Anti-icing airspeed meter

Abstract

The utility model relates to an anti-icing airspeed meter, which comprises a main shell, an airspeed tube, a heat preservation head, a cavity shell, a detection unit, a base and a heating unit, a mounting cavity, a dynamic pressure chamber, a static pressure chamber and a pipe mounting hole with two through ends are formed in the main shell; the tail end of the airspeed tube is mounted in a tube mounting hole of the main shell; the thermal insulation head sleeves the periphery of the airspeed tube and is fixed on the main shell; an air flow channel is formed in the cavity shell, the cavity shell is detachably mounted on the main shell, the detection unit comprises a circuit board and a sensor, the circuit board is arranged in the mounting cavity, and the sensor is arranged on the circuit board; the base is mounted at the bottom of the main shell; the heating unit is electrically connected with the circuit board. The airspeed tube and the dynamic pressure hole are in butt joint through the cavity shell, and the cavity shell is detachable, so that assembly is facilitated, and stains on the airspeed tube and the dynamic pressure hole can be cleaned conveniently; and the heating unit is arranged to heat the airspeed tube, so that the situation that the airspeed tube orifice is frozen and cannot work when the airspeed tube works at the temperature below zero can be avoided.

Description

Technical Field

[0001] This utility model relates to the field of flight measurement tool technology, and in particular to an anti-icing airspeed meter. Background Technology

[0002] An airspeed measuring device is a device that senses the total and static pressure of airflow and transmits the measured pressure data to an air data computer and flight instruments. Airspeed sensors are primarily used to measure flight speed and are a crucial means of accurately measuring aircraft speed; they also possess a variety of other functions.

[0003] In existing technologies, the pitot tube and the pitot sensor are separate. Generally, the pitot sensor and the pitot tube are quite far apart, requiring a relatively long flexible tube for connection. This makes assembly inconvenient and cleaning of the tube opening difficult. Furthermore, traditional pitot tubes are prone to freezing at sub-zero temperatures, rendering them inoperable.

[0004] Therefore, it is necessary to design an airspeed measuring instrument that is suitable for use. Utility Model Content

[0005] Therefore, the purpose of this utility model is to overcome the shortcomings of the prior art and provide an anti-icing airspeed measuring instrument.

[0006] To achieve the above objectives, the technical solution adopted by this utility model is as follows:

[0007] An anti-icing airspeed meter includes:

[0008] Main housing, airspeed tube, insulation head, cavity shell, detection unit, base, and heating unit;

[0009] The main housing has an installation cavity, a dynamic pressure chamber, a static pressure chamber, and a pipe installation hole that extends through both ends. The main housing is also provided with a dynamic pressure hole that connects to the dynamic pressure chamber and a static pressure hole that connects to the static pressure chamber.

[0010] The end of the airspeed tube is installed in the tube mounting hole of the main housing;

[0011] The heat-insulating head is sleeved on the outer periphery of the airspeed tube and fixed to the main housing;

[0012] An airflow channel is formed inside the cavity shell, and the cavity shell is detachably installed on the main housing so that the opening at the end of the airspeed tube, the airflow channel and the dynamic pressure hole are connected in sequence;

[0013] The detection unit includes a circuit board and a sensor. The circuit board is disposed in the mounting cavity, and the sensor is disposed on the circuit board. The sensor is provided with a dynamic pressure connector and a static pressure connector, wherein the dynamic pressure connector extends into the dynamic pressure chamber, and the static pressure connector extends into the static pressure chamber.

[0014] The base is installed at the bottom of the main housing to cover the opening of the mounting cavity;

[0015] The heating unit is electrically connected to the circuit board and is partially disposed on the outer wall of the airspeed tube.

[0016] In one embodiment, the mounting cavity communicates with the tube mounting hole. The heating unit includes a heating cable, a heating resistor, and a temperature and humidity sensor. The heating cable is disposed on the outer wall of the airspeed tube. A portion of the heating cable passes through the tube mounting hole and extends into the mounting cavity to be electrically connected to the circuit board. The heating resistor is fixed to the heating cable located on the outer wall of the airspeed tube. The temperature and humidity sensor is installed on the side of the insulation head and is electrically connected to the heating cable.

