Probe structure and pitot tube

Abstract

The application discloses a probe structure and an airspeed tube, and relates to the technical field of airborne atmospheric detection. The probe structure is applied to an aircraft, and the probe structure comprises a tube body, a plurality of fluid capillary structures are arranged along the axial direction of the tube body, and the plurality of fluid capillary structures are distributed in the circumferential direction of the inner wall of the tube body. The fluid capillary structures are in communication with the interior of the tube body, the communication positions of the fluid capillary structures and the tube body are provided with constrictions, and the fluid capillary structures are in communication with the atmosphere. The airspeed tube comprises the probe structure. The application contains and discharges liquid water through the fluid capillary structures, the overall containing capacity and the drainage efficiency of the fluid capillary structures are high, and the drainage holes are omitted, so that the risk of blockage during drainage is effectively reduced.

Description

Technical Field

[0001] This application relates to the field of airborne atmospheric detection technology, and in particular to a probe structure and a pitot tube. Background Technology

[0002] Airborne atmospheric sounding typically employs pitot tubes or atmospheric probes to collect atmospheric data, which is used as an important parameter for aircraft flight or for scientific research. Water ingress into the pitot tube or probe can affect atmospheric data collection and cause the pitot tube or probe to malfunction.

[0003] Related technologies typically include a drain hole on the side of the pitot tube or atmospheric probe closest to the aircraft, using the fluid's flow to expel liquid water. However, this allows liquid to flow through the sensor section of the pitot tube or probe, posing a significant risk of sensor damage in the event of a drainage failure. A drainage failure could also lead to the pitot tube or atmospheric probe malfunctioning. Summary of the Invention

[0004] The embodiments of this application disclose a probe structure and a sampling probe to solve the technical problem in the related art where the pitot tube is drained through a drain hole, which is prone to drainage failure under conditions of large water inflow or extreme temperature, leading to the failure of the pitot tube or atmospheric probe.

[0005] To address the above problems, the embodiments of this application adopt the following technical solutions: In a first aspect, embodiments of this application provide a probe structure for use in an aircraft. The probe structure includes a tube body, and a plurality of fluid capillary structures are provided along the axial direction of the tube body. The plurality of fluid capillary structures are circumferentially distributed on the inner wall of the tube body. The fluid capillary structure is connected to the interior of the tube, and the connection between the fluid capillary structure and the tube is a constriction. The fluid capillary structure is also connected to the atmosphere.

[0006] Furthermore, the fluid capillary structure extends from one end of the tube to the other end, with the fluid capillary structure connected to the atmosphere at one end of the tube.

[0007] Furthermore, a variable diameter section is provided at the end of the tube that connects to the atmosphere, and the outer diameter of the variable diameter section gradually decreases from the end closer to the aircraft to the end closer to the atmosphere.

[0008] Furthermore, the fluid capillary structure includes a tank that is embedded in the inner wall of the tube, and the tank has a slit that connects the interior of the tank and the interior of the tube. The width of the slit is less than the width of the groove.

[0009] Furthermore, the width of the trough gradually increases from the slit opening towards the outer side of the pipe along the radial direction of the pipe body.

[0010] Furthermore, the depth of the tank is 10 μm to 1 / 10 of the tube diameter.

[0011] Furthermore, the cross-section of the trough is one or more of the following: rectangular, wedge-shaped, or wavy.

[0012] Furthermore, an annular diaphragm is provided inside the tube, which is circumferentially attached to the inner wall of the tube and at least partially covers the end of the tube that is connected to the atmosphere.

[0013] Furthermore, one end of the annular diaphragm is located at the end of the tube closest to the atmosphere, and the other end of the annular diaphragm extends towards the end of the tube closest to the aircraft. The length of the annular diaphragm is 1 / 20 to 1 / 5 of the length of the tube.

[0014] Furthermore, the inner wall of the tube is provided with an circumferential groove, which is circumferentially connected to the fluid capillary structure.

[0015] Furthermore, a connecting hole is provided between two adjacent fluid capillary structures, and the fluid capillary structures are circumferentially connected through the connecting hole.

