WO2025107828A1 - Super-cooled large droplet detector - Google Patents

Abstract

A super-cooled large droplet detector, which can accurately and reliably identify and distinguish super-cooled large droplet freezing weather. The super-cooled large droplet detector comprises a detector base and a detection structure, wherein the detection structure is used for detecting super-cooled droplets in airflow and for identifying freezing weather and distinguishing super-cooled large droplet freezing weather from the freezing weather; an outer layer of the detection structure is a temperature sensor layer, an intermediate layer thereof is an electric heating film layer, and an inner layer thereof is a structure substrate; the electric heating film layer provides heating energy by means of a plurality of electric heating loops, such that the surface of the detection structure maintains at a uniform temperature; the temperature sensor layer is provided with a plurality of temperature sensors; and a controller is provided in the structure substrate, and the controller infers an impact range of the super-cooled droplets by means of temperature changes, which are caused by the super-cooled large droplets impacting the detection structure, at a plurality of different positions, and determines, by means of determining whether the impact range exceeds a critical impact range obtained when the super-cooled droplets exceeding a critical size impact the detection structure, whether the previous impacting super-cooled droplets are super-cooled large droplets.

Description

Supercooled large water droplet detector Technical Field

The present invention relates to a supercooled large water drop detector, in particular to a supercooled large water drop detector with a (for example, spherical) detection structure, which is used to identify and distinguish supercooled large water drop freezing weather and belongs to the field of ice detection.

Background Art

The aviation industry has strict requirements on icing weather because icing weather can endanger the safety of aircraft and may pose serious flight risks to aircraft.

Icing weather includes supercooled water droplets below 50 microns (Appendix C of Part 25 of the Civil Aviation Regulations of China) and supercooled large water droplets over 50 microns (Appendix 0 of the Civil Aircraft Airworthiness Management Regulations of the People's Republic of China). Traditional icing detectors can be used to identify icing weather, but they cannot further distinguish whether it is supercooled water droplets or supercooled large water droplets.

Conventional aircraft anti-icing systems are designed based on icing weather conditions with a particle size of less than 50 microns. Therefore, when an aircraft enters an icing weather condition with supercooled large droplets exceeding 50 microns, the anti-icing capability is insufficient to cover this type of icing weather, and the aircraft may freeze rapidly and then stall and crash, which is a safety incident.

At present, a feasible solution for supercooled large water droplet icing weather is to immediately execute an escape action once the detector recognizes that it has entered supercooled large water droplet icing weather. To this end, it is very important to develop a detector that can accurately and reliably identify and distinguish supercooled large water droplet icing weather.

Summary of the invention

The present invention is made to solve the above technical problems, and its purpose is to provide a supercooled A water drop detector, more specifically a supercooled large water drop detector having a (eg spherical) detection structure, can accurately and reliably identify and distinguish supercooled large water drop icing weather.

In order to achieve the above-mentioned purpose, the present invention provides a supercooled large water droplet detector, including a detector base and a detection structure, wherein the detection structure is used to detect supercooled water droplets in the airflow and to identify and distinguish from icing weather the icing weather in which the supercooled water droplets exceed a critical size of supercooled large water droplets, and the detection structure includes a three-layer structure, an outer layer is a uniformly arranged temperature sensor layer, a middle layer is an electric heating film layer, and an inner layer is a structural base, and the electric heating film layer uniformly arranged in the middle layer of the detection structure provides heating energy through a plurality of electric heating circuits located at a plurality of different positions, so that the surface of the detection structure is free from external The temperature is kept uniform when impacted by 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 positions of the detection structure. A controller is arranged in the base of the structure. The controller infers the impact range of the supercooled water droplets through the temperature changes at the multiple different positions caused by the supercooled water droplets impacting the detection structure, and 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.

