An integrated device and method for anti-icing, de-icing, and icing detection of helicopter rotors.

Abstract

This invention provides an integrated device and method for anti-icing, de-icing, and icing detection of helicopter rotors. The device includes a sinusoidal AC plasma exciter, a high-voltage sinusoidal AC power supply, an anti-icing controller, a temperature sensor, and a pressure sensor. The sinusoidal AC plasma exciter is arranged in the protective area of ​​the rotor leading edge. The sinusoidal AC plasma exciter includes an insulating dielectric layer, a first exposed electrode, a second exposed electrode, and a buried electrode. This invention proposes an integrated device and method for anti-icing, de-icing, and icing detection of helicopter rotors, simultaneously achieving anti-icing, de-icing, icing detection, and flow control of the rotor with a single system, thereby effectively reducing energy consumption and overall cost, and improving system efficiency and reliability.

Description

Technical Field

[0001] This invention belongs to the field of anti-icing / de-icing technology for helicopter rotors, specifically relating to an integrated device and method for anti-icing, de-icing, and icing detection of helicopter rotors. Background Technology

[0002] Helicopters typically fly below 6000m, where they frequently encounter severe weather conditions such as rain, snow, and frost. When helicopter rotors encounter clouds containing supercooled water droplets, icing can occur on the windward surface of the rotor. The helicopter rotor serves as both a lift generator and a primary control component. Icing on the rotor surface disrupts its aerodynamic shape, increases drag, and reduces lift. Most seriously, irregular icing on the rotor surface severely affects the aircraft's maneuverability and stability, thus directly threatening helicopter safety.

[0003] Due to differences in flight speed and weather conditions, icing during flight can be classified into three types: (1) frost ice; (2) clear ice; and (3) mixed ice. Frost ice generally forms below -10℃, has a regular shape, is opaque, and often contains air bubbles, resulting in low density, fragility, and easy removal, thus having a relatively small impact on flight safety. Clear ice generally forms between 0℃ and -10℃. Clear ice is smoother and harder than frost ice, making it difficult to detach, and usually forms irregularly shaped "corner ice," which has a significant impact on flight safety. Because aircraft encounter different types and degrees of weather and icing conditions during flight, a combination of frost ice and clear ice—mixed ice—often forms. This is the most common type of icing during actual flight, forming quickly, with a thicker layer, and is difficult to detach from the surface. Its hazards are no less than those of clear ice.

[0004] De-icing is challenging for airfoils (such as rotor blades) of rotorcraft such as helicopters. Existing de-icing solutions for rotorcraft include electrothermal ice protection systems, which consist of heaters mounted on the leading edge of the rotor. The goal of the heaters in the de-icing process is to rapidly raise the temperature of the ice-rotor interface above 0°C, typically seeking above 10°C; the heating process is controlled to melt only the ice interface, using the centrifugal force inherent in the rotating rotor to remove the ice from the surface. This approach has the following drawbacks: (1) If the heaters apply heat too slowly, the rotor surface will not be completely freed from the ice because the centrifugal force of the rotor is not large enough to overcome the bond between the ice and the rotor. Localized melting of the ice occurs on the rotor surface, and liquid water flows to the tail of the blades and refreezes. However, backflow and refreezing on the rotor blades has the following drawbacks: the refreezing location is usually in an area that significantly reduces airfoil performance, and its location is usually outside the area affected by the heaters, thus reducing airfoil performance. (2) The system requires a generator to apply electrical energy to one or more components of the rotor blades, and the large energy consumption becomes a cost burden. (3) In order to reduce peak power requirements, the heater cladding is divided into multiple blocks. However, there cannot be any unheated areas between the blocks, which increases the cost of purchasing and manufacturing the rotor blades.

[0005] Therefore, how to effectively perform anti-icing and de-icing operations on helicopter rotors, while simultaneously reducing energy consumption and overall costs, is an urgent problem that needs to be solved. Summary of the Invention

[0006] To address the shortcomings of existing technologies, this invention provides an integrated device and method for anti-icing, de-icing, and icing detection of helicopter rotors, which can effectively solve the aforementioned problems.

[0007] To achieve the above objectives, the present invention adopts the following technical solution:

[0008] This invention provides an integrated device for anti-icing and de-icing detection of helicopter rotors, including a sinusoidal AC plasma exciter (2), a high-voltage sinusoidal AC power supply, an anti-icing controller, a temperature sensor, and a pressure sensor;

[0009] The sinusoidal alternating plasma exciter (2) is arranged in the protective area of ​​the leading edge of the rotor (1); the sinusoidal alternating plasma exciter (2) includes an insulating dielectric layer (2-1), a first exposed electrode (2-2), a second exposed electrode (2-3), and a buried electrode (2-4); the insulating dielectric layer (2-1) has a thickness of 0.3 mm and is fixed to the surface of the rotor (1); the buried electrode (2-4) with a width of 10 mm and a thickness of 0.03 mm is fixedly arranged at the center of the lower surface of the insulating dielectric layer (2-1). 2-4), and the buried electrode (2-4) is embedded inside the rotor (1), with the upper surface of the buried electrode (2-4) flush with the surface of the rotor (1); the upper surface of the insulating dielectric layer (2-1), and the projection positions of the two sides of the buried electrode (2-4), are each fixedly provided with the first exposed electrode (2-2) and the second exposed electrode (2-3); the width of the first exposed electrode (2-2) and the thickness of the second exposed electrode (2-3) are 3mm and 0.03mm respectively;

[0010] The first exposed electrode (2-2) and the second exposed electrode (2-3) are connected to the low-voltage end of the high-voltage sinusoidal AC power supply; the buried electrode (2-4) is connected to the high-voltage end of the high-voltage sinusoidal AC power supply.

[0011] The temperature sensor and the pressure sensor are evenly arranged on the surface of the rotor (1), and the interval between two adjacent sensors is 10% of the chord length of the rotor (1) profile.

[0012] The temperature sensor and the pressure sensor are connected to the input terminal of the anti-icing controller; the output terminal of the anti-icing controller is connected to the high-voltage sinusoidal AC power supply.

[0013] Preferably, the sinusoidal AC plasma exciter (2) is a sinusoidal AC surface dielectric barrier discharge plasma exciter.

[0014] Preferably, a plurality of sinusoidal alternating plasma exciters (2) are arranged in parallel at equal intervals in the protective area of ​​the leading edge of the rotor (1).

[0015] Preferably, the spacing between two adjacent sinusoidal alternating plasma exciters (2) is 18 mm.

[0016] The present invention also provides a method for the integrated anti-icing and de-icing detection device for helicopter rotors, comprising the following steps:

[0017] Step S1: Determine the structural parameters of the insulating dielectric layer (2-1), the first exposed electrode (2-2), the second exposed electrode (2-3), and the buried electrode (2-4), including: the thickness of the insulating dielectric layer (2-1), the width and thickness of the buried electrode (2-4), and the width and thickness of the first exposed electrode (2-2) and the second exposed electrode (2-3);

[0018] Step S2: During helicopter flight, temperature and pressure sensors detect the temperature and pressure at the installation location in real time and transmit the detected temperature and pressure to the anti-icing controller in real time.

