A plasma device and method for anti-icing and de-icing of swept wings

Abstract

This invention provides a plasma device and method for de-icing swept wings, including a plasma power supply and a plasma actuator. The plasma actuator is a surface dielectric barrier discharge plasma actuator, comprising an insulating dielectric layer, exposed electrodes, and buried electrodes. This invention uses a high-voltage AC surface dielectric barrier discharge plasma actuator for de-icing, which has advantages such as small size, light weight, low power consumption, fast response, no mechanical parts, and high heating efficiency. Furthermore, by utilizing the aerodynamic effect of the plasma actuator, energy can be injected into the airfoil boundary layer, delaying surface flow separation and improving the aerodynamic performance of the wing.

Description

Technical Field

[0001] This invention belongs to the field of plasma physics and anti-icing technology, specifically relating to a plasma device and method for anti-icing of swept wings. Background Technology

[0002] To enhance high-speed performance, modern large transport aircraft mostly employ high-aspect-ratio swept wings. At low altitudes and low speeds, when an aircraft flies over icing clouds, supercooled water droplets from the clouds impact its windward surface, causing icing. Icing during flight often poses a significant threat to flight safety. Icing on swept wings disrupts their streamlined aerodynamic shape, increases drag, and reduces lift. Most seriously, irregular icing at the leading edge of the swept wing severely affects the aircraft's handling and stability. Therefore, swept-wing icing is one of the key issues directly impacting flight safety.

[0003] To address the icing problem during flight, researchers have proposed numerous anti-icing / de-icing methods. Based on their purpose, these can be categorized into de-icing and anti-icing. De-icing involves allowing a certain amount of ice to accumulate and then removing it, while anti-icing aims to ensure that no ice forms during flight in icy environments. Based on the form of energy used in the anti-icing / de-icing process, they can be classified into chemical liquid anti-icing, mechanical de-icing, and heat source anti-icing.

[0004] Chemical liquid de-icing involves spraying a low-freezing-point liquid (such as ethanol or ethylene glycol) onto the areas requiring protection to remove existing ice buildup. The chemical liquid adheres to the aircraft surface for a period of time, thus providing short-term anti-icing protection. Liquid de-icing is typically used for aircraft about to take off during the ground phase to prevent icing during takeoff.

[0005] Mechanical de-icing utilizes mechanical force to disrupt the structure and adhesion properties of ice, causing it to detach from the surface under the influence of gravity and aerodynamic forces. This includes pneumatic strip de-icing and electrical pulse de-icing. Pneumatic strip de-icing uses air inflation to achieve periodic deformation of the protected area surface, which significantly impacts wing aerodynamic performance and is prone to aging, thus requiring regular inspection and maintenance. This method can only remove ice, not prevent it. Electrical pulse de-icing uses periodic electromagnetic pulses to induce periodic deformation of the wing skin, disrupting the adhesion properties of the ice layer and causing it to detach. However, issues related to skin fatigue and electromagnetic interference still require further resolution.

[0006] Heat source de-icing refers to directly heating the protected area using electric or gas heating to raise its surface temperature above freezing, thus preventing and removing ice. This is currently the mainstream de-icing method, but it consumes a lot of power, and drawing heat from the engine can reduce engine efficiency.

[0007] Therefore, how to solve the problems of various anti-icing and de-icing methods in the existing technology that damage the aerodynamic shape, require a heat source, and have high power consumption is a difficult point that needs to be addressed in order to meet the development needs of future aircraft. Summary of the Invention

[0008] To address the shortcomings of existing technologies, this invention provides a plasma device and method for anti-icing and de-icing of swept wings, which can effectively solve the above-mentioned problems.