[0016] Furthermore, a waterproof and breathable barrier is provided at one end of the tube closest to the aircraft, and the waterproof and breathable barrier completely covers the end of the tube.

[0017] Furthermore, the tube wall is provided with several heating sections, which are distributed along the axial direction of the tube and are used to heat the tube.

[0018] Secondly, embodiments of this application provide an airspeed tube, including a sensor and a probe structure as described in the first aspect, wherein the sensor is connected to one end of the probe structure near the aircraft.

[0019] The technical solutions adopted in the embodiments of this application can achieve the following beneficial effects: The embodiments of this application employ an axial fluid capillary structure to draw in liquid water within the tube. After drawing in the liquid water, the fluid capillary structure uses a pressure difference to expel the liquid water from within itself. In related technologies, liquid water is discharged by providing drainage holes, which can easily lead to damage to the pitot tube or atmospheric probe due to blockage of the drainage holes. The embodiments of this application exhibit higher overall capacity and drainage efficiency of the fluid capillary structure, and because no drainage holes are provided, the risk of blockage during drainage is reduced. This is particularly true under conditions of large inflow or extreme temperatures, where the risk of drainage failure is significantly lower. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in the embodiments of this application 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 only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0021] Figure 1 This is a cross-sectional schematic diagram of the probe structure disclosed in the embodiments of this application; Figure 2 This is an embodiment disclosed in this application. Figure 1 A magnified view of part A in the middle; Figure 3 This is a schematic diagram of the end face of the probe structure disclosed in the embodiments of this application; Figure 4 This is an embodiment disclosed in this application. Figure 3 A magnified view of part B in the middle section; Figure 5 This is a cross-sectional view of the probe structure with a circumferential diaphragm as disclosed in the embodiments of this application; Figure 6 This is a schematic diagram of the end face structure of the probe structure with a circumferential diaphragm as disclosed in the embodiments of this application; Figure 7 This is an embodiment disclosed in this application. Figure 6 A magnified view of part C in the middle; Figure 8 This is a cross-sectional view of the probe structure with a heating element as disclosed in the embodiments of this application; Figure 9 This is a cross-sectional view of the probe structure disclosed in the embodiments of this application, wherein the heating part is provided and the circumferential diaphragm is lengthened.

[0022] In the picture: 100. Pipe body; 110. Reducing part; 200. Fluid capillary structure; 210. Tank; 220. Slit; 300. Waterproof and breathable barrier; 400. Annular diaphragm; 500. Heating section. Detailed Implementation

[0023] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions of this application will be described in detail below. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. Based on the embodiments in this application, all other implementation methods obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0024] The terms "first," "second," etc., used in the specification and claims of this application are used to distinguish similar objects and not to describe a specific order or sequence. It should be understood that such terms can be used interchangeably where appropriate so that embodiments of this application can be implemented in orders other than those illustrated or described herein, and the objects distinguished by "first," "second," etc., are generally of the same class and the number of objects is not limited; for example, a first object can be one or more. Furthermore, in the specification and claims, "and / or" indicates at least one of the connected objects, and the character " / " generally indicates that the preceding and following objects are in an "or" relationship.

[0025] Pitot tubes and airborne atmospheric probes are core sensors in an aircraft's air data system. Pitot tubes calculate key parameters such as flight speed, altitude, and rate of climb / descendancy by measuring the dynamic pressure of airflow (the difference between total pressure and static pressure). Atmospheric probes collect atmospheric data to conduct experiments. Both are based on high-altitude gas parameter measurements, and their accuracy directly affects flight safety and experimental success rates. Therefore, the influence of liquid water must be eliminated.

[0026] Taking the pitot tube as an example, in actual operating environments, the pitot tube and atmospheric probe will inevitably encounter the incidence of liquid water (rainwater, cloud droplets, melted ice crystals) and high-altitude ice crystals. The physical properties of water are significantly different from those of air, and its intervention is one of the main physical reasons for pitot tube pressure measurement inaccuracies or even complete failure.

[0027] Related technologies typically include a drain hole on the pitot tube or atmospheric probe near the aircraft side to expel liquid water that has entered the pitot tube or atmospheric probe. However, the operating environment of aircraft is usually characterized by low temperature and air pressure. If liquid water is trapped at the drain hole, it can easily freeze and become clogged. When the drain hole is clogged, it can damage the sensors inside the pitot tube or atmospheric probe, leading to the failure of the pitot tube or atmospheric probe.