[0019] In step S3, the anti-icing controller adjusts and controls the power parameters of the high-voltage sinusoidal AC power supply based on the real-time detected temperature and pressure. By comprehensively utilizing the ionization heat effect and aerodynamic effect generated by the sinusoidal AC plasma exciter (2), it can perform anti-icing operation on the protective area of ​​the rotor (1) leading edge. At the same time, when the helicopter in forward flight experiences dynamic stall, the aerodynamic effect generated by the sinusoidal AC plasma exciter (2) is used to improve the dynamic stall phenomenon.

[0020] Preferably, in step S3, the ionization thermal effect and aerodynamic effect generated by the sinusoidal AC plasma exciter (2) are specifically as follows:

[0021] Ionization heat effect:

[0022] The first exposed electrode (2-2) and the buried electrode (2-4) are respectively connected to the low-voltage end and the high-voltage end of the high-voltage sinusoidal AC power supply. By applying a high potential difference between them, the air around the first exposed electrode (2-2) is ionized, thereby forming a uniform glow discharge plasma on the surface of the insulating dielectric layer (2-1). Similarly, the second exposed electrode (2-3) and the buried electrode (2-4) are respectively connected to the low-voltage end and the high-voltage end of the high-voltage sinusoidal AC power supply. By applying a high potential difference between them, the air around the second exposed electrode (2-3) is ionized, thereby forming a uniform glow discharge plasma on the surface of the insulating dielectric layer (2-1).

[0023] Therefore, a large amount of heat is generated in the region between the first exposed electrode (2-2), the second exposed electrode (2-3), and the buried electrode (2-4), thereby producing an ionization heat effect;

[0024] Aerodynamic effects:

[0025] The first exposed electrode (2-2) and the buried electrode (2-4) are respectively connected to the low-voltage end and the high-voltage end of the high-voltage sinusoidal AC power supply. By applying a high potential difference between them, the air around the first exposed electrode (2-2) is triggered to ionize. The charged ions generated in this process collide with neutral particles, triggering airflow near the surface. This airflow flows from the first exposed electrode (2-2) to the buried electrode (2-4).

[0026] Similarly: the second exposed electrode (2-3) and the buried electrode (2-4) are connected to the low-voltage end and the high-voltage end of the high-voltage sinusoidal AC power supply, respectively. By applying a high potential difference between them, the air around the second exposed electrode (2-3) is ionized. The charged ions generated in this process collide with neutral particles, triggering an airflow near the surface. This airflow flows from the second exposed electrode (2-3) to the buried electrode (2-4).

[0027] As the airflow flows from the first exposed electrode (2-2) to the buried electrode (2-4) and from the second exposed electrode (2-3) to the buried electrode (2-4), the two airflows form a convection phenomenon. At the buried electrode (2-4), the two airflows collide and eventually form a vertically upward jet, thus forming an upward jet perpendicular to the wall between the first exposed electrode (2-2) and the second exposed electrode (2-3), thereby generating an aerodynamic effect.

[0028] Preferably, the anti-icing controller adjusts and controls the power parameters of the high-voltage sinusoidal AC power supply based on the real-time detected temperature and pressure. By comprehensively utilizing the ionization heat effect and aerodynamic effect generated by the sinusoidal AC plasma exciter (2), it can perform anti-icing operation on the protective area of ​​the rotor (1) leading edge, specifically:

[0029] In step S3.1, at time t, the temperature sensor senses the temperature change through the change in resistance, detects the temperature T(t) in real time, and transmits it to the anti-icing controller in the form of a voltage signal; the pressure sensor senses the pressure change through the change in capacitance, detects the pressure P(t) in real time, and transmits it to the anti-icing controller in the form of a voltage signal.

[0030] Step S3.2, the anti-icing controller uses formulas (1) and (2) to obtain the spectrum FFT(V) of the temperature signal at time t. Tt ) and the spectrum FFT (V) of the pressure signal Pt ):

[0031]

[0032] in:

[0033] f T The sampling frequency of the temperature sensor;

[0034] f P The sampling frequency for the pressure sensor;

[0035] V T (t) represents the voltage of the temperature sensor at time t, which is calculated using formula (3);

[0036] V P (t) represents the voltage of the pressure sensor at time t, which is calculated using formula (4);

[0037] V T (t)=αT(t)+V T0 (3)

[0038] V P (t)=βP(t)+V P0 (4)

[0039] in:

[0040] α and β are the sensitivity coefficients of the temperature sensor and the pressure sensor, respectively;

[0041] V T0 and V P0 , which are the bias voltages of the temperature sensor and the pressure sensor, respectively;

[0042] Step S3.3, the anti-icing controller performs FFT(V) on the spectrum of the temperature signal at time t. Tt ) and the spectrum FFT (V) of the pressure signal Pt The data is compared with the pre-stored spectrum and mapping table of various anti-icing parameters in the database to determine whether supercooled water droplet impact occurs in the current rotor protection area and whether icing occurs. If icing occurs, the specific icing parameters are obtained, including: icing type and icing thickness.

[0043] If supercooled water droplet impact is detected in the current rotor protection area, proceed to step S3.4;

[0044] If icing is detected in the current rotor protection area, proceed to step S3.5;

[0045] Step S3.4, the anti-icing controller activates the anti-icing mode:

[0046] Specifically, when the detection results show that there is a supercooled water droplet impact in the incoming flow, it indicates that there is a risk of icing. At this time, the anti-icing controller adjusts the parameters of the high-voltage sinusoidal AC power supply to make it operate in anti-icing mode. Through the ionization heat effect and aerodynamic effect generated by the sinusoidal AC plasma exciter (2), the supercooled water droplets are prevented from forming ice after impact, thereby achieving the anti-icing effect on the surface of the rotor (1).

[0047] Step S3.5, the anti-icing controller activates the de-icing mode:

[0048] If there is already ice on the surface of the rotor (1), the anti-icing controller adjusts the parameters of the high-voltage sinusoidal AC power supply to make it operate in the de-icing mode; through the ionization heat effect and aerodynamic effect generated by the sinusoidal AC plasma exciter (2), the ice layer melts, splits and falls off rapidly, achieving the de-icing effect on the surface of the rotor (1).