[0017] In one embodiment, a cable bonding plane is provided on the outer wall surface of the airspeed tube, and the heating cable is fixed on the cable bonding plane.

[0018] In one embodiment, both the dynamic pressure chamber and the static pressure chamber have openings communicating with the mounting cavity. The sensor is located at the openings of the dynamic pressure chamber and the static pressure chamber, and the opening of the dynamic pressure chamber is provided with a first sealing gasket that abuts against the outer wall of the sensor.

[0019] In one embodiment, a second sealing gasket is provided at one end of the air flow channel and is connected to the pipe mounting hole, and a third sealing gasket is provided at the other end of the air flow channel and is connected to the dynamic pressure hole.

[0020] In one embodiment, a cushioning pad is provided at the bottom of the base.

[0021] In one embodiment, the detection unit further includes a power connector, which is disposed at the bottom of the circuit board, and the base is provided with a through hole for the power connector to be exposed.

[0022] In one embodiment, the outer side of the main housing is provided with a plug-in protrusion, and the cavity housing is provided with a plug-in groove that matches the plug-in protrusion.

[0023] In one embodiment, the cavity shell is provided with a drain hole that communicates with the air flow channel.

[0024] In one embodiment, the base is connected to the main housing by screws.

[0025] Compared with traditional technologies, the beneficial effects of this anti-icing airspeed meter are:

[0026] This invention uses a cavity shell to connect the airspeed tube and the dynamic pressure port. The cavity shell is detachable, which facilitates assembly and cleaning of dirt on the airspeed tube and the dynamic pressure port. In addition, a heating unit is provided to heat the airspeed tube, which can prevent the airspeed tube port from freezing and becoming inoperable when operating at sub-zero temperatures.

[0027] To better understand and implement this invention, the following detailed description is provided in conjunction with the accompanying drawings. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the airspeed meter in the embodiments of this application;

[0029] Figure 2 This is a schematic diagram of the exploded structure of the airspeed meter in the embodiments of this application;

[0030] Figure 3 This is a cross-sectional structural diagram of the airspeed meter in the embodiments of this application;

[0031] Figure 4 This is a schematic diagram of the main housing structure in an embodiment of this application;

[0032] Figure 5 This is a cross-sectional structural diagram of the main housing in an embodiment of this application;

[0033] Figure 6 This is a schematic diagram of the cavity shell structure in an embodiment of this application;

[0034] Figure 7 This is a schematic diagram of the detection unit in an embodiment of this application;

[0035] Figure 8 This is a schematic diagram of the airspeed tube and heating unit in the embodiments of this application;

[0036] Figure 9 This is a schematic diagram of the airspeed meter installed on an unmanned aerial vehicle in this embodiment;

[0037] Explanation of reference numerals in the attached figures:

[0038] 1. Main housing; 11. Mounting cavity; 12. Dynamic pressure chamber; 13. Dynamic pressure hole; 14. Static pressure chamber; 15. Static pressure hole; 16. Pipe mounting hole; 17. Insertion protrusion; 2. Pipe; 21. Cable mating plane; 3. Insulation head; 4. Cavity shell; 41. Airflow channel; 42. Insertion slot; 43. Drain hole; 51. Circuit board; 52. Sensor; 521. Dynamic pressure connector; 522. Static pressure connector; 53. Power connector; 6. Base; 61. Through hole; 7. Heating unit; 71. Heating cable; 72. Heating resistor; 73. Temperature and humidity sensor; 81. First sealing gasket; 82. Second sealing gasket; 83. Third sealing gasket; 9. Buffer pad. Detailed Implementation

[0039] To further illustrate the various embodiments, the present invention provides accompanying drawings. These drawings are part of the disclosure of the present invention and are mainly used to illustrate the embodiments, and can be used in conjunction with the relevant descriptions in the specification to explain the operating principles of the embodiments. With reference to these drawings, those skilled in the art should be able to understand other possible implementation methods and the advantages of the present invention.

