Supercooled large droplet detector

Abstract

A supercooled large droplet detector capable of accurately and reliably identifying and distinguishing supercooled large droplet icing weather. The supercooled large droplet detector includes a detector base and a detection structure for detecting supercooled droplets in an air flow and for identifying and distinguishing supercooled large droplet icing weather from icing weather, the detection structure having an outer layer of temperature sensor layer, an intermediate layer of electrically heated film layer, and an inner layer of structural base, the electrically heated film layer providing heating energy through a plurality of electrically heated circuits to maintain a uniform temperature on the surface of the detection structure, the temperature sensor layer having a plurality of temperature sensors, and a controller disposed in the structural base, the controller inferring an impact range of a supercooled droplet by temperature changes at a plurality of different locations caused by the supercooled droplet impacting the detection structure, and determining whether the supercooled droplet that was previously impacted was a supercooled large droplet by determining whether the impact range exceeds a critical impact range for a supercooled droplet of a critical size impacting the detection structure.

Description

Technical Field

[0001] This invention relates to a supercooled large water droplet detector, specifically, to a supercooled large water droplet detector with (e.g., spherical) detection structure, used to identify and distinguish supercooled large water droplet icing weather, belonging to the field of icing detection. Background Technology

[0002] The aviation industry has strict requirements regarding icing weather conditions because icing weather can endanger aircraft safety and may pose serious flight risks.

[0003] Icing weather includes icing weather of supercooled water droplets smaller than 50 micrometers (Appendix C of Part 25 of the Civil Aviation Regulations of China) and icing weather of supercooled large water droplets larger than 50 micrometers (Appendix O of the Regulations on Airworthiness Management of Civil Aircraft of the People's Republic of China). Traditional icing detectors can be used to identify icing weather, but they cannot further distinguish between icing weather of supercooled water droplets and icing weather of supercooled large water droplets.

[0004] Typical aircraft anti-icing systems are designed for icing conditions of less than 50 micrometers. Therefore, when an aircraft enters an environment where supercooled water droplets larger than 50 micrometers form icing conditions, the anti-icing capability may be insufficient to cover such conditions, potentially leading to rapid icing and a stall or crash.

[0005] One feasible solution for dealing with supercooled large water droplet icing weather is to immediately initiate an escape maneuver once the detector detects the entry of such weather. Therefore, developing a detector capable of accurately and reliably identifying and distinguishing supercooled large water droplet icing weather is crucial. Summary of the Invention

[0006] The present invention was made to solve the above-mentioned technical problems, and its purpose is to provide a supercooled large water droplet detector, more specifically a supercooled large water droplet detector with a (e.g., spherical) detection structure, which can accurately and reliably identify and distinguish supercooled large water droplet icing weather.

[0007] To achieve the above objectives, the present invention provides a supercooled large water droplet detector, comprising a detector base and a detection structure. The detection structure is characterized in that it is used to detect supercooled water droplets in an airflow and to identify and distinguish from icing weather conditions those supercooled large water droplets exceeding a critical size. The detection structure comprises a three-layer structure: an outer layer of uniformly arranged temperature sensors, a middle layer of electrically heated film, and an inner layer of structural substrate. The electrically heated film, uniformly arranged in the middle layer of the detection structure, provides heating energy through multiple electrically heated circuits located at multiple different positions, ensuring that the surface of the detection structure is heated even without external interference. The temperature remains uniform under the influence of airflow and water droplets. The temperature sensor layer, uniformly arranged on the outer layer of the electric heating film layer, has multiple temperature sensors for real-time detection of surface temperature changes at multiple different locations of the detection structure. A controller is provided in the structural substrate. The controller infers the impact range of the supercooled water droplets by the temperature changes at multiple different locations caused by the impact of the supercooled water droplets on the detection structure. The controller determines whether the previously impacted supercooled water droplets are the supercooled large water droplets by judging whether the impact range exceeds the critical impact range when the supercooled water droplets of the critical size impact the detection structure.