[0049] Preferably, the aerodynamic effect parameters of the aerodynamic effect generated by the sinusoidal alternating plasma exciter (2) are adjustable, including:

[0050] Step S3-1: Establish the high-voltage AC characteristic equation of the sinusoidal AC plasma exciter (2):

[0051] V exc (t)=V m ·e i(ωt+φ) (5)

[0052] ω=2πf exc (6)

[0053] in:

[0054] V exc (t) is the time-varying excitation voltage of the sinusoidal AC plasma exciter (2), which is a complex number representing the instantaneous voltage value;

[0055] V m It is the amplitude of the excitation voltage, and is the maximum value, representing the maximum amplitude of the excitation voltage;

[0056] φ is the phase angle, in radians, representing the initial phase shift of the high-voltage sinusoidal AC power supply;

[0057] ω is the angular frequency of the high-voltage sinusoidal AC power supply;

[0058] fexc is the frequency of the high-voltage sinusoidal AC power supply;

[0059] Step S3-2, establish the relationship equation between the total induced energy E of the sinusoidal AC plasma exciter (2) and its excitation voltage:

[0060]

[0061] in:

[0062] R is the resistance of the sinusoidal AC plasma exciter (2);

[0063] Step S3-3, establish the equations for the total induced energy E and the induced jet velocity of the sinusoidal AC plasma exciter (2):

[0064]

[0065] in:

[0066] C V The constant-volume specific heat of the exciter is a constant after the structure of the sinusoidal AC plasma exciter (2) is determined;

[0067] ρ is the air density;

[0068] μ is the kinetic viscosity of air;

[0069] u(t) and v(t) are the horizontal and vertical velocity components of the jet induced by the sinusoidal alternating plasma exciter (2) at a certain position in space, respectively.

[0070] and These are the mean values ​​of the horizontal velocity component and the vertical velocity component of the jet induced by the sinusoidal AC plasma exciter (2) at a certain position in space during the calculation period S, respectively.

[0071] u′(t) and v′(t) are the horizontal and vertical pulsating velocity components of the jet induced by the sinusoidal alternating plasma exciter (2) at a certain position in space, respectively.

[0072] and These are the mean values ​​of the horizontal and vertical pulsating velocity components of the jet induced by the sinusoidal AC plasma exciter (2) at a certain position in space during the calculation period S, respectively.

[0073] P(t) represents the pressure detected by the pressure sensors at each location at time t.

[0074] T(t) represents the temperature detected by the temperature sensors at each location at time t.

[0075] x and y represent the longitude and latitude coordinates of the sinusoidal alternating plasma exciter (2) induced by the jet at a certain position in space;

[0076] Steps S3-4, therefore, by adjusting the frequency f of the high-voltage sinusoidal AC power supply... exc By adjusting the phase angle φ, the total energy E induced by the sinusoidal AC plasma exciter (2) corresponding to the adjusted high-voltage sinusoidal AC power supply can be obtained through formulas (5), (6) and (7).

[0077] Based on the pressure P(t) detected by the pressure sensors at each location at time t, and the temperature T(t) detected by the temperature sensors at each location at time t, combined with the total energy E induced by the sinusoidal AC plasma exciter (2), and by solving the equations (8), (9), (10) and (11), the horizontal velocity component u(t) and vertical velocity component v(t) of the jet induced by the sinusoidal AC plasma exciter (2) at a certain location in space can be obtained.

[0078] Therefore, by adjusting the frequency f of the high-voltage sinusoidal AC power supply exc By adjusting the phase angle φ, the horizontal velocity component u(t) and vertical velocity component v(t) of the induced jet at a certain position in space can be directly adjusted;

[0079] Therefore, when a helicopter experiences dynamic stall while in flight, the frequency f of the high-voltage sinusoidal AC power supply can be adjusted. exc Adjust the phase angle φ to adjust the induced jet of the sinusoidal alternating plasma exciter (2), change the velocity value and velocity distribution of the induced jet perpendicular to the wall surface and upward generated by the sinusoidal alternating plasma exciter (2), that is: adjust the aerodynamic effect generated by it, thereby alleviating the dynamic stall state of the rotor and improving the aerodynamic performance of the rotor.

[0080] Furthermore, by adjusting the generated aerodynamic effect, the mixing efficiency of ionization heat and incoming flow is improved under the action of airflow effect, thereby enhancing the thermal effect and improving energy utilization efficiency.

[0081] The integrated device and method for anti-icing, de-icing, and icing detection of helicopter rotors provided by this invention have the following advantages:

[0082] This invention proposes an integrated device and method for anti-icing, de-icing, and icing detection of helicopter rotors. By using a single system, anti-icing, de-icing, icing detection, and flow control of the rotor can be achieved simultaneously, thereby effectively reducing energy consumption and overall cost, and improving system efficiency and reliability. Attached Figure Description

[0083] Figure 1 A perspective view of the arrangement position of the sinusoidal alternating plasma exciter on the rotor surface in the integrated anti-icing and de-icing detection device for helicopter rotors provided by the present invention.

[0084] Figure 2 A schematic cross-sectional view of the arrangement position of the sinusoidal alternating plasma exciter on the rotor surface provided by the present invention;

[0085] Figure 3 A top view schematic diagram of the arrangement position of the sinusoidal alternating plasma exciter on the rotor surface provided by the present invention;

[0086] Figure 4 A cross-sectional view of the arrangement position of the sinusoidal alternating plasma exciter on the rotor surface provided by the present invention;

[0087] Figure 5 The schematic diagram of the integrated anti-icing and icing detection device for helicopter rotors provided by the present invention.

[0088] Explanation of reference numerals in the attached figures:

[0089] 1. Rotor; 2. Sinusoidal AC plasma exciter; 2-1. Insulating dielectric layer; 2-2. First exposed electrode; 2-3. Second exposed electrode; 2-4. Buried electrode. Detailed Implementation

[0090] 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.

[0091] Currently, helicopter rotor de-icing mainly relies on electrothermal and hot gas methods, resulting in significant energy consumption and a substantial cost burden. To address this issue, this invention proposes an integrated device and method for helicopter rotor de-icing and icing detection. This system simultaneously achieves rotor de-icing, icing detection, and flow control, effectively reducing energy consumption and overall cost while improving system efficiency and reliability.

[0092] Specifically, this invention proposes an integrated device and method for anti-icing, de-icing, and icing detection of helicopter rotors, comprising a sinusoidal AC plasma power supply, a sinusoidal AC surface dielectric barrier discharge plasma exciter, an anti-icing controller, a temperature sensor, and a pressure sensor. Its continuous AC plasma exciter design employs a layout of two exposed electrodes and one buried electrode, capable of generating a large amount of heat and a volumetric force jet perpendicular to the wall surface during operation. With the synergistic action of the temperature sensor, pressure sensor, and anti-icing controller, the device achieves multiple functions of rotor anti-icing / de-icing, icing detection, and flow control. Compared to traditional technologies, this invention effectively solves problems such as high energy consumption, complex structure, and high maintenance costs. Furthermore, by arranging the plasma power supply externally to the rotor, the internal structural design is simplified, thereby reducing manufacturing and maintenance costs.

[0093] This device has the advantages of small size, light weight, low power consumption, fast response and no mechanical parts. In addition, it has a significant thermal effect during operation and is accompanied by volume force jet, thereby realizing helicopter rotor de-icing and flow control.

