Anti-icing, deicing and icing detection integrated device and method for helicopter rotor

Abstract

The invention provides an ice prevention and removal and icing detection integrated device and method for a helicopter rotor. The device comprises a sine alternating current plasma exciter, a high-voltage sine alternating current power supply, an ice prevention and removal controller, a temperature sensor and a pressure sensor. The sine alternating-current plasma exciter is arranged in a protection area of the front edge of the rotor wing; the sine alternating current plasma exciter comprises an insulating dielectric layer, a first bare electrode, a second bare electrode and a buried electrode. According to the anti-icing, deicing and icing detection integrated device and method for the helicopter rotor wing, anti-icing, deicing, icing detection and flow control of the rotor wing are achieved at the same time with the help of one system, so that energy consumption and the overall cost are effectively reduced, and the system efficiency and reliability are improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of helicopter rotor anti-icing / de-icing, and in particular relates to an integrated device and method for helicopter rotor anti-icing / de-icing and ice detection. Background Art

[0002] The flight altitude of helicopters is mostly below 6000m. In this altitude range, they often encounter severe weather such as rain, snow, ice and frost. When the helicopter rotor encounters clouds containing supercooled water droplets, ice will appear on the windward surface of the rotor. The helicopter rotor is not only a lift component, but also undertakes major functions such as control. Ice on the rotor surface will destroy its aerodynamic shape, increase flight resistance, and reduce lift. The most serious thing is that the irregular ice formed on the rotor surface will seriously affect the maneuverability and stability of the aircraft. Therefore, ice on the rotor surface will directly threaten the safety of the helicopter.

[0003] Due to the differences in flight speed and weather conditions, ice formation during flight can be divided into three categories: (1) frost ice; (2) clear ice; and (3) mixed ice. Frost ice is generally formed below -10°C. It has a regular shape and is opaque. It is often accompanied by bubbles, so it has a low density, is fragile and easy to remove, and has little impact on flight safety. Clear ice is generally formed between 0°C and -10°C. Clear ice is smoother and harder than frost ice and is not easy to fall off. It usually forms irregular "corner ice", which has a great impact on flight safety. Since aircraft will encounter different types and degrees of weather and icing conditions during flight, a combination of frost ice and clear ice - mixed ice - is often formed. This is the most common type of ice formation during actual flight. It forms faster, has a thicker ice layer, and is difficult to fall off from the surface. Its harm is no less than that of clear ice.

[0004] De-icing is challenging for the airfoils (e.g., rotor blades) of rotorcraft such as helicopters. Existing de-icing solutions for rotorcraft are electrothermal ice protection systems that include heaters mounted on the leading edge of the rotor. For the de-icing process, the goal of the heater is to quickly raise the temperature of the interface between the ice and the rotor to above 0°C, usually seeking to be greater than 10°C; the heating process is controlled to melt only the interface of the ice, and the centrifugal force inherent in the rotating rotor is used to remove the ice from the surface. This approach has the following shortcomings: (1) If the heater applies heat too slowly, the rotor surface will not completely release the ice because the centrifugal force of the rotor is not large enough to overcome the combination of ice and the rotor. The ice on the rotor surface will partially melt, and the liquid water will flow to the tail of the blade and refreeze. However, backflow and refreezing on the rotor blade have the following hazards: the refreezing location is usually in an area that significantly reduces the airfoil performance, and its location is usually outside the area affected by the heater, thereby reducing the airfoil performance. (2) The system requires a generator to apply electrical energy to one or more components of the rotor blade, and the large amount of energy consumption becomes a cost burden. (3) In order to reduce the peak power demand, the heater blanket is divided into multiple blocks. However, the heater cannot have any unheated areas between blocks, thereby increasing the cost of purchasing and manufacturing the rotor blade.

[0005] Therefore, how to effectively perform anti-icing and de-icing operations on helicopter rotors, while effectively reducing energy consumption and overall costs, is an issue that urgently needs to be addressed. Summary of the invention

[0006] In view of the defects in the prior art, the present invention provides an integrated device and method for helicopter rotor deicing and ice detection, which can effectively solve the above problems.