[0008] Based on the above-described configuration, the size of the supercooled water droplets is quantified by measuring the range of temperature changes in the detection structure caused by the supercooled water droplets when they collide with the detection structure of the supercooled large water droplet detector in the airflow. This solves the technical problem that traditional icing detectors can only be used to identify icing weather but cannot further distinguish between icing weather caused by supercooled water droplets and icing weather caused by supercooled large water droplets. By accurately and reliably identifying and distinguishing icing weather caused by supercooled large water droplets, safety incidents caused by insufficient anti-icing capabilities leading to rapid icing and subsequent stall and crash of aircraft can be prevented, thereby improving the safety and airworthiness of aircraft.

[0009] In this invention, the detection structure is preferably spherical. This is because when a sphere collides with the airflow at any direction and angle, the relative position of the airflow with respect to the first stagnation point (the critical impact range of a critically sized supercooled water droplet) and the maximum stagnation point (the maximum impact range of a supercooled water droplet) of the detection structure (i.e., the maximum arc length of the impact area of ​​the first and second regions) remains unchanged. Furthermore, when a supercooled water droplet impacts the detection structure, supercooled water droplets below the critical size only impact the first region between the first stagnation points of the airflow, while large supercooled water droplets exceeding the critical size impact both the first and second regions between the maximum stagnation points of the airflow. Additionally, considering that aircraft, especially civil aircraft, have maximum angles of ascent and descent, it is impossible for them to take off vertically with their noses pointing 90 degrees upwards or downwards. Therefore, as long as the relative position of the airflow with respect to the first and maximum stagnation points of the detection structure remains unchanged within the flight range between the maximum angles of ascent and descent of the aircraft, the detection structure is not limited to a strict sphere; it can also be a substantially spherical structure where the airflow impact area is spherical. Ideally, the part connected to the duct (the non-impact area of ​​the airflow) should be shaped into a streamlined shape suitable for allowing air to flow through with low resistance.

[0010] Preferably, the supercooled large water droplet detector is installed at the nose of the aircraft. The supercooled large water droplet detector also has a curved pipe connecting the detector base to the detection structure. The detector base, which is connected to one end of the pipe, is installed inside the aircraft skin (not shown) and fixed to the airframe structure. The pipe is bent so that the detection structure, which is connected to the other end of the pipe, is parallel to the airflow direction of the aircraft and faces the airflow.

[0011] As described above, this curved pipe design minimizes the impact of the pipe on the airflow field of the detection structure, ensuring that supercooled water droplets in the airflow do not collide with the detection structure.

[0012] In addition, preferably, the multiple temperature sensors transmit the temperature detection value or temperature change value at the corresponding position to the controller through temperature sensor cables, and the multiple electric heating circuits are connected to the controller via power cables. The controller is responsible for providing current to the multiple electric heating circuits of the electric heating film layer and collecting and processing the signals from the multiple temperature sensors of the temperature sensor layer.

[0013] More preferably, the pipe is a hollow pipe, and the temperature sensor cable and the power cable are arranged inside the pipe.

[0014] As described above, by employing a hollow structure, the cables (sensor cables, power cables) connecting the temperature sensor and the electric heating circuit between the detection structure and the detector base (within which the controller is installed) can be arranged inside the pipe, preventing the cables from being exposed to the outside and aging, thereby improving the service life and safety of the detector.

[0015] Preferably, each of the electric heating circuits corresponding to different positions in the electric heating film layer is arranged in a spiral or a U-shape, and the measurement position of the temperature sensor is uniformly arranged at the center of the U-shape or spiral of each of the electric heating circuits in the electric heating film layer.

[0016] As described above, the spiral or U-shaped electric heating circuit can provide uniform heating power to each position, improving temperature stability during use. Furthermore, by uniformly arranging the temperature sensors at the center of the U-shaped or spiral configuration of the electric heating circuit, the measurement consistency of the outer temperature sensors can be guaranteed.

[0017] In addition, preferably, the structural substrate is made of a material that is a poor conductor of heat.

[0018] As described above, the heat generated by the electrically heated film layer in the intermediate layer is primarily conducted to the outer layer of the detection structure.

