Airspeed height detection tool for unmanned aerial vehicle
The UAV airspeed and altitude detection tool, which uses a combination of a balloon and a cannula, utilizes a one-way valve to control airspeed and altitude detection, solving the problems of saliva blockage and cold environments, and achieving stability and sensor protection for UAV airspeed and altitude detection.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- XIAN AISHENG TECH GRP
- Filing Date
- 2025-05-09
- Publication Date
- 2026-05-12
AI Technical Summary
Existing methods for detecting airspeed and altitude in drones suffer from problems such as saliva clogging the airspeed tube, harm to operators in cold environments, and inability to accurately control the force of blowing and sucking, which can lead to sensor damage.
The system uses a balloon and tube sleeve, with an inlet check valve and an outlet check valve to connect the air intake and outlet channels of the airspeed tube, respectively. Airspeed and altitude can be detected by manipulating the balloon, avoiding direct manual blowing and sucking.
实现了无人机空速高度检测的稳定性和精确性，保护操作人员，避免传感器损坏，结构简单，操作方便，适用于全寿命周期的免维护检测。
Smart Images
Figure CN224225306U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of drone sensor detection, specifically to a drone airspeed and altitude detection tool. Background Technology
[0002] Currently, drones are widely used in both military and civilian fields. With the development of drone technology, the number of onboard sensors is also increasing. Dynamic and static pressure sensors, used to measure airspeed and altitude, are essential equipment on drones. Dynamic and static pressure sensors cannot directly measure the airspeed and altitude of a drone; they need to be connected to a pitot tube via tubing to complete the measurement. The pitot tube, tubing, dynamic pressure sensor, and static pressure sensor together constitute the drone airspeed and altitude measurement system.
[0003] During the overall system testing of a drone, it is necessary to check whether the dynamic pressure line from the pitot tube inlet to the dynamic pressure sensor is normal (referred to as airspeed testing), and to check whether the static pressure line from the pitot tube altitude orifice to the static pressure sensor is normal (referred to as altitude testing), to confirm that the dynamic pressure sensor and the static pressure sensor are in normal measurement condition. Figure 1 As shown, Figure 1 This is a structural diagram of the pitot tube. When testing airspeed, the operator blows air into the inlet at the very front of the pitot tube and checks the dynamic pressure sensor for changes. When testing altitude, the operator inhales through the altitude port on the outer wall of the pitot tube and checks the static pressure sensor for changes. The inlet at the front of the pitot tube connects to the dynamic pressure port at the rear of the pitot tube via an internal air passage. The dynamic pressure port is connected to the dynamic pressure sensor via a conduit. The altitude port connects to the static pressure chamber inside the pitot tube. The static pressure chamber is connected to the static pressure port at the rear of the pitot tube, which is connected to the static pressure sensor via a conduit. The static pressure and dynamic pressure air passages formed inside the pitot tube are not interconnected. There are two sets of altitude ports, five in each set, located on the same circumference of the outer wall of the static pressure chamber. The inlet at the front of the pitot tube is used to sense the airflow velocity, and the altitude orifice is used to sense the atmospheric pressure. When air is blown into the inlet at the front of the pitot tube, the dynamic pressure sensor will sense the increase in pressure and will display an increase in airspeed. When air is inhaled into the altitude orifice, the static pressure sensor will sense the decrease in pressure and will display an increase in altitude.
[0004] The above-mentioned detection method has certain drawbacks. When detecting airspeed, saliva, foreign objects, etc. from the human mouth can easily be blown into the airspeed tube, causing blockage. In cold winters or at high altitudes, the lips can easily stick to the metal surface of the airspeed tube due to the cold, which can tear the lips and cause injury to the operator. Furthermore, by having the operator blow into the airspeed tube opening and altitude hole, it is impossible to accurately control the blowing and suction force, which can easily damage the dynamic pressure sensor and the static pressure sensor.
[0005] Therefore, there is a need to provide a tool for detecting the airspeed and altitude of drones to solve the above problems. Summary of the Invention
[0006] The technical problem to be solved:
[0007] To overcome the shortcomings of existing technologies, this utility model provides a tool for detecting the airspeed and altitude of unmanned aerial vehicles (UAVs). It uses a balloon and a tube to work together, with an inlet check valve and an outlet check valve installed at their interface, which connect to two cavities inside the tube. The airspeed tube is placed in the cavity connected to the inlet check valve, and the airspeed and altitude can be detected by manipulating the balloon, thus solving the problem of the lack of existing tools for detecting the airspeed and altitude of UAVs.