[0028] In view of this, embodiments of this application provide a probe structure. By setting a fluid capillary structure, the connection between the fluid capillary structure and the inside of the tube is set as a constriction. So when liquid water enters the tube, the fluid capillary structure absorbs the liquid water. The fluid capillary structure is connected to the atmosphere, and the liquid water in the fluid capillary structure can be discharged from the tube through the pressure difference, which greatly reduces the risk of drainage failure of the pitot tube or atmospheric probe.

[0029] The following is in conjunction with the appendix Figures 1 to 9 The present application provides a detailed description of a probe structure and sampling probe through specific embodiments and application scenarios.

[0030] Some embodiments of this application provide a probe structure for use in an aircraft in the first aspect.

[0031] Please see Figure 1 As shown, the probe structure includes a tube body 100, with a plurality of fluid capillary structures 200 arranged along the axial direction of the tube body 100. The fluid capillary structures 200 are circumferentially distributed on the inner wall of the tube body 100 and are in communication with the interior of the tube body 100. The fluid capillary structures 200 are used to contain liquid water, which can flow along the axial direction of the tube body 100 after entering the fluid capillary structures 200.

[0032] The connection between the fluid capillary structure 200 and the tube body 100 is a constricted design. The size of the area connecting the fluid capillary structure 200 to the interior of the tube body 100 is relatively small, while the size inside the fluid capillary structure 200 is relatively large. This allows the fluid capillary structure 200 to utilize Bernoulli's principle to create suction at the constriction when liquid water enters the tube body 100, drawing the liquid water into its interior and preventing liquid water from remaining inside the tube body 100. The fluid capillary structure 200 is connected to the atmosphere, allowing liquid water within it to be discharged into the atmosphere. Since there are numerous fluid capillary structures 200 connected to the atmosphere, and the amount of liquid water entering the tube body 100 is generally small, the fluid capillary structure 200 effectively serves the function of storing and discharging liquid water, preventing liquid water from flowing deeper into the tube body 100.

[0033] For example, when liquid water enters the tube 100, it flows from the side of the tube 100 closest to the atmosphere to the side of the tube 100 closest to the aircraft. When the liquid water comes into contact with the connection between the fluid capillary structure 200 and the interior of the tube 100, the liquid water is drawn into the fluid capillary structure 200, and the amount of liquid water in the tube 100 decreases. The liquid water is then discharged to the atmosphere through the fluid capillary structure 200.

[0034] In some embodiments of this application, please refer to... Figure 1 As shown, the fluid capillary structure 200 can be used to collect substances from the atmosphere. Because the fluid capillary structure 200 can generate suction to draw in liquid water from the air, it can also draw in particles of a suitable size. The fluid capillary structure 200 has storage space. When air flows into the tube 100, it can effectively draw in and store liquid water and particulate matter from the atmosphere, and carry these substances back to the ground, thus completing the atmospheric collection.

[0035] For some embodiments of this application, please refer to Figure 1 and Figure 2As shown, the fluid capillary structure 200 extends from one end of the tube 100 to the other end. This allows the fluid capillary structure 200 to absorb liquid water along the entire length of the tube 100, preventing insufficient coverage of the liquid water and thus enhancing the ability to remove liquid water, preventing it from interfering with the normal operation of the pitot tube or atmospheric probe. The fluid capillary structure 200 is connected to the atmosphere at one end of the tube 100. The fluid capillary structure 200 is also connected to the atmosphere at the other end of the tube 100, allowing liquid water to drain from the point of entry into the tube 100, preventing a decrease in the structural strength of the tube 100 due to side-to-side atmospheric connection.

[0036] For some embodiments of this application, please refer to Figure 3 , Figure 5 , Figure 6 , Figure 8 and Figure 9 As shown, an annular diaphragm 400 is provided inside the tube 100. The annular diaphragm 400 is circumferentially attached to the inner wall of the tube 100, and at least partially covers the end of the tube 100 that is connected to the atmosphere. Through the arrangement of the annular diaphragm 400, a pressure difference can be created between the fluid capillary structure 200 covered by the annular diaphragm 400 and the fluid capillary structure 200 uncovered by the annular diaphragm 400, utilizing Bernoulli's principle. This pressure difference can compress the liquid water within the fluid capillary structure 200, thereby facilitating the discharge of liquid water.

