Waterproof airspeed tube convenient to disassemble and assemble for unmanned aerial vehicle

Abstract

The invention relates to the technical field of unmanned aerial vehicle parts, in particular to an unmanned aerial vehicle waterproof airspeed tube convenient to disassemble and assemble, which comprises an air inlet piece, a pressure separation piece, an air inlet pipe and an airspeed tube. The air inlet pipe and the airspeed tube are both mounted in the pressure separation piece and are not directly communicated with each other; the air inlet piece is connected with the pressure separation piece, and external air enters the airspeed tube through the air inlet pipe to be measured. An air inlet cavity and a water baffle are arranged in the air inlet piece, and primary drainage is achieved through a first drainage assembly; the pressure separation part comprises a horizontal pressure transmission part and an inclined height difference flow guide part and is provided with a second drainage assembly, and the second drainage assembly comprises a water collection cavity and a second drainage port and is installed between the air inlet pipe and the airspeed pipe to achieve air-water separation and secondary drainage. The airspeed tube air inlet hole is higher than the air inlet tube exhaust hole, and accumulated water is further prevented from flowing backwards. The device is reasonable in structure, has good waterproof and drainage capacity, can improve the airspeed measurement precision, and is suitable for various unmanned aerial vehicle platforms with fixed wings, vertical take-off and landing and the like.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of unmanned aerial vehicle parts, and particularly relates to a waterproof air speed pipe for unmanned aerial vehicle which is convenient to disassemble and assemble. BACKGROUND

[0002] With the rapid development of unmanned aerial vehicle technology, the requirements of various parts are also higher and higher, among which, the problem of air speed pipe is more and more serious. The air speed pipe, also known as the pitot tube, is one of the core sensing elements for measuring the flight speed of the aircraft. Its basic working principle is based on Bernoulli's law in fluid mechanics. The total pressure and static pressure difference of the airflow formed on the aircraft are measured to obtain the dynamic pressure value, and the flight speed is further converted.

[0003] The traditional air speed pipe structure mainly includes a dynamic pressure hole, a static pressure hole, an internal air guide cavity and a heating module for deicing and the like. In the application of unmanned aerial vehicle, in order to pursue light weight and high integration, the air speed pipe structure is usually simplified. However, under complex weather conditions (such as heavy rain, fog and high altitude low temperature), the traditional air speed pipe faces the following prominent problems: 1. Rainy day air speed pipe water inlet: the traditional air speed pipe cannot effectively block water droplets in rainy days, which leads to pressure measurement error or even instrument damage after entering the cavity; 2. Water accumulation after deicing: the air speed pipe is frozen at high altitude, and the heating module can melt ice, but there is no reasonable drainage structure, and the melted water droplets are easy to accumulate and affect the measurement accuracy; 3. Simple structure is easy to block: without reasonable flow guide and drainage path, water droplets or impurities in the air are easy to accumulate; 4. Poor adaptability: most of the current air speed pipe structures are mainly for fixed-wing platforms, and lack of dynamic adaptation to transition flight modes such as vertical take-off and landing.

[0004] Therefore, the prior art urgently needs an air speed measuring device with a more reasonable structure, waterproof and drainage functions, and suitable for complex flight environment of unmanned aerial vehicle. SUMMARY

[0005] In order to solve the above technical problems, the present application discloses a waterproof air speed pipe for unmanned aerial vehicle which is convenient to disassemble and assemble, overcomes the problem of insufficient waterproof performance of the traditional air speed pipe under adverse weather conditions, and provides a waterproof air speed pipe with compact structure, high drainage efficiency and prevention of water vapor entering the measurement module, which is particularly suitable for multi-mode unmanned aerial vehicle platforms such as vertical take-off and high-altitude cruising.

[0006] The application discloses a waterproof air speed pipe for an unmanned aerial vehicle, which is convenient to disassemble and assemble, and comprises an air inlet part, a pressure separation part, an air inlet pipe and an air speed pipe.

