Air pressure detecting member and unmanned aerial vehicle

Abstract

The utility model relates to an unmanned plane technical field discloses a kind of air pressure detection piece and unmanned plane, the air pressure detection piece includes: shell, baffle ring and air pressure sensor, shell is used to set in the outer side of the shell of unmanned plane, the lateral wall of shell is equipped with outer ring air hole, baffle ring is located in the inside of shell, baffle ring and lateral wall form annular groove, baffle ring is equipped with inner ring air hole, outer ring air hole and inner ring air hole are staggered arrangement, and respectively communicate annular groove, air pressure sensor is located in the inside of baffle ring. Air pressure detection piece uses independent external structure, gets rid of body heat interference and electromagnetic interference, suppresses temperature drift error, realizes the stable detection of unmanned plane long flight state, improves data reliability and flight safety. The staggered structure of inner ring air hole and outer ring air hole has pressure stabilizing function, baffle ring increases the flow resistance of airflow, weakens the dynamic pressure interference generated by high-speed airflow, provides buffer guarantee for the external scheme of air pressure detection piece, reduces the influence of external airflow on air pressure detection.

Description

Technical Field

[0001] This application relates to the field of unmanned aerial vehicle (UAV) technology, and more particularly to a barometric pressure detection device and an UAV. Background Technology

[0002] Barometric pressure sensors monitor the relative altitude and flight status of UAVs by collecting ambient atmospheric static pressure. In related technologies, barometric pressure sensors are typically integrated into the flight control circuit board inside the fuselage. During flight, these sensors are prone to temperature drift and zero-point offset. This accumulated temperature drift error leads to a significant decrease in altitude measurement accuracy during long-endurance flight, making it difficult to meet the high-precision, high-stability, and high-safety flight control requirements of UAVs. Utility Model Content

[0003] This application aims to address at least one of the technical problems existing in the prior art or related technologies.

[0004] The first aspect of this application provides a pressure detection device, which includes: a housing, a retaining ring, and a pressure sensor. The housing is used to be installed on the outer side of the casing of a UAV. The side wall of the housing is provided with an outer ring vent hole. The retaining ring is located inside the housing. The retaining ring and the side wall form an annular groove. The retaining ring is provided with an inner ring vent hole. The outer ring vent hole and the inner ring vent hole are staggered and connected to the annular groove respectively. The pressure sensor is located inside the retaining ring.

[0005] In some of the technical solutions provided in this application, the air pressure detection component further includes: a first buffer component, which is located in an annular groove. The airflow that enters the housing through the outer ring vent hole flows through the first buffer component and then enters the inner ring vent hole.

[0006] In some of the technical solutions provided in this application, the diameter of the outer ring vent is greater than or equal to the diameter of the inner ring vent.

[0007] In some of the technical solutions provided in this application, the number of vent holes in the outer ring is greater than or equal to the number of vent holes in the inner ring.

[0008] In some of the technical solutions provided in this application, the outer ring vent holes and the inner ring vent holes have the same height.

[0009] In some of the technical solutions provided in this application, the air pressure detection component also includes: a circuit board and a shielding cover. The circuit board is located inside the retaining ring, the air pressure sensor is located on the upper surface of the circuit board, the shielding cover is connected to the circuit board, the shielding cover is located outside the air pressure sensor, the shielding cover has a through air inlet hole, and the shielding cover is used to shield electromagnetic interference signals.

[0010] In some of the technical solutions provided in this application, the air pressure detection component further includes: a second buffer, which is located inside the shield and covers the air pressure sensor. The airflow that enters the shield through the air inlet flows through the second buffer and then contacts the air pressure sensor.

[0011] In some of the technical solutions provided in this application, the air pressure detection device also includes an indicator light, which is located on the top surface of the housing and is used to emit light to display the status of the air pressure detection device.

[0012] In some of the technical solutions provided in this application, the air pressure detection component also includes: a support rod and a mounting base, the top of the support rod being connected to the bottom of the housing, the mounting base being connected to the bottom of the support rod, and the mounting base being connected to the outer wall of the housing.

[0013] The second aspect of the technical solution of this application proposes an unmanned aerial vehicle (UAV) comprising: a fuselage and any one of the aforementioned pressure detection components, wherein the pressure detection component is located on the outside of the fuselage.