According to the structure as described above, when supercooled water droplets of different sizes in the airflow hit the detection structure of the supercooled large water droplet detector, the size of the supercooled water droplets is quantified by the position range of the temperature change of the detection structure caused by the supercooled water droplets, thereby solving the technical problem that traditional icing detectors can only be used to identify icing weather but cannot further distinguish whether it is supercooled water droplet icing weather or supercooled large water droplet icing weather. By accurately and reliably identifying and distinguishing supercooled large water droplet icing weather, safety incidents such as rapid freezing of the aircraft and subsequent stall and crash due to insufficient anti-icing capability can be prevented, thereby improving the safety and airworthiness of the aircraft.

In the present invention, the detection structure is preferably spherical. This is because the sphere collides with the airflow in any direction and angle, and the airflow is relatively stable relative to the first stagnation point (critical impact range of supercooled water droplets of critical size) and the maximum stagnation point (supercooled water droplet) of the detection structure. In addition, when supercooled water droplets impact the detection structure, supercooled water droplets below the critical size only impact the first area between the first stagnation points of the airflow, while supercooled large water droplets exceeding the critical size impact the second area between the maximum stagnation points of the airflow while impacting the first area. In addition, considering that aircraft, especially civil aircraft, have maximum lift and pitch angles, it is impossible for the nose to rise vertically with 90 degrees upward, nor is it possible for the nose to fall vertically with 90 degrees downward. Therefore, as long as it is ensured that the relative position of the airflow relative to the first stagnation point and the maximum stagnation point of the detection structure does not change within the flight range between the maximum lift and pitch angles of the aircraft, the detection structure is not limited to a sphere in the strict sense, but may also be a substantially spherical shape with a spherical airflow impact area. At this time, it is ideal to form the portion connected to the pipe (airflow non-impact area) into a streamlined shape suitable for air to flow through with low resistance.

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

According to the structure as described above, the curved pipe can minimize the influence of the pipe on the air flow field of the detection structure, so as to ensure that the supercooled water droplets in the air flow collide with the detection structure.

In addition, preferably, the multiple temperature sensors respectively transmit the temperature detection values or temperature change values at the corresponding positions to the controller through the temperature sensor cables, and the multiple electric heating circuits are connected to the controller using power cables. The controller is responsible for providing current to the multiple electric heating circuits of the electric heating film layer and collecting the signals of the multiple temperature sensors of the temperature sensor layer and performing data processing.

It is further preferred that the pipe is a hollow pipe, and the temperature sensor line The cable and the powered cable are arranged inside the pipe.

According to the configuration as described above, by adopting a hollow structure, the temperature sensor connected between the detection structure and the detector base (controller installed inside) and the cables of the electric heating circuit (sensor cable, power cable) can be arranged inside the pipe to prevent the cables from being exposed to the outside and aging, thereby improving the service life and safety of the detector.

Preferably, each of the electric heating loops corresponding to different positions in the electric heating film layer is arranged in a spiral shape or a U-shape, and the measuring position of the temperature sensor is uniformly arranged at the exact center of the U-shape or spiral of each of the electric heating loops in the electric heating film layer.

According to the above structure, the electric heating circuit with a spiral arrangement or a U-shaped arrangement can provide uniform heating power for each position, thereby improving the temperature stability during use. In addition, by uniformly arranging the measurement position of the temperature sensor at the exact center of the U-shaped or spiral shape of the electric heating circuit, the measurement consistency of the temperature sensor of the outer layer can be ensured.

In addition, it is preferred that the structural base is made of a material that is a poor thermal conductor.

According to the above-described structure, the heat generated by the electric heating film layer of the intermediate layer can be mainly conducted toward the outer layer side of the detection structure.

Limited by the current technical level, in icing weather, supercooled water droplets below a certain critical size (50 microns) can be prevented from freezing by the aircraft anti-icing system, while supercooled large water droplets exceeding the critical size can only be immediately escaped. However, it is not ruled out that with the development of future technology, in the current supercooled large water droplets icing weather where only escape can be performed immediately, for icing weather where supercooled water droplets are below another critical size, other actions can be taken instead of just immediately executing the escape action. At this time, the other critical size can be regarded as the critical size of the present invention to identify and distinguish the area where only escape can be performed, or the critical size of 50 microns and the other critical size can be regarded as the critical size of the present invention at the same time. The first area for performing the first action, the second area for performing the second action, and the third area for performing the third action (escape action) are identified and distinguished by the detection structure. Thus, the icing weather has icing weather with multiple supercooled water droplets of different critical sizes, and the supercooled large water droplet detector can detect the size range of the supercooled water droplets that hit the detection structure to determine the current icing weather.