[0019] Due to current technological limitations, in icing weather conditions, supercooled water droplets below a certain critical size (50 micrometers) can be prevented from icing by aircraft anti-icing systems. However, supercooled large water droplets exceeding this critical size can only be escaped immediately. But with future technological advancements, it's possible that in icing weather conditions where only immediate escape is possible for supercooled large water droplets below another critical size, other actions could be taken instead of just immediate escape. In this case, the other critical size can be considered as the critical size of this invention to identify and distinguish areas where only escape is possible. Alternatively, both the 50-micrometer critical size and the other critical size can be considered as the critical sizes of this invention to identify and distinguish the first area for the first action, the second area for the second action, and the third area for the third action (escape). Thus, the icing weather conditions can involve supercooled water droplets with multiple different critical sizes. The supercooled large water droplet detector can detect the size range of the supercooled water droplets impacting the detection structure to determine the current icing weather condition.

[0020] The size of the detection structure is 30-300 mm. Preferably, the size of the detection structure, the cross-sectional size of the temperature sensor, and the layout size of the electric heating circuit include the following combinations: Combination 1: the size of the detection structure is 50 mm, the cross-sectional size of the temperature sensor is 1 mm, and the layout size of the electric heating circuit is 3 mm; Combination 2: the size of the detection structure is 100 mm, the cross-sectional size of the temperature sensor is 2 mm, and the layout size of the electric heating circuit is 4 mm; Combination 3: the size of the detection structure is 150 mm, the cross-sectional size of the temperature sensor is 3 mm, and the layout size of the electric heating circuit is 5 mm; Combination 4: the size of the detection structure is 200 mm, the cross-sectional size of the temperature sensor is 3 mm, and the layout size of the electric heating circuit is 6 mm. Attached Figure Description

[0021] Figure 1 This is a schematic structural diagram of a supercooled large water droplet detector according to an embodiment of the present invention, used for detecting (identifying and distinguishing) supercooled large water droplet icing weather.

[0022] Figure 2 yes Figure 1 The image shows a cross-sectional view of, for example, a spherical detection structure of a supercooled large water droplet detector.

[0023] Figure 3 This is a layout diagram of the electric heating circuit and temperature sensor arranged in a first form (spiral shape) in the spherical detection structure of the supercooled large water droplet detector of the present invention.

[0024] Figure 4 This is a layout diagram of the electric heating circuit and temperature sensor arranged in a second form (U-shape) within the spherical detection structure of the supercooled large water droplet detector of the present invention.

[0025] (Symbol Explanation)

[0026] 100 supercooled large water droplet detector;

[0027] 200 detector base;

[0028] 300 spherical detection structure;

[0029] 300A First Area

[0030] 300B Second Zone

[0031] 310 temperature sensor layer;

[0032] 311 temperature sensor;

[0033] 312 temperature sensor cable;

[0034] 320 electric heating film layer;

[0035] 321 electric heating circuit;

[0036] 322 power cable;

[0037] 330 spherical structure base;

[0038] 400 pipe;

[0039] 500 controller. Detailed Implementation

[0040] The following is for reference Figures 1 to 4 The structure of the supercooled large water droplet detector 100 of the present invention will be described in detail, wherein, Figure 1 This is a schematic structural diagram of a supercooled large water droplet detector 100 according to an embodiment of the present invention, used for detecting (identifying and distinguishing) supercooled large water droplet icing weather. Figure 2 yes Figure 1 A cross-sectional view of the (e.g., spherical) detection structure 300 of the supercooled large water droplet detector 100 is shown. Additionally, Figure 3 and Figure 4 This is a layout diagram of the electric heating circuit 321 and temperature sensor 311 under two different configurations in the detection structure 300 of the supercooled large water droplet detector of the present invention. Figure 3 It is a spiral layout as the first form, and Figure 4 It is a circular layout in the second form.

[0041] like Figure 1 As shown, the supercooled large water droplet detector 100 of the present invention includes a detector base 200, a detection structure 300, and a pipe 400 connecting the detector base 200 and the detection structure 300.

[0042] The detector base 200 is installed inside the aircraft skin (not shown) and connected to the airframe structure, providing support for the supercooled large water droplet detector 100 of the present invention. Additionally, in this invention, a controller 500 is arranged within the base 200.