[0094] This invention provides an integrated device for helicopter rotor anti-icing, de-icing, and icing detection. (See reference...) Figures 1-5 It includes a sinusoidal AC plasma exciter 2, a high-voltage sinusoidal AC power supply, an anti-icing controller, a temperature sensor, and a pressure sensor;

[0095] The sinusoidal AC plasma actuator 2 is arranged in the protective area of ​​the leading edge of the rotor 1. The sinusoidal AC plasma actuator 2 is a sinusoidal AC surface dielectric barrier discharge plasma actuator, including an insulating dielectric layer 2-1, a first exposed electrode 2-2, a second exposed electrode 2-3, and a buried electrode 2-4. The insulating dielectric layer 2-1 is made of polyimide film with a thickness of 0.3 mm and is fixed to the surface of the rotor 1 to provide electrical insulation. The buried electrode 2, with a width of 10 mm and a thickness of 0.03 mm, is fixedly installed at the center of the lower surface of the insulating dielectric layer 2-1. -4, and the buried electrode 2-4 is embedded inside the rotor 1, with the upper surface of the buried electrode 2-4 flush with the surface of the rotor 1; the first exposed electrode 2-2 and the second exposed electrode 2-3 are fixedly disposed on the upper surface of the insulating dielectric layer 2-1, at the projection positions of the two sides of the buried electrode 2-4; the width of the first exposed electrode 2-2 and the second exposed electrode 2-3 is 3mm and the thickness is 0.03mm; the first exposed electrode 2-2 and the second exposed electrode 2-3 are in direct contact with the atmosphere to assist in the generation of plasma.

[0096] The first exposed electrode 2-2, the second exposed electrode 2-3, and the buried electrode 2-4 are all made of copper.

[0097] The first exposed electrode 2-2 and the second exposed electrode 2-3 are connected to the low-voltage end of the high-voltage sinusoidal AC power supply; the buried electrode 2-4 is connected to the high-voltage end of the high-voltage sinusoidal AC power supply.

[0098] The high-voltage sinusoidal AC power supply has peak-to-peak voltage ranging from 5kV to 30kV and a frequency adjustable from 5kHz to 20kHz. The number and length of the sinusoidal AC plasma exciters 2 can be flexibly adjusted according to the size of the protected area; therefore, multiple sinusoidal AC plasma exciters 2 are arranged in parallel at equal intervals in the protected area of ​​the rotor 1, with a spacing of 18mm between adjacent exciters. This design ensures effective plasma generation at the rotor leading edge, combating icing and improving flight safety and efficiency.

[0099] The first exposed electrode 2-2, the second exposed electrode 2-3, and the buried electrode 2-4 are connected to a sinusoidal AC power supply. By applying a high potential difference between them, the air around the exposed electrodes is ionized, thereby forming a uniform glow discharge plasma on the surface of the insulating dielectric layer 2-1. The charged ions generated in this process collide with neutral particles, triggering an airflow near the surface, which flows from the exposed electrode to the buried electrode. The current generates a large amount of heat in the region near the electrodes, and the aerodynamic effect generated by plasma excitation improves the mixing efficiency of ionization heat and incoming flow. Compared to the conventional scheme using only a single exposed electrode, the current design uses a combination configuration of two exposed electrodes and one buried electrode, forming an upward jet perpendicular to the wall between the two exposed electrodes, thereby enhancing the thermal effect and improving energy utilization efficiency.

[0100] The temperature sensor and the pressure sensor are evenly arranged on the surface of the rotor 1, and the interval between two adjacent sensors is 10% of the chord length of the rotor 1.

[0101] The temperature sensor and the pressure sensor are connected to the input terminal of the anti-icing controller; the output terminal of the anti-icing controller is connected to the high-voltage sinusoidal AC power supply.

[0102] The present invention also provides a method for the integrated anti-icing and de-icing detection device for helicopter rotors, comprising the following steps:

[0103] Step S1: Determine the structural parameters of the insulating dielectric layer 2-1, the first exposed electrode 2-2, the second exposed electrode 2-3, and the buried electrode 2-4, including: the thickness of the insulating dielectric layer 2-1, the width and thickness of the buried electrode 2-4, and the width and thickness of the first exposed electrode 2-2 and the second exposed electrode 2-3.

[0104] Step S2: During helicopter flight, temperature and pressure sensors detect the temperature and pressure at the installation location in real time and transmit the detected temperature and pressure to the anti-icing controller in real time.

[0105] In step S3, the anti-icing controller adjusts and controls the power parameters of the high-voltage sinusoidal AC power supply based on the real-time detected temperature and pressure. By comprehensively utilizing the ionization heat effect and aerodynamic effect generated by the sinusoidal AC plasma exciter 2, it can perform anti-icing operation on the protective area of ​​the leading edge of the rotor 1. At the same time, when the helicopter experiences dynamic stall in forward flight, the aerodynamic effect generated by the sinusoidal AC plasma exciter 2 is used to improve the dynamic stall phenomenon.

[0106] In this invention, the ionization thermal effect and aerodynamic effect generated by the sinusoidal AC plasma exciter 2 are specifically as follows:

[0107] Ionization heat effect:

[0108] The first exposed electrode 2-2 and the buried electrode 2-4 are respectively connected to the low-voltage end and the high-voltage end of the high-voltage sinusoidal AC power supply. By applying a high potential difference between them, the air around the first exposed electrode 2-2 is ionized, thereby forming a uniform glow discharge plasma on the surface of the insulating dielectric layer 2-1. Similarly, the second exposed electrode 2-3 and the buried electrode 2-4 are respectively connected to the low-voltage end and the high-voltage end of the high-voltage sinusoidal AC power supply. By applying a high potential difference between them, the air around the second exposed electrode 2-3 is ionized, thereby forming a uniform glow discharge plasma on the surface of the insulating dielectric layer 2-1.

[0109] Therefore, a large amount of heat is generated in the region between the first exposed electrode 2-2, the second exposed electrode 2-3 and the buried electrode 2-4, thereby generating an ionization heat effect;

[0110] Aerodynamic effects:

[0111] The first exposed electrode 2-2 and the buried electrode 2-4 are respectively connected to the low-voltage end and the high-voltage end of the high-voltage sinusoidal AC power supply. By applying a high potential difference between them, the air around the first exposed electrode 2-2 is triggered to ionize. The charged ions generated in this process collide with neutral particles, causing airflow near the surface. This airflow flows from the first exposed electrode 2-2 to the buried electrode 2-4.

[0112] Similarly: the second exposed electrode 2-3 and the buried electrode 2-4 are respectively connected to the low-voltage end and the high-voltage end of the high-voltage sinusoidal AC power supply. By applying a high potential difference between them, the air around the second exposed electrode 2-3 is triggered to ionize. The charged ions generated in this process collide with neutral particles, causing airflow near the surface. This airflow flows from the second exposed electrode 2-3 to the buried electrode 2-4.

