi-26 and the like.
The metal heating element converts electric energy into heat energy, the temperature sensor and the controller are used for detecting the temperature of the interface between the tail blade heating component and the blade to control and prevent the temperature from being over-heated, and the collector ring supplies the electric energy on the engine body to the tail blade. The heating assembly is arranged at the front edge of the tail blade, and the heating element converts anti-icing electric energy into heat energy, so that the anti-icing function can be achieved. The existing electric heating anti-icing system using metal as a heating element has more component structures and more additional weight.
PTC (positive Temperature coefficient) material is also called as positive Temperature coefficient thermosensitive material, and the material has the characteristic that the resistivity is increased along with the rise of Temperature, namely, the material has the functions of automatic switching such as heat sensitivity, current limitation, time delay and the like. At present, many research teams design and develop PTC materials as self-temperature-control heating materials, a local thermal control system of a spacecraft, which uses the PTC materials as heating elements, is designed by a Li Tanzi professor team of Beijing aerospace university, and a heating unit based on PTC ceramic materials and applied to preventing/deicing of wings of fixed-wing aircraft is designed by utilizing the characteristics of automatic temperature control and overheating protection of PTC ceramic thermistors by a Zhukongjun professor team of Nanjing aerospace university, and the PTC materials are not applied to the field of helicopter tail blade anti-icing currently.
Disclosure of Invention
The purpose of the invention is as follows: the PTC flexible heating film for the helicopter tail blade anti-icing is provided, the PTC material is applied to the helicopter tail blade anti-icing, a controller and a complex control law are not needed, and the weight of the whole tail blade anti-icing system can be reduced.
The technical scheme of the invention is as follows: on one hand, the PTC flexible heating film for helicopter tail blade anti-icing is provided, has flexibility, and sequentially comprises a flexible rubber layer 1, a PTC coating layer 2, a comb electrode layer 3 and a high-temperature-resistant supporting layer from outside to inside; the PTC coating layer 2 generates heat under the power supply condition of the comb electrode layer 3, and has PTC effect.
Optionally, the PTC coating 2 comprises PTC ceramic powder, an organic phase, a flexible component and a conductive component; the PTC coating 2 is sprayed on the comb teeth electrode coating 3 in a spraying mode.
Optionally, the organic phase is selected from one or more of low density polyethylene, ethylene-vinyl acetate copolymer or paraffin; the flexible component is styrene butadiene rubber; the conductive component is metal powder or graphite.
Optionally, the comb-teeth electrode layer 3 includes a set of oppositely disposed comb-teeth electrodes, and the comb-teeth electrodes are connected to the lead 4.
Optionally, the comb-shaped electrode is a comb-shaped electrode made of copper foil for making the PTC coating generate heat more uniformly.
Optionally, the flexible rubber layer 1 is a styrene butadiene rubber layer; is sprayed on the PTC coating layer 1 by adopting a spraying mode and is used for protecting the PTC coating layer inside.
Optionally, the high-temperature-resistant support layer comprises a glass fiber layer 5 and a PI film layer 6 which are bonded into a whole, and is used for increasing the tensile resistance and the mechanical strength of the whole PTC flexible heating film.
On the other hand, the heating assembly is arranged at the front edge of the tail blade of the helicopter and used for preventing the tail blade of the helicopter from being iced, and comprises a metal protective layer, a heat conducting rubber layer, a PTC flexible heating film and a heat insulating rubber layer from outside to inside in sequence; the heat insulation rubber layer is positioned between the PTC flexible heating film and the leading edge skin of the tail rotor blade.
The invention has the advantages that: the PTC flexible heating film for preventing the helicopter tail blade from being iced can obtain different resistances, PTC effects and Curie temperatures by adjusting the material proportion of the PTC coating, and can meet the requirements of different tail blade anti-icing. It has certain flexibility, and can adapt to different complicated blade shapes by being combined with other parts of the heating assembly. The electric energy can be converted into heat energy when the tail blade anti-icing system is applied to the helicopter, the resistance of the tail blade anti-icing system increases along with the increase of the temperature, the heating power of the tail blade anti-icing system decreases along with the increase of the temperature when the voltage provided by the outside is not changed, and the tail blade anti-icing system has the characteristic of self-adaptive temperature.
The PTC flexible heating film for helicopter tail blade anti-icing provided by the invention is combined with the rest part of the heating assembly to form the heating assembly, and is verified by an icing wind tunnel test, so that the anti-icing function can be realized.
Description of the drawings:
fig. 1 is a schematic view of the entirety of a PTC flexible heating film;
fig. 2 is a schematic view showing a specific structure of the PTC flexible heating film.
The specific implementation mode is as follows:
the present invention is described in further detail below with reference to the attached drawings.
Example 1
The invention provides a PTC flexible heating film for preventing helicopter tail blades from being iced, which is shown in figure 1.