[0043] The detection structure 300 is used to detect supercooled water droplets in the airflow and to identify and distinguish supercooled large water droplets exceeding 50 micrometers from icing weather.

[0044] like Figure 2As shown, the detection structure 300 is, for example, spherical and includes a three-layer structure: an outer layer of uniformly arranged temperature sensor layer 310, a middle layer of uniformly arranged electric heating film layer 320, and an inner layer of (e.g., spherical) structural substrate 330. The detection function of supercooled water droplets is achieved by uniformly arranging the electric heating film structure 320 of the middle layer and the temperature sensor 310 of the outer layer on the structural substrate 330 of the inner layer.

[0045] The temperature sensor layer 310, which is uniformly arranged on the outer layer of the electric heating film layer 320, has multiple temperature sensors 311 for real-time detection of surface temperature changes at multiple locations (different locations) of the detection structure 300, and transmits the temperature detection value or temperature change value to the controller 500 for analysis via temperature sensor cable 312.

[0046] The electrically heated film layer 320, uniformly arranged in the intermediate layer of the structural substrate 330, provides heating energy through multiple electrically heated circuits 321 connected by power cables 322, ensuring that the surface of the detection structure 300 maintains a uniform temperature when there is no external airflow or water droplet interference. It should be noted that the electrically heated film layer 320 should maintain temperature stability during use and should have a certain adjustable temperature range, for example, 100–130°C.

[0047] ℃. In order to provide uniform heating power, the layout of each electric heating circuit 321 in the electric heating film layer 320 corresponding to different positions can be adopted. Figure 3 The spiral layout shown is the first configuration (i.e., each electric heating circuit 321 is arranged in a spiral shape) or Figure 4 The second form shown is a U-shaped layout (i.e., each electric heating circuit 321 is arranged in a U-shape). In addition, in order to ensure the measurement consistency of the outer layer temperature sensor 311, the measurement position of the temperature sensor 311 is uniformly arranged at the center of the U-shape or spiral of each electric heating circuit 321 of the electric heating film layer 320.

[0048] The inner structural substrate 330 is made of a non-metallic, poorly conductive material, so that the heat generated by the electric heating film layer 320 in the middle layer is mainly conducted to the outer side of the detection structure 300.

[0049] One end of the pipe 400 is connected to the detector base 200, and the other end is connected to the detection structure 300. The pipe 400 is hollow and curved. By employing a hollow structure, the cables (sensor cable 312, power cable 322) connecting the temperature sensor 311 and the electric heating circuit 321 between the detection structure 300 and the detector base 200 (with the controller 500 installed inside) can be arranged inside the pipe 400. Furthermore, this curved pipe design ensures that the detection structure 300, connected to the other end of the pipe 400, is substantially parallel to the aircraft's airflow direction, minimizing the impact of the pipe 400 on the airflow field of the detection structure 300 and ensuring minimal impact of supercooled water droplets in the airflow on the detection structure 300.

[0050] The controller 500 is responsible for providing current to the electric heating circuit 321 of the electric heating film layer 320 and collecting and processing the signals from the temperature sensor 311 of the temperature sensor layer 310. The temperature sensor 311 used therein should have high accuracy in order to accurately determine the temperature changes at multiple locations (different locations) caused by the impact of the supercooled water droplet, thereby inferring the impact range of the supercooled water droplet.

[0051] The supercooled large water droplet detector 100 of the present invention is installed at the nose of the aircraft. When the aircraft is powered on, the supercooled large water droplet detector 100 starts to work. The controller 500 supplies power to the electric heating film layer 320 of the middle layer of the detection structure 300. Each electric heating circuit 321 is provided with the same voltage and current, so that the detection structure 300 is uniformly heated and the temperature is maintained between 100 and 130°C.