The size of the detection structure is 30-300mm, and the size of the detection structure, the cross-sectional size of the temperature sensor, and the layout size of the electric heating circuit preferably include the following combinations: Combination 1, i.e., 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, i.e., 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, i.e., 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, i.e., 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.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG1 is a schematic structural diagram of a supercooled large water droplet detector for detecting (identifying and distinguishing) supercooled large water droplet icing weather according to an embodiment of the present invention.

FIG. 2 is a cross-sectional view of a spherical detection structure of the supercooled large water droplet detector shown in FIG. 1 .

FIG3 is a layout diagram of an electric heating circuit and a temperature sensor in a first form (spiral shape) in the spherical detection structure of the supercooled large water droplet detector of the present invention.

FIG. 4 is a layout diagram of an electric heating circuit and a temperature sensor in a second form (U-shaped) layout in the spherical detection structure of the supercooled large water droplet detector of the present invention.

(Explanation of symbols)

100  Supercooled large water drop detector;

200  Detector base;

300  Spherical detection structure;

300A First Area

300B Second Area

310  Temperature sensor layer;

311  Temperature sensor;

312  Temperature sensor cable;

320  Electric heating film layer;

321  Electric heating circuit;

322  Electrical cables;

330  Spherical structure base;

400 pipelines;

500 controller.

DETAILED DESCRIPTION

Hereinafter, the structure of the supercooled large water drop detector 100 of the present invention will be described in detail with reference to FIGS. 1 to 4 , wherein FIG. 1 is a schematic structural diagram of a supercooled large water drop detector 100 for detecting (identifying and distinguishing) supercooled large water drop icing weather according to an embodiment of the present invention, and FIG. 2 is a cross-sectional view of a (e.g., spherical) detection structure 300 of the supercooled large water drop detector 100 shown in FIG. 1 . In addition, FIGS. 3 and 4 are layout diagrams of an electric heating circuit 321 and a temperature sensor 311 in two forms in the detection structure 300 of the supercooled large water drop detector of the present invention, wherein FIG. 3 is a spiral layout as a first form, and FIG. 4 is a U-shaped layout as a second form.

As shown in FIG. 1 , 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 .

The detector base 200 is installed inside the aircraft skin (not shown) and is connected to the aircraft body. The base 200 is connected to the controller 500 to provide support for the supercooled large water drop detector 100 of the present invention. In addition, in the present invention, the controller 500 is arranged in the base 200.

The detection structure 300 is used to detect supercooled water droplets in the airflow and to identify and distinguish supercooled large water droplet icing weather with supercooled water droplets exceeding 50 microns from icing weather. As shown in FIG2 , the detection structure 300 is, for example, spherical, and includes a three-layer structure, an outer layer is a uniformly arranged temperature sensor layer 310, a middle layer is a uniformly arranged electric heating film layer 320, and an inner layer is a (for example, spherical) structural base 330, and the detection function of supercooled water droplets is realized 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 base 330 of the inner layer.

The temperature sensor layer 310 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 positions (different positions) of the detection structure 300, and transmits the temperature detection value or temperature change value to the controller 500 for analysis through the temperature sensor cable 312.

The electric heating film layer 320 uniformly arranged on the middle layer of the structural base 330 provides heating energy through a plurality of electric heating loops 321 connected by energized cables 322, so that the surface of the detection structure 300 is kept at a uniform temperature when there is no external airflow and water droplets. Here, it should be noted that the electric heating film layer 320 should maintain temperature stability during use and should have a certain adjustable temperature range, such as 100-130°C. In order to provide uniform heating power, the layout of each electric heating loop 321 corresponding to different positions in the electric heating film layer 320 can adopt a spiral layout as a first form shown in FIG3 (that is, each electric heating loop 321 is arranged in a spiral shape) or a Chinese-shaped layout as a second form shown in FIG4 (that is, each electric heating loop 321 is arranged in a Chinese-shaped shape). In addition, in order to ensure the measurement consistency of the temperature sensor 311 of the outer layer, the measurement position of the temperature sensor 311 is uniformly arranged at the center of the Chinese-shaped or spiral shape of each electric heating loop 321 of the electric heating film layer 320.