[0008] The technical solution of this utility model is: a tool for detecting the airspeed and altitude of a drone, comprising:
[0009] The balloon has an exhaust port at one end and a connecting sleeve sealed at the other end; the connecting sleeve has a first air hole and a second air hole, both of which are connected to the inner cavity of the balloon.
[0010] The sleeve is sealed to the connecting sleeve. One end of the sleeve is provided with an air inlet and an air outlet. The air inlet is connected to the first air hole and the air outlet is connected to the second air hole. The other end of the sleeve is provided with an opening. The air inlet is connected to the air inlet chamber inside the sleeve, the air outlet is connected to the air outlet chamber inside the sleeve, and the opening is connected to the air inlet chamber. The end of the air outlet chamber away from the air outlet is provided with an inlet that is connected to the air inlet chamber.
[0011] An intake check valve is installed at the junction of the first air hole and the air inlet, with one end located inside the first air hole and the other end located inside the air inlet.
[0012] And an exhaust check valve, installed at the junction of the second vent and the exhaust vent, with one end inside the second vent and the other end inside the exhaust vent;
[0013] The air intake chamber of the tube sleeve is equipped with the air speed tube of the UAV. The air speed tube opening faces the air intake check valve, and its height hole corresponds to the axial position of the inlet. Its tail end dynamic pressure interface and static pressure interface are located at the open end of the tube sleeve.
[0014] A further technical solution of this utility model is that the air inlet chamber and the air outlet chamber are two independent cavities inside the sleeve, and are connected only at the inlet.
[0015] A further technical solution of this utility model is: when the air intake one-way valve is working, the air in the balloon flows through the air intake one-way valve into the air intake chamber, and at this time the air outlet one-way valve is closed; when the air outlet one-way valve is working, the air in the air outlet chamber flows through the air outlet one-way valve into the balloon, and at this time the air intake one-way valve is closed.
[0016] A further technical solution of this utility model is: the sleeve is an elastic sleeve, the middle part of which is provided with a conical surface along the axial direction for matching with the conical surface at the front end of the airspeed tube, and the air intake chamber inside the sleeve matches the outer dimensions of the airspeed tube.
[0017] A further technical solution of this utility model is: the conical surface of the sleeve is provided with an exhaust hole, the exhaust hole is connected to the air intake chamber, and the exhaust hole is used to discharge excess air in the air intake chamber when the air speed tube is inserted into the air intake chamber.
[0018] A further technical solution of this utility model is: the inner wall of the open end of the sleeve near the edge is provided with an annular protrusion, which is used to seal with the outer wall of the airspeed tube and prevent the airspeed tube from falling out of the sleeve.
[0019] A further technical solution of this utility model is that the access port is located inside the annular protrusion.
[0020] A further technical solution of this utility model is: the balloon is an elliptical hollow structure that can be squeezed and rebounded.
[0021] The beneficial effects of this invention are as follows: This invention provides a UAV airspeed and altitude detection tool. By sealing and connecting a tube sleeve and a balloon, an air inlet and an air outlet are provided at the connection point. An air inlet one-way valve is installed in the air inlet, and an air outlet one-way valve is installed in the air outlet. By squeezing the balloon, air is introduced through the air inlet or vented through the air outlet, enabling blowing and sucking of air onto the airspeed tube installed inside the tube sleeve. This simulates the operator blowing air into the airspeed tube opening and sucking air into the airspeed tube's altitude orifice through their lips, while maintaining a stable blowing and sucking force. This tool replaces manual blowing and sucking detection with direct mouth operation, protects the operator in high-altitude and cold regions, and avoids damage to the airspeed tube and dynamic / static pressure sensors caused by existing detection methods.
[0022] In this invention, two independent cavities are set inside the tube sleeve, which are respectively connected to the air intake channel (i.e., dynamic pressure air channel) and the air intake channel (i.e., static pressure air channel) inside the air velocity tube. Each cavity of the tube sleeve is equipped with a corresponding one-way valve at the connection point with the balloon, which can realize that blowing and inhaling do not interfere with each other.