[0009] The technical solution adopted in this invention is as follows:

[0010] This invention provides a plasma device for anti-icing and de-icing of swept wings, comprising a plasma power supply and a plasma actuator; the plasma actuator is a surface dielectric barrier discharge plasma actuator, comprising an insulating dielectric layer (1), exposed electrodes (2) and buried electrodes (3); the exposed electrodes (2) are laid on the upper surface of the insulating dielectric layer (1); the buried electrodes (3) are laid on the lower surface of the insulating dielectric layer (1); in the length direction, the exposed electrodes (2) and the buried electrodes (3) are arranged in parallel, asymmetrical and staggered manner; in the width direction, there is no covering or gap between the exposed electrodes (2) and the buried electrodes (3);

[0011] The plasma power supply is connected to the exposed electrode (2) and the buried electrode (3) respectively, and is used to supply high-voltage alternating current to the exposed electrode (2) and the buried electrode (3);

[0012] The plasma exciter is laid on the surface of the swept wing (4) such that the length direction of the exposed electrode (2) and the buried electrode (3) of the plasma exciter is parallel to the generatrix direction of the wing.

[0013] Preferably, the plasma exciter is laid on the leading edge of the swept wing (4), specifically at the following positions: in the span direction, measured from the wingtip of the swept wing (4), at a position of 18% to 75% of the span of the swept wing (4); in the chord direction, measured from the leading edge of the swept wing (4), at a position of 0% to 16% of the chord length of the swept wing (4).

[0014] Preferably, the insulating dielectric layer (1) is a 0.35 mm thick polyimide film material; the exposed electrode (2) and the buried electrode (3) are both 0.06 mm thick copper tape; the width of the buried electrode (3) is 5 mm-10 mm; the width of the exposed electrode (2) is 3 mm-5 mm; and the effective working length of the exposed electrode (2) and the buried electrode (3) is 100 mm-150 mm.

[0015] Preferably, both the exposed electrode (2) and the buried electrode (3) are rounded.

[0016] Preferably, n exposed electrodes (2) are laid at intervals on the upper surface of the insulating dielectric layer (1); a buried electrode (3) is laid at the interval between every two adjacent exposed electrodes (2) and on the lower surface of the insulating dielectric layer (1), thereby laying a total of n-1 buried electrodes (3); therefore, every two adjacent exposed electrodes (2) share the same corresponding buried electrode (3), forming multiple sets of exciter units.

[0017] Preferably, the n exposed electrodes (2) are sequentially represented along the width direction as: the first exposed electrode, the second exposed electrode, ..., the nth exposed electrode; the n-1 buried electrodes (3) are sequentially represented along the width direction as: the first buried electrode, the second buried electrode, ..., the n-1th buried electrode; then, along the width direction, the arrangement order of each electrode is: the first exposed electrode, the first buried electrode, the second exposed electrode, the second buried electrode, ..., the n-1th buried electrode, the nth exposed electrode, and each electrode is parallel, asymmetrical, and staggered.

[0018] Preferably, the insulating dielectric layer (1) is a double parallelogram shape, including a left parallelogram insulating dielectric layer and a right parallelogram insulating dielectric layer located symmetrically on both sides of the center line of the insulating dielectric layer; each of the buried electrodes (3) and the exposed electrodes (2) forms an electrode group. When the electrode group is arranged on the double parallelogram-shaped insulating dielectric layer (1), the center of the electrode group is located on the center line of the insulating dielectric layer. At this time, its arrangement on the surface of the swept wing is as follows: the electrode at the center of the electrode group is located at the leading edge stagnation line of the swept wing (4), and then the left parallelogram insulating dielectric layer is folded along the center position of the electrode group and laid on the lower surface of the swept wing; the right parallelogram insulating dielectric layer is folded along the center position of the electrode group and laid on the upper surface of the swept wing.

[0019] The present invention also provides a method for de-icing a plasma device for swept-wing de-icing, comprising the following steps:

[0020] Step 1: During the flight of the aircraft, real-time detection is performed to check whether supercooled water droplets are present in the incoming stream and whether ice has formed on the surface of the swept wing. If no supercooled water droplets are detected in the incoming stream and the surface of the swept wing is not iced, proceed to Step 2; if supercooled water droplets are detected in the incoming stream and the surface of the swept wing is not iced, proceed to Step 3; if ice is detected on the surface of the swept wing, proceed to Step 4 regardless of whether supercooled water droplets are present in the incoming stream.