[0113] As the airflow flows from the first exposed electrode 2-2 to the buried electrode 2-4 and from the second exposed electrode 2-3 to the buried electrode 2-4 respectively, the two airflows form a convection phenomenon. At the buried electrode 2-4, the two airflows collide and eventually form a vertically upward jet, thus forming an upward jet perpendicular to the wall between the first exposed electrode 2-2 and the second exposed electrode 2-3, thereby generating an aerodynamic effect.

[0114] As a specific implementation method, the anti-icing controller adjusts and controls the power parameters of the high-voltage sinusoidal AC power supply based on the real-time detected temperature and pressure. By comprehensively utilizing the ionization heat effect and aerodynamic effect generated by the sinusoidal AC plasma exciter 2, it can perform anti-icing and de-icing operations on the protective area of ​​the leading edge of the rotor 1. Specifically:

[0115] In step S3.1, at time t, the temperature sensor senses the temperature change through the change in resistance, detects the temperature T(t) in real time, and transmits it to the anti-icing controller in the form of a voltage signal; the pressure sensor senses the pressure change through the change in capacitance, detects the pressure P(t) in real time, and transmits it to the anti-icing controller in the form of a voltage signal.

[0116] Step S3.2, the anti-icing controller uses formulas (1) and (2) to obtain the spectrum FFT(V) of the temperature signal at time t. Tt ) and the spectrum FFT (V) of the pressure signal Pt ):

[0117]

[0118] in:

[0119] f T The sampling frequency of the temperature sensor;

[0120] f P The sampling frequency for the pressure sensor;

[0121] V T (t) represents the voltage of the temperature sensor at time t, which is calculated using formula (3);

[0122] V P (t) represents the voltage of the pressure sensor at time t, which is calculated using formula (4);

[0123] V T (t)=αT(t)+V T0 (3)

[0124] V P (t)=βP(t)+V P0 (4)

[0125] in:

[0126] α and β are the sensitivity coefficients of the temperature sensor and the pressure sensor, respectively;

[0127] V T0 and V P0 , which are the bias voltages of the temperature sensor and the pressure sensor, respectively;

[0128] Step S3.3, the anti-icing controller performs FFT(V) on the spectrum of the temperature signal at time t. Tt ) and the spectrum FFT (V) of the pressure signal PtThe data is compared with the pre-stored spectrum and mapping table of various anti-icing parameters in the database to determine whether supercooled water droplet impact occurs in the current rotor protection area and whether icing occurs. If icing occurs, the specific icing parameters are obtained, including: icing type and icing thickness.

[0129] If supercooled water droplet impact is detected in the current rotor protection area, proceed to step S3.4;

[0130] If icing is detected in the current rotor protection area, proceed to step S3.5;

[0131] Step S3.4, the anti-icing controller activates the anti-icing mode:

[0132] Specifically, when the detection results show that there is supercooled water droplet impact in the incoming flow, it indicates that there is a risk of icing. At this time, the anti-icing controller adjusts the parameters of the high-voltage sinusoidal AC power supply to make it operate in anti-icing mode. Through the ionization heat effect and aerodynamic effect generated by the sinusoidal AC plasma exciter 2, the supercooled water droplets are prevented from forming ice after impact, thereby achieving the anti-icing effect on the surface of rotor 1.

[0133] Step S3.5, the anti-icing controller activates the de-icing mode:

[0134] If there is already ice on the surface of rotor 1, the anti-icing controller adjusts the parameters of the high-voltage sinusoidal AC power supply to make it operate in de-icing mode; through the ionization heat effect and aerodynamic effect generated by the sinusoidal AC plasma exciter 2, the ice layer melts, breaks apart and falls off rapidly, achieving the de-icing effect on the surface of rotor 1.

[0135] In this invention, the aerodynamic effect parameters of the aerodynamic effect generated by the sinusoidal AC plasma exciter 2 are adjustable, including:

[0136] Step S3-1: Establish the high-voltage AC characteristic equation of the sinusoidal AC plasma exciter 2:

[0137] V exc (t)=V m ·e i(ωt+φ) (5)

[0138] ω=2πf exc (6)

[0139] in:

[0140] V exc (t) represents the time-varying excitation voltage of the sinusoidal AC plasma exciter 2, which is a complex number representing the instantaneous voltage value.

[0141] V mIt is the amplitude of the excitation voltage, and is the maximum value, representing the maximum amplitude of the excitation voltage;

[0142] φ is the phase angle, in radians, representing the initial phase shift of the high-voltage sinusoidal AC power supply;

[0143] ω is the angular frequency of the high-voltage sinusoidal AC power supply;

[0144] fexc is the frequency of the high-voltage sinusoidal AC power supply;

[0145] Step S3-2, establish the relationship equation between the total induced energy E of the sinusoidal AC plasma exciter 2 and its excitation voltage:

[0146]

[0147] in:

[0148] R is the resistance of the sinusoidal AC plasma exciter 2;

[0149] Step S3-3: Establish the equations for the total induced energy E and the induced jet velocity of the sinusoidal AC plasma exciter 2:

[0150]

[0151]

[0152] in:

[0153] C V The constant-volume specific heat of the exciter is a constant after the structure of the sinusoidal AC plasma exciter 2 is determined.

[0154] ρ is the air density;

[0155] μ is the kinetic viscosity of air;

[0156] u(t) and v(t) are the horizontal and vertical velocity components of the jet induced by the sinusoidal AC plasma exciter 2 at a certain position in space, respectively.

[0157] and These are the mean values ​​of the horizontal velocity component and the mean value of the vertical velocity component of the jet induced by the sinusoidal AC plasma exciter 2 at a certain position in space during the calculation period S, respectively.

[0158] u′(t) and v′(t) are the horizontal and vertical pulsating velocity components of the jet induced by the sinusoidal AC plasma exciter 2 at a certain position in space, respectively.

[0159] and These are the mean values ​​of the horizontal and vertical pulsating velocity components of the jet induced by the sinusoidal AC plasma exciter 2 at a certain position in space during the calculation period S, respectively.

[0160] P(t) represents the pressure detected by the pressure sensors at each location at time t.

[0161] T(t) represents the temperature detected by the temperature sensors at each location at time t.

[0162] x and y represent the longitude and latitude coordinates of the jet induced by the sinusoidal alternating plasma exciter 2 at a certain position in space;

[0163] Steps S3-4, therefore, by adjusting the frequency f of the high-voltage sinusoidal AC power supply... exc By adjusting the phase angle φ, the total energy E induced by the sinusoidal AC plasma exciter 2 corresponding to the adjusted high-voltage sinusoidal AC power supply can be obtained through formulas (5), (6) and (7).

[0164] Based on the pressure P(t) detected by the pressure sensors at each location at time t, and the temperature T(t) detected by the temperature sensors at each location at time t, combined with the total energy E induced by the sinusoidal AC plasma exciter 2, and by solving the equations (8), (9), (10) and (11), the horizontal velocity component u(t) and vertical velocity component v(t) of the jet induced by the sinusoidal AC plasma exciter 2 at a certain location in space can be obtained.