The inner structural base 330 is made of non-metal or other poor thermal conductor materials, so that the heat generated by the electric heating film layer 320 of the middle layer is mainly conducted to the outer layer side of the detection structure 300.

One end of the pipe 400 is connected to the detector base 200, and the other end is connected to the detection structure 300, and the pipe 400 is a hollow and curved pipe. By adopting a hollow structure, the temperature sensor 311 connected between the detection structure 300 and the detector base 200 (the controller 500 disposed therein) and the cables (sensor cable 312, power cable 322) of the electric heating circuit 321 can be arranged inside the pipe 400. In addition, through this curved pipe design, the detection structure 300 connected to the other end of the pipe 400 is basically parallel to the airflow direction of the aircraft and faces the airflow, which minimizes the influence of the pipe 400 on the air flow field of the detection structure 300, so as to ensure that the supercooled water droplets in the airflow collide with the detection structure 300.

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 of the temperature sensor 311 of the temperature sensor layer 310. The temperature sensor 311 used therein should have high accuracy so as to accurately determine the temperature changes at multiple locations (different locations) caused by the impact of the supercooled water droplets, thereby inferring the impact range of the supercooled water droplets.

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

When there are supercooled water droplets in the airflow, the supercooled water droplets will impact the surface of the detection structure 300. The impact limit range of supercooled water droplets larger than 50 microns (supercooled large water droplets) on the surface of the detection structure 300 is greater than the impact range of supercooled water droplets (ordinary water droplets) smaller than 50 microns. At the same time, the heat of the impacted area will be taken 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, and then compares the impact range (impacted area) with the impact range of 50 microns of supercooled large water droplets to determine whether the previously impacted water droplets are supercooled water droplets larger than 50 microns (supercooled large water droplets), thereby To identify and distinguish whether it is in (or entering) supercooled large droplet icing weather.

In FIG1 , supercooled water droplets (ordinary water droplets) smaller than 50 microns will only hit the first area 300A, while supercooled water droplets larger than 50 microns will hit the second area 300B while hitting the first area 300A. That is, the critical line between the first area 300A and the second area 300B (that is, the maximum arc length of the first area 300A) is the first stagnation point when the supercooled water droplets of 50 microns hit the detection structure 300 (or the critical impact range of the supercooled water droplets of critical size), and the maximum arc length of the second area 300B is the maximum stagnation point when the supercooled water droplets hit the detection structure 300 (or the maximum impact range of the supercooled water droplets). At this time, no matter how large the supercooled water droplets are, it is impossible for them to hit other areas of the detection structure 300 other than the first area 300A and the second area 300B. When the flight angle changes, the actual positions of the first area 300A and the second area 300B in the detection structure 300 will change, but the relative positions of the airflow relative 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 area 300A and the second area 300B) will not change. When passing through clouds, if the impact area of the supercooled water droplets in flight increases and exceeds the first area 300A (i.e., the arc length of the impact area is greater than the maximum arc length of the first area 300A), it can be determined that the previously impacted water droplets are supercooled water droplets larger than 50 microns (supercooled large water droplets), and the current situation is (or has entered) supercooled large water droplet freezing weather. On the contrary, if the impact area of the supercooled water droplets in flight does not exceed the first area 300A (i.e., the arc length of the impact area is less than the maximum arc length of the first area 300A), it is determined that the previously impacted water droplets are not supercooled large water droplets, and are not in (or have entered) supercooled large water droplet freezing weather.