[0014] Compared with related technologies, this utility model has at least the following beneficial effects: The barometric pressure sensor adopts an independent external structure, eliminating thermal and electromagnetic interference from the fuselage, suppressing temperature drift errors, and enabling stable detection during long-duration UAV operation, thus improving data reliability and flight safety. The external modular design facilitates maintenance and enhances the sensor's versatility and expandability. The staggered structure of the inner and outer vents provides pressure stabilization, while the retaining ring increases airflow resistance, preventing direct impact from external airflow onto the internal pressure sensor and reducing dynamic pressure interference from high-speed airflow. This provides a buffer for the external design, minimizing the influence of external airflow on pressure detection and enabling the sensor to collect static pressure close to the real environment, resulting in more accurate altitude measurement data. Furthermore, the retaining ring forms a protective cavity within the housing, protecting the internal pressure sensor and preventing large dust particles and water droplets from directly impacting it. Attached Figure Description

[0015] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of some embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of this application. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings: Figure 1 One of the partial structural schematic diagrams of a pressure detection device according to an embodiment of this application; Figure 2 A top view of a pressure detection device according to an embodiment of this application; Figure 3 It shows Figure 2 A sectional view cut along section AA. Figure 4 A front view of a pressure detection element according to an embodiment of this application; Figure 5 This application provides a schematic diagram of the structure of the housing and retaining ring according to one embodiment. Figure 6 An exploded view of a partial structure of a pressure detection device according to an embodiment of this application; Figure 7 A second partial structural schematic diagram of a pressure detection device according to an embodiment of this application; Figure 8 It shows Figure 7 A sectional view cut along BB.

[0016] in, Figures 1 to 8 The correspondence between the reference numerals and component names in the attached drawings is as follows: 10. Pressure detection component; 100. Housing; 110. Outer shell; 111. Outer ring vent; 112. Indicator light; 120. Bottom shell; 130. Top cover; 200. Retaining ring; 210. Inner ring vent; 220. Annular groove; 300. Pressure sensor; 410. First buffer; 420. Second buffer; 500. Circuit board; 600. Shielding cover; 610. Air inlet; 700. Mounting base; 710. Mounting hole; 800. Support rod. Detailed Implementation

[0017] To better understand the above technical solutions, the technical solutions of the embodiments of this application will be described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the embodiments of this application and the specific features in the embodiments are detailed descriptions of the technical solutions of the embodiments of this application, rather than limitations on the technical solutions of this application. In the absence of conflict, the embodiments of this application and the technical features in the embodiments can be combined with each other.

[0018] The first aspect of this application provides a pressure detection element 10, such as... Figure 1 , Figure 3 , Figure 4 and Figure 5 As shown, the air pressure detection component 10 includes: a housing 100, a retaining ring 200, and an air pressure sensor 300. The housing 100 is used to be installed on the outside of the drone's casing. The side wall of the housing 100 is provided with an outer ring ventilation hole 111. The retaining ring 200 is located inside the housing 100. The retaining ring 200 and the side wall form an annular groove 220. The retaining ring 200 is provided with an inner ring ventilation hole 210. The outer ring ventilation hole 111 and the inner ring ventilation hole 210 are staggered and connected to the annular groove 220 respectively. The air pressure sensor 300 is located inside the retaining ring 200.

[0019] In this embodiment, the housing 100 is located on the outside of the drone's casing, so that the barometric pressure sensor 10 is arranged entirely on the outside of the drone's casing. The barometric pressure sensor 10 is in direct contact with the outside atmosphere and is far away from the sealed cavity of the drone body. This avoids temperature drift and thermal interference caused by heat sources inside the drone body, improves the stability of long-term barometric pressure measurement of the barometric pressure sensor 10, and reduces electromagnetic interference generated by electrical components inside the drone body.

[0020] The top of the housing 100 is cylindrical. A retaining ring 200 is provided inside the housing 100. An annular sidewall at the top of the housing 100 surrounds the outer circumference of the retaining ring 200 and is coaxially arranged with it. An annular space is provided between the retaining ring 200 and the sidewall of the housing 100, forming an annular groove 220. The annular groove 220 is located outside the retaining ring 200, and a pressure sensor 300 is provided inside the retaining ring 200. The sidewall of the housing 100 and the retaining ring 200 are respectively provided with staggered outer ring vent holes 111 and inner ring vent holes 210, which communicate with the annular groove 220. Airflow from outside the housing 100 enters the annular groove 220 inside the housing 100 through the outer ring vent 111. The staggered arrangement of the two side vents creates a bent airflow channel within the annular groove 220. This bent airflow channel prevents direct external airflow from entering the housing 100. After entering the annular groove 220, the airflow first impacts the baffle ring 200, reducing the airflow velocity during the drone's flight or hovering. As the airflow flows along the outer wall of the baffle ring 200, its velocity is further reduced, allowing the decelerated airflow to enter the inner side of the baffle ring 200 through the inner ring vent 210, contacting the air pressure sensor 300 inside the baffle ring 200 so that the air pressure sensor 300 can measure the airflow pressure.

