CN113148183A - Plasma hot knife and hydrophobic material combined type deicing device and application - Google Patents
Plasma hot knife and hydrophobic material combined type deicing device and application Download PDFInfo
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- CN113148183A CN113148183A CN202011603349.6A CN202011603349A CN113148183A CN 113148183 A CN113148183 A CN 113148183A CN 202011603349 A CN202011603349 A CN 202011603349A CN 113148183 A CN113148183 A CN 113148183A
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- 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
- B64D15/02—De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
- B64D15/04—Hot gas application
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Abstract
The invention discloses a plasma hot knife and hydrophobic material combined deicing device and application thereof. The deicing device can heat the wings and air around the wings, wherein the heating of the wings is beneficial to melting ice on the wings, and after the air around the wings is heated, the melted crushed ice is blown off under the action of the incoming flow aerodynamic force, so that the deicing effect is achieved.
Description
Technical Field
The invention relates to the technical field of airplane protection, in particular to a plasma hot knife and hydrophobic material combined type deicing device and application.
Background
When the aircraft passes through the cloud layer, supercooled water drops in the cloud layer are easy to condense into ice on the surface of the aircraft, and the icing on the surface of the wing seriously threatens the flight safety; for many years, the loss is very disastrous compared with the flight accidents caused by the problem of icing on the outer surface of an airplane; in order to solve the problem, part of airplanes have an anti-icing and deicing system, so far, the anti-icing and deicing technologies of the airplanes are various, and the existing anti-icing and deicing technologies can be divided into a chemical liquid anti-icing and deicing technology, a mechanical deicing technology and a thermal anti-icing and deicing technology, wherein the chemical liquid anti-icing and deicing technology is used for reducing freezing temperature and ice adhesion force to achieve the purpose of anti-icing and deicing, but the anti-icing liquid contains a large amount of organic matters, and part of the anti-icing and deicing liquid contains toxicity, so that the anti-icing and deicing system can pollute the environment or is corrosive to airports and organism materials, and the effective anti-icing and deicing time is short and the dosage is huge; the mechanical deicing technology is characterized in that mechanical force is generated in an airplane protection area through modes of electricity, gas or sound waves and the like to damage an ice accretion structure, an expansion pipe can damage an airplane pneumatic molded surface and the like during deicing in the mode, resistance can be increased, a pneumatic belt can be aged and damaged along with time, and the deicing effect cannot be ensured in application or the expansion pipe cannot effectively bounce off the ice accretion due to ice adhesion and environmental pressure; the thermal deicing and ice prevention is to prevent the parts from being frozen or to remove ice by heating the surface of the airplane, the heating mode adopts a heating wire mode, the energy consumption is huge, the efficiency of an engine can be reduced, the power is insufficient, the energy utilization rate is low, the response of a system is slow, and when the energy is insufficient, the deicing effect cannot be achieved;
therefore, a plasma hot knife and hydrophobic material combined deicing device and application are needed to solve the problems of complex structure, high energy consumption and slow response of the traditional deicing technology.
Disclosure of Invention
In view of the above, the invention provides a plasma hot knife and hydrophobic material combined type deicing device and application thereof.
The plasma hot knife and hydrophobic material combined deicing device comprises a plasma generator, wherein the plasma generator is arranged on an airfoil and used for heating the airfoil and air around the airfoil through generated plasma.
Further, the plasma generator also comprises a base layer used for being attached to the wing, and the plasma generator is installed on the base layer.
Furthermore, a hydrophobic area is arranged on the base layer, and when the base layer is installed on the wing, the hydrophobic area is located on one side, facing the trailing edge, of the base layer.
Further, the base layer is made of an insulating material, the plasma generator comprises an upper electrode plate and a lower electrode plate which are arranged on the base layer, and the upper electrode plate and the lower electrode plate are isolated through the base layer.
Further, the projections of the upper electrode plate and the lower electrode plate in the vertical direction have overlapped parts.