[0021] Step 2: At this point, no anti-icing operation is required; keep the plasma power supply off.

[0022] Step 3: For cases with supercooled water droplets but no ice formation, anti-icing operation is required. The specific method is as follows: control the plasma power supply and apply a 13kV, 9kHz sinusoidal alternating current to the plasma exciter, so that the plasma exciter works according to the anti-icing parameters. Through the ionization heat effect and aerodynamic effect of plasma excitation, ice formation is prevented after the supercooled water droplets collide, thus achieving the anti-icing effect on the swept wing surface.

[0023] Step 4: In the case of icing, de-icing operation is required. The specific method is as follows: control the plasma power supply and apply a 13kV, 9kHz sinusoidal alternating current to the plasma exciter, so that the plasma exciter works according to the de-icing parameters. Through the ionization heat effect and aerodynamic effect of plasma excitation, the ice layer on the swept wing surface melts, splits and falls off rapidly, so as to achieve the effect of de-icing the swept wing surface.

[0024] Among them: when the plasma exciter performs steps 3 and 4, by designing the position and direction of the plasma exciter on the surface of the swept wing, after the plasma exciter is turned on, the surrounding air is ionized under the strong electric field of the exposed electrode (2) to generate plasma. The plasma is driven by the electric field to generate flow, thereby generating aerodynamic effect, thus injecting energy into the boundary layer of the swept wing airfoil, delaying the flow separation on the surface of the swept wing, and improving the aerodynamic performance of the swept wing.

[0025] The plasma device and method for anti-icing and de-icing of swept wings provided by the present invention have the following advantages:

[0026] This invention employs a high-voltage AC surface dielectric barrier discharge plasma exciter for de-icing, which has advantages such as small size, light weight, low power consumption, fast response, no mechanical parts, and high heating efficiency. Furthermore, by utilizing the aerodynamic effect of the plasma exciter, energy can be injected into the airfoil boundary layer, delaying surface flow separation and improving the aerodynamic performance of the wing. Attached Figure Description

[0027] Figure 1 This is a cross-sectional schematic diagram of the plasma exciter provided in Embodiment 1 of the present invention;

[0028] Figure 2 This is a top view of the plasma exciter provided in Embodiment 1 of the present invention;

[0029] Figure 3 This is a schematic diagram of the plasma power supply output voltage waveform provided in Embodiment 1 of the present invention;

[0030] Figure 4 This is a perspective view of the plasma exciter provided in Embodiment 2 of the present invention;

[0031] Figure 5 This is a diagram showing the arrangement of the plasma exciter on the swept wing according to Embodiment 2 of the present invention;

[0032] Figure 6 This is a schematic diagram of the arrangement of electrodes in the electrode width direction in the plasma exciter provided in Embodiment 2 of the present invention;

[0033] Figure 7 This is a schematic diagram showing the misalignment of two adjacent electrodes in the length direction in the plasma exciter provided in Embodiment 2 of the present invention. Detailed Implementation

[0034] To make the technical problems solved, the technical solutions, and the beneficial effects of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and are not intended to limit the invention.

[0035] This invention provides a plasma device for anti-icing and de-icing of swept wings, comprising a plasma power supply and a plasma actuator. The plasma actuator is a surface dielectric barrier discharge plasma actuator, comprising an insulating dielectric layer 1, exposed electrodes 2, and buried electrodes 3. The exposed electrodes 2 are laid on the upper surface of the insulating dielectric layer 1, and are in direct contact with the atmospheric environment. The buried electrodes 3 are laid on the lower surface of the insulating dielectric layer 1, and are covered by the insulating dielectric layer 1. In the length direction, the exposed electrodes 2 and the buried electrodes 3 are arranged in parallel, asymmetrical, and staggered configurations. In the width direction, there is no covering or gap between the exposed electrodes 2 and the buried electrodes 3. For details regarding the length and width directions, please refer to [reference needed]. Figure 2 .