[0007] In order to achieve the above object, the present invention adopts the following technical solution:

[0008] The present invention provides an integrated device for helicopter rotor deicing and ice detection, comprising a sinusoidal AC plasma actuator (2), a high-voltage sinusoidal AC power supply, an deicing controller, a temperature sensor and a pressure sensor;

[0009] The sinusoidal AC plasma actuator (2) is arranged in a protective area at the leading edge of the rotor (1); the sinusoidal AC plasma actuator (2) comprises 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 0.3 mm thick and is fixed to the surface of the rotor (1); the buried electrode (2-4) having 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 in the interior of the rotor (1), and the upper surface of the buried electrode (2-4) is flush with the surface of the rotor (1); the upper surface of the insulating medium layer (2-1), and located at the projection position of the edges on both sides of the buried electrode (2-4), the first exposed electrode (2-2) and the second exposed electrode (2-3) are fixedly arranged; the width of the first exposed electrode (2-2) and the second exposed electrode (2-3) are 3 mm, and the thickness is 0.03 mm;

[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) section;

[0012] The temperature sensor and the pressure sensor are connected to the input end of the anti-icing controller; the output end 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 the sinusoidal AC plasma actuators (2) are arranged in parallel at equal intervals in the protection area of ​​the leading edge of the rotor (1).

[0015] Preferably, the distance between two adjacent sinusoidal AC plasma actuators (2) is 18 mm.

[0016] The present invention also provides a method for the integrated device for helicopter rotor deicing and ice detection, comprising the following steps:

[0017] Step S1, determining 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), the width and thickness of the first exposed electrode (2-2) and the second exposed electrode (2-3);

[0018] Step S2, during the flight of the helicopter, the temperature sensor and the pressure sensor detect the temperature and pressure of the installation position in real time, and transmit the detected temperature and pressure to the anti-icing controller in real time;

[0019] Step S3, the anti-icing controller adjusts and controls the power supply parameters of the high-voltage sinusoidal AC power supply according to the temperature and pressure detected in real time, and comprehensively utilizes the ionization heat effect and aerodynamic effect generated by the sinusoidal AC plasma actuator (2) to perform anti-icing operations on the protection area at the leading edge of the rotor (1); at the same time, when a helicopter in a forward flight state experiences a dynamic stall phenomenon, the aerodynamic effect generated by the sinusoidal AC plasma actuator (2) is utilized to improve the dynamic stall phenomenon.

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

[0021] Ionization heating 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, and a high potential difference is applied between the two to trigger the air around the first exposed electrode (2-2) to be 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, and a high potential difference is applied between the two to trigger the air around the second exposed electrode (2-3) to be 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 area 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;

[0024] Aerodynamic effect:

[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, and a high potential difference is applied between the two to trigger the ionization of the air around the first exposed electrode (2-2). The charged ions generated in this process collide with neutral particles, triggering an airflow near the surface, and the 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, and a high potential difference is applied between the two to trigger the ionization of the air around the second exposed electrode (2-3). The charged ions generated in this process collide with neutral particles, triggering an airflow near the surface, and the airflow flows from the second exposed electrode (2-3) to the buried electrode (2-4);

[0027] Since the airflows flow 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 position of the buried electrode (2-4), the two airflows impact and eventually form a vertical upward jet, thereby 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 supply parameters of the high-voltage sinusoidal AC power supply according to the temperature and pressure detected in real time, and comprehensively utilizes the ionization heat effect and aerodynamic effect generated by the sinusoidal AC plasma actuator (2) to perform an anti-icing operation on the protection area at the leading edge of the rotor (1), specifically:

[0029] Step S3.1, at time t, the temperature sensor senses the temperature change through the change of 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 of 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 formula (1) and formula (2) to obtain the frequency spectrum FFT (V Tt ) and the frequency spectrum FFT of the pressure signal (V Pt ):

[0031]

[0032] in:

[0033] f T Collect frequency for temperature sensor;

[0034] f P Acquisition frequency for pressure sensor;

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

[0036] V P (t) represents the voltage of the pressure sensor at time t, calculated by 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 pressure sensor, respectively;

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

[0042] Step S3.3, the anti-icing controller calculates the frequency spectrum FFT (V Tt ) and the frequency spectrum FFT of the pressure signal (V Pt ), and compare it with the mapping table of the frequency spectrum and various anti-icing phenomenon parameters pre-stored in the database, so as to obtain whether there is a phenomenon of supercooled water droplet impact in the current rotor protection area, and whether icing occurs. If icing occurs, obtain specific icing parameters, including: ice accumulation type and ice accumulation thickness;

[0043] If it is detected that supercooled water droplets impact the current rotor protection area, execute step S3.4;

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

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

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

[0047] Step S3.5, the anti-icing controller starts the deicing mode:

[0048] If ice has already accumulated on the surface of the rotor (1), the anti-deicing controller adjusts the parameters of the high-voltage sinusoidal AC power supply so that it operates in a deicing mode; the ionization heat effect and aerodynamic effect generated by the sinusoidal AC plasma actuator (2) cause the ice layer to melt, split and fall off rapidly, thereby achieving a deicing effect on the surface of the rotor (1).

