Passive wing de-icing method, device and system

Abstract

The application discloses a kind of wing passive monitoring deicing method, device and system, belong to wing deicing technical field.The method includes: obtaining the first mapping relationship between the aircraft flight speed and the piezoelectric ceramic piece vibration frequency under the wing ice-free state, obtaining the second mapping relationship between the aircraft flight speed, piezoelectric ceramic piece vibration frequency and ice layer constraint parameter under the wing icing state;When the aircraft starts to fly, the piezoelectric ceramic piece is in the non-vibration energy storage state, in the aircraft flight state, according to the set starting condition interval, start the icing monitoring program, provide the first voltage for the piezoelectric ceramic piece after each time starting icing monitoring program and obtain monitoring vibration frequency;Using the first mapping relationship, the second mapping relationship and monitoring vibration frequency, determine the wing icing state, and determine whether the state switching between non-vibration energy storage state and vibration deicing state according to the determination result.The application not only simple system design, and cost is lower.

Description

Technical Field

[0001] This invention relates to the field of wing de-icing technology, and in particular to a passive monitoring de-icing method, device and system for wings. Background Technology

[0002] Wing icing alters the aerodynamic shape of the wing, increases weight, reduces lift, and seriously affects flight safety. Therefore, it is necessary to monitor wing icing and perform wing de-icing.

[0003] In related technologies, ultrasonic methods are generally used to monitor ice thickness, and mechanical de-icing is employed for de-icing. However, current monitoring and de-icing methods involve complex systems and are costly.

[0004] Therefore, there is an urgent need to provide a monitoring and de-icing system that is simple to design and has lower design costs. Summary of the Invention

[0005] This invention provides a passive monitoring and de-icing method, device, and system for airfoils, which solves the problems of complex system design and high cost in related technologies. The technical solution is as follows:

[0006] On the one hand, a passive monitoring-based de-icing method for airfoils is provided, which utilizes a monitoring-based de-icing system, the monitoring-based de-icing system comprising at least an energy storage battery and multiple piezoelectric ceramic plates disposed on the surface of the airfoil; the method includes:

[0007] A first mapping relationship between the aircraft's flight speed and the vibration frequency of the piezoelectric ceramic sheet in the uniced state of the wing is obtained, and a second mapping relationship between the aircraft's flight speed, the vibration frequency of the piezoelectric ceramic sheet, and the ice layer constraint parameters in the iced state of the wing is obtained; the vibration frequency of the piezoelectric ceramic sheet in both the first and second mapping relationships is obtained under the action of a first voltage;

[0008] When the aircraft begins flight, the piezoelectric ceramic sheet is in a non-vibration energy storage state. During flight, the icing monitoring program is activated at intervals according to the set activation conditions. Each time the icing monitoring program is activated, the first voltage is provided to the piezoelectric ceramic sheet and the monitoring vibration frequency is acquired. In the non-vibration energy storage state, the piezoelectric ceramic sheet charges the energy storage battery under the action of wind pressure.

[0009] Using the first mapping relationship, the second mapping relationship, and the monitored vibration frequency, the wing icing state is determined, and based on the determination result, it is determined whether to switch between the non-vibration energy storage state and the vibration de-icing state.

[0010] On the other hand, a passive monitoring and de-icing device for an airfoil is provided, located within a monitoring and de-icing system, the monitoring and de-icing system further including at least an energy storage battery and multiple piezoelectric ceramic plates disposed on the surface of the airfoil; the device includes:

[0011] The acquisition unit is used to acquire a first mapping relationship between the aircraft's flight speed and the vibration frequency of the piezoelectric ceramic sheet when the wing is not iced, and to acquire a second mapping relationship between the aircraft's flight speed, the vibration frequency of the piezoelectric ceramic sheet, and the ice layer constraint parameters when the wing is iced; the vibration frequency of the piezoelectric ceramic sheet in the first mapping relationship and the second mapping relationship are both acquired under the action of a first voltage;

[0012] The monitoring unit is used to ensure that the piezoelectric ceramic sheet is in a non-vibration energy storage state when the aircraft starts flying, and to activate the icing monitoring program at set activation intervals during the aircraft's flight. Each time the icing monitoring program is activated, the first voltage is provided to the piezoelectric ceramic sheet and the monitoring vibration frequency is acquired. In the non-vibration energy storage state, the piezoelectric ceramic sheet charges the energy storage battery under wind pressure.

[0013] The switching unit is used to determine the wing icing state by using the first mapping relationship, the second mapping relationship and the monitored vibration frequency, and to determine whether to switch between the non-vibration energy storage state and the vibration de-icing state based on the determination result.