[0036] In this invention, the exposed electrode 2 and the buried electrode 3 are made of conductive materials, such as metallic copper. The length, number, and installation position of the plasma exciter are determined according to actual usage requirements.

[0037] The plasma power supply is connected to both the exposed electrode 2 and the buried electrode 3, and is used to supply high-voltage alternating current V to the exposed electrode 2 and the buried electrode 3. p-p A macroscopically uniform glow discharge plasma is formed on the upper surface of the insulating dielectric layer 1, and de-icing is achieved by relying on the thermal and aerodynamic effects generated during plasma excitation. In this invention, as... Figure 3 As shown, the plasma excitation applied during both anti-icing and de-icing processes is a sinusoidal alternating current with a peak voltage of 13 kV and a frequency of 9 kHz.

[0038] The plasma actuator is tightly laid on the surface of the swept wing 4 and fixed with pressure-sensitive adhesive, so that the length direction of the exposed electrode 2 and the buried electrode 3 of the plasma actuator is parallel to the generatrix direction of the wing.

[0039] As a preferred method, the plasma exciter is laid on the leading edge of the swept wing 4, specifically at the following positions: in the span direction, from the wingtip of the swept wing 4, at a position of 18% to 75% of the span of the swept wing 4; and in the chord direction, from the leading edge of the swept wing 4, at a position of 0% to 16% of the chord length of the swept wing 4.

[0040] For example, a plasma anti-icing device was installed on a swept wing with a chord length of 165 mm, a span of 380 mm, and a sweep angle of 30°. The device, 250 mm long and 80 mm wide, was applied to the leading edge of the swept wing using pressure-sensitive adhesive. After installation, the length of the anti-icing device was parallel to the wing's generatrix to ensure the electrodes were parallel to the wing's generatrix. The anti-icing device was positioned at 18% to 75% of the swept wing's span (from the wingtip) and at 0% to 16% of the chord length (from the leading edge), covering a total area of ​​14.25% of the swept wing's surface area.

[0041] This arrangement, with the electrodes parallel to the wing's generatrix, generates thermal and aerodynamic effects that rapidly raise the temperature of the leading edge of the swept wing and the surrounding air, enabling the swept wing to de-ic. Furthermore, because the electrodes are parallel to the wing's generatrix, the adverse effects of arranging the plasma de-icing device on the wing's aerodynamic performance can be minimized.

[0042] In this invention, the structural parameters of the insulating dielectric layer 1, the exposed electrode 2, and the buried electrode 3 are as follows: the insulating dielectric layer 1 is a 0.35mm thick polyimide (Kapton) film material; both the exposed electrode 2 and the buried electrode 3 are 0.06mm thick copper tapes; the width of the buried electrode 3 is 5mm-10mm; the width of the exposed electrode 2 is 3mm-5mm; and the effective working length of the exposed electrode 2 and the buried electrode 3 is 100mm-150mm. To avoid tip discharge, both the exposed electrode 2 and the buried electrode 3 are rounded.

[0043] The insulating dielectric layer 1 can be a single piece or several pieces spliced ​​together. It needs to completely cover and bury the electrode 3. Moreover, a margin of more than 10mm should be left in the width direction of the electrode to prevent the electrode from crossing the dielectric layer and discharging. That is, in the width direction, the insulating dielectric layer 1 has a margin of more than 10mm and no electrodes are placed there.

[0044] In this invention, the number of exposed electrodes 2 and buried electrodes 3 laid on the upper and lower surfaces of the insulating dielectric layer 1 can be one or more, depending on the actual application requirements. Two embodiments are described below:

[0045] Example 1:

[0046] This implementation example Figure 1 and Figure 2 As shown, the plasma actuator includes an insulating dielectric layer 1, exposed electrodes 2, and buried electrodes 3; wherein, there is one exposed electrode 2 and one buried electrode 3, distributed on both sides of the insulating dielectric layer 1. Other parameters and principles are the same as described above, and will not be repeated here.