[0007] Optionally, the air inlet part is internally provided with an air inlet cavity, one end of the air inlet cavity is provided with an air inlet port, and the end of the air inlet part far from the air inlet port is connected with the pressure separation part.

[0008] Optionally, the air inlet cavity is internally provided with a water baffle, the water baffle is arranged at the top of the air inlet cavity and covers the air inlet port at least partially, and the distance between the water baffle and the air inlet port is 20-25 mm.

[0009] Optionally, the first water drainage assembly comprises a first water drainage hole, and the first water drainage hole is arranged at the lowest part of the air inlet part.

[0010] Optionally, the pressure separation part comprises a pressure transmission part and a height difference flow guide part, the internal cavity of the pressure transmission part is horizontally arranged, and the internal cavity of the height difference flow guide part is inclined at an angle of 125-145 degrees.

[0011] Optionally, the shape of the air inlet pipe is matched with the pressure transmission part and the height difference flow guide part, one end of the air inlet pipe is horizontally arranged, and the other end is inclined at an angle of 125-145 degrees.

[0012] Optionally, the second water drainage assembly comprises a water collecting cavity, the water collecting cavity is arranged in the cavity of the pressure separation part, and the air outlet hole of the air inlet pipe and the air inlet hole of the air speed pipe are both arranged in the water collecting cavity.

[0013] Optionally, the air inlet hole of the air speed pipe is higher than the air outlet hole of the air inlet pipe.

[0014] Optionally, the second water drainage assembly further comprises a second water drainage port, and the second water drainage port is arranged at the bottom of the water collecting cavity.

[0015] An unmanned aerial vehicle comprises the waterproof air speed pipe for an unmanned aerial vehicle.

[0016] Compared with the prior art, the technical scheme provided by the application has the following advantages.

[0017] The application realizes efficient air-water separation and anti-backflow function by introducing independent modular design of air inlet part and pressure separation part in airspeed tube structure, combining air inlet cavity expansion structure, top water baffle, two-stage drainage system (first drainage hole and water collecting cavity + second drainage port), and height difference flow guide path and air inlet / exhaust hole height arrangement. The flow paths between modules are independent, the functions are clear, and water vapor can be effectively blocked from entering the pressure measurement module, significantly improving the accuracy of airspeed measurement and the reliability of system operation. At the same time, the structure is suitable for multiple types of unmanned aerial vehicle platforms (such as fixed-wing, VTOL, etc.), has good environmental adaptability, rain and ice resistance, and engineering implementability, and is especially suitable for high dynamic flight tasks under complex weather conditions. BRIEF DESCRIPTION OF DRAWINGS

[0018] The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present disclosure and serve to explain the principles of the present disclosure, together with the description.

[0019] In order to more clearly illustrate the technical solutions in the embodiments of the present disclosure or the prior art, the accompanying drawings needed to be used in the embodiments or prior art description will be briefly introduced. Obviously, those skilled in the art can obtain other drawings according to these drawings without any creative effort.

[0020] Figure 1 Structure diagram of the waterproof airspeed tube for the unmanned aerial vehicle convenient for disassembly in the embodiments of the present application;

[0021] Figure 2 Sectional view of the waterproof airspeed tube for the unmanned aerial vehicle convenient for disassembly in the embodiments of the present application;

[0022] Figure 3 Sectional view of the air inlet part in the embodiments of the present application;

[0023] Figure 4 Front view of the right part of the pressure separation part in the embodiments of the present application;

[0024] Figure 5 Front view of the left part of the pressure separation part in the embodiments of the present application;

[0025] Figure 6 Schematic diagram of the second drainage port in the embodiments of the present application.