[0014] On the other hand, a monitoring and de-icing system is provided, including: the wing passive monitoring and de-icing device as described above, and also including an energy storage battery and a plurality of piezoelectric ceramic plates disposed on the wing surface.

[0015] The technical solution provided by this invention can bring at least the following beneficial effects:

[0016] Because piezoelectric ceramic sheets can convert pressure into electrical energy under pressure and vibrate when voltage is applied, multiple piezoelectric ceramic sheets can be installed on the wing surface. These sheets can function as energy storage devices, vibration de-icing devices, and ice monitoring devices using vibration frequency. All three functions are integrated and can be achieved by the piezoelectric ceramic sheets. By pre-acquiring the first and second mapping relationships, the aircraft can periodically activate the icing monitoring program during flight to determine whether to switch between non-vibration energy storage and vibration de-icing states. This system design is simple and does not require an external power source. It can complete the monitoring and de-icing tasks while self-storing energy, further reducing system costs. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 This is a flowchart of a passive monitoring and de-icing method for an aircraft wing provided by an embodiment of the present invention;

[0019] Figure 2 This is a structural diagram of a passive monitoring and de-icing device for an aircraft wing provided in an embodiment of the present invention;

[0020] Figure 3 This is a structural diagram of a monitoring and de-icing system provided in an embodiment of the present invention;

[0021] Figure 4 This is a schematic diagram illustrating the arrangement relationship between a piezoelectric ceramic sheet and an airfoil according to an embodiment of the present invention;

[0022] Figure 5 This is a hardware architecture diagram of a computer device provided in an embodiment of the present invention. Detailed Implementation

[0023] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are some embodiments of the present invention, but not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0024] Please refer to Figure 1 This invention provides a passive monitoring de-icing method for airfoils, implemented using a monitoring de-icing system. The monitoring de-icing system includes at least an energy storage battery and multiple piezoelectric ceramic plates disposed on the airfoil surface. The method includes:

[0025] Step 100: Obtain the first mapping relationship between the aircraft's flight speed and the vibration frequency of the piezoelectric ceramic sheet when the wing is not iced, and obtain the second mapping relationship between the aircraft's flight speed, the vibration frequency of the piezoelectric ceramic sheet, and the ice layer constraint parameters when the wing is iced; the vibration frequency of the piezoelectric ceramic sheet in the first mapping relationship and the second mapping relationship are both obtained under the action of the first voltage;

[0026] Step 102: When the aircraft starts flying, the piezoelectric ceramic sheet is in a non-vibration energy storage state. During the flight, the icing monitoring program is started at intervals according to the set start conditions. Each time the icing monitoring program is started, the first voltage is provided to the piezoelectric ceramic sheet and the monitoring vibration frequency is obtained. In the non-vibration energy storage state, the piezoelectric ceramic sheet charges the energy storage battery under the action of wind pressure.

[0027] Step 104: Using the first mapping relationship, the second mapping relationship, and the monitored vibration frequency, determine the wing icing state, and determine whether to switch between the non-vibration energy storage state and the vibration de-icing state based on the determination result.

[0028] In this embodiment of the invention, since the piezoelectric ceramic sheet can convert pressure into electrical energy under pressure and vibrate after being supplied with voltage, multiple piezoelectric ceramic sheets can be installed on the wing surface. These piezoelectric ceramic sheets can be used as energy storage devices, vibration de-icing devices, and ice monitoring devices using vibration frequency. These three functions are integrated and can all be achieved by the piezoelectric ceramic sheet. Furthermore, by pre-obtaining the first and second mapping relationships, the icing monitoring program can be activated intermittently during aircraft flight to determine whether to switch between non-vibration energy storage and vibration de-icing states. This not only simplifies the system design but also eliminates the need for an external power source, enabling the monitoring and de-icing tasks to be completed while self-storing energy, further reducing system costs.

[0029] The following description Figure 1 The execution method of each step is shown.

[0030] First, for step 100, a first mapping relationship between the aircraft's flight speed and the vibration frequency of the piezoelectric ceramic sheet in the uniced state of the wing is obtained, and a second mapping relationship between the aircraft's flight speed, the vibration frequency of the piezoelectric ceramic sheet, and the ice layer constraint parameters in the iced state of the wing is obtained; the vibration frequency of the piezoelectric ceramic sheet in the first mapping relationship and the second mapping relationship are both obtained under the action of the first voltage.