Further, the base layer is formed by overlapping a plurality of high-temperature-resistant insulating layers, and the upper electrode plate and the lower electrode plate are respectively bonded on two sides of the base layer.
Further, the base layer is strip-shaped, the base layer is divided into a plasma hot knife area and a hydrophobic area in the length direction, and the plasma generator is installed in the plasma hot knife area.
Further, the thickness of the base layer is 0.12-0.3mm, and the thickness of the upper electrode plate and the lower electrode plate is 0.04-0.1 mm.
The invention also provides application of the plasma hot knife and the hydrophobic material composite deicing device, and a plurality of plasma hot knives and hydrophobic material composite deicing devices are arranged on the wing along the wingspan direction.
Further, a plasma hot knife area corresponding to each plasma hot knife and the hydrophobic material composite deicing device is located at the front edge of the wing, the hydrophobic area extends to the rear edge of the wing along the upper surface of the wing, and the plasma hot knife area extends to the lower surface of the wing by bypassing the front edge of the wing through the upper surface of the wing.
The invention has the beneficial effects that:
the deicing device realizes deicing by combining the plasma hot knife and the hydrophobic layer, wherein the main action mechanism of the plasma hot knife is thermal effect and inflow aerodynamic force, the heat production of the plasma hot knife is divided into two parts, one part is used for heating the air around the plasma generator, and the other part is used for heating the wing body by heating the base medium; the wing is heated to melt ice on the wing and quickly flows away along with airflow, supercooled water drops are quickly heated in a single period in a convection heat transfer/heat transfer mode through quickly heated gas, and when the supercooled water drops impact a heating area of a plasma hot knife, the supercooled water drops are quickly heated and flow away to prevent the ice; each deicing device cuts the ice on the wing into a plurality of independent small ice blocks, the poor ice adhesion that falls into the small ice blocks can be blown away by the external flow field, the purpose of deicing is reached, the adhesion between ice sheet and the wing profile and the ice sheet inner structure are destroyed through the heat effect, the destroyed ice sheet on the wing profile surface is blown away through aerodynamic force, meanwhile, the situation that overflow water flows to a hydrophobic region through the hydrophobic region and rapidly flies away from the wing along with airflow is prevented, ice ridges cannot be formed, and the combination of plasma deicing and the hydrophobic region achieves good deicing and the effect of preventing from refreezing.
Drawings
The invention is further described below with reference to the figures and examples.
FIG. 1 is a schematic plan view of the structure;
FIG. 2 is a schematic sectional view (example 1);
FIG. 3 is a schematic sectional view of the structure (example 2);
FIG. 4 is a schematic sectional view of the structure (example 3);
FIG. 5 is a schematic sectional view of the structure (example 4);
FIG. 6 is a schematic view of the deicing device applied to an airfoil;
Detailed Description
As shown in the drawings, the plasma hot knife and hydrophobic material composite deicing device in the embodiment includes a plasma generator, which is installed on the wing and heats the wing and the air around the wing through the generated plasma. The plasma generator comprises an arc plasma generator, a power frequency arc plasma generator, a high-frequency induction plasma generator, a low-pressure plasma generator, a combustion plasma generator and the like, the structure form of the corresponding plasma generator is selected according to the structure form of the wing, the plasma generator can be self-made according to the actual structure of the wing, the plasma generator is ensured to be in a flat structure and attached to the wing, and the thickness of the plasma generator is controlled within 1mm so as to prevent the pneumatic appearance of the wing from being influenced; the plasma generator is used for ionizing gas to form plasma, wherein the plasma is composed of unionized gas molecules, atoms, positive ions with equal total charge quantity, free electrons and negative ions, the aggregation state of the plasma is listed after solid, liquid and gas states, the fourth state of the plasma is called as a matter, the plasma is neutral on the whole and has larger conductivity, the movement of the plasma is mainly governed by electromagnetic force, the plasma has very high temperature, and the higher the ionization degree of the gas is, the higher the temperature of the plasma is; the complex structure and different characteristics of the ice shape have certain influence on the effect of the plasma deicing technology; the common ice forms formed on the wing surfaces are mainly classified into open ice, frost ice and mixed ice. The three types of ice have different structures, and the open ice has a smooth surface and a dense structure; frost ice is milky opaque in appearance and loose in structure; the mixed