In addition, in the present invention, a detection structure 300, for example, which is spherical and has a heating function, is used, and based on the aerodynamic principle, the detection of the diameter of the supercooled water droplets (i.e., the judgment of the supercooled large water droplets) is converted into the detection of the temperature distribution. When the diameter of the spherical detection structure 300 increases, the area (i.e., the second area) where the supercooled water droplets exceeding 50 microns (supercooled large water droplets) hit the spherical detection structure 300 becomes larger than the supercooled water droplets (ordinary water droplets) below 50 microns. Therefore, under the same detection requirements, there is no need to use an expensive and highly sensitive small-sized temperature sensor. However, the supercooled large water droplet detector 100 is used in aircraft. When it comes to use, compact structure and easy installation are still the factors that should be given priority consideration.

In the present invention, the size of the (spherical) detection structure 300 is not a fixed value, but the following two factors are mainly considered when determining the appropriate size:

(1) On the one hand, the larger the diameter of the detection structure 300 is, the more accurate and sensitive the temperature sensor 311 of the same size is in measuring the temperature field distribution on the surface of the detection structure 300. However, a large-sized detection structure 300 (and a more accurate measurement of the temperature field distribution) will bring about the disadvantage of increased power consumption of the device;

(2) On the other hand, the smaller the diameter of the detection structure 300, the lower the measurement accuracy and sensitivity of the temperature sensor 311 of the same size to the temperature field distribution on the surface of the detection structure 300. 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 the layout of the electric heating circuit 321 is required to be more sophisticated.

In summary, taking various factors into consideration, the size of the preferred detection structure 300 of the present invention can be between 30 and 300 mm, and the size of the detection structure 300 and the combination of the heating circuit size 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 dimension combinations shown in Table 1.

Table 1:

Additional advantages and modifications will readily occur to those skilled in the art. Therefore, the invention in its broader aspects is not limited to the specific details shown and described herein. Accordingly, modifications may be made without departing from the spirit or scope of the general inventive concept as defined by the appended claims and their equivalents.

For example, in the present invention, the detection structure 300 is listed as a spherical detection structure for explanation. This is when the sphere collides with the airflow in any direction and angle. The relative position of the airflow relative 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 area 300A and the second area 300B) will not change. However, considering that aircraft, especially civil aircraft, have maximum lift angles and pitch angles, as long as the maximum lift angle and pitch angle of the aircraft are guaranteed, the maximum lift angle and pitch angle of the aircraft can be adjusted. Within the flight range between the depression angles, the relative position of the airflow relative 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 area and the second area) does not change. The detection structure 300 is not limited to a sphere in a strict sense, but can also be a substantially spherical shape with a spherical airflow impact area. In this case, it is preferred that the portion connected to the pipe 400 (airflow non-impact area) is formed into a streamlined shape suitable for air to flow through with low resistance.

In addition, in the present invention, 50 microns is used as the critical size of the supercooled water droplets that are distinguished from the supercooled large water droplets, but the present invention is not limited to this, and does not rule out further division of the critical size from the perspective of airworthiness in the future, that is, it can also be any suitable value other than 50 microns.

In addition, under the current technology, supercooled water droplets below 50 microns can be prevented from freezing by the aircraft anti-icing system, while supercooled large water droplets exceeding 50 microns will immediately execute an escape action. However, it is not ruled out that with the development of future technology, in icing weather below a first size (e.g., 50 microns), the aircraft will adopt a first action (e.g., prevent freezing through the aircraft anti-icing system), in icing weather exceeding the first size and below the second size, the aircraft will adopt a second action, and in icing weather exceeding the second size, the aircraft will adopt a third action (e.g., immediately execute an escape action). At this time, 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 area 300A for executing the anti-icing action and the second area 300B for executing the escape action, and the first size can also be used as the critical point. The first area for performing the first action, the second area for performing the second action, and the third area for performing the third action are identified and distinguished as the critical points in the aforementioned embodiment.