[0047] Example 2:

[0048] The main difference between this embodiment and the one described above is that, for example, this embodiment... Figures 4 to 7 As shown, n exposed electrodes 2 are laid at intervals on the upper surface of the insulating dielectric layer 1; a buried electrode 3 is laid at the interval between every two adjacent exposed electrodes 2 and on the lower surface of the insulating dielectric layer 1, thereby laying a total of n-1 buried electrodes 3; therefore, every two adjacent exposed electrodes 2 share the same corresponding buried electrode 3, forming multiple sets of exciter units.

[0049] Therefore, the anti-icing device includes multiple actuator units, which can share the exposed electrode 2 or the buried electrode 3, thus forming different actuator layouts.

[0050] Plasma actuators are flexible and can be easily laid on the surface of swept wings without affecting their aerodynamic characteristics. Therefore, multiple sets of plasma actuators can be laid on swept wings according to actual needs.

[0051] The n exposed electrodes 2 are sequentially represented along the width direction as: the 1st exposed electrode, the 2nd exposed electrode, ..., the nth exposed electrode; the n-1 buried electrodes 3 are sequentially represented along the width direction as: the 1st buried electrode, the 2nd buried electrode, ..., the (n-1)th buried electrode; then, along the width direction, the arrangement order of each electrode is: the 1st exposed electrode, the 1st buried electrode, the 2nd exposed electrode, the 2nd buried electrode, ..., the (n-1)th buried electrode, the nth exposed electrode, and each electrode is parallel, asymmetrical, and staggered.

[0052] exist Figures 4 to 7In this configuration, n is 4, therefore, a total of 4 exposed electrodes 2 and 3 buried electrodes 3 are set. Any two adjacent exposed electrodes share a buried electrode. All four exposed electrodes are 5mm wide and 180mm long. Two of the three buried electrodes are 10mm wide, and the other is 5mm wide, both 180mm long. The 5mm wide buried electrodes are symmetrically laid on the stagnation line of the leading edge of the swept wing. Then, the remaining exposed and buried electrodes are laid on the insulating dielectric layer without overlap or gaps in the width direction. In the length direction, the buried and exposed electrodes are not symmetrically distributed; they are staggered to reduce the possibility of dielectric layer breakdown during operation. Due to the stagger, the effective operating length of the actuator is 150mm. To ensure that the electrodes are in the same position in the span direction of the swept wing, there is also a certain degree of stagger between the electrodes.

[0053] As designed by the inventor, such as Figure 4 As shown, the insulating dielectric layer 1 is a double parallelogram shape with a length of 250 mm and a width of 80 mm, including a left parallelogram insulating dielectric layer and a right parallelogram insulating dielectric layer located symmetrically on both sides of the center line of the insulating dielectric layer; each buried electrode 3 and exposed electrode 2 forms an electrode group. When the electrode group is arranged on the double parallelogram-shaped insulating dielectric layer 1, the center of the electrode group is located at the center line of the insulating dielectric layer. At this time, its arrangement on the swept wing surface is as follows: Figure 5 As shown, the electrode at the center of the electrode assembly is positioned at the leading edge stagnation line of the swept wing 4. Then, the left parallelogram insulating dielectric layer is folded along the center of the electrode assembly and laid on the lower surface of the swept wing; the right parallelogram insulating dielectric layer is folded along the center of the electrode assembly and laid on the upper surface of the swept wing.

[0054] The use of a double parallelogram-shaped insulating dielectric layer 1 and the above-mentioned electrode arrangement has the following advantages: after the exciter is turned on, the thermal and aerodynamic effects generated by it can quickly raise the temperature of the leading edge of the swept wing and the surrounding air, enabling the swept wing to achieve de-icing.