[0165] Therefore, by adjusting the frequency f of the high-voltage sinusoidal AC power supply exc By adjusting the phase angle φ, the horizontal velocity component u(t) and vertical velocity component v(t) of the induced jet at a certain position in space can be directly adjusted;

[0166] Therefore, when a helicopter experiences dynamic stall while in flight, the frequency f of the high-voltage sinusoidal AC power supply can be adjusted. exc The phase angle φ is adjusted to regulate the induced jet of the sinusoidal AC plasma exciter 2, thereby changing the velocity value and velocity distribution of the induced jet generated by the sinusoidal AC plasma exciter 2 perpendicular to the wall and upward. In other words, the aerodynamic effect generated by it is adjusted to alleviate the dynamic stall state of the rotor and improve the aerodynamic performance of the rotor.

[0167] Furthermore, by adjusting the generated aerodynamic effect, the mixing efficiency of ionization heat and incoming flow is improved under the action of airflow effect, thereby enhancing the thermal effect and improving energy utilization efficiency.

[0168] The integrated device and method for helicopter rotor anti-icing, de-icing, and icing detection provided by this invention has the following characteristics:

[0169] (1) The sinusoidal AC plasma actuator 2 adopts a unique structural design. The thickness of the insulating dielectric layer 2-1 is 0.3 mm. A buried electrode 2-4 with a width of 10 mm and a thickness of 0.03 mm is located on the lower surface, while two exposed electrodes with a width of 3 mm and a thickness of 0.03 mm are provided on the upper surface. The exposed electrodes are respectively arranged at the projected positions of the edges of the buried electrodes and are connected to the low-voltage and high-voltage ends of the high-voltage sinusoidal AC power supply. This high-voltage sinusoidal AC power supply provides a high-voltage AC current with a peak voltage of 5 kV to 30 kV and a frequency range of 5 kHz to 20 kHz. Through this structure, a uniform glow discharge plasma is formed on the upper surface of the insulating dielectric layer 2-1, generating an upward airflow perpendicular to the wall surface, bringing a large amount of heat. The sinusoidal AC plasma actuator 2 exhibits excellent performance in icing detection and de-icing processes. The number and length of the sinusoidal AC plasma actuator 2 can be flexibly adjusted according to the actual size of the protected area. The advantages of this system include small size, light weight, low power consumption, fast response, and high-frequency operation, and it has no mechanical parts. It only requires exposed electrodes, buried electrodes 2-4 and insulating dielectric layer 2-1 on the rotor surface to achieve anti-icing function, without the need for complex internal heating devices, thus greatly reducing manufacturing and maintenance costs.

[0170] (2) The device integrates a high-frequency temperature sensor and a pressure sensor, which can continuously monitor changes in physical quantities such as temperature and pressure on the rotor blades. These changes in physical quantities are converted into electrical signals and transmitted to the anti-icing controller. The temperature sensor senses temperature changes through changes in resistance, while the pressure sensor senses pressure changes through changes in capacitance.

[0171] The anti-icing controller analyzes these electrical signals, calculating their average value, root mean square, and other statistical characteristics, and identifies features such as sudden rises and falls in the signal waveform. These analysis results are then compared with a built-in database to determine whether supercooled water droplets are impacting the rotor surface, whether ice accumulation exists, and the type and thickness of the ice. Based on this analysis, the anti-icing controller can intelligently adjust the electrical parameters of the sinusoidal AC plasma exciter 2 to achieve optimal anti-icing performance with minimal power consumption. This technical solution not only improves the accuracy of icing detection but also optimizes energy efficiency and safety during the anti-icing process, ensuring reliable rotor operation in complex environments.

[0172] (3) It has the ability to effectively cope with different icing risks:

[0173] When icing detection results indicate the presence of supercooled water droplet impacts in the incoming flow, it signifies a risk of icing. In this case, the anti-icing controller activates the sinusoidal AC plasma exciter 2, causing it to operate according to specific anti-icing parameters. Through the ionization thermal and aerodynamic effects of plasma excitation, the supercooled water droplets effectively prevent icing after impact, thus achieving an anti-icing effect on the rotor surface. If a certain amount of ice already exists on the rotor surface, the system can also use the ionization thermal and aerodynamic effects of plasma excitation to rapidly melt, break up, and detach the ice layer, achieving de-icing. This dual function ensures the safe and normal operation of the rotor in various humid and cold environments, effectively avoiding performance degradation or safety hazards caused by icing.

[0174] (4) This device utilizes sinusoidal AC surface dielectric barrier discharge plasma aerodynamic excitation to effectively control the dynamic stall phenomenon of helicopter rotors and improve their mean aerodynamic forces. Due to the combined effects of rotor blade pitch, flapping, and periodic pitch, unsteady dynamic stall is prone to occur when the angle of attack is too large. To address this, the device uses pressure sensors to measure the pressure data on the blade surface in real time to determine whether dynamic stall has occurred. Once dynamic stall is detected, the anti-icing controller adjusts the power parameters of the exciter to generate vertically upward volume force jets of varying intensities. Through the aerodynamic effect induced by plasma excitation, a virtual bulge region is formed, increasing the flow velocity on the blade surface and increasing the momentum of the boundary layer. This control mechanism effectively reduces the influence of the adverse pressure gradient on the blade profile, suppresses flow separation, thereby increasing the lift coefficient of the rotor blades and reducing the nose-down moment coefficient. Therefore, this device not only improves the aerodynamic performance of the rotor blades but also significantly alleviates the dynamic stall problem of the rotor, enhancing the flight stability and handling performance of the helicopter.

[0175] The beneficial effects of this invention are:

[0176] (1) The anti-icing and de-icing device of the present invention features a multi-functional integrated design, which uses the same set of equipment to realize detection, anti-icing and de-icing and flow control functions. The integrated design significantly reduces the complexity of the rotor anti-icing and de-icing system and enhances the reliability of the system.

[0177] (2) The optimized actuator layout design of the present invention, compared with the traditional actuator layout, adopts a layout in which two exposed electrodes share a buried electrode, which can generate more heat and volume force jet perpendicular to the wall, significantly improving the efficiency of anti-icing and flow control, and overcoming the problems of high energy consumption and low energy utilization in the traditional method.

[0178] (3) The adjustable anti-icing strategy of the present invention can flexibly adjust the excitation intensity of the plasma exciter by adjusting the voltage and frequency of the sinusoidal AC power supply, so that the anti-icing system can optimize power consumption according to actual meteorological conditions, thereby achieving effective anti-icing effect with optimal parameters in different environments.

[0179] (4) The present invention enhances the aerodynamic performance of the rotor. The sinusoidal AC plasma exciter is not only used for de-icing, but also as a flow control technology. It helps to improve the aerodynamic performance of the rotor blades by adjusting the excitation voltage and pulse frequency, and suppresses the dynamic stall of the rotor.