The PTC flexible heating film for preventing the helicopter tail blade from being iced heats by the PTC coating 2 and has PTC effect. The PTC effect specifically means: the resistance of the material increases along with the increase of the temperature, and once a certain temperature (Curie temperature) is exceeded, the resistance value shows a step-like increase along with the increase of the temperature; when the voltage provided by the outside is not changed, the resistance is increased, the heating power is correspondingly reduced, and the heating temperature can be automatically adjusted. The remaining layers of material are used to encapsulate and protect the PTC coating 2.
The PTC coating is mainly composed of PTC ceramic powder, various organic phases, a flexible component and a conductive component and is prepared by a spraying method. The PTC coating is characterized in that PTC ceramic powder is used for providing a PTC effect, a plurality of organic phase low-density polyethylene LDPE, ethylene-vinyl acetate copolymer EVA, paraffin PF and the like are used for adjusting the Curie temperature of the PTC coating, styrene butadiene rubber is used as a flexible component to improve the flexibility of the PTC coating, and metal powder, graphite and the like are used as conductive components to adjust the conductive capability of the PTC coating. By adjusting the proportion of the PTC ceramic powder, the various organic phases, the flexible component and the conductive component, the PTC flexible heating film with different resistances, different local temperatures, different PTC effects and certain flexibility can be adjusted, so that the anti-icing requirements of different tail rotor blades can be met.
The structural layout of the PTC flexible heating film for preventing the helicopter tail blade from being iced mainly comprises a plurality of layers of different materials, as shown in figure 2, a glass fiber layer 5 is composed of a layer of glass fiber and is bonded with a PI film layer 6 into a whole, the tensile resistance and the mechanical strength of the whole PTC flexible heating film can be improved, a comb tooth electrode layer 3 is arranged on the glass fiber layer 5, the comb tooth electrode is a comb tooth-shaped electrode made of copper foil, the PTC coating can be heated more uniformly, a lead 4 is connected with the comb tooth electrode layer 3 in a welding mode, the PTC coating 2 is sprayed on the comb tooth electrode coating 3 in a spraying mode, the uppermost layer is a flexible rubber layer 1, and the PTC coating is sprayed on the PTC coating 2 in a spraying mode to protect the PTC coating inside. The flexible rubber layer 1 is specifically a styrene butadiene rubber layer.
Compared with the traditional metal heating component, the invention has the advantages;
at present, all the helicopter tail blade anti-icing systems are used metal heating elements, but the anti-icing heating component based on the metal sheet resistance heating element still has certain limitation, and mainly has the following defects:
1. due to the complex shape of the paddle, the metal heating element is generally sheet-shaped or filiform, and needs to be specially designed, so that the metal heating element is suitable for the paddle with the complex shape;
2. based on the fact that the power density of the metal sheet resistance heating element is a constant value, the time of power-on heating needs to be controlled by arranging a temperature sensor in the structure of the metal sheet resistance heating element or designing a heating control law, the internal overtemperature is prevented, and the structure is complex;
3. the problems of failure, control circuit fault and the like of the temperature sensor are easy to occur, the design of the control law is very complex, and in order to adapt to different temperatures and helicopter flight states, the designed heating control time sequence and time length are conservative, so that the problems of low overall reliability of the system and high energy consumption are caused.
The PTC material is a novel heating material, and is applied to a tail rotor anti-icing system as a heating element:
1. the heating device can integrally heat, can realize the anti-icing of the outer surface of a complex curved surface, and does not need to greatly change the internal structure of a matrix;
2. the temperature control circuit has the characteristics of automatic temperature control and overheating protection, can avoid the complicated internal resistance wire structural design and circuit arrangement, reduces the weight of the whole system and increases the reliability;
3. the heating power can be changed in a self-adaptive mode according to the environment temperature changing outside, self-adaptive control is more fine, and the anti-icing energy consumption of the tail rotor blade is lower.
At present, the application of the PTC material on an anti-icing system is basically applied to the anti-icing system of a fixed wing, the application of the PTC material on the anti-icing system of a tail rotor of a helicopter is not realized, the PTC coating applied on the fixed wing generally has no flexibility, and if the PTC coating is directly applied to a blade of the helicopter, the PTC coating can crack under the movement of the blade, so that the PTC material can not be applied to the anti-icing of the rotor wing according to the use mode of the PTC material on the fixed wing, and the PTC material needs to be correspondingly designed according to the flight characteristics of the rotor wing.
The invention provides a tail blade anti-icing PTC flexible heating film, which has certain flexibility and can adapt to the complex appearance of the tail blade and the large deformation motion of the tail blade.