[0055] The present invention also provides a method for de-icing a plasma device for anti-icing of swept wings, comprising the following steps:

[0056] Step 1: During the flight of the aircraft, real-time detection is performed to check whether supercooled water droplets are present in the incoming airflow and whether ice has formed on the surface of the swept wing. If no supercooled water droplets are detected in the incoming airflow and the surface of the swept wing is not iced, proceed to Step 2. If supercooled water droplets are detected in the incoming airflow and the surface of the swept wing is not iced, for example, when the aircraft passes through an icy cloud and there is a supercooled water droplet impact phenomenon in the incoming airflow, there is a risk of icing, proceed to Step 3. If ice is detected on the surface of the swept wing, that is, if it is determined that ice has formed on the surface of the swept wing and there is ice accumulation, then regardless of whether there are supercooled water droplets in the incoming airflow, proceed to Step 4.

[0057] Step 2: At this point, no anti-icing operation is required; keep the plasma power supply off.

[0058] Step 3: For cases with supercooled water droplets but no ice formation, anti-icing operation is required. The specific method is as follows: control the plasma power supply and apply a 13kV, 9kHz sinusoidal alternating current to the plasma exciter, so that the plasma exciter works according to the anti-icing parameters. Through the ionization heat effect and aerodynamic effect of plasma excitation, ice formation is prevented after the supercooled water droplets collide, thus achieving the anti-icing effect on the swept wing surface.

[0059] Step 4: In the case of icing, de-icing operation is required. The specific method is as follows: control the plasma power supply and apply a 13kV, 9kHz sinusoidal alternating current to the plasma exciter, so that the plasma exciter works according to the de-icing parameters. Through the ionization heat effect and aerodynamic effect of plasma excitation, the ice layer on the swept wing surface melts, splits and falls off rapidly, so as to achieve the effect of de-icing the swept wing surface.

[0060] In other words, the operating conditions of the exciter can be divided into three categories based on the environment in which the aircraft is located: (1) no supercooled water droplets, no icing; (2) supercooled water droplets, no icing; (3) icing. Corresponding operations are performed for different detection results.

[0061] For (1) cases where there are no supercooled water droplets and no ice formation, there is no need for de-icing. The controller controls the plasma power supply to keep it off.

[0062] For (2) where there are supercooled water droplets but no ice formation, anti-icing measures are required. The controller controls the plasma power supply to operate according to the anti-icing parameters to ensure that no ice formation occurs in the protected area.

[0063] For (3) cases where there is icing, it is necessary to remove the ice. The controller controls the plasma power supply to operate according to the parameters for removing ice, so as to remove the ice in the protected area as soon as possible.

[0064] Specifically: When the plasma exciter performs steps 3 and 4, by designing the position and orientation of the plasma exciter on the swept wing surface, after the plasma exciter is turned on, the surrounding air is ionized under the strong electric field of the exposed electrode 2 to generate plasma. The plasma flows under the drive of the electric field, thereby generating aerodynamic effects, thus injecting energy into the boundary layer of the swept wing airfoil, delaying the flow separation on the swept wing surface, and improving the aerodynamic performance of the swept wing.

[0065] This invention provides a plasma device and method for anti-icing and de-icing of swept wings, which has the following characteristics:

[0066] (1) The exposed and buried electrodes of the plasma exciter involved in the anti-icing device have been rounded to prevent tip discharge from breaking down the dielectric layer. In addition, the exposed and buried electrodes are installed in a staggered manner along the length, which facilitates the connection of the circuit and also prevents the phenomenon of breaking down the dielectric layer.

[0067] (2) The anti-icing device includes multiple sets of plasma actuators, and these actuators can share exposed electrodes or buried electrodes, thus forming different actuator layouts. The plasma actuators are flexible and can be easily laid on the surface of the swept wing without affecting its aerodynamic characteristics. Therefore, multiple sets of plasma actuators can be laid on the swept wing according to actual needs.

[0068] (3) Regarding the design of the location and orientation of the plasma actuator on the swept wing surface, after the plasma actuator is turned on, it can not only quickly achieve the anti-icing function, but also inject energy into the boundary layer of the swept wing airfoil through aerodynamic effects, delay the flow separation on the swept wing surface, and improve the aerodynamic performance of the swept wing.