[0021] The barometric pressure sensor 10 adopts an independent external structure, eliminating thermal and electromagnetic interference from the fuselage, suppressing temperature drift errors, and achieving stable detection during long-duration UAV operation, thus improving data reliability and flight safety. The external modular design facilitates maintenance of the barometric pressure sensor 10 and enhances its versatility and expandability. The staggered structure of the inner and outer vent holes 210 provides pressure stabilization, while the baffle ring 200 increases airflow resistance, preventing direct impact from external airflow on the internal pressure sensor 300 and reducing dynamic pressure interference from high-speed airflow. This provides a buffer for the external design of the barometric pressure sensor 10, reducing the impact of external airflow on pressure detection and enabling the barometric pressure sensor 10 to collect static pressure close to the real environment, resulting in more accurate altitude measurement data. Furthermore, the baffle ring 200 forms a protective cavity inside the housing 100, protecting the internal pressure sensor 300 and preventing large dust particles and water droplets from directly impacting it.

[0022] In some embodiments provided in this application, such as Figure 3 As shown, the air pressure detection component 10 also includes a first buffer component 410, which is located in the annular groove 220. The airflow that enters the housing 100 through the outer ring vent hole 111 flows through the first buffer component 410 and then enters the inner ring vent hole 210.

[0023] In this embodiment, the first buffer 410 has a porous structure for airflow. For example, the first buffer 410 can be polyurethane foam, and the annular first buffer 410 is filled in the annular groove 220 without any buildup. External airflow enters the annular groove 220 through the outer ring vents 111, passes through the first buffer 410, and flows into the inner ring vents 210. The first buffer 410 further dissipates the kinetic energy of the airflow, suppresses drastic pressure fluctuations caused by gusts and blade turbulence, and optimizes the static pressure acquisition effect. Furthermore, as a pressure-stabilizing filter structure, the first buffer 410 can filter out high-frequency turbulence, noise, and local instantaneous pressure differences, achieving uniform circumferential pressure. Moreover, the first buffer 410 can filter out some dust and moisture, preventing contaminants from entering the internal sensor area and extending the sensor's lifespan.

[0024] In some embodiments provided in this application, the diameter of the outer ring vent 111 is greater than or equal to the diameter of the inner ring vent 210.

[0025] In this embodiment, the relatively large outer vent 111 allows external air to smoothly enter the annular groove 220. The large vent provides sufficient air intake cross-sectional area, ensuring the airflow of the pressure detection element 10. The relatively small inner vent 210 throttles and slows the airflow, reducing airflow impact. The size matching of the inner and outer vents balances ventilation response speed and resistance to airflow disturbance.

[0026] For example, the inner vent 210 has a diameter of 0.7 mm to 0.9 mm. The small diameter of the inner vent 210 can effectively reduce the entry of large particles into the inside of the sensor, thus providing better interception and protection. The outer vent 111 has a diameter of 0.9 mm to 1.1 mm. For example, the inner vent 210 has a diameter of 0.8 mm, and the outer vent 111 has a diameter of 1 mm.

[0027] In some embodiments provided in this application, the number of outer ring vent holes 111 is greater than or equal to the number of inner ring vent holes 210.

[0028] In this embodiment, multiple outer ring vents 111 and multiple inner ring vents 210 are distributed circumferentially at intervals, enabling the UAV to avoid steady-state pressure deviation caused by a single vent facing the wind or being carried away by the wind when flying in any direction. The relatively large number of outer ring vents 111 makes the air intake position of the shell 100 more uniform and the total air intake area sufficient, ensuring the airflow of the pressure detection element 10. This allows the internal air pressure detection element 10 to quickly follow changes in external atmospheric pressure, making the air pressure response more sensitive and avoiding measurement lag when altitude changes. The fewer number of inner ring vents 210, combined with the staggered structure, reduces the direct influx of turbulent flow, balancing response speed and anti-interference performance.

[0029] For example, the number of inner ring vent holes 210 is 5 to 7, and the number of outer ring vent holes 111 is 7 to 9. For example, the number of inner ring vent holes 210 is 6, and the number of outer ring vent holes 111 is 8.

