A cross-media flow sensing device based on a magnetic cantilever beam

Abstract

The application discloses a cross-medium flow sensing device based on a magnetic cantilever beam, which is applied to an aircraft and comprises a cantilever beam with a magnetic component and a magnetic sensor arranged on a mounting assembly. The structure of the mounting assembly makes the environment around the magnetic sensor a sealed environment, so that the whole magnetic sensing device can adapt to two use environments of water and air. The cantilever beam can be deformed under the action of flow. The deformation drives the magnetic component on the cantilever beam to deflect, so that the magnetic field around the cantilever beam changes. The magnetic sensor is used for detecting the magnetic field change caused by the deformation of the cantilever beam and converting the magnetic field change into an electric signal to accurately reflect the speed and flow direction of the aircraft in the two media (air and water) and other flow field characteristics.

Description

Technical Field

[0001] This invention relates to the field of transmedium flight technology for aircraft, specifically to a transmedium flow sensing device based on a magnetic cantilever beam. Background Technology

[0002] With the advancement of technology, aircraft technology has evolved from traditional aerial vehicles to multi-domain, multi-medium transboundary aircraft. Transboundary aircraft are those capable of switching between at least two different physical media (such as water and air) and performing tasks. The emergence of these aircraft has solved many problems that traditional aircraft cannot efficiently perform tasks in complex environments, and they have significant application value, especially in amphibious flight, ocean exploration, deep-sea operations, and emergency rescue.

[0003] Despite the broad application prospects of transmedia spacecraft, achieving efficient switching between two or more different media still faces a series of technical challenges, including:

[0004] Compatibility issues with sensor systems: Traditional aircraft are typically equipped with sensor systems adapted to a specific environment (such as pressure sensors, angle sensors, etc.), but environmental parameters such as air pressure and flow velocity differ greatly between underwater and air. Existing sensors often only work efficiently in a single medium, making it difficult to provide the real-time, multi-dimensional environmental perception data required for cross-domain flight.

[0005] Complex flow perception problem in cross-medium flight: Because the underwater flow environment is significantly different from the atmospheric environment, existing flow perception systems are often not applicable to both media at the same time, resulting in severe control problems when aircraft fly across different media.

[0006] To overcome these limitations, it is necessary to develop sensor devices capable of sensing complex flows in cross-boundary mass flight and providing the key flow parameters required for flight control. Summary of the Invention

[0007] The purpose of this invention is to provide a cross-medium flow sensing device based on a magnetic cantilever beam. By utilizing the magnetic field changes caused by the deformation of the magnetic cantilever beam under the influence of different fluid dynamics in water and air, the device can sense the flow field characteristics of an aircraft in two media (air and water) in real time, such as speed and flow direction, thereby solving the technical problems existing in the prior art.

[0008] To solve the above-mentioned technical problems, the present invention specifically provides the following technical solution:

[0009] A cross-medium flow sensing device based on a magnetic cantilever beam includes: a cantilever beam with magnetic components, which deforms under the action of airflow; the magnetic components on the cantilever beam causing a change in the magnetic field around the cantilever beam; a magnetic sensor for detecting the change in the magnetic field caused by the deformation of the cantilever beam and converting it into an electrical signal to reflect the intensity and direction of the flow field around the cantilever beam; and a mounting assembly for mounting and fixing the cantilever beam and the magnetic sensor, wherein the structure of the mounting assembly makes the environment around the magnetic sensor a sealed environment, enabling the entire magnetic sensing device to adapt to both underwater and airborne operating environments.

[0010] Furthermore, the main body of the cantilever beam is a carbon fiber rod, and the magnetic component is a ring-shaped permanent magnet, which is sleeved on the carbon fiber rod.

[0011] Furthermore, the carbon fiber rod is provided with positioning sleeves at both ends of the permanent magnet, and the positioning sleeves are in transition fit with the carbon fiber rod to limit the permanent magnet; and the permanent magnet is wrapped in a copper tube to protect the permanent magnet.

[0012] Furthermore, the mounting assembly includes a mounting base and a cover plate. The mounting base has a first groove for mounting the magnetic sensor. The cover plate is used to cover the first groove, and an external force is applied to the cover plate to fit against the first groove, so that a sealed cavity is formed between the first groove and the cover plate.

[0013] The cover plate has through holes for fixing the carbon fiber rod, so that the magnetic component is located directly above the sensor.

[0014] Furthermore, the distance between the magnetic component and the magnetic sensor is 4-6 mm.

[0015] Furthermore, the magnetic sensor is integrated on the base, and the base has a wiring module connected to the magnetic sensor on the back side relative to the sensor, which serves as the power line interface and signal line interface of the magnetic sensor.

[0016] The base is disposed between the first groove and the cover plate. The size of the base can be fitted into the first groove, and the side of the base on which the magnetic sensor is integrated faces the cover plate.

[0017] Furthermore, the cover plate has an inner groove facing the magnetic sensor, and when an external force is applied to the cover plate, it fits into the base, so that there is a space between the cover plate and the base to accommodate the magnetic sensor.

[0018] Furthermore, the mounting base has a second groove within the first groove, forming a space for accommodating the wiring module;

[0019] The side wall of the mounting base has a through groove that communicates with the second groove, through which the power line and signal line of the magnetic sensor pass to connect to the wiring module.