ice is in two mixed forms, and the mixed ice is closely compounded with the body, so that the rough surface of the mixed ice is easy to develop into the goat horn ice, and the harm is greatest; the plasma generator is arranged on the wing, corresponding output power is selected by the plasma generator according to the ice-shaped structure, and the corresponding output power is selected by environmental information detected by a sensor arranged on the wing in the actual operation process, so that the energy consumption is reduced to the maximum extent under the condition of ensuring the deicing; the plasma generator is arranged in an area where the wing is easy to freeze, the plasma generator is started to generate plasma, the plasma heats the wing and air around the installation position of the plasma generator on the wing, wherein the heating of the wing is beneficial to melting ice on the wing, so that the melted crushed ice is blown off under the action of incoming flow aerodynamic force, and the deicing effect is achieved; the deicing mode of the structure can be quickly responded, the surface of the wing is quickly heated to melt an ice layer, and broken ice flies away from the wing under the action of pneumatic power.
In this embodiment, the aircraft further comprises a base layer 1 for attaching to the wing, and the plasma generator is mounted on the base layer. As shown in fig. 1, the base layer is preferably an insulating layer, and serves as a base layer, which facilitates installation of the plasma generator and adhesion to the wing 4, and in addition, the base layer serves as a base, which facilitates the whole deicing device to form a thin sheet structure, so as to reduce influence on aerodynamic configuration of the wing.
In this embodiment, the base layer has a hydrophobic region thereon, and when the base layer is mounted on the wing, the hydrophobic region is located on a side of the base layer facing the trailing edge of the wing. The method comprises the following steps that a hydrophobic area can be formed by a hydrophobic coating coated on the upper surface of a base layer, or the base layer can be formed by splicing the base layers made of two materials, wherein the hydrophobic area is formed by the base layer made of a hydrophobic material; in the existing deicing device adopting an electric heating wire heating mode, overflow water flows to the rear edge side of the wing under the action of aerodynamic force and is frozen in a non-protection area to form ice ridges, and the molded surfaces are seriously damaged after the ice ridges are formed, so that flight accidents are easily caused; in the embodiment, in the process that the overflow water flows to the trailing edge of the wing, the overflow water is isolated from the wing by the hydrophobic area, so that the overflow water flows to the hydrophobic area and quickly flies away from the wing along with the airflow, and an ice ridge cannot be formed, thereby achieving a good deicing effect; the structure is the result of combining the plasma ice prevention and removal technology with the passive ice prevention and removal technology, the whole structure has the advantages of simple structure, quick response, wide frequency band, easiness in realizing automation and the like, and the problems of energy optimization, structure optimization and icing of overflow water at the rear edge to form ice ridges are also preliminarily solved.
In this embodiment, the base layer is made of an insulating material, the plasma generator includes an upper electrode plate 2 and a lower electrode plate 3 mounted on the base layer, and the upper electrode plate and the lower electrode plate are isolated from each other by the base layer. The isolation means that the two electrodes form a non-contact state through a base layer, the specific installation mode can be that a lower electrode plate is installed on the upper surface of the base layer, the lower electrode plate is installed on the lower surface of the base layer, or the lower electrode plate can be embedded in the base layer, when the base layer is attached to an airfoil, an upper electrode plate is exposed in the air, the upper electrode plate and the lower electrode plate are both made of copper foil or aluminum foil, as shown in a combined figure 1, only a high-voltage pulse is applied between the two electrodes, wherein the lower electrode plate is grounded, the positive electrode and the negative electrode of a high-voltage pulse power supply are respectively connected with the two electrode plates, wherein the high-voltage electrode generally needs a high voltage of more than 3kV, the normal ice prevention and removal needs a voltage of 6kV, the corresponding voltage can be selected according to the actual ice-shaped structure and the external environment, when the high-voltage is applied, plasma is generated, and the structure that the base layer is matched with the two electrode plates, the thickness of the whole deicing device is favorably controlled, so that the deicing device achieves a good deicing effect under the condition of reduced thickness, the deicing effect is guaranteed, the deicing device is prevented from influencing the aerodynamic shape of the wing, and the good aerodynamic performance of the wing is guaranteed.