[0030] In some embodiments provided in this application, the outer ring vent 111 and the inner ring vent 210 have the same height.

[0031] In this embodiment, the centers of the outer ring vent 111 and the inner ring vent 210 are at the same height, and the airflow flows circumferentially at the same horizontal height within the annular groove 220, making the airflow more stable and reducing vertical impact. Furthermore, this facilitates the processing and positioning of the outer ring vent 111 and the inner ring vent 210, simplifying the manufacturing process.

[0032] In some embodiments provided in this application, such as Figure 6 , Figure 7 and Figure 8 As shown, the air pressure detection component 10 also includes: a circuit board 500 and a shield 600. The circuit board 500 is located inside the retaining ring 200, the air pressure sensor 300 is located on the upper surface of the circuit board 500, the shield 600 is connected to the circuit board 500, the shield 600 covers the air pressure sensor 300, and the shield 600 has a through air inlet 610. The shield 600 is used to shield electromagnetic interference signals.

[0033] In this embodiment, a barometric pressure sensor 300 and a shielding cover 600 for shielding electromagnetic interference signals are mounted on the circuit board 500. The circuit board 500 can be a PCB (Printed Circuit Board). The shielding cover 600 is mounted on the circuit board 500 by clips, and the open end of the shielding cover 600 is connected to the circuit board 500. The perimeter of the open end is sealed with adhesive to isolate air. The shielding cover 600 provides an independent electromagnetic shielding cavity for the barometric pressure sensor 300, isolating it from external electromagnetic interference, reducing altitude misjudgments caused by electromagnetic interference, improving the reliability of the data collected by the barometric pressure sensor 300, and enhancing the flight safety of the UAV.

[0034] The shield 600 is provided with an air inlet 610. The airflow inside the baffle ring 200 enters the interior of the shield 600 through the air inlet 610 to contact the pressure sensor 300. The shield 600 performs secondary low-speed buffering on the airflow that has passed through the baffle ring 200 for primary pressure stabilization through the air inlet 610, realizing a secondary refined airflow processing structure and improving the measurement stability under dynamic flight conditions.

[0035] For example, there is one air inlet 610, and the diameter of the air inlet 610 is 0.5mm to 1.5mm. For example, the diameter of the air inlet 610 is 0.5mm, 1mm or 1.5mm to ensure the voltage stabilization and current limiting capability.

[0036] In some embodiments provided in this application, such as Figure 6 As shown, the air pressure detection device 10 also includes a second buffer 420, which is located inside the shield 600. The second buffer 420 covers the air pressure sensor 300. The airflow that enters the shield 600 through the air inlet 610 flows through the second buffer 420 and then contacts the air pressure sensor 300.

[0037] In this embodiment, the shielding cover 600 also includes a second buffer 420 covering the pressure sensor 300. The second buffer 420 has a porous structure for airflow, for example, it can be polyurethane foam. Airflow entering the shielding cover 600 passes through the second buffer 420 and then contacts the pressure sensor 300. The airflow is further buffered and attenuated by the second buffer 420, filtering out high-frequency turbulence and noise. This multi-buffering structure eliminates airflow pulsation interference, achieving noise reduction and stable flow. Furthermore, the second buffer 420 directly covers the surface of the pressure sensor 300, preventing fine dust and condensation from directly falling onto the sensor chip surface, providing physical protection and interception for the pressure sensor 300, and extending its service life.

[0038] In some embodiments provided in this application, such as Figure 2 As shown, the air pressure detection device 10 also includes an indicator light 112, which is located on the top surface of the housing 100 and is used to emit light to display the status of the air pressure detection device 10.

[0039] In this embodiment, the top surface of the housing 100 is provided with an indicator light 112 to display the status of the air pressure detector 10. For example, the indicator light 112 is communicatively connected to the circuit board 500 and emits light to display the detection status or alarm status of the air pressure detector 10. The operator can intuitively observe the status of the indicator light 112 from the outside of the drone to obtain the working status or fault status of the air pressure detector 10, making the information transmission method more efficient and convenient.

[0040] In some embodiments provided in this application, such as Figure 1 and Figure 3 As shown, the air pressure detection component 10 also includes a support rod 800 and a mounting base 700. The top of the support rod 800 is connected to the bottom of the housing 100, the mounting base 700 is connected to the bottom of the support rod 800, and the mounting base 700 is connected to the outer wall of the housing.