[0031] Under normal circumstances, if a voltage is applied to a piezoelectric ceramic sheet, it will vibrate, and the vibration frequency will remain constant when the voltage is constant. When the piezoelectric ceramic sheet is placed on the surface of an aircraft wing, the wind pressure during flight will suppress the vibration of the piezoelectric ceramic sheet, thus affecting its vibration frequency. In other words, the vibration frequency of the piezoelectric ceramic sheet will be different depending on the aircraft's flight speed.

[0032] Based on this, the first mapping relationship between the aircraft's flight speed and the vibration frequency of the piezoelectric ceramic sheet in the case of an icy wing can be obtained through flight test experiments or wind tunnel experiments.

[0033] The experimental setup is as follows: a piezoelectric ceramic sheet is placed on the wing surface, a first voltage is applied to the piezoelectric ceramic sheet, and the vibration frequency of the piezoelectric ceramic sheet is obtained during the experiment; the wing remains in an icy state throughout the experiment. In this way, the vibration frequencies of the piezoelectric ceramic sheet corresponding to different aircraft flight speeds under icy conditions can be obtained. The first voltage is the voltage that causes the piezoelectric ceramic sheet to vibrate at a low frequency, and this first voltage is not equal to a second voltage; the second voltage is the voltage that causes the piezoelectric ceramic sheet to vibrate at a resonant frequency.

[0034] Based on the experimental results, a first mapping relationship between the aircraft's flight speed and the vibration frequency of the piezoelectric ceramic sheet in the case of an uniced wing can be obtained.

[0035] When an aircraft wing is icy, the piezoelectric ceramic sheet placed on the wing surface will be affected by the gravity of the ice layer, resulting in increased vibration suppression of the piezoelectric ceramic sheet. Therefore, in this embodiment of the invention, the change in the vibration frequency of the piezoelectric ceramic sheet relative to the icy state of the wing can be used to determine whether the wing is icy, thus achieving an icing monitoring function.

[0036] Based on this, a second mapping relationship between the aircraft's flight speed, the vibration frequency of the piezoelectric ceramic sheet, and the ice constraint parameters under wing icing conditions can be obtained through flight test experiments or wind tunnel experiments.

[0037] The experimental setup was the same as that for the first mapping relationship acquisition experiment. However, during the experiment, the wing gradually entered an icing state, and the icing thickness and area gradually increased. During the experiment, it was necessary to test the mapping relationship between the vibration frequency of the piezoelectric ceramic sheet and the ice constraint parameters at each aircraft flight speed. That is, multiple aircraft flight speed test points were set, and at each test point, the ice constraint parameters were gradually increased to obtain the vibration frequency of the piezoelectric ceramic sheet as the ice constraint parameters gradually increased.

[0038] In this embodiment of the invention, the larger the size of the piezoelectric ceramic sheet, the more the vibration suppression effect of wing icing on the piezoelectric ceramic sheet is related to both the icing area and the icing thickness. However, if the size of the piezoelectric ceramic sheet is very small, the vibration suppression effect of wing icing on the piezoelectric ceramic sheet is not affected by the icing area, but only by the ice thickness. Therefore, the ice constraint parameters can include at least the following two:

[0039] The first type of ice layer constraint parameter is the ice layer thickness;

[0040] The second ice layer constraint parameter is the gravity of the piezoelectric ceramic sheet constrained by the ice layer.

[0041] The following sections will explain these two ice layer constraint parameters respectively.

[0042] For the first type of ice layer constraint parameters:

[0043] Under the first ice constraint parameters, the vibration suppression of the piezoelectric ceramic sheet by wing icing is related to the ice thickness. Therefore, the size of the piezoelectric ceramic sheet needs to be very small. In one implementation, the size of the piezoelectric ceramic sheet is no greater than 10 mm. In this way, the icing area can be disregarded.

[0044] Under the first ice layer constraint parameter, the ice layer thickness can be measured by ultrasonic means, thereby obtaining the second mapping relationship between the aircraft flight speed, the vibration frequency of the piezoelectric ceramic sheet and the ice layer constraint parameter under the wing icing state.

[0045] For the second type of ice layer constraint parameters:

[0046] Under this second type of ice constraint parameter, the vibration suppression of the piezoelectric ceramic sheet by wing icing is related to both the icing area and the ice thickness. Although the size of the piezoelectric ceramic sheet is not limited, the icing area needs to be considered. In one implementation, the constraint gravity is determined based on the product of the ice thickness and the icing area; the icing area is determined jointly by multiple piezoelectric ceramic sheets.