[0037] When the fluid capillary structure 200 is connected to the atmosphere at the end of the tube 100, the pressure difference formed at the annular diaphragm 400 can be used to discharge liquid water from the end of the tube 100. In this way, the liquid water in the fluid capillary structure 200 can flow more continuously and is less likely to form blockages, thereby allowing more liquid water to be discharged from the tube 100.

[0038] For some embodiments of this application, please refer to Figure 2 As shown, a variable diameter section 110 is provided at the end of the tube 100 that connects to the atmosphere. The outer diameter of the variable diameter section 110 gradually decreases from the end closer to the aircraft to the end closer to the atmosphere. The variable diameter section 110 forms an inclined surface at the end of the tube 100. When air enters the tube 100, the variable diameter section 110 will guide the flow at the end of the tube 100, thereby preventing flow blockage at the end of the tube 100.

[0039] Therefore, when the fluid capillary structure 200 discharges liquid water from the end of the pipe body 100 through the action of pressure difference, the variable diameter section 110 can guide the liquid water from the variable diameter section 110 to the outside of the pipe body 100 through flow guiding. This can prevent the discharged liquid water from re-entering the inside of the pipe body 100.

[0040] For some embodiments of this application, please refer to Figure 3 and Figure 4 As shown, the fluid capillary structure 200 includes a tank 210, which is embedded in the inner wall of the tube 100. The tank 210 has a slit 220, and the interior of the tank 210 and the tube 100 are connected through the slit 220. Liquid water is contained within the tank 210, and the slit 220 is designed to be constricted, thus effectively drawing liquid water into the tank 210 through the slit 220.

[0041] The width of the opening 220 is smaller than the width of the tank 210. This makes it easier to utilize Bernoulli's principle to create suction, thereby drawing liquid water into the tank 210.

[0042] For some embodiments of this application, please refer to Figure 4 and Figure 7 As shown, the width of the tank 210 gradually increases from the slit 220 towards the outer side of the pipe 100 along the radial direction of the pipe 100. This variation in width allows the fluid capillary structure 200 to more stably draw liquid water into the tank 210 from the slit 220. This also prevents flow blockage caused by turbulence or eddies due to drastic changes in the width of the tank 210 after the liquid water enters the tank.

[0043] In some embodiments of this application, the depth of the tank 210 is from 10 μm to 1 / 10 of the diameter of the tube 100. When the depth of the tank 210 is 10 μm, the suction generated by the tank 210 can draw in liquid water. When the depth of the tank 210 exceeds 1 / 10 of the diameter of the tube 100, it will affect the normal operation of the pneumatic tube or atmospheric probe. Therefore, this application selects the depth of the tank 210 to be within the range of 10 μm to 1 / 10 of the diameter of the tube 100 to ensure that the liquid water can be discharged without affecting the normal operation of the pneumatic tube or atmospheric probe.

[0044] In some embodiments of this application, the cross-section of the tank 210 is rectangular, wedge-shaped, or wavy, or one or more of these shapes. When the cross-section of the tank 210 is rectangular, the tank 210 can effectively draw in and contain liquid water, resulting in a higher liquid water capacity. When the cross-section of the tank 210 is wedge-shaped, the fluid capillary structure 200 can generate a greater suction force, thereby enabling more stable intake of liquid water. When the cross-section of the tank 210 is wavy, the fluid capillary structure 200 is less prone to backflow, preventing liquid water in the fluid capillary structure 200 from flowing back into the pipe 100.