[0040] In the description of this utility model, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "left", "right", "top", "bottom", "inner", "outer", "axial", "radial", "circumferential", etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this utility model and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on this utility model.

[0041] Please see Figures 1 to 8 This embodiment provides an anti-icing airspeed meter, which includes: a main housing 1, an airspeed tube 2, an insulation head 3, a cavity shell 4, a detection unit, a base 6, and a heating unit 7.

[0042] In this embodiment, the main housing 1 has an installation cavity 11, a dynamic pressure chamber 12, a static pressure chamber 14, and a pipe installation hole 16 extending through both ends. The main housing 1 is also provided with a dynamic pressure hole 13 communicating with the dynamic pressure chamber 12 and a static pressure hole 15 communicating with the static pressure chamber 14. The axial direction of the dynamic pressure hole 13 is perpendicular to the axial direction of the static pressure hole 15. The dynamic pressure hole 13 is used to detect the total pressure, and the static pressure hole 15 is used to detect the atmospheric pressure. The dynamic pressure hole 13 is a windward hole. The direction of the static pressure hole 15 is different from that of the dynamic pressure hole 13, which is beneficial for detecting atmospheric pressure and avoids interference from airflow.

[0043] The airspeed tube 2 is installed at its end in the tube mounting hole 16 of the main housing 1, and the first end of the airspeed tube 2 is the air inlet end.

[0044] The heat insulation head 3 is sleeved on the outer periphery of the pitot tube 2 and fixed to the main housing 1, and is used to insulate the pitot tube 2 to prevent the heat of the pitot tube 2 from being lost with the airflow during flight.

[0045] An airflow channel 41 is formed within the cavity shell 4. The cavity shell 4 is detachably mounted on the main housing 1, so that the opening at the end of the pitot tube 2, the airflow channel 41, and the dynamic pressure port 13 are sequentially connected. As can be seen from the above, this embodiment uses the cavity shell 4 as a conductor between the pitot tube 2 and the dynamic pressure port 13, allowing the opening at the end of the pitot tube 2, the airflow channel 41, and the dynamic pressure port 13 to be sequentially connected. When the airspeed meter is working, airflow can enter from the beginning of the pitot tube 2, pass through the airflow channel 41 of the cavity shell 4, and then enter the dynamic pressure chamber 12 through the dynamic pressure port 13. In this embodiment, the airflow channel 41 has a bend, which prevents rainwater, dust, and small particles of sand from entering the dynamic pressure port 13, thus preventing the dynamic pressure port 13 from being blocked by dust and small particles of sand. On the other hand, the cavity shell 4 is detachably connected to the main housing 1, facilitating overall maintenance and cleaning, and making it convenient to use.

[0046] The detection unit can detect functions such as air velocity. In this embodiment, the detection unit includes a circuit board 51 and a sensor 52. The circuit board 51 is disposed in the mounting cavity 11, and the sensor 52 is disposed on the circuit board 51. The sensor 52 is provided with a dynamic pressure connector 521 and a static pressure connector 522. The dynamic pressure connector 521 extends into the dynamic pressure chamber 12, and the static pressure connector 522 extends into the static pressure chamber 14. The dynamic pressure connector 521 of the sensor 52 can detect the total pressure in the dynamic pressure chamber 12, and the static pressure connector 522 can detect the atmospheric pressure in the static pressure chamber 14. Thus, based on the difference between the atmospheric pressure at the static pressure orifice 15 and the measured total pressure at the dynamic pressure orifice 13, an air velocity electrical signal is generated and output according to a corresponding functional relationship. The sensor 52 is generally a capacitive sensor 52, a diaphragm pressure sensor 52, a vibrating cylinder pressure sensor 52, or a piezoresistive pressure sensor 52.

[0047] The base 6 is installed at the bottom of the main housing 1 to cover the opening of the mounting cavity 11 and prevent external debris from entering the mounting cavity 11.