Example 2
In this embodiment, a heating assembly is provided, which is disposed at a leading edge of a tail blade of a helicopter and is used for anti-icing of the tail blade of the helicopter, and the heating assembly sequentially includes a metal protective layer, a heat conducting rubber layer, a PTC flexible heating film and a heat insulating rubber layer from outside to inside; the heat insulation rubber layer is positioned between the PTC flexible heating film and the leading edge skin of the tail rotor blade. Wherein the metal protective layer is coated with iron and is used for protecting internal materials; the heat conducting rubber layer is used for leading out heat generated by the PTC flexible heating film to the metal protective layer.
Claims (8)
1. The PTC flexible heating film for helicopter tail blade anti-icing is characterized by having flexibility and sequentially comprising a flexible rubber layer (1), a PTC coating (2), a comb electrode layer (3) and a high-temperature-resistant supporting layer from outside to inside; the PTC coating (2) generates heat under the power supply condition of the comb electrode layer (3) and has PTC effect.
2. The PTC flexible heating film according to claim 1, wherein the PTC coating layer (2) comprises a PTC ceramic powder, an organic phase, a flexible component and a conductive component; the PTC coating (2) is sprayed on the comb tooth electrode coating (3) in a spraying mode.
3. The PTC flexible heating film according to claim 2, wherein the organic phase is one or more selected from low-density polyethylene, ethylene-vinyl acetate copolymer, and paraffin wax; the flexible component is styrene butadiene rubber; the conductive component is metal powder or graphite.
4. The PTC flexible heating film according to claim 1, wherein the comb-teeth electrode layer (3) comprises a set of oppositely disposed comb-teeth-shaped electrodes, and the comb-teeth-shaped electrodes are connected to the lead wires (4).
5. The PTC flexible heating film according to claim 4, wherein the comb-shaped electrode is a comb-shaped electrode made of copper foil for making the PTC coating layer generate heat more uniformly.
6. The PTC flexible heating film according to claim 1, wherein the flexible rubber layer (1) is a styrene-butadiene rubber layer; is sprayed on the PTC coating (1) in a spraying way to protect the PTC coating inside.
7. The PTC flexible heating film according to claim 1, wherein the high temperature-resistant support layer comprises a glass fiber layer (5) and a PI film layer (6) bonded as one body for increasing the tensile resistance and mechanical strength of the entire PTC flexible heating film.
8. A heating assembly is arranged at the front edge of a tail blade of a helicopter and is used for preventing the tail blade of the helicopter from icing, and is characterized by comprising a metal protective layer, a heat conducting rubber layer, a PTC flexible heating film and a heat insulating rubber layer from outside to inside in sequence; the heat insulation rubber layer is positioned between the PTC flexible heating film and the leading edge skin of the tail rotor blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111381928.5A CN114007288A (en) | 2021-11-19 | 2021-11-19 | PTC flexible heating film and heating assembly for helicopter tail blade anti-icing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111381928.5A CN114007288A (en) | 2021-11-19 | 2021-11-19 | PTC flexible heating film and heating assembly for helicopter tail blade anti-icing |
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| Publication Number | Publication Date |
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| CN114007288A true CN114007288A (en) | 2022-02-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111381928.5A Pending CN114007288A (en) | 2021-11-19 | 2021-11-19 | PTC flexible heating film and heating assembly for helicopter tail blade anti-icing |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2003109804A (en) * | 2001-09-28 | 2003-04-11 | Matsushita Electric Ind Co Ltd | Flexible ptc heating element |
| US20110297665A1 (en) * | 2010-06-04 | 2011-12-08 | Robert Parker | Self Regulating Electric Heaters |
| EP3624554A1 (en) * | 2018-09-13 | 2020-03-18 | Goodrich Corporation | Hybrid heater for aircraft wing ice protection |
| CN111038705A (en) * | 2018-10-11 | 2020-04-21 | 古德里奇公司 | Additive manufactured heater element for propeller anti-icing |
| CN112572808A (en) * | 2020-12-31 | 2021-03-30 | 南京航空航天大学 | Double-layer anti-icing and electric heating structure and wing adopting same |
-
2021
- 2021-11-19 CN CN202111381928.5A patent/CN114007288A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2003109804A (en) * | 2001-09-28 | 2003-04-11 | Matsushita Electric Ind Co Ltd | Flexible ptc heating element |
| US20110297665A1 (en) * | 2010-06-04 | 2011-12-08 | Robert Parker | Self Regulating Electric Heaters |
| EP3624554A1 (en) * | 2018-09-13 | 2020-03-18 | Goodrich Corporation | Hybrid heater for aircraft wing ice protection |
| CN111038705A (en) * | 2018-10-11 | 2020-04-21 | 古德里奇公司 | Additive manufactured heater element for propeller anti-icing |
| CN112572808A (en) * | 2020-12-31 | 2021-03-30 | 南京航空航天大学 | Double-layer anti-icing and electric heating structure and wing adopting same |
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