[0052] When supercooled water droplets are present in the airflow, they will impact the surface of the detection structure 300. The impact limit of supercooled water droplets larger than 50 micrometers (large supercooled water droplets) on the surface of the detection structure 300 is greater than that of supercooled water droplets smaller than 50 micrometers (ordinary water droplets). Simultaneously, the heat in the impacted area is carried away by the impacted water droplets, resulting in a significant temperature difference between this area (impacted area) and the non-impacted area. The controller 500 analyzes the surface temperature data of the detection structure 300 to determine the impact range (impacted area) of the supercooled water droplets on the surface of the detection structure 300. It then compares this impact range (impacted area) with the impact range of a 50-micrometer supercooled water droplet to determine whether the previously impacted water droplets were supercooled water droplets larger than 50 micrometers (large supercooled water droplets), thereby identifying and distinguishing whether the system is in (or has entered) a supercooled water droplet icing weather condition.

[0053] exist Figure 1In this process, supercooled water droplets smaller than 50 micrometers (ordinary water droplets) will only collide with the first region 300A, while supercooled water droplets larger than 50 micrometers will collide with the second region 300B at the same time as colliding with the first region 300A. That is, the critical line between the first region 300A and the second region 300B (i.e., the maximum arc length of the first region 300A) is the first stagnation point (or the critical impact range of supercooled water droplets of critical size) when a 50-micrometer supercooled water droplet collides with the detection structure 300. The maximum arc length of the second region 300B is the maximum stagnation point (or the maximum impact range of supercooled water droplets) when a supercooled water droplet collides with the detection structure 300. At this point, no matter how large the supercooled water droplet is, it is impossible for it to collide with any region other than the first region 300A and the second region 300B of the detection structure 300. When the flight angle changes, the actual positions of the first region 300A and the second region 300B on the detection structure 300 will change, but the relative positions of the airflow with respect to the first stagnation point (critical impact range of supercooled water droplets of critical size) and the maximum stagnation point (maximum impact range of supercooled water droplets) of the detection structure 300 (i.e., the maximum arc length of the impact area of ​​the first region 300A and the second region 300B) will not change. When passing through clouds, if the impact area of ​​a supercooled water droplet increases and exceeds the first region 300 Å (i.e., the arc length of the impact area is greater than the maximum arc length of the first region 300 Å), it can be determined that the previously impacted water droplet was a supercooled water droplet larger than 50 micrometers (a supercooled large water droplet), and is currently in (or has entered) a supercooled large water droplet icing weather. Conversely, if the impact area of ​​a supercooled water droplet does not exceed the first region 300 Å (i.e., the arc length of the impact area is less than the maximum arc length of the first region 300 Å), it is determined that the previously impacted water droplet was not a supercooled large water droplet, and is not in (or has entered) a supercooled large water droplet icing weather.

[0054] Furthermore, in this invention, a spherical detection structure 300 with heating function is used, for example, and the detection of the diameter of supercooled water droplets (i.e., the judgment of large supercooled water droplets) is transformed into the detection of temperature distribution based on aerodynamic principles. When the diameter of the spherical detection structure 300 increases, the area (i.e., the second region) in which supercooled water droplets larger than 50 micrometers (large supercooled water droplets) impact the spherical detection structure 300, which is different from supercooled water droplets smaller than 50 micrometers (ordinary water droplets), becomes larger. Thus, under the same detection requirements, it is not necessary to use expensive and highly sensitive small-sized temperature sensors. However, since the supercooled large water droplet detector 100 is used on an aircraft, compact structure and easy installation are still preferred factors.

[0055] In this invention, the size of the (spherical) detection structure 300 is not a fixed value, but the following two factors are mainly considered when determining a suitable size:

[0056] (1) On the one hand, the larger the diameter of the detection structure 300, the more accurate and sensitive the temperature field distribution measurement of the surface of the detection structure 300 will be by the temperature sensor 311 of the same size. However, the large size of the detection structure 300 (and the more accurate measurement of the temperature field distribution) will bring the disadvantage of increased power consumption of the device.

[0057] (2) On the other hand, the smaller the diameter of the detection structure 300, the lower the measurement accuracy and sensitivity of the temperature field distribution on the surface of the detection structure 300 by the temperature sensor 311 of the same size. At the same time, the smaller the diameter of the detection structure 300, the smaller, more expensive and more sensitive the temperature sensor 311 is required, and a more refined layout of the electric heating circuit 321 is required.