[0069] This invention provides a plasma device and method for anti-icing and de-icing of swept wings, which has the following advantages:

[0070] (1) This invention employs a high-voltage AC surface dielectric barrier discharge plasma exciter for anti-icing and de-icing, which has advantages such as small size, light weight, low power consumption, fast response, no mechanical parts, and high heating efficiency, avoiding the disadvantages of high energy consumption and low energy utilization of traditional anti-icing and de-icing methods. Unlike traditional gas-heated and electrothermal anti-icing technologies, plasma excitation directly heats the near-wall space, and then improves the mixing of ionization heat and incoming flow through the aerodynamic effect of plasma excitation itself, thereby achieving higher energy conversion efficiency and lower anti-icing temperature, without thermal damage to composite materials.

[0071] (2) The anti-icing method of the present invention can easily adjust the excitation intensity by changing the voltage and frequency of the exciter, and facilitates the control of the power consumption of the anti-icing system according to the actual meteorological conditions, so as to achieve the anti-icing effect with the optimal excitation parameters.

[0072] (3) The plasma actuator itself can serve as a flow control technology, thus causing no potential loss of aerodynamic performance to the aircraft. Furthermore, icing areas on aircraft are often located in regions where aerodynamic performance changes drastically. When the actuator is activated, the surrounding air is ionized under the strong electric field of the exposed electrodes, generating plasma. This plasma then flows under the drive of the electric field. Utilizing the aerodynamic effect of this plasma actuator, energy can be injected into the boundary layer of the airfoil, delaying surface flow separation and improving the aerodynamic performance of the wing.

[0073] (4) The plasma de-icing method is electrically driven and does not require mechanical systems or hot gas pipelines, so it can be easily used as a de-icing system for the next generation of all-electric aircraft.

[0074] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A plasma device for anti-icing and de-icing of swept wings, characterized in that, It includes a plasma power supply and a plasma exciter; the plasma exciter is a surface dielectric barrier discharge plasma exciter, including an insulating dielectric layer (1), an exposed electrode (2) and a buried electrode (3); the exposed electrode (2) is laid on the upper surface of the insulating dielectric layer (1); the buried electrode (3) is laid on the lower surface of the insulating dielectric layer (1); in the length direction, the exposed electrode (2) and the buried electrode (3) are arranged in parallel, asymmetrical and staggered manner; in the width direction, there is no cover and no gap between the exposed electrode (2) and the buried electrode (3); The plasma power source is connected to the exposed electrode (2) and the buried electrode (3) respectively, and is used to supply high voltage AC power to the exposed electrode (2) and the buried electrode (3); The plasma exciter is laid on the surface of the swept wing (4) such that the length direction of the exposed electrode (2) and the buried electrode (3) of the plasma exciter is parallel to the generatrix direction of the wing; The insulating dielectric layer (1) is a double parallelogram shape, including a left parallelogram insulating dielectric layer and a right parallelogram insulating dielectric layer located on the left and right sides of the center line of the insulating dielectric layer and symmetrically arranged; each of the buried electrodes (3) and the exposed electrodes (2) forms an electrode group. When the electrode group is arranged on the double parallelogram shaped insulating dielectric layer (1), the center of the electrode group is located at the center line of the insulating dielectric layer. At this time, its arrangement on the surface of the swept wing is as follows: the electrode at the center of the electrode group is located at the leading edge stagnation line of the swept wing (4), and then the left parallelogram insulating dielectric layer is folded along the center position of the electrode group and laid on the lower surface of the swept wing; the right parallelogram insulating dielectric layer is folded along the center position of the electrode group and laid on the upper surface of the swept wing.

2. The plasma device for anti-icing and de-icing of swept wings according to claim 1, characterized in that, The plasma exciter is laid on the leading edge of the swept wing (4), specifically at the following positions: in the span direction, starting from the wingtip of the swept wing (4), at a position of 18% to 75% of the span of the swept wing (4); in the chord direction, starting from the leading edge of the swept wing (4), at a position of 0% to 16% of the chord length of the swept wing (4).