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

[0050] Step S3-1, establishing the high voltage AC characteristic equation of the sinusoidal AC plasma actuator (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 excitation voltage of the sinusoidal AC plasma exciter (2) that varies with time, and is an instantaneous voltage value expressed as a complex number;

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

[0056] φ is the phase angle, in radians, which represents the initial phase offset of the high voltage sinusoidal AC power source;

[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, establishing 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 actuator (2);

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

[0064]

[0065] in:

[0066] C V is the constant volume specific heat of the actuator, which is a constant after the structure of the sinusoidal AC plasma actuator (2) is determined;

[0067] ρ is the air density;

[0068] μ is the kinematic viscosity of air;

[0069] u(t) and v(t) are the horizontal velocity component and vertical velocity component of the jet induced by the sinusoidal AC plasma actuator (2) at a certain position in space, respectively;

[0070] and are respectively the mean value of the horizontal velocity component and the mean value of the vertical velocity component of the jet induced by the sinusoidal AC plasma actuator (2) at a certain position in space in the calculation period S;

[0071] u′(t) and v′(t) are respectively the horizontal pulsating velocity component and the vertical pulsating velocity component of the jet induced by the sinusoidal AC plasma actuator (2) at a certain position in space;

[0072] and are respectively the mean value of the horizontal pulsating velocity component and the mean value of the vertical pulsating velocity component of the jet induced by the sinusoidal AC plasma actuator (2) at a certain position in space in the calculation period S;

[0073] P(t) is the pressure detected by the pressure sensor at each position at time t;

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

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

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

[0077] Then, according to the pressure P(t) detected by the pressure sensors at various positions at time t, and the temperature T(t) detected by the temperature sensors at various positions at time t, combined with the total energy E induced by the sinusoidal AC plasma actuator (2), the horizontal velocity component u(t) and the vertical velocity component v(t) of the jet induced by the sinusoidal AC plasma actuator (2) at a certain position in space can be obtained by combining formulas (8), (9), (10) and (11);

[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 the vertical velocity component v(t) of the induced jet at a certain position in space can be directly adjusted;

[0079] Therefore, when a helicopter in the current flight state experiences a dynamic stall, the frequency f of the high-voltage sinusoidal AC power supply is exc and the phase angle φ are adjusted to adjust the induced jet of the sinusoidal AC plasma actuator (2), and to change the velocity value and velocity distribution of the induced jet generated by the sinusoidal AC plasma actuator (2) and perpendicular to the wall surface, that is, to adjust the aerodynamic effect generated thereby to alleviate the dynamic stall state of the rotor and improve the aerodynamic performance of the rotor;

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

[0081] The invention provides an integrated device and method for helicopter rotor deicing and ice detection, which has the following advantages:

[0082] The present invention proposes an integrated device and method for helicopter rotor anti-icing and ice detection, which uses a set of systems to simultaneously achieve rotor anti-icing, ice detection and flow control, thereby effectively reducing energy consumption and overall costs and improving system efficiency and reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0083] Figure 1 A three-dimensional diagram of the arrangement position of the sinusoidal AC plasma actuator on the rotor surface in the integrated device for helicopter rotor deicing and ice detection provided by the present invention;

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

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

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

[0087] Figure 5 A schematic diagram of the integrated device for helicopter rotor deicing and ice detection provided by the present invention.

[0088] Description of reference numerals:

[0089] 1. Rotor; 2. Sinusoidal AC plasma actuator; 2-1. Insulating dielectric layer; 2-2. First exposed electrode; 2-3. Second exposed electrode; 2-4. Buried electrode. DETAILED DESCRIPTION

[0090] In order to make the technical problems, technical solutions and beneficial effects solved by the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0091] At present, the anti-icing and de-icing of helicopter rotors mainly relies on electric heating and hot air methods, which leads to a large amount of energy consumption and becomes a large cost burden. In view of this problem, the present invention proposes an integrated device and method for helicopter rotor anti-icing and ice detection, which can realize the anti-icing, ice detection and flow control of the rotor at the same time with the help of a set of systems, thereby effectively reducing energy consumption and overall cost, and improving system efficiency and reliability.

[0092] Specifically, the present invention proposes an integrated device and method for helicopter rotor anti-icing and ice detection, including a sinusoidal AC plasma power supply, a sinusoidal AC surface dielectric barrier discharge plasma actuator, an anti-icing controller, a temperature sensor and a pressure sensor. Its continuous AC plasma actuator design adopts a layout of two exposed electrodes and one buried electrode, which can generate a large amount of heat and a body force jet perpendicular to the wall during operation. Under the synergistic effect of the temperature sensor, the pressure sensor and the anti-icing controller, the device realizes the multiple functions of rotor anti-icing / de-icing, ice detection and flow control. Compared with traditional technologies, the present invention effectively solves the problems of high energy consumption, complex structure and high maintenance cost, and simplifies the internal structure design by arranging the plasma power supply outside the rotor, thereby reducing manufacturing and maintenance costs.