[0045] In some embodiments of this application, one end of the annular diaphragm 400 is located at the end of the tube 100 closest to the atmosphere. Liquid water is subjected to a pressure difference at the location of the annular diaphragm 400 and is discharged from the end of the tube 100 closest to the atmosphere. The other end of the annular diaphragm 400 extends towards the end of the tube 100 closest to the aircraft. Changing the length of the annular diaphragm 400 allows for adaptive modification of the liquid water discharge efficiency according to actual needs. The length of the annular diaphragm 400 is 1 / 20 to 1 / 5 of the length of the tube 100. The annular diaphragm 400 is configured with different lengths according to different usage requirements. When the length of the annular diaphragm 400 is 1 / 20 of the length of the tube 100, it can effectively generate a pressure difference to discharge liquid water from the tube 100. At this time, the fluid capillary structure 200 inside the tube 100 can hold more liquid water. When the length of the tube 100 is 1 / 5, a larger pressure difference can be formed, thereby discharging the liquid water inside the tube 100 faster and effectively improving the discharge efficiency of liquid water.

[0046] In some embodiments of this application, the inner wall of the tube 100 is provided with an circumferential groove, which is circumferentially connected to the fluid capillary structure 200. By setting the circumferential groove, the circumferentially distributed fluid capillary structures 200 can be connected, thereby allowing the liquid water in each fluid capillary structure 200 to flow circumferentially, avoiding the risk of liquid water overflowing in some of the fluid capillary structures 200.

[0047] In some embodiments of this application, a connecting hole is provided between two adjacent fluid capillary structures 200, and the fluid capillary structures 200 are circumferentially connected through the connecting hole. The connection hole enables liquid water to flow effectively between circumferentially adjacent fluid capillary structures 200, and the flow rate can be effectively controlled to maintain the stability of axial discharge of liquid water using pressure difference.

[0048] For some embodiments of this application, please refer to Figure 5 , Figure 8 and Figure 9 As shown, a waterproof and breathable barrier 300 is provided at the end of the tube 100 near the aircraft, completely covering the end of the tube 100. The waterproof and breathable barrier 300 isolates the end of the tube 100 near the aircraft, preventing liquid water inside the tube 100 from flowing to the sensor location and thus isolating it from affecting the function of the pitot tube or atmospheric probe. However, the waterproof and breathable barrier 300 does not affect gas flow, so gas can pass through the barrier and contact the sensor without affecting the normal operation of the pitot tube and atmospheric probe.

[0049] For example, when an annular diaphragm 400 and a waterproof and breathable barrier 300 are provided inside the tube 100, the waterproof and breathable barrier 300 separates the sensor from the tube 100, preventing liquid water from affecting the sensor. The annular diaphragm 400 enhances the pressure difference, thereby improving the efficiency of draining liquid water from the tube 100. In this case, the embodiment of this application can be used on seaplanes, ensuring that the sensor inside the pitot tube is not affected by liquid water when the seaplane is in water. When the seaplane takes off from the water, the liquid water inside the pitot tube can be quickly drained, preventing any impact on the normal operation of the pitot tube.

[0050] For some embodiments of this application, please refer to Figure 8 and Figure 9 As shown, when an aircraft is flying at high altitude and encounters ice crystals in the atmosphere that enter the tube 100, the ice crystals may not melt naturally inside the tube 100 at times. If the ice crystals cannot melt naturally, the entry of liquid water into the fluid capillary structure 200 will be obstructed, accelerating crystallization inside the tube 100 and thus reducing the drainage efficiency of the tube 100. By providing several heating sections 500 in the tube wall of the tube 100, the heating sections 500 are used to heat the tube 100. By using the heating sections 500 to heat the tube 100, the ice crystals are melted, so that the drainage efficiency of the fluid capillary structure 200 is not affected. The heating sections 500 can be one or more of heating blocks, heating rods, or heating rings. When a heating ring is used, heat can be generated circumferentially on the inner wall of the tube 100, thereby covering the inner wall of the tube 100 more comprehensively. The heating element 500 is distributed along the axial direction of the tube 100, covering a larger heating area in the axial direction of the tube 100, thus preventing ice crystals from entering the tube 100 and remaining on the side of the tube 100 closest to the aircraft. When there is liquid water in the fluid capillary structure 200, the heating element 500 can also use the liquid water in the fluid capillary structure 200 as a heat transfer medium, thereby utilizing the high specific heat capacity of liquid water to prevent the tube 100 from being deformed or cracked due to local thermal stress.