3. The plasma device for anti-icing and de-icing of swept wings according to claim 1, characterized in that, The insulating dielectric layer (1) is a 0.35 mm thick polyimide film material; the exposed electrode (2) and the buried electrode (3) are both 0.06 mm thick copper tape; the width of the buried electrode (3) is 5 mm-10 mm; the width of the exposed electrode (2) is 3 mm-5 mm; the effective working length of the exposed electrode (2) and the buried electrode (3) is 100 mm-150 mm.

4. A plasma device for anti-icing and de-icing of swept wings according to claim 1, characterized in that, Both the exposed electrode (2) and the buried electrode (3) are rounded.

5. A plasma device for anti-icing and de-icing of swept wings according to claim 1, characterized in that, n exposed electrodes (2) are laid at intervals on the upper surface of the insulating dielectric layer (1); a buried electrode (3) is laid at the interval between every two adjacent exposed electrodes (2) and on the lower surface of the insulating dielectric layer (1), thereby laying a total of n-1 buried electrodes (3); therefore, every two adjacent exposed electrodes (2) share the same corresponding buried electrode (3), forming multiple sets of exciter units.

6. A plasma device for anti-icing and de-icing of swept wings according to claim 5, characterized in that, The n exposed electrodes (2) are sequentially represented along the width direction as: the first exposed electrode, the second exposed electrode, ..., the nth exposed electrode; the n-1 buried electrodes (3) are sequentially represented along the width direction as: the first buried electrode, the second buried electrode, ..., the n-1th buried electrode; then, along the width direction, the arrangement order of each electrode is: the first exposed electrode, the first buried electrode, the second exposed electrode, the second buried electrode, ..., the n-1th buried electrode, the nth exposed electrode, and each electrode is parallel, asymmetrical, and staggered.

7. A method for de-icing a plasma device for anti-icing and de-icing of swept-wing according to any one of claims 1-6, characterized in that, Includes the following steps: Step 1: During the flight of the aircraft, real-time detection is performed to check whether there are supercooled water droplets in the incoming flow and whether the swept wing surface is icy. If no supercooled water droplets are detected in the incoming flow and the swept wing surface is not icy, then proceed to Step 2. If supercooled water droplets are detected in the incoming flow and the swept wing surface is not icy, proceed to step 3; if icing is detected on the swept wing surface, proceed to step 4 regardless of whether supercooled water droplets are present in the incoming flow. Step 2: At this point, no anti-icing operation is required; keep the plasma power supply off. Step 3: For cases with supercooled water droplets but no ice formation, anti-icing operation is required. The specific method is as follows: control the plasma power supply and apply a 13 kV, 9 kHz sinusoidal alternating current to the plasma exciter, so that the plasma exciter works according to the anti-icing parameters. Through the ionization heat effect and aerodynamic effect of plasma excitation, ice formation is prevented after the supercooled water droplets collide, thus achieving the anti-icing effect on the swept wing surface. Step 4: In the case of icing, de-icing operation is required. The specific method is as follows: control the plasma power supply and apply a 13 kV, 9 kHz sinusoidal alternating current to the plasma exciter, so that the plasma exciter works according to the de-icing parameters. Through the ionization heat effect and aerodynamic effect of plasma excitation, the ice layer on the swept wing surface melts, splits and falls off rapidly, so as to achieve the effect of de-icing the swept wing surface. Among them: when the plasma exciter performs steps 3 and 4, by designing the position and direction of the plasma exciter on the surface of the swept wing, after the plasma exciter is turned on, the surrounding air is ionized under the strong electric field of the exposed electrode (2) to generate plasma. The plasma is driven by the electric field to generate flow, thereby generating aerodynamic effect, thus injecting energy into the boundary layer of the swept wing airfoil, delaying the flow separation on the surface of the swept wing, and improving the aerodynamic performance of the swept wing.

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