[0093] The device has the advantages of small size, light weight, low power consumption, fast response, and no mechanical parts. In addition, it has obvious thermal effect during the working process and is accompanied by volume force jet, thereby realizing helicopter rotor deicing and flow control.

[0094] The present invention provides an integrated device for helicopter rotor deicing and ice detection, see Figure 1 to Figure 5 , 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;

[0095] The sinusoidal AC plasma actuator 2 is arranged in the protection 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 a polyimide film with a thickness of 0.3 mm, 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 fixed at the center position of the lower surface of the insulating dielectric layer 2-1. -4, and the buried electrode 2-4 is embedded in the interior of the rotor 1, and the upper surface of the buried electrode 2-4 is flush with the surface of the rotor 1; the upper surface of the insulating medium layer 2-1, and located at the projection position of the edges on both sides of the buried electrode 2-4, the first exposed electrode 2-2 and the second exposed electrode 2-3 are fixedly set; 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 directly in contact with the atmosphere to assist in generating 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 power supply parameters of the high-voltage sinusoidal AC power supply are a peak-to-peak voltage of 5kV to 30kV, and a frequency adjustable within a range of 5kHz to 20kHz. The number and length of the sinusoidal AC plasma actuators 2 can be flexibly adjusted according to the size of the protection area; therefore, in the protection area of ​​the leading edge of the rotor 1, a plurality of the sinusoidal AC plasma actuators 2 are arranged in parallel at equal intervals, and the interval between two adjacent sinusoidal AC plasma actuators 2 is 18mm. This design ensures that plasma is effectively generated at the leading edge of the rotor, combats icing, and improves 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 the two, the air around the exposed electrode is triggered to ionize, thereby forming a uniform glow discharge plasma on the surface of the insulating dielectric layer 2-1. The charged ions generated by 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 area near the electrode, and the aerodynamic effect generated by the plasma excitation is used to improve the mixing efficiency of the ionization heat and the incoming flow. Compared with the traditional scheme using only a single exposed electrode, the current design uses a combination of two exposed electrodes and one buried electrode to form a jet perpendicular to the wall between the two exposed electrodes, thereby enhancing the thermal effect and improving the 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 section;

[0101] The temperature sensor and the pressure sensor are connected to the input end of the anti-icing controller; the output end 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 device for helicopter rotor deicing and ice detection, comprising the following steps:

[0103] Step S1, determining 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, the width and thickness of the first exposed electrode 2-2 and the second exposed electrode 2-3;

[0104] Step S2, during the flight of the helicopter, the temperature sensor and the pressure sensor detect the temperature and pressure of the installation position in real time, and transmit the detected temperature and pressure to the anti-icing controller in real time;

[0105] Step S3, the anti-icing controller adjusts and controls the power supply parameters of the high-voltage sinusoidal AC power supply according to the temperature and pressure detected in real time, and comprehensively utilizes the ionization thermal effect and aerodynamic effect generated by the sinusoidal AC plasma actuator 2 to perform anti-icing operations on the protection area of ​​the leading edge of the rotor 1; at the same time, when a dynamic stall occurs in a helicopter in a forward flight state, the aerodynamic effect generated by the sinusoidal AC plasma actuator 2 is utilized to improve the dynamic stall phenomenon.

[0106] In the present invention, the ionization thermal effect and aerodynamic effect generated by the sinusoidal AC plasma actuator 2 are specifically:

[0107] Ionization heating 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, and a high potential difference is applied between the two to trigger the air around the first exposed electrode 2-2 to be 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, and a high potential difference is applied between the two to trigger the air around the second exposed electrode 2-3 to be 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 area 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 effect:

[0111] The first exposed electrode 2-2 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 the two, 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 an airflow near the surface. The 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 connected to the low voltage end and the high voltage end of the high voltage sinusoidal AC power supply respectively, and a high potential difference is applied between the two to trigger the ionization of the air around the second exposed electrode 2-3. The charged ions generated in this process collide with the neutral particles, triggering an airflow near the surface, which flows from the second exposed electrode 2-3 to the buried electrode 2-4;

[0113] Since the airflows flow 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 position of the buried electrode 2-4, the two airflows collide and eventually form a vertical upward jet, thereby forming an upward jet perpendicular to the wall between the first exposed electrode 2-2 and the second exposed electrode 2-3, thereby producing an aerodynamic effect.