[0180] (5) This invention has a high energy conversion efficiency. Unlike traditional gas-thermal and electrothermal de-icing technologies, this invention directly heats the rotor wall and utilizes the aerodynamic effect generated by plasma excitation to improve the mixing efficiency of ionization heat and incoming flow. This method not only has a high energy conversion efficiency and can prevent icing at low temperatures, but also avoids thermal damage to the blade composite material.

[0181] 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 method for an integrated anti-icing, de-icing, and icing detection device for helicopter rotors, characterized in that, The integrated device for anti-icing and icing detection of helicopter rotors includes a sinusoidal AC plasma exciter (2), a high-voltage sinusoidal AC power supply, an anti-icing controller, a temperature sensor, and a pressure sensor. The sinusoidal alternating plasma exciter (2) is arranged in the protective area of ​​the leading edge of the rotor (1); the sinusoidal alternating plasma exciter (2) includes an insulating dielectric layer (2-1), a first exposed electrode (2-2), a second exposed electrode (2-3), and a buried electrode (2-4); the insulating dielectric layer (2-1) has a thickness of 0.3 mm and is fixed to the surface of the rotor (1); the buried electrode (2-4) with a width of 10 mm and a thickness of 0.03 mm is fixedly arranged at the center of the lower surface of the insulating dielectric layer (2-1). 2-4), and the buried electrode (2-4) is embedded inside the rotor (1), with the upper surface of the buried electrode (2-4) flush with the surface of the rotor (1); the upper surface of the insulating dielectric layer (2-1), and the projection positions of the two sides of the buried electrode (2-4), are each fixedly provided with the first exposed electrode (2-2) and the second exposed electrode (2-3); the width of the first exposed electrode (2-2) and the thickness of the second exposed electrode (2-3) are 3mm and 0.03mm respectively; The first exposed electrode (2-2) and the second exposed electrode (2-3) are connected to the low-voltage end of the high-voltage sinusoidal AC power supply; the buried electrode (2-4) is connected to the high-voltage end of the high-voltage sinusoidal AC power supply. The temperature sensor and the pressure sensor are evenly arranged on the surface of the rotor (1), and the interval between two adjacent sensors is 10% of the chord length of the rotor (1) profile. The temperature sensor and the pressure sensor are connected to the input terminal of the anti-icing controller; the output terminal of the anti-icing controller is connected to the high-voltage sinusoidal AC power supply. The method for the integrated anti-icing, de-icing, and icing detection device for helicopter rotors includes the following steps: Step S1: Determine the structural parameters of the insulating dielectric layer (2-1), the first exposed electrode (2-2), the second exposed electrode (2-3), and the buried electrode (2-4), including: the thickness of the insulating dielectric layer (2-1), the width and thickness of the buried electrode (2-4), and the width and thickness of the first exposed electrode (2-2) and the second exposed electrode (2-3); Step S2: During helicopter flight, temperature and pressure sensors detect the temperature and pressure at the installation location in real time and transmit the detected temperature and pressure to the anti-icing controller in real time. Step S3: The anti-icing controller adjusts and controls the power parameters of the high-voltage sinusoidal AC power supply based on the real-time detected temperature and pressure. By comprehensively utilizing the ionization heat effect and aerodynamic effect generated by the sinusoidal AC plasma exciter (2), it can perform anti-icing operation on the protective area of ​​the rotor (1) leading edge. At the same time, when the helicopter in forward flight experiences dynamic stall, the aerodynamic effect generated by the sinusoidal AC plasma exciter (2) is used to improve the dynamic stall phenomenon. The anti-icing controller adjusts and controls the power parameters of the high-voltage sinusoidal AC power supply based on the real-time detected temperature and pressure. By comprehensively utilizing the ionization heat effect and aerodynamic effect generated by the sinusoidal AC plasma exciter (2), it can perform anti-icing operation on the protective area of ​​the rotor (1) leading edge, specifically: In step S3.1, at time t, the temperature sensor senses the temperature change through the change in resistance, detects the temperature T(t) in real time, and transmits it to the anti-icing controller in the form of a voltage signal; the pressure sensor senses the pressure change through the change in capacitance, detects the pressure P(t) in real time, and transmits it to the anti-icing controller in the form of a voltage signal. Step S3.2, the anti-icing controller uses formulas (1) and (2) to obtain the spectrum FFT(V) of the temperature signal at time t. Tt ) and the spectrum FFT (V) of the pressure signal Pt ): in: f T The sampling frequency of the temperature sensor; f P The sampling frequency for the pressure sensor; V T (t) represents the voltage of the temperature sensor at time t, which is calculated using formula (3); V P (t) represents the voltage of the pressure sensor at time t, which is calculated using formula (4); V T (t)=αT(t)+V T0 (3) V P (t)=βP(t)+V P0 (4) in: α and β are the sensitivity coefficients of the temperature sensor and the pressure sensor, respectively; V T0 and V P0 , which are the bias voltages of the temperature sensor and the pressure sensor, respectively; Step S3.3, the anti-icing controller performs FFT(V) on the spectrum of the temperature signal at time t. Tt ) and the spectrum FFT (V) of the pressure signal Pt The data is compared with the pre-stored spectrum and mapping table of various anti-icing parameters in the database to determine whether supercooled water droplet impact occurs in the current rotor protection area and whether icing occurs. If icing occurs, the specific icing parameters are obtained, including: icing type and icing thickness. If supercooled water droplet impact is detected in the current rotor protection area, proceed to step S3.4; If icing is detected in the current rotor protection area, proceed to step S3.5; Step S3.4, the anti-icing controller activates the anti-icing mode: Specifically, when the detection results show that there is a supercooled water droplet impact in the incoming flow, it indicates that there is a risk of icing. At this time, the anti-icing controller adjusts the parameters of the high-voltage sinusoidal AC power supply to make it operate in anti-icing mode. Through the ionization heat effect and aerodynamic effect generated by the sinusoidal AC plasma exciter (2), the supercooled water droplets are prevented from forming ice after impact, thereby achieving the anti-icing effect on the surface of the rotor (1). Step S3.5, the anti-icing controller activates the de-icing mode: If there is already ice on the surface of the rotor (1), the anti-icing controller adjusts the parameters of the high-voltage sinusoidal AC power supply to make it operate in the de-icing mode; through the ionization heat effect and aerodynamic effect generated by the sinusoidal AC plasma exciter (2), the ice layer melts, splits and falls off rapidly, achieving the de-icing effect on the surface of the rotor (1).