In this embodiment, the projections of the upper electrode plate and the lower electrode plate in the vertical direction have an overlapping portion. Referring to fig. 1, the Y direction is the flight direction of the airplane, the direction is consistent with the flow direction of the airflow, the X direction is the length direction of the wing, the span direction of the wing, and the vertical direction is consistent with the height direction of the airplane and the thickness direction of the wing; referring to fig. 1, the upper electrode plate and the lower electrode plate are strip-shaped copper foils in the airflow direction, the upper electrode plate and the lower electrode plate are used for puncturing air to generate plasma after voltage is applied to the upper electrode plate and the lower electrode plate, the thickness of the electrode plates is required to meet the requirements of strength and aerodynamic appearance of wings, the copper foils are adhesive tape-type copper foils, one surface of each copper foil is provided with high-viscosity adhesive, and the high-viscosity adhesive is directly adhered to a base layer to ensure that the copper foils cannot fall off; as shown in fig. 2, the arrangement of the upper electrode plate and the lower electrode plate in fig. 2 corresponds to that in fig. 1, the width (X-direction size) of the upper electrode plate is smaller than that of the lower electrode plate, the center of the upper electrode plate is positioned in the position vertically opposite to the center of the lower electrode plate, plasma generated by the plasma generator of the structure can diffuse on both sides of the upper electrode plate in the X direction, and the vertically opposite arrangement structure of the upper electrode plate and the lower electrode plate is favorable for reducing the voltage required for air breakdown; of course, a plurality of upper electrode plates and lower electrode plates may be arranged in the base layer, as shown in fig. 4, one lower electrode plate corresponds to two upper electrode plates, vertical projections of the two upper electrode plates completely fall into the lower electrode plate, as shown in fig. 5, two groups of electrode structures may be arranged on the base layer, and each group of electrode structures has one upper electrode plate and one lower electrode plate which are vertically opposite; the specific arrangement form of the upper and lower electrode plates can be adjusted according to the actual required adaptability, and details are not repeated; the projection parts of the upper electrode plate and the lower electrode plate are overlapped, so that the critical condition required by air breakdown is favorably reduced, and the generation of plasma is favorably realized.
In this embodiment, the base layer is formed by stacking a plurality of high temperature resistant insulating layers, and the upper electrode sheet and the lower electrode sheet are respectively bonded to two sides of the base layer. In the embodiment, the base layer is made of Kapton adhesive tape, the adhesive tape is made of polyimide, the high temperature resistance range is about 300 ℃, the dielectric constant of the adhesive tape is 3.4, and the thickness of each layer is 0.06 mm; in the embodiment, three layers of Kapton tapes are adopted, the lower electrode plate can be directly adhered to the adhesive surface of the Kapton tape, the adhesive tape stacking mode is adopted, the high-temperature-resistant insulating layers can be tightly adhered, the deicing device can be conveniently adhered to the surface of the wing, the lower electrode plate can be firstly adhered to the wing, then the base layer is covered, the lower electrode plate is adhered to the wing, finally the high-voltage electrode is adhered to the upper surface of the base layer to form the deicing device, then high voltage is applied, plasma is generated, and the whole installation and control process is simple; in addition, the thickness of the base layer can be adjusted by overlapping the multiple layers of high-temperature-resistant insulating layers, so that the thickness of the base layer can be controlled within a reasonable range, the longer service life of the base layer is ensured, the voltage required by the upper electrode plate and the lower electrode plate during working is lower, and the purposes of environmental protection and energy conservation are achieved.