[0026] Among them,

[0027] 1, air inlet part; 11, air inlet; 12, air inlet cavity; 13, first drainage port; 14, water baffle;

[0028] 2, pressure separation part; 21, pressure transmission part; 22, height difference flow guide part; 23, water collecting cavity; 231, second drainage port;

[0029] 3, intake pipe; 4, air speed pipe; 5, fixing member. DETAILED DESCRIPTION

[0030] In order to enable a more clear understanding of the above-mentioned objects, features and advantages of the present disclosure, the schemes of the present disclosure will be further described below. It should be noted that the embodiments of the present disclosure and the features in the embodiments can be combined with each other without conflict.

[0031] In the following description, a large number of specific details are set forth in order to facilitate a thorough understanding of the present disclosure, but the present disclosure can also be implemented in other manners different from those described herein; obviously, the embodiments described in the specification are only a part of the embodiments of the present disclosure, and not all the embodiments.

[0032] In combination with Figures 1-6 As shown in the drawings, the embodiment of the present application discloses a waterproof air speed pipe for unmanned aerial vehicle which is convenient to disassemble, comprising an air inlet member 1, a pressure separation member 2, an intake pipe 3 and an air speed pipe 4, the intake pipe 3 and the air speed pipe 3 are installed in the pressure separation member 2, the intake pipe 3 and the air speed pipe 4 are not connected, the air inlet member 1 and the pressure separation member 2 are connected, the gas entering the air inlet member 1 is transmitted to the air speed pipe 4 through the intake pipe 3, the air inlet member 1 is provided with a first drainage assembly, the pressure separation member 2 is provided with a second drainage assembly, and the second drainage assembly is arranged between the intake pipe 3 and the air speed pipe 4. The air inlet member 1 is connected with the pressure separation member 2, the intake pipe 3 and the air speed pipe 4 are independently installed in the pressure separation member 2 respectively, forming a non-communicating flow guide structure, preventing short circuit of unseparated water vapor directly to the air speed module. This structure realizes independent partition pressure transmission between modules, effectively improves the waterproof stability, ensures that even if a single module is waterlogged, it does not affect the pressure core function, and improves the system robustness.

[0033] In an embodiment, the air inlet member 1 is internally provided with an air inlet cavity 12, one end of the air inlet cavity 12 is provided with an air inlet 11, the end of the air inlet member 1 away from the air inlet 11 is connected with the pressure separation member 2, the shape of the air inlet member 1 gradually expands after being away from the air inlet 11, the internal space of the air inlet cavity 12 gradually expands, forming a gas deceleration area, so that the airflow disturbance is reduced when flying at high speed, and water droplets are more easily settled, so that the present application is more suitable for high-speed cruising scenes, and the liquid droplets are more easily separated after the airflow is stabilized, improving the working efficiency of the first drainage assembly.

[0034] In an embodiment, a water baffle 14 is arranged in the air inlet cavity 12, which is arranged at the top of the air inlet cavity 12 and covers at least part of the air inlet 11, and the distance between the water baffle 14 and the air inlet 11 is 20-25 mm, so that the water droplets in the air inlet flow can be preliminarily separated. The water baffle is an arc-shaped water baffle made of aluminum alloy plate by CNC processing, which is welded to the top of the cavity and covers 60% of the air inlet cross section; or a floating water baffle made of flexible material is used, which can automatically deform to reduce resistance in strong wind

[0035] In an embodiment, the first drainage assembly includes a first drainage hole 11 arranged at the lowest part of the air inlet part 1.

[0036] In a further embodiment, the first drainage hole 13 has a diameter of 2 mm and is arranged at the lowest point of the bottom of the air inlet part 1 and is matched with a dust screen cover. Optionally, a one-way drainage diaphragm can be installed to enhance the drainage smoothness. When there is water in the air inlet cavity 12, the water droplets are first drained, preventing water vapor from rising with the airflow into the pressure cavity.

[0037] In an embodiment, the silicone pad or O-shaped sealing ring is used for sealing connection between each connecting part of the waterproof air speed pipe for unmanned aerial vehicle, which can maintain the sealing property of the device and effectively cope with the flight in rainy and humid environment.