[0048] The heating unit 7 is electrically connected to the circuit board 51 and is partially disposed on the outer wall of the airspeed tube 2. The heating unit 7 is used to heat the airspeed tube 2 to keep it within a certain temperature range, thereby preventing the airspeed tube from becoming blocked due to icing, ensuring unobstructed airflow in the airspeed tube 2, and giving the airspeed tube 2 anti-icing, rainproof, and dustproof functions. The airspeed tube can be made of a metal material with high thermal conductivity to facilitate heating.

[0049] As can be seen from the above configuration, in this embodiment, the pitot tube 2 and the dynamic pressure port 13 are connected by a housing 4. The housing 4 is detachable, which facilitates assembly and cleaning of dirt on the pitot tube 2 and the dynamic pressure port 13. On the other hand, a heating unit 7 is provided to heat the pitot tube 2, thereby preventing the pitot tube 2 from freezing and becoming inoperable when operating at sub-zero temperatures.

[0050] To facilitate the installation of the heating unit 7, specifically in this embodiment, the mounting cavity 11 communicates with the tube mounting hole 16. The heating unit 7 includes a heating cable 71, a heating resistor 72, and a temperature and humidity sensor 73. The heating cable 71 is disposed on the outer wall of the pitot tube 2. A portion of the heating cable 71 passes through the tube mounting hole 16 and extends into the mounting cavity 11 to be electrically connected to the circuit board 51, drawing power from the circuit board 51. The heating resistor 72 is fixed on the heating cable 71 located on the outer wall of the pitot tube 2 to generate heat. The temperature and humidity sensor 73 is installed on the side of the insulation head 3 and is electrically connected to the heating cable 71. The temperature and humidity sensor 73 is used to detect the ambient air temperature and humidity, so that the flight control can make better decisions or adjustments based on the actual environment. The external port of the temperature and humidity sensor 73 and the surrounding area of ​​the temperature and humidity sensor 73 are sealed with waterproof glue to prevent rainwater from flowing into the interior of the insulation head 3 through the gap. The heating unit 7 is designed to be easy to install and has high heating efficiency. The heating efficiency can also be adjusted according to temperature and humidity conditions.

[0051] Preferably, a cable-fitting plane 21 is provided on the outer wall surface of the airspeed tube 2, and the heating cable 71 is fixed on the cable-fitting plane 21. This makes the installation of the heating cable 71 more reasonable and less likely to fall off.

[0052] Specifically, in this embodiment, both the dynamic pressure chamber 12 and the static pressure chamber 14 have openings communicating with the mounting cavity 11. The sensor 52 is located at the openings of the dynamic pressure chamber 12 and the static pressure chamber 14. The opening of the dynamic pressure chamber 12 is provided with a first sealing gasket 81 that abuts against the outer wall of the sensor 52. This arrangement ensures the sealing of the dynamic pressure chamber 12 and prevents leakage of airflow flowing in from the dynamic pressure hole 13.

[0053] Furthermore, one end of the airflow channel 41 is provided with a second sealing gasket 82 and is connected to the pipe mounting hole 16, and the other end of the airflow channel 41 is provided with a third sealing gasket 83 and is connected to the dynamic pressure hole 13. This further prevents air leakage from the gap between the cavity shell 4 and the main shell 1. The second sealing gasket 82 has an opening corresponding to the pipe mounting hole 16, and the third sealing gasket 83 has an opening corresponding to the dynamic pressure hole 13.

[0054] Preferably, the bottom of the base 6 is provided with a buffer pad 9, which can reduce the vibration of the airspeed meter.

[0055] To facilitate power supply to the detection unit, specifically, the detection unit in this embodiment further includes a power connector 53, which is disposed at the bottom of the circuit board 51, and the base 6 is provided with a through hole 61 for the power connector 53 to be exposed.

[0056] On the other hand, the outer side of the main housing 1 is provided with a plugging protrusion 17, and the cavity housing 4 is provided with a plugging groove 42 that mates with the plugging protrusion 17. Through the cooperation of the plugging protrusion 17 and the plugging groove 42, the cavity housing 4 can be positioned and fixed to each other.