2. The method for the integrated anti-icing, de-icing, and icing detection device for helicopter rotors according to claim 1, characterized in that, In step S3, the ionization thermal effect and aerodynamic effect generated by the sinusoidal AC plasma exciter (2) are specifically as follows: Ionization heat effect: The first exposed electrode (2-2) and the buried electrode (2-4) are respectively connected to the low-voltage end and the high-voltage end of the high-voltage sinusoidal AC power supply. By applying a high potential difference between them, the air around the first exposed electrode (2-2) is ionized, thereby forming a uniform glow discharge plasma on the surface of the insulating dielectric layer (2-1). Similarly, the second exposed electrode (2-3) and the buried electrode (2-4) are respectively connected to the low-voltage end and the high-voltage end of the high-voltage sinusoidal AC power supply. By applying a high potential difference between them, the air around the second exposed electrode (2-3) is ionized, thereby forming a uniform glow discharge plasma on the surface of the insulating dielectric layer (2-1). Therefore, a large amount of heat is generated in the region between the first exposed electrode (2-2), the second exposed electrode (2-3), and the buried electrode (2-4), thereby producing an ionization heat effect; Aerodynamic effects: The first exposed electrode (2-2) and the buried electrode (2-4) are respectively connected to the low-voltage end and the high-voltage end of the high-voltage sinusoidal AC power supply. By applying a high potential difference between them, the air around the first exposed electrode (2-2) is triggered to ionize. The charged ions generated in this process collide with neutral particles, triggering airflow near the surface. This airflow flows from the first exposed electrode (2-2) to the buried electrode (2-4). Similarly: the second exposed electrode (2-3) and the buried electrode (2-4) are connected to the low-voltage end and the high-voltage end of the high-voltage sinusoidal AC power supply, respectively. By applying a high potential difference between them, the air around the second exposed electrode (2-3) is ionized. The charged ions generated in this process collide with neutral particles, triggering an airflow near the surface. This airflow flows from the second exposed electrode (2-3) to the buried electrode (2-4). As the airflow flows from the first exposed electrode (2-2) to the buried electrode (2-4) and from the second exposed electrode (2-3) to the buried electrode (2-4), the two airflows form a convection phenomenon. At the buried electrode (2-4), the two airflows collide and eventually form a vertically upward jet, thus forming an upward jet perpendicular to the wall between the first exposed electrode (2-2) and the second exposed electrode (2-3), thereby generating an aerodynamic effect.

3. The method for the integrated anti-icing and de-icing detection device for helicopter rotors according to claim 2, characterized in that, The aerodynamic parameters of the aerodynamic effect generated by the sinusoidal alternating plasma exciter (2) are adjustable, including: Step S3-1: Establish the high-voltage AC characteristic equation of the sinusoidal AC plasma exciter (2): V exc (t)=V m ·e i(ωt+φ) (5) ω=2πf exc (6) in: V exc (t) is the time-varying excitation voltage of the sinusoidal AC plasma exciter (2), which is a complex number representing the instantaneous voltage value; V m It is the amplitude of the excitation voltage, and is the maximum value, representing the maximum amplitude of the excitation voltage; φ is the phase angle, in radians, representing the initial phase shift of the high-voltage sinusoidal AC power supply; ω is the angular frequency of the high-voltage sinusoidal AC power supply; fexc is the frequency of the high-voltage sinusoidal AC power supply; Step S3-2, establish the relationship equation between the total induced energy E of the sinusoidal AC plasma exciter (2) and its excitation voltage: in: R is the resistance of the sinusoidal AC plasma exciter (2); Step S3-3, establish the equations for the total induced energy E and the induced jet velocity of the sinusoidal AC plasma exciter (2): in: C V The constant-volume specific heat of the exciter is a constant after the structure of the sinusoidal AC plasma exciter (2) is determined; ρ is the air density; μ is the kinetic viscosity of air; u(t) and v(t) are the horizontal and vertical velocity components of the jet induced by the sinusoidal alternating plasma exciter (2) at a certain position in space, respectively. and These are the mean values ​​of the horizontal velocity component and the vertical velocity component of the jet induced by the sinusoidal AC plasma exciter (2) at a certain position in space during the calculation period S, respectively. u′(t) and v′(t) are the horizontal and vertical pulsating velocity components of the jet induced by the sinusoidal alternating plasma exciter (2) at a certain position in space, respectively. and These are the mean values ​​of the horizontal and vertical pulsating velocity components of the jet induced by the sinusoidal AC plasma exciter (2) at a certain position in space during the calculation period S, respectively. P(t) represents the pressure detected by the pressure sensors at each location at time t. T(t) represents the temperature detected by the temperature sensors at each location at time t. x and y represent the longitude and latitude coordinates of the sinusoidal alternating plasma exciter (2) induced by the jet at a certain position in space; Steps S3-4, therefore, by adjusting the frequency f of the high-voltage sinusoidal AC power supply... exc By adjusting the phase angle φ, the total energy E induced by the sinusoidal AC plasma exciter (2) corresponding to the adjusted high-voltage sinusoidal AC power supply can be obtained through formulas (5), (6) and (7). Based on the pressure P(t) detected by the pressure sensors at each location at time t, and the temperature T(t) detected by the temperature sensors at each location at time t, combined with the total energy E induced by the sinusoidal AC plasma exciter (2), and by solving the equations (8), (9), (10) and (11), the horizontal velocity component u(t) and vertical velocity component v(t) of the jet induced by the sinusoidal AC plasma exciter (2) at a certain location in space can be obtained. Therefore, by adjusting the frequency f of the high-voltage sinusoidal AC power supply exc By adjusting the phase angle φ, the horizontal velocity component u(t) and vertical velocity component v(t) of the induced jet at a certain position in space can be directly adjusted; Therefore, when a helicopter experiences dynamic stall while in flight, the frequency f of the high-voltage sinusoidal AC power supply can be adjusted. exc Adjust the phase angle φ to adjust the induced jet of the sinusoidal alternating plasma exciter (2), change the velocity value and velocity distribution of the induced jet perpendicular to the wall surface and upward generated by the sinusoidal alternating plasma exciter (2), that is: adjust the aerodynamic effect generated by it, thereby alleviating the dynamic stall state of the rotor and improving the aerodynamic performance of the rotor. Furthermore, by adjusting the generated aerodynamic effect, the mixing efficiency of ionization heat and incoming flow is improved under the action of airflow effect, thereby enhancing the thermal effect and improving energy utilization efficiency.

4. The method for the integrated anti-icing, de-icing, and icing detection device for helicopter rotors according to claim 1, characterized in that, The sinusoidal AC plasma exciter (2) is a sinusoidal AC surface dielectric barrier discharge plasma exciter.

5. The method for the integrated anti-icing, de-icing, and icing detection device for helicopter rotors according to claim 1, characterized in that, In the protective area of ​​the leading edge of the rotor (1), a plurality of sinusoidal alternating plasma exciters (2) are arranged in parallel at equal intervals.

6. The method for the integrated anti-icing, de-icing, and icing detection device for helicopter rotors according to claim 5, characterized in that, The distance between two adjacent sinusoidal alternating plasma exciters (2) is 18 mm.

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