[0038] In an embodiment, the pressure separation part 2 includes a pressure transmission part 21 and a height difference flow guide part 22. The internal cavity of the pressure transmission part 21 is horizontally arranged, and the internal cavity of the height difference flow guide part 22 has an inclination angle of 125°-145°. The pressure transmission part 21 is a horizontally arranged cavity processed by CNC, and the height difference flow guide part 22 has an angle of 135°. The cavity is smooth and transitioned to reduce turbulence. In the inclined structure, the gravity is used to enhance the sinking of liquid droplets and improve the secondary gas-water separation rate.

[0039] The shape of the air inlet pipe 3 is matched with the pressure transmission part 21 and the height difference flow guide part 22. One end of the air inlet pipe 3 is horizontally arranged, and the other end is inclined at an angle of 125°-145°. The air inlet pipe 3 is a bent pipe assembly, which is bent to 135° after being horizontally connected with the pressure transmission part 21; or the air inlet pipe 3 uses a two-section combined structure for easy disassembly and maintenance. The air inlet pipe 3 can realize precise flow guiding, reduce connection stress, and improve assembly consistency.

[0040] In an embodiment, the second drainage assembly includes a water collecting cavity 23 arranged in the cavity of the pressure separation part 2. The air outlet hole of the air inlet pipe 3 and the air inlet hole of the air speed pipe 4 are arranged in the water collecting cavity 23. The water collecting cavity 23 is an injection molding structure with a volume of not less than 2 ml. The openings of the air inlet pipe 3 and the air speed pipe 4 are respectively arranged on the upper and lower sides of the cavity to form a settling zone. The liquid droplets in the airflow are deposited and gravity-drained in the settling zone, effectively blocking the water vapor path.

[0042] In a further embodiment, the air intake hole of the pitot tube 4 is higher than the air exhaust hole of the air intake tube 3, and the air intake hole of the pitot tube 4 is arranged 3 mm higher than the air exhaust hole of the air intake tube 3, and separation is achieved by using the natural height difference. Even if the water collection cavity is filled with liquid, water can be prevented from flowing back into the pitot tube.

[0043] In an embodiment, the second drainage assembly further includes a second drainage port 231 arranged at the bottom of the water collection cavity 23. The second drainage port 231 is arranged at the bottom of the water collection cavity 23, has a diameter of 2.5 mm, and is matched with a one-way valve assembly to be externally connected to a liquid guide hose for drainage to the bottom of the machine body. This ensures that the liquid in the water collection cavity can be automatically drained, avoiding liquid accumulation causing pressure measurement delay.

[0044] In an embodiment, the air exhaust port of the pitot tube 4 is mounted on the height difference flow guide portion by the fixing member 5, avoiding shaking or extrusion deformation of the air exhaust port of the pitot tube 4.

[0045] In a specific embodiment: The convenient-to-disassemble waterproof pitot tube for unmanned aerial vehicles in this embodiment is mainly used for fixed-wing unmanned aerial vehicle platforms, and includes an air intake member 1, a pressure separation member 2, an air intake tube 3, and a pitot tube 4. One end of the air intake member 1 is provided with an air intake port 11, and the other end is connected to the pressure separation member 2 through a fixing member 5. An air intake cavity 12 gradually expands from the air intake port 11 backward, and a water baffle 14 is mounted at the top, with a distance of 22 mm from the air intake port 11, for blocking and separating water droplets entering during flight. A first drainage port 13 is arranged at the lowest part of the air intake member 1 for timely draining water trapped by the water baffle. After preliminary separation, the airflow enters the pressure separation member 2 from the air intake cavity 12 through the air intake tube 3. The pressure separation member 2 includes an integrally formed pressure transmission portion 21 (arranged horizontally) and a height difference flow guide portion 22 (arranged at an angle of 135°), and the air intake tube 3 is matched in shape for easy sealing and smooth airflow introduction. When the airflow flows through the height difference flow guide portion 22, due to the change in flow direction and inertia, residual water droplets are deposited in a water collection cavity 23 arranged inside the pressure separation member 2. The air exhaust hole of the air intake tube 3 and the air intake hole of the pitot tube 4 are both arranged inside the water collection cavity 23, and the air intake hole of the pitot tube 4 is arranged above the air exhaust hole of the air intake tube 3, effectively preventing unseparated water droplets from entering the pitot module. A second drainage port 231 is arranged at the bottom of the water collection cavity 23 to complete natural drainage of residual water under the action of gravity. This structure realizes efficient separation and drainage of rainwater through the "primary water blocking + height difference flow guide + water collection cavity sedimentation + double drainage" method, improving the reliability of airspeed measurement.