[0114] As a specific implementation method, the anti-icing controller adjusts and controls the power supply parameters of the high-voltage sinusoidal AC power supply according to the temperature and pressure detected in real time, and comprehensively utilizes the ionization heat effect and aerodynamic effect generated by the sinusoidal AC plasma actuator 2 to perform anti-icing operations on the protection area of ​​the leading edge of the rotor 1, specifically:

[0115] Step S3.1, at time t, the temperature sensor senses the temperature change through the change of 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 of 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 formula (1) and formula (2) to obtain the frequency spectrum FFT (V Tt ) and the frequency spectrum FFT of the pressure signal (V Pt ):

[0117]

[0118] in:

[0119] f T Collect frequency for temperature sensor;

[0120] f P Acquisition frequency for pressure sensor;

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

[0122] V P (t) represents the voltage of the pressure sensor at time t, calculated by 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 pressure sensor, respectively;

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

[0128] Step S3.3, the anti-icing controller calculates the frequency spectrum FFT (V Tt ) and the frequency spectrum FFT of the pressure signal (V Pt), and compare it with the mapping table of the frequency spectrum and various anti-icing phenomenon parameters pre-stored in the database, so as to obtain whether there is a phenomenon of supercooled water droplet impact in the current rotor protection area, and whether icing occurs. If icing occurs, obtain specific icing parameters, including: ice accumulation type and ice accumulation thickness;

[0129] If it is detected that supercooled water droplets impact the current rotor protection area, execute step S3.4;

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

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

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

[0133] Step S3.5, the anti-icing controller starts the deicing mode:

[0134] If ice has already accumulated 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; the ionization heat effect and aerodynamic effect generated by the sinusoidal AC plasma actuator 2 cause the ice layer to melt, split and fall off quickly, thereby achieving the de-icing effect on the surface of the rotor 1.

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

[0136] Step S3-1, establishing the high voltage AC characteristic equation of the sinusoidal AC plasma actuator 2:

[0137] V exc (t) = V m ·e i(ωt+φ) (5)

[0138] ω=2πf exc (6)

[0139] in:

[0140] V exc (t) is the excitation voltage of the sinusoidal AC plasma exciter 2 that varies with time, and is an instantaneous voltage value represented by a complex number;

[0141] V mis the amplitude of the excitation voltage, which is the maximum value and indicates the maximum amplitude of the excitation voltage;

[0142] φ is the phase angle, in radians, which represents the initial phase offset of the high voltage sinusoidal AC power source;

[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, establishing 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 actuator 2;

[0149] Step S3-3, establish the equation group of the total induced energy E and the induced jet velocity of the sinusoidal AC plasma actuator 2:

[0150]

[0151]

[0152] in:

[0153] C V is the constant volume specific heat of the actuator, which is a constant after the structure of the sinusoidal AC plasma actuator 2 is determined;

[0154] ρ is the air density;

[0155] μ is the kinematic viscosity of air;

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

[0157] and are respectively the mean value of the horizontal velocity component and the mean value of the vertical velocity component of the jet induced by the sinusoidal AC plasma actuator 2 at a certain position in space in the calculation period S;

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

[0159] and are respectively the mean value of the horizontal pulsating velocity component and the mean value of the vertical pulsating velocity component of the jet induced by the sinusoidal AC plasma actuator 2 at a certain position in space in the calculation period S;

[0160] P(t) is the pressure detected by the pressure sensor at each position at time t;

[0161] T(t) is 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 AC plasma actuator 2 at a certain position in space;

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

[0164] Then, according to the pressure P(t) detected by the pressure sensors at various positions at time t, and the temperature T(t) detected by the temperature sensors at various positions at time t, combined with the total energy E induced by the sinusoidal AC plasma actuator 2, formula (8), formula (9), formula (10) and formula (11) are solved to obtain the horizontal velocity component u(t) and the vertical velocity component v(t) of the jet induced by the sinusoidal AC plasma actuator 2 at a certain position in space;

[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 the vertical velocity component v(t) of the induced jet at a certain position in space can be directly adjusted;

[0166] Therefore, when a helicopter in the current flight state experiences a dynamic stall, the frequency f of the high-voltage sinusoidal AC power supply is exc and the phase angle φ are adjusted to adjust the induced jet of the sinusoidal AC plasma actuator 2, and to change the velocity value and velocity distribution of the induced jet generated by the sinusoidal AC plasma actuator 2 and perpendicular to the wall surface, that is, to adjust the aerodynamic effect generated by it, thereby alleviating the dynamic stall state of the rotor and improving the aerodynamic performance of the rotor;

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

[0168] The integrated device and method for helicopter rotor deicing and ice detection provided by the present invention have 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, and 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 arranged at the projected positions of the edges of the buried electrodes, and are respectively connected to the low-voltage end and the high-voltage end of the high-voltage sinusoidal AC power supply. The high-voltage sinusoidal AC power supply provides high-voltage AC 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, and an airflow perpendicular to the wall surface is generated, bringing a large amount of heat. The sinusoidal AC plasma actuator 2 shows excellent performance in ice detection and anti-icing processes. According to the actual size of the protection area, the number and length of the sinusoidal AC plasma actuators 2 can be flexibly adjusted. The advantages of this system include small size, light weight, low power consumption, fast response and high-frequency operation, and no mechanical parts. It only needs to set exposed electrodes, buried electrodes 2-4 and insulating medium layer 2-1 on the rotor surface to achieve the anti-icing function, without the need for complex internal heating devices, thereby greatly reducing manufacturing and maintenance costs.