Claims (12)

A supercooled large water drop detector comprises a detector base and a detection structure. It is characterized in that The detection structure is used to detect supercooled water droplets in the airflow and to identify and distinguish icing weather in which the supercooled water droplets exceed a critical size from icing weather. The detection structure includes a three-layer structure, the outer layer is a uniformly arranged temperature sensor layer, the middle layer is an electric heating film layer, and the inner layer is a structural base. The electric heating film layer uniformly arranged on the middle layer of the detection structure provides heating energy through multiple electric heating circuits located at multiple different positions, so that the surface of the detection structure is kept at a uniform temperature when there is no external airflow and water droplets. The temperature sensor layer uniformly arranged on the outer layer of the electric heating film layer has a plurality of temperature sensors for real-time detection of surface temperature changes at the plurality of different positions of the detection structure. A controller is provided in the structural base, and the controller infers the impact range of the supercooled water droplet through the temperature changes at the multiple different positions caused by the supercooled water droplet impacting the detection structure, and determines whether the supercooled water droplet that previously impacted 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. The supercooled large water drop detector according to claim 1, characterized in that: The detection structure is spherical or substantially spherical. The supercooled large water drop detector according to claim 2, characterized in that: The critical impact range when the supercooled water droplet of the critical size impacts the detection structure is the first stagnation point of the airflow, The maximum impact range of the supercooled water droplet when it impacts the detection structure is the maximum stagnation point of the airflow. When the airflow collides with the detection structure in any direction and angle within the flight range between the maximum lift angle and the maximum pitch angle of the aircraft, the first stagnation point of the airflow and the maximum stagnation point of the airflow are The relative position of the dead points does not change. The supercooled large water droplet detector according to claim 3 is characterized in that: When supercooled water droplets hit the detection structure, supercooled water droplets below the critical size only hit the first area between the first stagnation points of the airflow, while supercooled large water droplets exceeding the critical size hit the second area between the maximum stagnation points of the airflow while hitting the first area. The supercooled large water droplet detector according to claim 3 is characterized in that: The supercooled large water droplet detector is installed at the nose of the aircraft. The supercooled large water drop detector also has a curved pipe connecting the detector base with the detection structure. The detector base connected to one end of the pipe is installed inside the aircraft skin (not shown) and fixed to the fuselage structure. The duct is bent so that the detection structure connected to the other end of the duct faces the airflow in parallel with the airflow direction of the aircraft. The supercooled large water droplet detector according to claim 5, characterized in that: The portion connected to the duct, ie, the airflow non-impacting area, is formed into a streamline shape suitable for allowing air to flow through with low resistance. The supercooled large water droplet detector according to claim 5, characterized in that: The plurality of temperature sensors transmit the temperature detection values or temperature change values at corresponding positions to the controller through temperature sensor cables respectively. A plurality of electric heating circuits are connected to the controller using powered cables. The controller is responsible for providing current to the multiple electric heating circuits of the electric heating film layer and collecting signals from the multiple temperature sensors of the temperature sensor layer and performing data processing. The supercooled large water drop detector according to claim 7, characterized in that: The pipe is a hollow pipe. The temperature sensor cable and the power cable are arranged inside the pipe. The supercooled large water drop detector according to any one of claims 1 to 8, characterized in that: Each of the electric heating loops corresponding to different positions in the electric heating film layer is arranged in a spiral shape or in a U-shaped shape. The measuring position of the temperature sensor is uniformly arranged at the exact center of the U-shaped or spiral-shaped electric heating loop of each electric heating film layer. The supercooled large water drop detector according to any one of claims 1 to 8, characterized in that: The structural base is made of a poor thermal conductor material. The supercooled large water drop detector according to any one of claims 1 to 8, characterized in that: The icing weather has a plurality of supercooled water droplets of different critical sizes. The supercooled large water droplet detector can detect the size range of the supercooled water droplets that hit the detection structure to determine the current icing weather. The supercooled large water drop detector according to any one of claims 1 to 8, characterized in that: The size of the detection structure is 30 to 300 mm. 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, that is, 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 loop is 3 mm; Combination 2, that is, the size of the detection structure is 100 mm, and the cross-sectional size of the temperature sensor is The size of the electric heating circuit is 2 mm, and the layout size of the electric heating circuit is 4 mm; Combination 3, that is, 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 loop is 5 mm; Combination 4, that is, 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 loop is 6 mm.