[0046] On the basis of the above-mentioned embodiments, a dynamic adaptation type suitable for the vertical take-off and landing platform can be further designed. Firstly, the curvature of the inner cavity of the air inlet member 1 and the angle of the water baffle 14 are optimized, and a floating flexible water baffle structure is adopted, so that the water baffle structure can still maintain high water separation efficiency under air flow disturbance during VTOL flight. Secondly, the second water outlet 231 is changed into a one-way water outlet valve structure to avoid water backflow during attitude switching. The embodiment is more suitable for multi-rotor / compound wing / vertical take-off and landing unmanned aerial vehicle platforms.

[0047] In an embodiment, a freeze-proof heating type air speed tube is adopted, specifically, a heating element such as a PTC ceramic sheet is additionally arranged outside the basic structure. The PTC ceramic sheet is respectively embedded on the outer periphery of the air inlet 11 of the air inlet member 1, the lower part of the water baffle 14, and the outer surface of the height difference flow guide part 22 of the pressure separation member 2, and is combined with a temperature control sensor to automatically heat when the external temperature is lower than 5°C, effectively preventing blockage or error caused by rain and snow icing. The heat-sensitive element is linked to the flight control system for linkage control, and the heating power is automatically turned on and off according to the temperature change. The heating circuit uses 5V low-voltage power supply, and the power does not exceed 3W, which ensures the service life of the flight battery. The inner walls of all water drainage holes are coated with a hydrophobic coating to improve the water drainage efficiency in a low-temperature environment.

[0048] The application discloses an unmanned aerial vehicle, which is provided with a convenient-to-disassemble waterproof air speed tube at the nose of a fixed-wing unmanned aerial vehicle, so that the flight data stability of the unmanned aerial vehicle is good; or a tilt bracket is arranged above a propeller blade of a VTOL unmanned aerial vehicle, so that the air speed tube drainage area is away from a turbulent flow area; or the air speed tube is used for a ship-borne unmanned aerial vehicle, and cooperates with a corrosion-resistant coating to resist sea wind salt spray for a long time. The convenient-to-disassemble waterproof air speed tube can significantly improve the adaptability and flight safety of the unmanned aerial vehicle system in a complex weather environment.

[0049] The specific implementation manners and principles are the same as those of the above-mentioned embodiments and can bring the same or similar technical effects, which will not be described here again. For details, refer to the description of the above cover airtightness detection tool embodiment.

[0050] In the description of the embodiments disclosed in the present application, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "height", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the embodiments of the present disclosure and simplifying the description, and do not indicate or imply that the structure or device referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the embodiments of the present disclosure.