In this embodiment, the base layer is a strip, the base layer is divided into a plasma hot knife area and a hydrophobic area in the length direction, and the plasma generator is installed in the plasma hot knife area. The length of the base layer is determined according to the specific structure of the wing, and as shown in fig. 1, a strip-shaped plasma hot knife area is formed on the base layer near the front edge of the wing, the hot knife effect is generated in the area to melt ice on the wing, each deicing device cleans the ice on the wing in the Y direction, so that the ice is divided into a plurality of independent small ice areas in the X direction of the wing, the adhesive force of ice blocks is reduced, and the residual ice blocks are peeled off from the wing under the action of inflow aerodynamic force;
in this embodiment, the thickness of the base layer is 0.12-0.3mm, and the thickness of the upper electrode plate and the lower electrode plate is 0.04-0.1 mm. In the embodiment, the base layer is formed by overlapping three layers of Kapton tapes with the thickness of 0.06mm, the total thickness is 0.18mm, the thicknesses of the upper electrode plate and the lower electrode plate are 0.06mm, the total thickness of the whole deicing device is not more than 0.31mm, and the pneumatic appearance of the deicing device cannot be influenced when the deicing device is attached to a wing.
The embodiment also provides application of the plasma hot knife and the hydrophobic material composite deicing device, and a plurality of plasma hot knives and the hydrophobic material composite deicing devices are arranged on the wing in the wingspan direction. As shown in the combined figure 1, the arrangement of the deicing devices is favorable for cutting the ice on the wings into a plurality of independent small ice blocks arranged in the X direction, the independent small ice blocks naturally fall off under the action of the incoming flow aerodynamic force by controlling the distance between the deicing devices, and the structure can only heat the local area of the wings to remove the whole ice layer, so that the energy consumption is reduced.
In this embodiment, a plasma hot knife region corresponding to each plasma hot knife and hydrophobic material composite deicing device is located at a leading edge of the wing, and the hydrophobic region extends from the upper surface of the wing to the trailing edge of the wing, and the plasma hot knife region extends from the upper surface of the wing to the lower surface of the wing around the leading edge of the wing. Wind tunnel experiments and flight experiments show that the water collection coefficient of the front edge of the wing profile is the largest, and when supercooled water drops impact the surface of the wing profile, the wing profile can be quickly frozen and continuously grow; the area is typical important protection, so that a plasma hot knife area is mainly arranged from 5% C to 10% C of the upper surface of the lower surface of the front leading edge of the airfoil, wherein C is the length of the airfoil chord, a plasma hot knife is formed in the area, a hydrophobic coating is arranged from 10% C to 50% C of the upper surface, and as shown in a combined manner in FIG. 6, the plasma hot knife area corresponds to the area B, and the hydrophobic area corresponds to the area A; the ultra-hydrophobic area covering the surface of the wing is connected with the hot knife in parallel below the plasma hot knife, and when overflow water formed after the plasma hot knife is deiced develops backwards, the overflow water is quickly separated from the surface of the wing by means of the characteristics of the ultra-hydrophobic area and the aerodynamic force of incoming flow, so that a good deicing effect is achieved.
The deicing device is mainly used for realizing deicing through the combination of a plasma hot knife and a hydrophobic layer, wherein the main action mechanism of the plasma hot knife is thermal effect and inflow aerodynamic force, the heat production of the plasma hot knife is divided into two parts, one part is used for heating the air around a plasma generator, and the other part is used for heating the wing body through a base medium; the super cooled water droplets are rapidly heated in a single cycle by convective heat transfer by the rapidly heating gas. Therefore, once the supercooled water drops hit the heating area of the "plasma hot knife", they are rapidly heated and flow away, preventing icing; and in the middle of the adjacent heating areas, areas which are not fully heated possibly still exist, but according to the principle of a plasma hot knife, ice divided into small blocks has poor adhesive force and is easily blown away by an external flow field to achieve the aim of deicing, the adhesive force between an ice layer and an airfoil and the internal structure of the ice layer are damaged through a thermal effect, the damaged ice layer on the surface of the airfoil is blown away through aerodynamic force, meanwhile, the situation that overflow water flows to a hydrophobic area and quickly flies away from the airfoil along with airflow through the hydrophobic area is prevented, ice ridges cannot be formed, and the plasma deicing and the hydrophobic area are combined to achieve a good deicing effect.