[0170] (2) The device integrates high-frequency temperature sensors and pressure sensors, 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, calculates their statistical characteristics such as average value and root mean square, and identifies the characteristics such as sudden rise and fall in the signal waveform. Subsequently, these analysis results are compared with the built-in database to determine whether there are supercooled water droplets impacting the rotor surface, whether there is ice accumulation, and the type and thickness of the ice accumulation. Based on the above analysis, the anti-icing controller can intelligently control the electrical parameters of the sinusoidal AC plasma actuator 2 to achieve the best anti-icing effect with the lowest possible power consumption. This technical solution not only improves the accuracy of ice detection, but also optimizes the energy efficiency and safety of the anti-icing process, ensuring the reliable operation of the rotor in complex environments.

[0172] (3) Ability to effectively deal with different icing risks:

[0173] When the ice detection results show that there is a supercooled water droplet impact phenomenon in the incoming flow, it indicates that there is an icing risk. At this time, the anti-icing controller will enable the sinusoidal AC plasma actuator 2 to make it work according to specific anti-icing parameters. Through the ionization thermal effect and aerodynamic effect of plasma excitation, it can effectively prevent supercooled water droplets from forming ice accumulation after impact, thereby achieving the anti-icing effect on the rotor surface. If there is already a certain amount of ice accumulation on the rotor surface, the system can also use the ionization thermal effect and aerodynamic effect of plasma excitation to quickly melt, split and fall off the ice layer to achieve the purpose of deicing. This dual function ensures the safety and normal operation of the rotor in various wet and cold environments, and effectively avoids performance degradation or safety hazards caused by ice accumulation.

[0174] (4) The device uses sinusoidal AC surface dielectric barrier discharge plasma aerodynamic excitation to effectively control the dynamic stall phenomenon of the helicopter rotor and improve its average aerodynamic force. Due to the combined effects of the pitch change, flapping and periodic pitch change of the rotor blades, unsteady dynamic stall is prone to occur when the angle of attack is too large. To this end, the device measures the pressure data on the blade surface in real time through a pressure sensor to determine whether dynamic stall occurs. Once the dynamic stall phenomenon is detected, the anti-icing controller adjusts the power supply parameters of the exciter to generate vertical upward volume force jets of different intensities. Through the aerodynamic effect caused by plasma excitation, a virtual convex area is formed, which increases the flow velocity on the blade surface and increases the momentum of the boundary layer. This control mechanism effectively weakens the influence of the adverse pressure gradient on the blade profile, suppresses flow separation, thereby increasing the lift coefficient of the rotor blade and reducing the nose-down moment coefficient. Therefore, the device not only improves the aerodynamic performance of the rotor blade, but also significantly alleviates the dynamic stall problem of the rotor, improving the flight stability and control performance of the helicopter.

[0175] The beneficial effects of the present invention are:

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

[0177] (2) Compared with the traditional exciter layout, the optimized exciter layout design of the present invention adopts a layout in which two exposed electrodes share one buried electrode, which can generate more heat and body force jets perpendicular to the wall, significantly improving the efficiency of deicing and flow control, and overcoming the high energy consumption and low energy utilization problems in traditional methods.

[0178] (3) The adjustable anti-icing strategy of the present invention can flexibly adjust the excitation intensity of the plasma actuator 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 effects with optimal parameters in different environments.

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

[0180] (5) The present invention has a high energy conversion efficiency. Unlike traditional gas-heat and electric-heat deicing technologies, the present invention directly heats the rotor wall and uses the aerodynamic effect generated by plasma excitation to improve the mixing efficiency of ionized heat and incoming air. 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 is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principle of the present invention. These improvements and modifications should also be considered as the scope of protection of the present invention.