[0058] In summary, taking into account various factors, the preferred size of the detection structure 300 of the present invention can be between 30 and 300 mm. The combination of the size of the detection structure 300, the size of the heating circuit, and the cross-sectional size of the temperature sensor can be exemplarily taken as shown in Table 1 below. However, those skilled in the art should know that the dimensions of the present invention should not be limited to the size combinations shown in Table 1.

[0059] Table 1:

[0060]

[0061] Other advantages and modifications will readily occur to those skilled in the art. Therefore, more broadly, the invention is not limited to the specific details and representative embodiments shown and described herein. Thus, modifications can be made without departing from the spirit or scope of the overall inventive concept as defined by the appended claims and their equivalents.

[0062] For example, in this invention, a spherical detection structure 300 is described. This is an example where the sphere collides with the airflow at any direction and angle. The relative positions of the airflow with respect to the first stagnation point (critical impact range of the supercooled water droplet of critical size) and the maximum stagnation point (maximum impact range of the supercooled water droplet) of the detection structure 300 (i.e., the maximum arc length of the impact area of ​​the first region 300A and the second region 300B) do not change. However, considering that aircraft, especially civil aircraft, have maximum angles of climb and pitch, as long as the maximum angle of climb of the aircraft is maintained... Within the flight range between the pitch angles, if the relative positions of the airflow with respect to the first stagnation point (critical impact range of the supercooled water droplet of critical size) and the maximum stagnation point (maximum impact range of the supercooled water droplet) of the detection structure 300 (i.e., the maximum arc length of the impact area of ​​the first region and the second region) do not change, then the detection structure 300 is not limited to a sphere in the strict sense, but can also be a substantial sphere in which the airflow impact area is spherical. In this case, it is preferable to form the part connected to the pipe 400 (the non-impact area of ​​the airflow) into a streamline shape suitable for allowing air to flow through with low resistance.

[0063] In addition, in this invention, 50 micrometers is used as the critical size that distinguishes the supercooled water droplets from the supercooled large water droplets. However, this invention is not limited to this and does not exclude the possibility that in the future, from the perspective of airworthiness, the critical size may be further divided, that is, it may be any suitable value other than 50 micrometers.

[0064] Furthermore, under current technology, icing of supercooled water droplets smaller than 50 micrometers can be prevented by the aircraft's anti-icing system, while icing of large supercooled water droplets larger than 50 micrometers will immediately trigger an escape maneuver. However, with future technological advancements, it is possible that in icing conditions below a first size (e.g., 50 micrometers), the aircraft will employ a first action (e.g., preventing icing through the aircraft's anti-icing system); in icing conditions exceeding the first size but below the second size, the aircraft will employ a second action; and in icing conditions exceeding the second size, the aircraft will employ a third action (e.g., immediately triggering an escape maneuver). In this case, the second size, different from the first size, can be used as the same critical point as in the aforementioned embodiment to identify and distinguish the first region 300A that performs the anti-icing action and the second region 300B that performs the escape maneuver. Alternatively, both the first and second sizes can be used as the same critical points as in the aforementioned embodiment to identify and distinguish the first region that performs the first action, the second region that performs the second action, and the third region that performs the third action.

Claims

1. A supercooled large water droplet detector, comprising a detector base and a detection structure, Its features are, The detection structure is used to detect supercooled water droplets in the airflow and to identify and distinguish from icing weather conditions large supercooled water droplets exceeding the critical size. The detection structure comprises three layers: an outer layer of uniformly arranged temperature sensors, a middle layer of electrically heated film, and an inner layer of structural substrate. The electrically heated film layer, uniformly arranged in the middle layer of the detection structure, provides heating energy through multiple electrically heated circuits located at various positions, ensuring that the surface of the detection structure maintains a uniform temperature when there is no external airflow or water droplet interference. The temperature sensor layer, uniformly arranged on the outer layer of the electric heating film layer, has multiple temperature sensors for real-time detection of surface temperature changes at multiple different locations of the detection structure. A controller is provided in the structural substrate. The controller infers the impact range of the supercooled water droplet by the temperature change at multiple different locations caused by the impact of the supercooled water droplet on the detection structure. The controller determines whether the previously impacted supercooled water droplet is the supercooled large water droplet by judging whether the impact range exceeds the critical impact range when the supercooled water droplet of the critical size impacts the detection structure.