[0023] In this invention, the inner wall of the air intake chamber of the sleeve is fitted to the shape of the pitot tube, with the pitot tube opening facing the air intake check valve. This allows air entering the air intake chamber through the check valve to enter the dynamic pressure air passage of the pitot tube through the tube opening. The air is then blown into the tube opening by squeezing the balloon. By aligning the inlet of the air outlet chamber inside the sleeve with the axial position of the height hole of the pitot tube installed in the air intake chamber, the static pressure air passage of the pitot tube is connected to the air outlet chamber of the sleeve. Releasing the squeezed balloon allows air to be drawn into the height hole. This design features a simple structure and convenient operation, requiring only one operator with one hand.
[0024] This testing tool boasts high reliability in connection and testing. It exhibits excellent sealing after connection with the pitot tube, preventing air leakage and ensuring overall high testing reliability. By incorporating an annular protrusion on the inner wall of the open end of the tube sleeve, a sealed connection between the pitot tube's outer wall and the tube sleeve is guaranteed, preventing air leakage during intake. This ensures that airflow during intake can only enter the tube sleeve's outlet chamber through the height hole from the pitot tube's static pressure chamber.
[0025] This testing tool is simple in design and has long component lifespan, enabling maintenance-free airspeed and altitude testing throughout the entire lifespan of a UAV. Its structure conforms to ergonomic principles, allowing for disassembly and storage, or it can be installed and stored as a whole. Attached Figure Description
[0026] To more clearly illustrate the technical solutions in the embodiments of this utility model 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 utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0027] Figure 1 This is a schematic diagram of the internal structure of the pitot tube.
[0028] Figure 2 This is a schematic diagram of the external structure of the pitot tube;
[0029] Figure 3 This is a schematic diagram of the internal structure of a drone airspeed and altitude detection tool according to the present invention;
[0030] Figure 4 This is a schematic diagram of the disassembled structure of a drone airspeed and altitude detection tool according to the present invention;
[0031] Figure 5 This is a schematic diagram of an airspeed and altitude detection tool for unmanned aerial vehicles (UAVs) according to this utility model.
[0032] Figure 6 This is a schematic diagram of the airspeed and altitude detection tool for unmanned aerial vehicles (UAVs) according to this utility model.
[0033] In the diagram: 1. Balloon, 11. Exhaust port, 2. Connecting sleeve, 21. First air hole, 22. Second air hole; 3. Tube sleeve, 31. Air inlet, 32. Air outlet, 33. Air inlet chamber, 34. Air outlet chamber, 35. Inlet, 36. Exhaust port, 37. Annular protrusion, 4. Inlet check valve, 5. Outlet check valve, 6. Air speed pipe, 61. Pipe opening, 62. Altitude hole, 63. Dynamic pressure interface, 64. Static pressure interface, 65. Static pressure chamber, 66. Dynamic pressure chamber. Detailed Implementation
[0034] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.
[0035] An embodiment of the UAV airspeed and altitude detection tool of this utility model, such as... Figure 3 , Figure 4 As shown, it includes: balloon 1, connecting sleeve 2, tube sleeve 3, inlet one-way valve 4, and outlet one-way valve 5.
[0036] The balloon 1 is a compressible, elliptical, hollow structure with an exhaust port 11 at one end and a connecting sleeve 2 sealed at the other end. The connecting sleeve 2 is made of rubber and serves to connect the balloon 1 and the tube sleeve 3. The connecting sleeve 2 has a first air hole 21 and a second air hole 22 arranged side by side, both of which are connected to the inner cavity of the balloon 1. The exhaust port 11 communicates with the inner cavity of the balloon and is used to expel gas from the balloon 1 when it is compressed. When the balloon 1 is released after compression, outside air can enter the balloon 1 through the exhaust port 11.
[0037] The sleeve 3 is sealed to the connecting sleeve 2. One end of the sleeve 3 has an air inlet 31 and an air outlet 32. The air inlet 31 connects to the first air hole 21, and the air outlet 32 connects to the second air hole 22. The air inlet 31 connects to the air inlet chamber 33 inside the sleeve, and the air outlet 32 connects to the air outlet chamber 34 inside the sleeve. The other end of the sleeve 3 is open, located at the end of the air inlet chamber 33 away from the air inlet 31. The air inlet chamber 33 and the air outlet chamber 34 are two independent cavities within the sleeve 3. The air outlet chamber 34 has an inlet 35 at the end away from the air outlet 32 that connects to the air inlet chamber 33.