[0047] Since multiple piezoelectric ceramic sheets are placed at different locations on the wing surface, it can be determined whether the area where the piezoelectric ceramic sheet is placed is icy by measuring whether the vibration frequency of the piezoelectric ceramic sheet satisfies the first mapping relationship. If it does not satisfy the relationship, it is determined that the area where the piezoelectric ceramic sheet is placed is icy. At this time, the ice thickness can also be measured by ultrasonic means. By using whether the corresponding areas of multiple piezoelectric ceramic sheets are icy, the icing area can be determined, and the constraint gravity can be determined using the following formula: G=S×L×g; where G is the constraint gravity, S is the icing area, L is the average ice thickness, and g is the gravitational acceleration, which can be taken as 9.8N / kg.

[0048] Based on the experimental results, a second mapping relationship can be obtained between the aircraft's flight speed, the vibration frequency of the piezoelectric ceramic sheet, and the ice constraint parameters under wing icing conditions.

[0049] It should be noted that the first mapping relationship and the second mapping relationship in this step 100 are both obtained in advance. After obtaining the first mapping relationship and the second mapping relationship, they can be applied to the monitoring and de-icing during actual flight of the aircraft.

[0050] Then, regarding step 102, when the aircraft starts flying, the piezoelectric ceramic sheet is in a non-vibration energy storage state. When the aircraft is in flight, the icing monitoring program is started at intervals according to the set start conditions. Each time the icing monitoring program is started, the first voltage is provided to the piezoelectric ceramic sheet and the monitoring vibration frequency is obtained. In the non-vibration energy storage state, the piezoelectric ceramic sheet charges the energy storage battery under the action of wind pressure.

[0051] In this embodiment of the invention, a monitoring and de-icing system can be pre-set for the aircraft, with multiple piezoelectric ceramic sheets set on the wing surface. The setting position and method should be as similar as possible to the setting during the experiment to further ensure accuracy.

[0052] In this embodiment of the invention, since the de-icing monitoring system includes an energy storage battery, no additional power source is required. When the aircraft begins flight, the piezoelectric ceramic sheet can be in a non-vibrational energy storage state, meaning that the wing is not yet iced. The piezoelectric ceramic sheet is subjected to wind pressure during flight, converting the pressure into electrical energy to charge the energy storage battery. However, as the flight time gradually increases, the wing may ic up. To achieve icing monitoring, activation conditions can be preset to initiate the icing monitoring program at preset intervals.

[0053] In one embodiment of the present invention, the set start-up condition can be a fixed interval. For example, it can be started once every 1 minute.

[0054] Considering that the rate of icing is related to the ice layer constraint parameters after the last de-icing, the flight speed since the last de-icing, flight altitude, and flight duration, if startups are performed at fixed intervals, and multiple startups fail to meet the de-icing conditions, it will affect energy storage. To maximize energy storage, in another embodiment of the invention, the following method can be used to determine whether the conditions for the next startup have been met:

[0055] The system acquires the monitored values ​​of flight parameters and uses these values, along with the state of the piezoelectric ceramic sheet since the last activation of the icing monitoring program, to calculate the time interval corresponding to the next activation condition.

[0056] The flight parameters include at least:

[0057] The initial values ​​of the ice layer constraint parameters corresponding to the most recent start of the icing monitoring program;

[0058] The average flight speed corresponding to the most recent activation of the icing monitoring program; and

[0059] The average flight altitude since the most recent activation of the icing monitoring program.

[0060] In one implementation, if the piezoelectric ceramic sheet is in a non-vibrational energy storage state after the most recent activation of the icing monitoring program, the time interval corresponding to the next activation condition is calculated using the following formula. t 1 :

[0061]

[0062] in, h0 These are the initial values ​​for the ice layer constraint parameters. h a This is the critical value for de-icing. ρ The density of ice, V For flight speed, LWC ( H ( ) represents flight altitude H The corresponding liquid water content, E ( V,H The collection efficiency is related to flight speed and altitude; this parameter is dimensionless and is typically [value missing]. 0<E≤1 .

[0063] Since ice formation is typically related to the impact of supercooled water droplets, during flight, when an aircraft passes through clouds containing supercooled water droplets, these droplets impact the wing surface and ic up. This icing process is influenced by several factors, such as temperature, liquid water content (LWC), and flight speed. Flight altitude affects air temperature and LWC, while flight speed affects the impact rate of the cold water droplets. Icing rate models involve collection efficiency (i.e., how many water droplets actually impact the wing surface), LWC, and flight speed. Therefore, icing rate models can be used to calculate the time required to reach the de-icing critical value from the initial values ​​of ice constraint parameters.