[0057] Specifically, the cavity shell 4 is provided with a drain hole 43 that communicates with the air flow channel 41, so that rainwater flowing into the air speed tube can be discharged.

[0058] The base 6 is connected to the main housing 1 by screws, which facilitates disassembly and assembly.

[0059] like Figure 9 The diagram shown is a structural schematic of the airspeed meter A installed on the unmanned aerial vehicle in this embodiment. It can be understood that the airspeed meter A can be installed at the end of the fuselage or on the wing.

[0060] The embodiments described above are merely examples of several implementations of this utility model, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the utility model. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this utility model, and these modifications and improvements all fall within the protection scope of this utility model.

Claims

1. An anti-icing airspeed meter, characterized in that: Main housing, airspeed tube, insulation head, cavity shell, detection unit, base, and heating unit; The main housing has an installation cavity, a dynamic pressure chamber, a static pressure chamber, and a pipe installation hole that extends through both ends. The main housing is also provided with a dynamic pressure hole that connects to the dynamic pressure chamber and a static pressure hole that connects to the static pressure chamber. The end of the airspeed tube is installed in the tube mounting hole of the main housing; The heat-insulating head is sleeved on the outer periphery of the airspeed tube and fixed to the main housing; An airflow channel is formed inside the cavity shell, and the cavity shell is detachably installed on the main housing so that the opening at the end of the airspeed tube, the airflow channel and the dynamic pressure hole are connected in sequence; The detection unit includes a circuit board and a sensor. The circuit board is disposed in the mounting cavity, and the sensor is disposed on the circuit board. The sensor is provided with a dynamic pressure connector and a static pressure connector, wherein the dynamic pressure connector extends into the dynamic pressure chamber, and the static pressure connector extends into the static pressure chamber. The base is installed at the bottom of the main housing to cover the opening of the mounting cavity; The heating unit is electrically connected to the circuit board and is partially disposed on the outer wall of the airspeed tube.

2. The anti-icing airspeed meter according to claim 1, characterized in that: The mounting cavity communicates with the tube mounting hole. The heating unit includes a heating cable, a heating resistor, and a temperature and humidity sensor. The heating cable is disposed on the outer wall of the airspeed tube. A portion of the heating cable passes through the tube mounting hole and extends into the mounting cavity to be electrically connected to the circuit board. The heating resistor is fixed on the heating cable located on the outer wall of the airspeed tube. The temperature and humidity sensor is installed on the side of the insulation head and is electrically connected to the heating cable.

3. The anti-icing airspeed meter according to claim 2, characterized in that: A cable bonding plane is provided on the outer wall surface of the airspeed tube, and the heating cable is fixed on the cable bonding plane.

4. The anti-icing airspeed meter according to claim 1, characterized in that: Both the dynamic pressure chamber and the static pressure chamber have openings that communicate with the mounting cavity. The sensor is located at the openings of the dynamic pressure chamber and the static pressure chamber. The opening of the dynamic pressure chamber is provided with a first sealing gasket that abuts against the outer wall of the sensor.

5. The anti-icing airspeed meter according to claim 1, characterized in that: One end of the airflow channel is provided with a second sealing gasket and is connected to the pipe mounting hole, and the other end of the airflow channel is provided with a third sealing gasket and is connected to the dynamic pressure hole.

6. The anti-icing airspeed meter according to claim 1, characterized in that: The bottom of the base is provided with a cushioning pad.

7. The anti-icing airspeed meter according to claim 1, characterized in that: The detection unit also includes a power connector, which is located at the bottom of the circuit board, and the base has a through hole for the power connector to be exposed.

8. The anti-icing airspeed meter according to claim 1, characterized in that: The outer side of the main housing is provided with a plug-in protrusion, and the cavity housing is provided with a plug-in groove that matches the plug-in protrusion.

9. The anti-icing airspeed meter according to any one of claims 1 to 8, characterized in that: The cavity shell is provided with a drain hole that communicates with the air flow channel.

10. The anti-icing airspeed meter according to claim 1, characterized in that: The base is connected to the main housing by screws.

Images