[0038] An intake check valve 4 is installed inside the air inlet 31. One end of the intake check valve 4 is airtightly connected to the first air hole 21, and the other end is airtightly connected to the air inlet 31. An exhaust check valve 5 is installed inside the air outlet 32. One end of the exhaust check valve 5 is airtightly connected to the second air hole 22, and the other end is airtightly connected to the air outlet 32. In this embodiment, the airtight connection between the intake check valve 4 and the exhaust check valve 5 is achieved using 303 adhesive. The intake check valve 4 enables unidirectional flow of air from the airbag 1 to the air inlet chamber 33, and the exhaust check valve 5 enables unidirectional flow of air from the air outlet chamber 34 to the airbag 1. Therefore, when the intake check valve 4 is working, the air in the airbag 1 flows through the intake check valve 4 into the air inlet chamber 33, at which time the exhaust check valve 4 is closed; when the exhaust check valve 4 is working, the air in the air outlet chamber 34 flows through the exhaust check valve 5 into the airbag 1, at which time the intake check valve 4 is closed.
[0039] The structure of pitot tube 6 is as follows Figure 1 , Figure 2 As shown, the pitot tube 6 has an opening 61 at one end. A dynamic pressure chamber 66 is located inside the pitot tube 6 near the opening 61. The dynamic pressure chamber 66 is connected to the dynamic pressure interface 63 at the tail end of the pitot tube 6 via a dynamic pressure channel within the pitot tube 6, thus forming a dynamic pressure air passage. Two sets of altitude orifices 62, each set containing five orifices, are located on the same circumference of the outer wall of the static pressure chamber 65 inside the pitot tube 6. The static pressure chamber 65 is an annular cavity. The altitude orifices 62 are connected to the static pressure chamber 65, which is connected to the static pressure interface 64 at the tail end of the pitot tube 6 via a static pressure channel within the pitot tube 6, thus forming a static pressure air passage. The dynamic pressure air passage and the static pressure air passage inside the pitot tube 6 are two independent air passages.
[0040] The airspeed tube 6 is installed inside the intake chamber 33 of the sleeve 3. The sleeve 3 is an elastic sleeve with a tapered surface along its axial direction in its middle section to match the tapered surface at the front end of the airspeed tube 6. The intake chamber 33 inside the sleeve 3 matches the outer dimensions of the airspeed tube 6. An exhaust port 36 is provided on the tapered surface of the sleeve 3, which connects to the intake chamber 33. The exhaust port 36 is used to expel excess air from the intake chamber 33 when the airspeed tube 6 is inserted into the intake chamber 33, preventing excessive air from entering the airspeed tube 6. The diameter of the exhaust port 36 is set to 2mm. During installation, the port 61 of the airspeed tube 6 faces the intake check valve 4, and its height hole 62 corresponds to the axial position of the inlet 35. The dynamic pressure interface 63 and static pressure interface 64 at the tail end of the airspeed tube 6 are exposed at the open end of the sleeve 3. An annular protrusion 37 is provided on the inner wall near the edge of the open end of the sleeve 3. The annular protrusion 37 protrudes radially by 1 mm and is used to seal with the outer wall of the airspeed tube 6, so that the airspeed tube 6 is completely wrapped and prevents the airspeed tube 6 from falling out of the sleeve. The inlet 35, which connects the air outlet chamber 34 and the air inlet chamber 33 inside the sleeve 3, is located inside the annular protrusion 37.
[0041] Specific working principle:
[0042] like Figure 5 As shown, when testing airspeed, the airspeed and altitude detection tool of this UAV is inserted into the outside of the airspeed tube 6, so that the airspeed tube 6 is embedded in the air intake chamber 33 of the sleeve 3. During the insertion process, excess air in the air intake chamber 33 is discharged from the exhaust port 36 of the sleeve 3. Then, the exhaust port 11 of the balloon 1 is blocked with the thumb, and the balloon 1 is gently squeezed, so that the air in the balloon 1 slowly pushes open the ball in the air intake one-way valve 4 (at this time, the air exhaust one-way valve 5 is closed). The air flows into the dynamic pressure air passage in the airspeed tube 6 through the tube opening 61. The dynamic pressure interface 63 at the end of the dynamic pressure air passage is connected to the dynamic pressure sensor through the pipeline. This air will create positive pressure on the dynamic pressure sensor, increasing the airspeed and obtaining data of gradually increasing airspeed, thereby achieving the purpose of testing airspeed.