[0064] In another implementation, if the piezoelectric ceramic sheet is in a vibration de-icing state after the most recent activation of the icing monitoring program, the time interval corresponding to the next activation condition is calculated using the following formula. t 2 :

[0065]

[0066] in, h 0 These are the initial values ​​for the ice layer constraint parameters. β The overall de-icing efficiency constant (calibrated experimentally). f The resonant frequency of the piezoelectric ceramic sheet. V For flight speed, γ ( H ) is the de-icing efficiency coefficient related to flight altitude H (calibrated experimentally).

[0067] Vibration de-icing can cause ice to detach, and the vibration frequency affects the de-icing rate. For example, high-frequency vibration can cause ice to break or detach more quickly. In addition, since flight speed affects aerodynamic scouring, resonant frequency affects the rate of mechanical de-icing, and flight altitude affects air density and temperature, thus affecting de-icing efficiency, a dynamic model of the de-icing system can be provided to calculate the time required from the initial values ​​of ice constraint parameters to the complete removal of ice.

[0068] As can be seen, in this embodiment of the invention, when the state of the piezoelectric ceramic sheet is different (non-vibration energy storage state or vibration de-icing state) after the most recent start of the icing monitoring program, different calculation formulas are needed to calculate the time interval corresponding to the next start of the icing monitoring program.

[0069] It should be noted that, in order to ensure that the state switching can be achieved after the icing monitoring program is started, for example, if the icing monitoring program is started in the non-vibration energy storage state and it is determined that the wing is iced and the de-icing conditions are met, then the state switches to the vibration de-icing state; if the icing monitoring program is started in the vibration de-icing state and it is determined that the wing is not iced, indicating that de-icing has been completed, then the state can be switched to the non-vibration energy storage state; based on this, after the time interval is calculated by the above two calculation formulas, a set duration can be added to the calculated time interval, for example, the set duration is 2 seconds, to improve the effectiveness of each icing monitoring program start-up.

[0070] Finally, for step 104, the wing icing state is determined using the first mapping relationship, the second mapping relationship, and the monitored vibration frequency, and the state of wing icing is determined based on the determination result to decide whether to switch between the non-vibration energy storage state and the vibration de-icing state.

[0071] In one embodiment of the present invention, the determination of wing icing status and whether to switch states can be performed in the following manner:

[0072] The first vibration frequency of the piezoelectric ceramic sheet corresponding to the current aircraft flight speed is determined using the first mapping relationship, and it is determined whether the monitored vibration frequency is equal to the first vibration frequency.

[0073] If they are equal, the wing icing status is determined to be non-iced. After the icing monitoring program is activated, the non-vibration energy storage state will be entered.

[0074] If they are not equal, the determination result of the wing icing state is wing icing; further, the target mapping relationship between the vibration frequency of the piezoelectric ceramic sheet and the ice layer constraint parameters is determined by using the second mapping relationship and the current aircraft flight speed, and the target ice layer constraint parameter value corresponding to the monitored vibration frequency is determined by using the target mapping relationship, and whether to switch states is determined based on the target ice layer constraint parameter value.

[0075] It should be noted that since the first mapping relationship is obtained by fitting, if the error between the monitored vibration frequency and the first vibration frequency is within the set error range, then the two are determined to be equal.

[0076] When the monitored vibration frequency is equal to the first vibration frequency, it indicates that the first mapping relationship of no icing on the wing is met, and vibration de-icing is not required. After the icing monitoring program is initiated, the system can enter a non-vibration energy storage state to continue energy storage. When the monitored vibration frequency is not equal to the first vibration frequency, it indicates that the first mapping relationship of no icing on the wing is not met, and icing has occurred on the wing. However, the vibration de-icing state is not immediately initiated once icing is detected on the wing. Instead, the severity of icing needs to be further determined using the ice layer constraint parameter value. In this embodiment of the invention, the target ice layer constraint parameter value can be determined through a second mapping relationship.

[0077] Specifically, when determining whether to perform a state switch based on the target ice layer constraint parameter value, the following may be included:

[0078] The relationship between the target ice layer constraint parameter value and the de-icing critical value is used to determine whether the current de-icing condition has been met.

[0079] If the target ice layer constraint parameter value is not less than the de-icing critical value, the de-icing condition is met, and a second voltage is provided to the piezoelectric ceramic sheet to enter the vibration de-icing state, so that the piezoelectric ceramic sheet reaches the resonant frequency, so that the wing de-icing is achieved through the vibration of the piezoelectric ceramic sheet; otherwise, if the de-icing condition is not met, the non-vibration energy storage state is entered.