Claims

1. An integrated device for helicopter rotor deicing and ice detection, characterized in that: 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; The sinusoidal AC plasma actuator (2) is arranged in a protective area at the leading edge of the rotor (1); the sinusoidal AC plasma actuator (2) comprises 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 0.3 mm thick and is fixed to the surface of the rotor (1); the buried electrode (2-4) having 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 in the interior of the rotor (1), and the upper surface of the buried electrode (2-4) is flush with the surface of the rotor (1); the upper surface of the insulating medium layer (2-1), and located at the projection position of the edges on both sides of the buried electrode (2-4), the first exposed electrode (2-2) and the second exposed electrode (2-3) are fixedly arranged; the width of the first exposed electrode (2-2) and the second exposed electrode (2-3) are 3 mm, and the thickness is 0.03 mm; 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) section; The temperature sensor and the pressure sensor are connected to the input end of the anti-icing controller; the output end of the anti-icing controller is connected to the high-voltage sinusoidal AC power supply.

2. The integrated device for helicopter rotor deicing and ice detection according to claim 1, characterized in that: The sinusoidal AC plasma exciter (2) is a sinusoidal AC surface dielectric barrier discharge plasma exciter.

3. The integrated device for helicopter rotor deicing and ice detection according to claim 1, characterized in that: In the protection area of ​​the leading edge of the rotor (1), a plurality of the sinusoidal AC plasma actuators (2) are arranged in parallel at equal intervals.

4. The integrated device for helicopter rotor deicing and ice detection according to claim 3, characterized in that: The distance between two adjacent sinusoidal AC plasma actuators (2) is 18 mm.

5. A method for an integrated device for helicopter rotor deicing and ice detection as claimed in any one of claims 1 to 4, characterized in that: The following steps are involved: Step S1, determining 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), the width and thickness of the first exposed electrode (2-2) and the second exposed electrode (2-3); Step S2, during the flight of the helicopter, the temperature sensor and the pressure sensor detect the temperature and pressure of the installation position 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 supply parameters of the high-voltage sinusoidal AC power supply according to the temperature and pressure detected in real time, and comprehensively utilizes the ionization heat effect and aerodynamic effect generated by the sinusoidal AC plasma actuator (2) to perform anti-icing operations on the protection area at the leading edge of the rotor (1); at the same time, when a helicopter in a forward flight state experiences a dynamic stall phenomenon, the aerodynamic effect generated by the sinusoidal AC plasma actuator (2) is utilized to improve the dynamic stall phenomenon.

6. The method for the integrated device for helicopter rotor deicing and ice detection according to claim 5, characterized in that: In step S3, the ionization thermal effect and aerodynamic effect generated by the sinusoidal AC plasma actuator (2) are specifically: Ionization heating 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, and a high potential difference is applied between the two to trigger the air around the first exposed electrode (2-2) to be 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, and a high potential difference is applied between the two to trigger the air around the second exposed electrode (2-3) to be 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 area 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; Aerodynamic 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, and a high potential difference is applied between the two to trigger the ionization of the air around the first exposed electrode (2-2). The charged ions generated in this process collide with neutral particles, triggering an airflow near the surface, and the 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, and a high potential difference is applied between the two to trigger the ionization of the air around the second exposed electrode (2-3). The charged ions generated in this process collide with neutral particles, triggering an airflow near the surface, and the airflow flows from the second exposed electrode (2-3) to the buried electrode (2-4); Since the airflows flow 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 position of the buried electrode (2-4), the two airflows impact and eventually form a vertical upward jet, thereby 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.

7. The method for the integrated helicopter rotor deicing and ice detection device according to claim 6, characterized in that: The anti-icing controller adjusts and controls the power supply parameters of the high-voltage sinusoidal AC power supply according to the temperature and pressure detected in real time, and comprehensively utilizes the ionization heat effect and aerodynamic effect generated by the sinusoidal AC plasma actuator (2) to perform anti-icing operations on the protection area at the leading edge of the rotor (1), specifically: Step S3.1, at time t, the temperature sensor senses the temperature change through the change of 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 of 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 formula (1) and formula (2) to obtain the frequency spectrum FFT (V Tt ) and the frequency spectrum FFT of the pressure signal (V Pt ): in: f T Collect frequency for temperature sensor; f P Acquisition frequency for pressure sensor; V T (t) represents the voltage of the temperature sensor at time t, calculated by formula (3); V P (t) represents the voltage of the pressure sensor at time t, calculated by 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 pressure sensor, respectively; V T0 and V P0 , are the bias voltages of the temperature sensor and the pressure sensor respectively; Step S3.3, the anti-icing controller calculates the frequency spectrum FFT (V Tt ) and the frequency spectrum FFT of the pressure signal (V Pt ), and compare it with the mapping table of the frequency spectrum and various anti-icing phenomenon parameters pre-stored in the database, so as to obtain whether there is a phenomenon of supercooled water droplet impact in the current rotor protection area, and whether icing occurs. If icing occurs, obtain specific icing parameters, including: ice accumulation type and ice accumulation thickness; If it is detected that supercooled water droplets impact the current rotor protection area, execute step S3.4; If icing is detected in the current rotor protection area, execute step S3.5; Step S3.4, the anti-icing controller starts the anti-icing mode: Specifically, when the detection result shows that there is a supercooled water droplet impact phenomenon in the incoming flow, it indicates that there is an icing risk. At this time, the anti-icing controller adjusts the parameters of the high-voltage sinusoidal AC power supply to make it operate in an anti-icing mode; through the ionization heat effect and aerodynamic effect generated by the sinusoidal AC plasma actuator (2), the supercooled water droplets are prevented from forming ice after the impact, thereby achieving an anti-icing effect on the surface of the rotor (1); Step S3.5, the anti-icing controller starts the deicing mode: If ice has already accumulated on the surface of the rotor (1), the anti-deicing controller adjusts the parameters of the high-voltage sinusoidal AC power supply so that it operates in a deicing mode; the ionization heat effect and aerodynamic effect generated by the sinusoidal AC plasma actuator (2) cause the ice layer to melt, split and fall off rapidly, thereby achieving a deicing effect on the surface of the rotor (1).