[0051] It has to be noted that, in the present document, the terms "first", "second", etc. merely serve the purpose of distinguishing between two entities or operations, without necessarily requiring or implying any actual relationship or order between these entities or operations. Moreover, the terms "comprising", "containing" or any other transitional term, do not exclude other matters besides the one(s) named in the respective claim from being present in the compositions, methods, articles, or devices of the application. The singular forms "a", "an" and "the" include plural referents unless the context clearly dictates otherwise. "Comprises" and "comprising" do not exclude the presence of elements or steps other than those listed in a process, method, article, or apparatus. The term "consisting of" or "consisting only of" excludes the presence of other elements or steps. Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The disclosure should not be construed as requiring any non-essential components or steps. The use of the terms "about" and "substantially" in the present document is intended to mean that a value or a characteristic is not exact, but is close to, but not necessarily exactly, the stated value or characteristic. The use of the term "substantially" in the present document is intended to mean that a value or a characteristic is not exact, but is close to, but not necessarily exactly, the stated value or characteristic.

[0052] The foregoing is considered as illustrative only of the principles of the application. Numerous modifications and changes will readily occur to those skilled in the art, which modifications and changes are to be understood as intended to be embraced by the principles described herein and new matters included in such principles. Therefore, it is the object of the appended claims to cover all such modifications and changes as fall within the true spirit and scope of the application.

Claims

1. A waterproof pitot tube for unmanned aerial vehicles (UAVs) that is easy to assemble and disassemble, characterized in that, The device includes an air intake component, a pressure separator, an air intake pipe, and an air speed pipe. The air intake pipe and the air speed pipe are installed in the pressure separator. The air intake pipe and the air speed pipe are independent and not connected to each other. The air intake component and the pressure separator are connected. Gas entering the air intake component is transferred to the air speed pipe through the air intake pipe. The air intake component is provided with a first drainage component, and the pressure separator is provided with a second drainage component. The second drainage component is disposed between the air intake pipe and the air speed pipe.

2. The waterproof pitot tube for UAVs that is easy to assemble and disassemble according to claim 1, characterized in that, The air intake component has an air intake chamber inside, and an air inlet is provided at one end of the air intake chamber. The end of the air intake component away from the air inlet is connected to the pressure separator. The shape of the air intake component gradually expands as it moves away from the air inlet.

3. The waterproof pitot tube for UAVs that is easy to assemble and disassemble according to claim 2, characterized in that, A baffle plate is provided inside the air intake chamber. The baffle plate is located at the top of the air intake chamber and at least partially covers the air intake. The distance between the baffle plate and the air intake is 20~25mm.

4. The waterproof pitot tube for UAVs that is easy to assemble and disassemble according to claim 1, characterized in that, The first drainage component includes a first drainage hole, which is located at the lowest part of the air intake component.

5. The waterproof pitot tube for UAVs that is easy to assemble and disassemble according to claim 1, characterized in that, The pressure separation component includes a pressure transmission section and a height difference guide section. The internal cavity of the pressure transmission section is horizontally arranged, and the inclination angle of the internal cavity of the height difference guide section is 125°~145°.

6. The waterproof pitot tube for UAVs that is easy to assemble and disassemble according to claim 5, characterized in that, The shape of the intake pipe is adapted to the pressure transmission part and the height difference guide part. One end of the intake pipe is horizontal, and the other end is inclined at 125°~145°.

7. The waterproof pitot tube for UAVs that is easy to assemble and disassemble according to claim 1, characterized in that, The second drainage component includes a water collection chamber, which is disposed within the cavity of the pressure separator, and the exhaust port of the air intake pipe and the air intake port of the air speed pipe are both disposed within the water collection chamber.

8. The waterproof pitot tube for UAVs that is easy to assemble and disassemble according to claim 7, characterized in that, The air intake port of the airspeed tube is higher than the exhaust port of the air intake tube.

9. The waterproof pitot tube for unmanned aerial vehicles that is easy to assemble and disassemble according to claim 7 or 8, characterized in that, The second drainage component further includes a second drain outlet, which is located at the bottom of the water collection chamber.

10. A drone, characterized in that, Including the waterproof pitot tube for unmanned aerial vehicles that is easy to install and remove as described in any one of claims 1-9.

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