[0080] The critical value for de-icing corresponds to the ice layer constraint parameter. For example, if the ice layer constraint parameter is the ice layer thickness, then the critical value for de-icing is the critical value for ice layer thickness. If the ice layer constraint parameter is the ice layer constraint gravity, then the critical value for de-icing is the critical value for ice layer constraint gravity.

[0081] In this embodiment of the invention, ice layer monitoring, energy storage and de-icing functions can be achieved using only piezoelectric ceramic sheets, without the need for additional power supply. The system design is simple and the cost is lower.

[0082] Please refer to Figure 2 This invention provides a passive monitoring and de-icing device for an aircraft wing, located within a monitoring and de-icing system. The monitoring and de-icing system further includes at least an energy storage battery and multiple piezoelectric ceramic plates disposed on the wing surface. The device comprises:

[0083] The acquisition unit 200 is used to acquire a first mapping relationship between the aircraft's flight speed and the vibration frequency of the piezoelectric ceramic sheet when the wing is not iced, and to acquire a second mapping relationship between the aircraft's flight speed, the vibration frequency of the piezoelectric ceramic sheet, and the ice layer constraint parameters when the wing is iced; the vibration frequency of the piezoelectric ceramic sheet in the first mapping relationship and the second mapping relationship are both acquired under the action of a first voltage;

[0084] The monitoring unit 202 is used to ensure that the piezoelectric ceramic sheet is in a non-vibration energy storage state when the aircraft starts flying, and to start the icing monitoring program at set start intervals according to the set start conditions when the aircraft is in flight. After each start of the icing monitoring program, the first voltage is provided to the piezoelectric ceramic sheet and the monitoring vibration frequency is obtained. In the non-vibration energy storage state, the piezoelectric ceramic sheet charges the energy storage battery under the action of wind pressure.

[0085] The switching unit 204 is used to determine the wing icing state by using the first mapping relationship, the second mapping relationship and the monitored vibration frequency, and to determine whether to switch between the non-vibration energy storage state and the vibration de-icing state based on the determination result.

[0086] In one embodiment of the present invention, the ice layer constraint parameter is the ice layer thickness; the size of the piezoelectric ceramic sheet is no greater than 10 mm.

[0087] In one embodiment of the present invention, the ice layer constraint parameter is the constraint gravity of the piezoelectric ceramic sheet on the ice layer; the constraint gravity is determined based on the product of the ice layer thickness and the ice area; the ice area is determined jointly by multiple piezoelectric ceramic sheets.

[0088] In one embodiment of the present invention, the switching unit is specifically used to: determine the first vibration frequency of the piezoelectric ceramic sheet corresponding to the current aircraft flight speed using the first mapping relationship, and determine whether the monitored vibration frequency is equal to the first vibration frequency; if they are equal, the determination result of the wing icing state is that the wing is not icing, and after the icing monitoring program is started, a non-vibration energy storage state is entered; if they are not equal, the determination result of the wing icing state is that the wing is icing; further, determine the target mapping relationship between the vibration frequency of the piezoelectric ceramic sheet and the ice layer constraint parameter using the second mapping relationship and the current aircraft flight speed, and determine the target ice layer constraint parameter value corresponding to the monitored vibration frequency using the target mapping relationship, and determine whether to switch states based on the target ice layer constraint parameter value.

[0089] In one embodiment of the present invention, when the switching unit performs the process of determining whether to switch states based on the target ice layer constraint parameter value, it specifically includes: determining whether the de-icing condition has been met by utilizing the relationship between the target ice layer constraint parameter value and the de-icing critical value; if the target ice layer constraint parameter value is not less than the de-icing critical value, the de-icing condition is met, and a second voltage is provided to the piezoelectric ceramic sheet to enter the vibration de-icing state, so that the piezoelectric ceramic sheet reaches the resonant frequency, so as to achieve wing de-icing through the vibration of the piezoelectric ceramic sheet; otherwise, if the de-icing condition is not met, a non-vibration energy storage state is entered.

[0090] In one embodiment of the present invention, when the monitoring unit executes the icing monitoring program at preset start-up intervals, it specifically includes:

[0091] The following method is used to determine whether the conditions for the next activation have been met: obtain the monitoring values ​​of the flight parameters, and use the monitoring values ​​of the flight parameters and the state of the piezoelectric ceramic sheet after the most recent activation of the icing monitoring program to calculate the time interval corresponding to the conditions for the next activation.