8. The method for the integrated helicopter rotor deicing and ice detection device according to claim 6, characterized in that: The aerodynamic effect parameters of the aerodynamic effect generated by the sinusoidal AC plasma actuator (2) are adjustable, including: Step S3-1, establishing the high voltage AC characteristic equation of the sinusoidal AC plasma actuator (2): V exc (t)=V m ·e i(ωt+φ) (5) ω=2πf exc (6) in: V exc (t) is the excitation voltage of the sinusoidal AC plasma exciter (2) that varies with time, and is an instantaneous voltage value expressed as a complex number; V m is the amplitude of the excitation voltage, which is the maximum value and indicates the maximum amplitude of the excitation voltage; φ is the phase angle, in radians, which represents the initial phase offset of the high voltage sinusoidal AC power source; 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, establishing 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 actuator (2); Step S3-3, establish the equation group of the induced total energy E and the induced jet velocity of the sinusoidal AC plasma actuator (2): in: C V is the constant volume specific heat of the actuator, which is a constant after the structure of the sinusoidal AC plasma actuator (2) is determined; ρ is the air density; μ is the kinematic viscosity of air; u(t) and v(t) are the horizontal velocity component and the vertical velocity component of the jet induced by the sinusoidal AC plasma actuator (2) at a certain position in space, respectively; and are respectively the mean value of the horizontal velocity component and the mean value of the vertical velocity component of the jet induced by the sinusoidal AC plasma actuator (2) at a certain position in space in the calculation period S; u′(t) and v′(t) are respectively the horizontal pulsating velocity component and the vertical pulsating velocity component of the jet induced by the sinusoidal AC plasma actuator (2) at a certain position in space; and are respectively the mean value of the horizontal pulsating velocity component and the mean value of the vertical pulsating velocity component of the jet induced by the sinusoidal AC plasma actuator (2) at a certain position in space in the calculation period S; P(t) is the pressure detected by the pressure sensor at each position at time t; T(t) is the temperature detected by the temperature sensors at each location at time t; x and y represent the longitude and latitude coordinates of a certain position in space of the jet induced by the sinusoidal AC plasma actuator (2); Step S3-4, therefore, by adjusting the frequency f of the high voltage sinusoidal AC power supply exc and phase angle φ are adjusted, and the total induced energy E of the sinusoidal AC plasma actuator (2) corresponding to the adjusted high voltage sinusoidal AC power supply can be obtained through formula (5), formula (6) and formula (7); Then, according to the pressure P(t) detected by the pressure sensors at various positions at time t, and the temperature T(t) detected by the temperature sensors at various positions at time t, combined with the total energy E induced by the sinusoidal AC plasma actuator (2), the horizontal velocity component u(t) and the vertical velocity component v(t) of the jet induced by the sinusoidal AC plasma actuator (2) at a certain position in space can be obtained by solving formula (8), formula (9), formula (10) and formula (11); 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 the vertical velocity component v(t) of the induced jet at a certain position in space can be directly adjusted; Therefore, when a helicopter in the current flight state experiences a dynamic stall, the frequency f of the high-voltage sinusoidal AC power supply is exc and the phase angle φ are adjusted to adjust the induced jet of the sinusoidal AC plasma actuator (2), and to change the velocity value and velocity distribution of the induced jet generated by the sinusoidal AC plasma actuator (2) and perpendicular to the wall surface, that is, to adjust the aerodynamic effect generated thereby to alleviate the dynamic stall state of the rotor and improve the aerodynamic performance of the rotor; Furthermore, by adjusting the aerodynamic effect generated, under the action of the airflow effect, the mixing efficiency of the ionization heat and the incoming flow is improved, the thermal effect is enhanced, and the energy utilization efficiency is improved.

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