Finally, the above embodiments are only for illustrating the technical solutions of the present invention and not for limiting, although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that modifications or equivalent substitutions may be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all of them should be covered in the claims of the present invention.
Claims (10)
1. The utility model provides a hot sword of plasma and hydrophobic material combined type defroster which characterized in that: comprises a plasma generator which is arranged on the wing and heats the wing and the air around the wing by the generated plasma.
2. The plasma hot knife and hydrophobic material composite deicing device of claim 1, wherein: the plasma generator further comprises a base layer attached to the wing, and the plasma generator is installed on the base layer.
3. The plasma hot knife and hydrophobic material composite deicing device of claim 2, wherein: the base layer is provided with a hydrophobic area, and when the base layer is installed on the wing, the hydrophobic area is positioned on one side of the base layer, which faces to the trailing edge of the wing.
4. The plasma hot knife and hydrophobic material composite deicing device of claim 2, wherein: the base layer is made of an insulating material, the plasma generator comprises an upper electrode plate and a lower electrode plate which are arranged on the base layer, and the upper electrode plate and the lower electrode plate are isolated through the base layer.
5. The plasma hot knife and hydrophobic material composite deicing device of claim 4, wherein: the projections of the upper electrode plate and the lower electrode plate in the vertical direction are provided with overlapped parts.
6. The plasma hot knife and hydrophobic material composite deicing device of claim 4, wherein: the base layer is formed by overlapping a plurality of high-temperature-resistant insulating layers, and the upper electrode plate and the lower electrode plate are respectively bonded on two sides of the base layer.
7. The plasma hot knife and hydrophobic material composite deicing device of claim 3, wherein: the base layer is in a long strip shape, the base layer is divided into a plasma hot knife area and a hydrophobic area in the length direction, and the plasma generator is installed in the plasma hot knife area.
8. The plasma hot knife and hydrophobic material composite deicing device of claim 6, wherein: the thickness of the base layer is 0.12-0.3mm, and the thickness of the upper electrode plate and the lower electrode plate is 0.04-0.1 mm.
9. The application of the plasma hot knife and hydrophobic material combined type deicing device is characterized in that: the plasma hot knife and hydrophobic material composite deicing device of any one of claims 1 to 8 is arranged in plurality in a spanwise arrangement on an airfoil.
10. The use of a plasma hot knife and hydrophobic material composite de-icing apparatus according to claim 9, wherein: and a plasma hot knife area corresponding to each plasma hot knife and the hydrophobic material composite deicing device is positioned at the leading edge of the wing, the hydrophobic area extends to the trailing edge of the wing along the upper surface of the wing, and the plasma hot knife area extends to the lower surface of the wing by bypassing the leading edge of the wing through the upper surface of the wing.
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| CN202011603349.6A CN113148183A (en) | 2020-12-29 | 2020-12-29 | Plasma hot knife and hydrophobic material combined type deicing device and application |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114143949A (en) * | 2021-12-03 | 2022-03-04 | 中国人民解放军空军工程大学 | Flexible hydrophobic barrier dielectric plasma anti-icing device and anti-icing method |
| WO2024021904A1 (en) * | 2022-07-29 | 2024-02-01 | 广东美的制冷设备有限公司 | Heat exchanger assembly, air conditioner outdoor unit, air conditioner indoor unit, air conditioner and antifrost control method |
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