[0092] In one embodiment of the present invention, the flight parameters include at least:

[0093] The initial values ​​of the ice layer constraint parameters corresponding to the most recent start of the icing monitoring program;

[0094] The average flight speed corresponding to the most recent activation of the icing monitoring program; and

[0095] The average flight altitude since the most recent activation of the icing monitoring program.

[0096] Please refer to Figure 3 The present invention also provides a monitoring and de-icing system, including: the wing passive monitoring and de-icing device as described above, and further including an energy storage battery and a plurality of piezoelectric ceramic plates disposed on the surface of the wing.

[0097] The energy storage battery is connected to the wing passive monitoring and de-icing device and multiple piezoelectric ceramic plates. The wing passive monitoring and de-icing device is also connected to multiple piezoelectric ceramic plates.

[0098] Please refer to Figure 4 This diagram illustrates the arrangement of a piezoelectric ceramic sheet and an airfoil. In one implementation, when the piezoelectric ceramic sheet is placed on the airfoil surface, its polarization direction is parallel to the airfoil. This allows the piezoelectric ceramic sheet to be parallel to the airfoil, resulting in a closer fit. Furthermore, since the piezoelectric ceramic sheet vibrates in all three directions, the polarization intensity parallel to its polarization direction is significantly greater than in other directions. Parallel placement allows the piezoelectric ceramic sheet to achieve maximum polarization intensity in the shear direction against the ice layer on the airfoil.

[0099] It should be noted that the passive wing monitoring and de-icing device provided in the above embodiments is only an example of the division of the above functional modules. In practical applications, the above functions can be assigned to different functional modules as needed, that is, the internal structure of the device can be divided into different functional modules to complete all or part of the functions described above. In addition, the passive wing monitoring and de-icing device provided in the above embodiments and the passive wing monitoring and de-icing method embodiments belong to the same concept, and the specific implementation process is detailed in the method embodiments, which will not be repeated here.

[0100] Embodiments of this application also provide a computer device, please refer to... Figure 5The computer device includes a processor and a memory, the memory storing at least one instruction, at least one program, code set or instruction set, the at least one instruction, at least one program, code set or instruction set being loaded and executed by the processor to implement the wing passive monitoring de-icing method provided in the above method embodiments.

[0101] The embodiments of this application also provide a computer-readable storage medium storing at least one instruction, at least one program, code set, or instruction set, wherein the at least one instruction, at least one program, code set, or instruction set is loaded and executed by a processor to implement the wing passive monitoring de-icing method provided in the above-described method embodiments.

[0102] Embodiments of this application also provide a computer program product, which includes a computer program. A processor of a computer device reads the computer program from a computer-readable storage medium and executes the computer program, causing the computer device to perform any of the wing passive monitoring de-icing methods described in the above embodiments.

[0103] For ease of description, the above systems or devices are described separately as various modules or units based on their functions. Of course, in implementing this application, the functions of each unit can be implemented in one or more software and / or hardware components.

[0104] As can be seen from the above description of the embodiments, those skilled in the art can clearly understand that this application can be implemented by means of software plus necessary general-purpose hardware platforms. Based on this understanding, the technical solution of this application, in essence, or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a storage medium, such as ROM / RAM, magnetic disk, optical disk, etc., and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute the methods described in various embodiments or some parts of the embodiments of this application.

[0105] Finally, it should be noted that in this document, relational terms such as first, second, third, and fourth are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0106] The above description is only a preferred embodiment of this application. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of this application, and these improvements and modifications should also be considered within the scope of protection of this application.