[0041] In this embodiment, the housing 100 includes an interconnected upper cover 130, an outer shell 110, and a bottom shell 120. The upper cover 130 fastens to the top opening of the outer shell 110. An indicator light 112 is located on the upper cover 130. The bottom shell 120 is connected to the bottom surface of the outer shell 110. A retaining ring 200 and a barometric pressure sensor 300 are located inside the outer shell 110. A support rod 800 extends along the height direction, with its two ends connected to the bottom shell 120 and a mounting base 700, respectively. The mounting base 700 is connected to the outer wall of the housing through mounting holes 710. There are four mounting holes 710 to accommodate different types of UAV housings. The support rod 800 raises the housing 100, placing the barometric pressure sensor 10 in the static pressure-free zone outside the housing, away from the boundary layer on the housing surface and the underwash airflow area of ​​the propeller blades, thus avoiding turbulence interference sources. The length of the support rod 800 is adapted to the model of the drone, thereby adjusting the length of the support rod 800 according to different models and improving the versatility of the barometric pressure sensor 10.

[0042] The support rod 800 is made of high-strength carbon fiber composite material as a support structure, while the shell 100 and the mounting base 700 are made of lightweight plastic material and are processed by 3D printing technology to reduce the overall structural weight of the air pressure detection component 10, so as to avoid adding extra payload to the drone and affecting the original endurance, maneuverability and flight attitude of the drone.

[0043] A second aspect of this application provides a drone, which includes a housing and any one of the aforementioned barometric pressure sensors 10, the barometric pressure sensor 10 being located on the outside of the housing.

[0044] In this embodiment, it should be noted that since the UAV includes the air pressure detection element 10 provided in any of the above embodiments, it has all the beneficial technical effects of the air pressure detection element 10. To avoid repetition, it will not be described in detail here.

[0045] In this utility model, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance; the term "multiple" refers to two or more unless otherwise explicitly defined. The terms "install," "connect," "join," and "fix" should be interpreted broadly. For example, "connect" can be a fixed connection, a detachable connection, or an integral connection; "join" can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0046] In the description of this utility model, it should be understood that the terms "upper", "lower", "left", "right", "front", "rear", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or unit referred to must have a specific orientation or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0047] In the description of this specification, the terms "one embodiment," "some embodiments," "specific embodiment," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0048] The above are merely some embodiments of this utility model and are not intended to limit the utility model. Various modifications and variations can be made to this utility model by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. A pressure detection device, characterized in that, include: A housing for mounting on the outside of a drone's fuselage, the sidewalls of which have an outer ring of ventilation holes; A retaining ring is disposed inside the housing. The retaining ring and the side wall form an annular groove. The retaining ring is provided with an inner ring vent hole. The outer ring vent hole and the inner ring vent hole are staggered and respectively connected to the annular groove. A pressure sensor is located inside the retaining ring.

2. The air pressure detection element according to claim 1, characterized in that, Also includes: The first buffer element is located in the annular groove. Airflow entering the housing through the outer ring vent hole flows through the first buffer element and then enters the inner ring vent hole.

3. The air pressure detection element according to claim 1, characterized in that, The diameter of the outer ring vent is greater than or equal to the diameter of the inner ring vent.

4. The air pressure detection element according to claim 1, characterized in that, The number of vent holes in the outer ring is greater than or equal to the number of vent holes in the inner ring.

5. The air pressure detection element according to claim 1, characterized in that, The outer ring vent hole is at the same height as the inner ring vent hole.

6. The air pressure detection element according to any one of claims 1 to 5, characterized in that, Also includes: A circuit board is located inside the retaining ring, and the air pressure sensor is located on the upper surface of the circuit board; A shielding cover is connected to the circuit board and covers the outside of the pressure sensor. The shielding cover has a through air inlet and is used to shield electromagnetic interference signals.

7. The air pressure detection element according to claim 6, characterized in that, Also includes: The second buffer is located inside the shield and covers the air pressure sensor. The airflow that enters the shield through the air inlet flows through the second buffer and then contacts the air pressure sensor.

8. The air pressure detection element according to any one of claims 1 to 5, characterized in that, Also includes: An indicator light is located on the top surface of the housing. The indicator light is used to emit light to indicate the status of the air pressure detection element.

9. The air pressure detection element according to any one of claims 1 to 5, characterized in that, Also includes: A support rod, the top of which is connected to the bottom of the housing; The mounting base is connected to the bottom of the support rod, and the mounting base is connected to the outer wall of the housing.

10. A drone, characterized in that, include: chassis; The air pressure detection element as described in any one of claims 1 to 9, wherein the air pressure detection element is located on the outside of the housing.

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