[0043] like Figure 6As shown, when testing altitude, first squeeze the balloon 1 of the airspeed altitude testing tool to expel excess air from the vent 11. Then, use your thumb to block the vent 11 of the balloon 1 without releasing it. Next, insert the airspeed altitude testing tool into the airspeed tube 6, so that the airspeed tube 6 is embedded in the air intake chamber 33 of the tube sleeve 3. Excess air in the air intake chamber 33 is expelled from the vent 36 of the tube sleeve 3. Keeping your thumb blocking the vent 11 of the balloon 1, gently release the balloon 1. The air in the air outlet chamber 34 of the airspeed tube 6 slowly opens the air outlet check valve 5 (at this time, the air intake check valve 4 is closed), and the air flows into the balloon 1. Since the air outlet chamber 34 is connected to the altitude port 62, it is connected to the static pressure channel in the airspeed tube 6. The static pressure interface 64 at the end of the static pressure channel is connected to the static pressure sensor through a pipeline, creating negative pressure on the static pressure sensor. The pressure on the static pressure sensor gradually decreases, and the altitude increases, thus obtaining data showing a gradual increase in altitude, thereby achieving the purpose of testing altitude.
[0044] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.
Claims
1. A tool for detecting the airspeed and altitude of a drone, characterized in that, include: The balloon has an exhaust port at one end and a connecting sleeve sealed at the other end; the connecting sleeve has a first air hole and a second air hole, both of which are connected to the inner cavity of the balloon. The sleeve is sealed to the connecting sleeve. One end of the sleeve is provided with an air inlet and an air outlet. The air inlet is connected to the first air hole and the air outlet is connected to the second air hole. The other end of the sleeve is provided with an opening. The air inlet is connected to the air inlet chamber inside the sleeve, the air outlet is connected to the air outlet chamber inside the sleeve, and the opening is connected to the air inlet chamber. The end of the air outlet chamber away from the air outlet is provided with an inlet that is connected to the air inlet chamber. An intake check valve is installed at the junction of the first air hole and the air inlet, with one end located inside the first air hole and the other end located inside the air inlet. And an exhaust check valve, installed at the junction of the second vent and the exhaust vent, with one end inside the second vent and the other end inside the exhaust vent; The air intake chamber of the tube sleeve is equipped with the air speed tube of the UAV. The air speed tube opening faces the air intake check valve, and its height hole corresponds to the axial position of the inlet. Its tail end dynamic pressure interface and static pressure interface are located at the open end of the tube sleeve.
2. The UAV airspeed and altitude detection tool according to claim 1, characterized in that, The air inlet chamber and the air outlet chamber are two independent cavities within the sleeve, connected only at the inlet.
3. The UAV airspeed and altitude detection tool according to claim 1, characterized in that, When the air intake check valve is working, the air inside the balloon flows through the air intake check valve into the air intake chamber, and at this time the air outlet check valve is closed; when the air outlet check valve is working, the air inside the air outlet chamber flows through the air outlet check valve into the balloon, and at this time the air intake check valve is closed.
4. The UAV airspeed and altitude detection tool according to claim 1, characterized in that, The sleeve is an elastic sleeve with a tapered surface in its middle along the axial direction, which is used to match the tapered surface at the front end of the airspeed tube. The air intake chamber inside the sleeve matches the outer dimensions of the airspeed tube.
5. The UAV airspeed and altitude detection tool according to claim 4, characterized in that, The conical surface of the sleeve is provided with an exhaust hole, which is connected to the air intake chamber. The exhaust hole is used to discharge excess air in the air intake chamber when the pitot tube is inserted into the air intake chamber.
6. The UAV airspeed and altitude detection tool according to claim 1, characterized in that, The inner wall of the open end of the sleeve near the edge is provided with an annular protrusion. The annular protrusion is used to seal with the outer wall of the airspeed tube and to prevent the airspeed tube from coming out of the sleeve.
7. The UAV airspeed and altitude detection tool according to claim 6, characterized in that, The access point is located inside the annular protrusion.
8. The UAV airspeed and altitude detection tool according to claim 1, characterized in that, The balloon is an ellipsoidal hollow structure that can be squeezed and rebounded.