Claims

1. A passive monitoring and de-icing method for airfoils, characterized in that, The de-icing is achieved using a monitoring system, which includes at least an energy storage battery and multiple piezoelectric ceramic plates disposed on the wing surface; the method includes: A first mapping relationship between the aircraft's flight speed and the vibration frequency of the piezoelectric ceramic sheet in the uniced state of the wing is obtained, and a second mapping relationship between the aircraft's flight speed, the vibration frequency of the piezoelectric ceramic sheet, and the ice layer constraint parameters in the iced state of the wing is obtained; the vibration frequency of the piezoelectric ceramic sheet in both the first and second mapping relationships is obtained under the action of a first voltage; When the aircraft begins flight, the piezoelectric ceramic sheet is in a non-vibration energy storage state. During flight, the icing monitoring program is activated at intervals according to the set activation conditions. Each time the icing monitoring program is activated, the first voltage is provided to the piezoelectric ceramic sheet and the monitoring vibration frequency is acquired. In the non-vibration energy storage state, the piezoelectric ceramic sheet charges the energy storage battery under the action of wind pressure. Using the first mapping relationship, the second mapping relationship, and the monitored vibration frequency, the wing icing state is determined, specifically including: using the first mapping relationship to determine the first vibration frequency of the piezoelectric ceramic sheet corresponding to the current aircraft flight speed, and determining whether the monitored vibration frequency is equal to the first vibration frequency; if they are equal, the wing icing state is determined as not icing, and after the icing monitoring program is started, a non-vibration energy storage state is entered; if they are not equal, the wing icing state is determined as icing; further, using the second mapping relationship and the current aircraft flight speed, a target mapping relationship between the piezoelectric ceramic sheet vibration frequency and the ice layer constraint parameter is determined, and the target mapping relationship is used to determine the target ice layer constraint parameter value corresponding to the monitored vibration frequency, and a state switch is determined based on the target ice layer constraint parameter value; Based on the judgment result, it is determined whether to switch between the non-vibration energy storage state and the vibration de-icing state. Specifically, this includes: using the relationship between the target ice layer constraint parameter value and the de-icing critical value to determine whether the de-icing condition has been met; if the target ice layer constraint parameter value is not less than the de-icing critical value, the de-icing condition has been met, and a second voltage is provided to the piezoelectric ceramic sheet to enter the vibration de-icing state, so that the piezoelectric ceramic sheet reaches the resonant frequency, so that the wing de-icing is achieved through the vibration of the piezoelectric ceramic sheet; otherwise, if the de-icing condition has not been met, the non-vibration energy storage state is entered.

2. The method according to claim 1, characterized in that, The ice layer constraint parameter is the ice layer thickness; the size of the piezoelectric ceramic sheet is no greater than 10 mm.

3. The method according to claim 1, characterized in that, The ice layer constraint parameter is the constraint gravity of the piezoelectric ceramic sheet on the ice layer; the constraint gravity is determined by the product of the ice layer thickness and the ice area; the ice area is determined by multiple piezoelectric ceramic sheets.

4. The method according to any one of claims 1-3, characterized in that, The step of activating the icing monitoring program at set activation intervals includes: Use the following method to determine whether the conditions for the next startup have been met: The system acquires the monitored values ​​of flight parameters and uses these values, along with the state of the piezoelectric ceramic sheet since the last activation of the icing monitoring program, to calculate the time interval corresponding to the next activation condition.

5. The method according to claim 4, characterized in that, The flight parameters include at least: The initial values ​​of the ice layer constraint parameters corresponding to the most recent start of the icing monitoring program; The average flight speed corresponding to the most recent activation of the icing monitoring program; and The average flight altitude since the most recent activation of the icing monitoring program.

6. A passive monitoring and de-icing device for airfoils, characterized in that, Located in the monitoring and de-icing system, the monitoring and de-icing system further includes at least an energy storage battery and a plurality of piezoelectric ceramic plates disposed on the wing surface; the device is used to perform the method as described in any one of claims 1-5, the device comprising: The acquisition unit is used to acquire a first mapping relationship between the aircraft's flight speed and the vibration frequency of the piezoelectric ceramic sheet when the wing is not iced, and to acquire a second mapping relationship between the aircraft's flight speed, the vibration frequency of the piezoelectric ceramic sheet, and the ice layer constraint parameters when the wing is iced; the vibration frequency of the piezoelectric ceramic sheet in the first mapping relationship and the second mapping relationship are both acquired under the action of a first voltage; The monitoring unit is used to ensure that the piezoelectric ceramic sheet is in a non-vibration energy storage state when the aircraft starts flying, and to activate the icing monitoring program at set activation intervals during the aircraft's flight. Each time the icing monitoring program is activated, the first voltage is provided to the piezoelectric ceramic sheet and the monitoring vibration frequency is acquired. In the non-vibration energy storage state, the piezoelectric ceramic sheet charges the energy storage battery under wind pressure. The switching unit is used to determine the wing icing state by using the first mapping relationship, the second mapping relationship and the monitored vibration frequency, and to determine whether to switch between the non-vibration energy storage state and the vibration de-icing state based on the determination result.

7. A monitoring and de-icing system, characterized in that, include: The wing passive monitoring and de-icing device as described in claim 6 further includes an energy storage battery and multiple piezoelectric ceramic plates disposed on the surface of the wing.

8. The monitoring and de-icing system according to claim 7, characterized in that, When the piezoelectric ceramic sheet is disposed on the wing surface, the polarization direction of the piezoelectric ceramic sheet is placed parallel to the wing.

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