2. The supercooled large water droplet detector as described in claim 1, characterized in that, The detection structure is spherical or substantially spherical.

3. The supercooled large water droplet detector as described in claim 2, characterized in that, The critical impact range when a supercooled water droplet of the critical size impacts the detection structure is the first stagnation point of the airflow. The maximum impact range when supercooled water droplets strike the detection structure is the point of maximum airflow stagnation. When the airflow collides with the detection structure at any direction and angle within the flight range between the maximum angle of ascent and maximum angle of depression of the aircraft, the relative positions of the first stagnation point and the maximum stagnation point of the airflow do not change.

4. The supercooled large water droplet detector as described in claim 3, characterized in that, When supercooled water droplets impact the detection structure, supercooled water droplets below the critical size only impact the first region between the first stagnation points of the airflow, while supercooled large water droplets exceeding the critical size impact the second region between the maximum stagnation points of the airflow while impacting the first region.

5. The supercooled large water droplet detector as described in claim 3, characterized in that, The supercooled large water droplet detector is installed at the nose of the aircraft. The supercooled large water droplet detector also has a curved pipe connecting the detector base to the detection structure. The detector base, connected to one end of the pipe, is installed inside the aircraft skin and fixed to the airframe structure. The pipe is bent so that the detection structure connected to the other end of the pipe is parallel to the direction of the aircraft's airflow and faces the airflow.

6. The supercooled large water droplet detector as described in claim 5, characterized in that, The part connected to the duct, i.e. the non-impact area of ​​the airflow, is shaped into a streamlined shape suitable for low-resistance airflow.

7. The supercooled large water droplet detector as described in claim 5, characterized in that, Each of the multiple temperature sensors transmits the temperature detection value or temperature change value at its corresponding location to the controller via temperature sensor cables. Multiple electric heating circuits are connected to the controller via power cables. The controller is responsible for providing current to multiple electric heating circuits of the electric heating film layer and collecting signals from multiple temperature sensors of the temperature sensor layer and processing the data.

8. The supercooled large water droplet detector as described in claim 7, characterized in that, The pipe is a hollow pipe. The temperature sensor cable and the power cable are arranged inside the pipe.

9. The supercooled large water droplet detector as described in any one of claims 1 to 8, characterized in that, Each of the electric heating circuits corresponding to different positions in the electric heating film layer is arranged in a spiral shape or a U-shape. The temperature sensors are uniformly arranged at the center of each electric heating circuit in the electric heating film layer, either in a U-shape or a spiral.

10. The supercooled large water droplet detector as described in any one of claims 1 to 8, characterized in that, The structural substrate is made of a material that is a poor conductor of heat.

11. The supercooled large water droplet detector as described in any one of claims 1 to 8, characterized in that, The icing meteorology described here involves icing meteorology with multiple supercooled water droplets of different critical sizes. The supercooled water droplet detector can detect the size range of supercooled water droplets impacting the detection structure to determine the current icing weather conditions.

12. The supercooled large water droplet detector as described in any one of claims 1 to 8, characterized in that, The size of the detection structure is 30–300 mm. The dimensions of the detection structure, the cross-sectional dimensions of the temperature sensor, and the layout dimensions of the electric heating circuit include the following combinations: Combination 1, namely, the size of the detection structure is 50mm, the cross-sectional size of the temperature sensor is 1mm, and the layout size of the electric heating circuit is 3mm; Combination 2, namely, the size of the detection structure is 100mm, the cross-sectional size of the temperature sensor is 2mm, and the layout size of the electric heating circuit is 4mm; Combination 3, namely, the size of the detection structure is 150mm, the cross-sectional size of the temperature sensor is 3mm, and the layout size of the electric heating circuit is 5mm; Combination 4, namely, the size of the detection structure is 200mm, the cross-sectional size of the temperature sensor is 3mm, and the layout size of the electric heating circuit is 6mm.

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