[0051] Please see Figures 1 to 9 As shown, some embodiments of this application provide a pitot tube in a second aspect, including a sensor and a probe structure of any of the aforementioned schemes. The pitot tube of this embodiment possesses the beneficial effects of the aforementioned probe structure, which will not be elaborated further here. In addition, the sensor is connected to the end of the probe structure closer to the aircraft. The pitot tube acquires parameters through the sensor, which is located on the side closer to the aircraft; therefore, the sensor is connected to the end of the probe structure closer to the aircraft.

[0052] It should be noted that, in this document, 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. Unless otherwise specified, 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 that element.

[0053] Furthermore, it should be noted that the scope of the methods and apparatus in the embodiments of this application is not limited to performing functions in the order shown or discussed, but may also include performing functions substantially simultaneously or in the reverse order, depending on the functions involved. For example, the described methods may be performed in a different order than described, and various steps may be added, omitted, or combined. In addition, features described with reference to certain examples may be combined in other examples.

[0054] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in this application should be included within the scope of protection of this application.

Claims

1. A probe structure applied to an aircraft, characterized in that, The probe structure includes a tube (100), and a plurality of fluid capillary structures (200) are provided along the axial direction of the tube (100). The plurality of fluid capillary structures (200) are circumferentially distributed on the inner wall of the tube (100). The fluid capillary structure (200) is connected to the interior of the tube body (100), the connection between the fluid capillary structure (200) and the tube body (100) is a constricted opening, and the fluid capillary structure (200) is connected to the atmosphere. The fluid capillary structure (200) extends from one end of the tube (100) to the other end of the tube (100), and the fluid capillary structure (200) is connected to the atmosphere at one end of the tube (100). The tube (100) is provided with an annular diaphragm (400), which is circumferentially attached to the inner wall of the tube (100), and the annular diaphragm (400) at least partially covers the end of the tube (100) that is connected to the atmosphere.

2. The probe structure according to claim 1, characterized in that, A variable diameter section (110) is provided at one end of the tube (100) that is connected to the atmosphere. The outer diameter of the variable diameter section (110) gradually decreases from the end closer to the aircraft to the end closer to the atmosphere.

3. The probe structure according to claim 1 or 2, characterized in that, The fluid capillary structure (200) includes a channel (210) embedded in the inner wall of the tube (100), and the channel (210) is provided with a slit (220), and the interior of the channel (210) and the tube (100) are connected through the slit (220); The width of the slit (220) is smaller than the width of the groove (210).

4. The probe structure according to claim 3, characterized in that, The width of the groove (210) gradually increases from the slot (220) toward the outer side of the tube (100) along the radial direction of the tube (100); And / or, the depth of the groove (210) is 10 μm to 1 / 10 of the diameter of the tube (100).

5. The probe structure according to claim 3, characterized in that, The cross-section of the groove (210) is one or more of the following: rectangular, wedge-shaped, or wavy.

6. The probe structure according to claim 1, characterized in that, One end of the annular diaphragm (400) is located at the end of the tube (100) closer to the atmosphere, and the other end of the annular diaphragm (400) extends toward the end of the tube (100) closer to the aircraft. The length of the annular diaphragm (400) is 1 / 20 to 1 / 5 of the length of the tube (100).

7. The probe structure according to claim 1 or 2, characterized in that, The inner wall of the tube (100) is provided with an circumferential groove, which is circumferentially connected to the fluid capillary structure (200). Alternatively, a connecting hole is provided between two adjacent fluid capillary structures (200), and the fluid capillary structures (200) are circumferentially connected through the connecting hole.

8. The probe structure according to claim 1 or 2, characterized in that, A waterproof and breathable barrier (300) is provided at one end of the tube (100) near the aircraft, and the waterproof and breathable barrier (300) completely covers the end of the tube (100); And / or, the tube wall of the tube body (100) is provided with a plurality of heating parts (500), the heating parts (500) are distributed along the axial direction of the tube body (100), and the heating parts (500) are used to heat the tube body (100).

9. A pitot tube, characterized in that, It includes a sensor and a probe structure as described in any one of claims 1 to 8, wherein the sensor is connected to one end of the probe structure near the aircraft.

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