[0020] Compared with the prior art, the present invention has the following advantages:

[0021] The magnetic cantilever beam-based cross-medium flight magnetic sensing device provided by this invention combines the technologies of magnetic cantilever beam and magnetic sensor, and can sense the flow field characteristics such as the speed and flow direction of the aircraft in two media (air and water) in real time.

[0022] By utilizing the magnetic field changes caused by the deformation of a magnetic cantilever beam under the different hydrodynamic characteristics in underwater and air, this device can accurately feed back flight data to the aircraft. It features high precision, high reliability, and low cost, and is suitable for cross-domain aircraft such as underwater drones, amphibious aircraft, and aerial drones. Attached Figure Description

[0023] To more clearly illustrate the embodiments of the present invention or the technical solutions in 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 merely exemplary, and those skilled in the art can derive other embodiments based on the provided drawings without creative effort.

[0024] Figure 1 This is a schematic diagram of the result of a cross-medium flow sensing device based on a magnetic cantilever beam.

[0025] Figure 2 This is a schematic diagram of the cantilever beam structure;

[0026] Figure 3 A schematic diagram showing the result of one embodiment of installing a magnetic sensor;

[0027] Figure 4 for Figure 1 Exploded view of the magnetic sensing device shown;

[0028] Figure 5 This diagram illustrates the magnitude of the magnetic field at different distances between the magnetic component and the sensor.

[0029] The labels in the diagram represent the following:

[0030] 1-Cantilever beam, 11-Magnetic component, 12-Carbon fiber rod, 13-Permanent magnet, 14-Positioning sleeve, 15-Copper tube;

[0031] 2-Magnetic sensor, 21-Base, 22-Wiring module;

[0032] 3-Mounting component, 31-Mounting base, 32-Cover plate, 311-First groove, 312-Second groove, 313-Through groove, 321-Through hole. Detailed Implementation

[0033] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0034] like Figure 1 As shown, the present invention provides a specific embodiment of a cross-medium flow sensing device based on a magnetic cantilever beam, including a cantilever beam 1 and a magnetic sensor 2 mounted on a mounting assembly 3.

[0035] The toughness and rigidity of the material used to make the cantilever beam 1 enable the cantilever beam 1 to deform under the action of airflow.

[0036] Specifically, in this embodiment, carbon fiber rod 12 is selected as the main body of the cantilever beam.

[0037] The cantilever beam 1 has a magnetic component 11, which causes the magnetic field around the cantilever beam 1 to change during the deformation caused by airflow.

[0038] The magnetic sensor 2 is used to detect the changes in the magnetic field caused by the deformation of the cantilever beam 1 and convert them into electrical signals for output. This allows it to accurately reflect the intensity and direction of the airflow around the cantilever beam 1, and thus the intensity and direction of the airflow around the entire aircraft.

[0039] Specifically, in this embodiment, the magnetic sensor 2 is a three-dimensional magnetic sensor 2, specifically the MLX90393 three-dimensional magnetic sensor, which can detect changes in the magnetic field in the X, Y, and Z directions in space. The flow direction information can be obtained through vector synthesis. The accuracy and sensitivity of the three-dimensional magnetic field sensor enable it to capture tiny signals in the airflow changes and convert them into electrical signals for subsequent data processing.

[0040] The mounting assembly is used to mount and fix the cantilever beam and the magnetic sensor. The structure of the mounting assembly makes the environment around the magnetic sensor a sealed environment, enabling the entire magnetic sensing device to be used in both underwater and air environments.

[0041] In addition to mounting and fixing the cantilever beam 1 and the magnetic sensor 2, the mounting component 3 is also used to mount and fix the entire magnetic sensing device to the outside of the aircraft, so that during the flight of the aircraft, the external force characteristics of the cantilever beam 1 received by the fluid are consistent and synchronized with the external force characteristics of the aircraft received by the fluid, so as to realize the real-time feedback of the electrical signal of the magnetic sensor 2 and improve the response speed.

[0042] Furthermore, in order to accurately reflect the airflow conditions around the aircraft, the installation position and orientation of the mounting component 3 and the aircraft are such that during the flight of the aircraft, the main body of the cantilever beam 1 is set vertically relative to the fluid, so that the deformation of the cantilever beam 1 can better reflect the fluid conditions.

[0043] This embodiment provides an example of a cantilever beam 1, such as... Figure 2 As shown:

[0044] The main body of the cantilever beam 1 is a carbon fiber rod 12, and the magnetic component 11 is a ring-shaped N52 permanent magnet 13, which is sleeved on the carbon fiber rod 12. The carbon fiber rod 12 is provided with positioning sleeves 14 at both ends of the permanent magnet 13. The positioning sleeves 14 are fitted with the carbon fiber rod 12 to limit the position of the permanent magnet 13, so that the position of the permanent magnet 13 on the carbon fiber rod 12 is fixed. The entire magnetic component 11 is wrapped in a copper tube 15 to protect the permanent magnet 13.

[0045] This embodiment provides an example of installing component 3, such as... Figure 3 As shown:

[0046] The mounting assembly 3 includes a mounting base 31 and a cover plate 32. The mounting base 31 has a first groove 311 for mounting the magnetic sensor 2. The cover plate 32 is used to cover the first groove 311, and the cover plate 32 is subjected to an external force to fit against the first groove 311, so that a sealed cavity is formed between the first groove 311 and the cover plate 32 to ensure waterproofness.

[0047] Specifically, the cover plate 32 is fixed to the mounting base 31 by bolts.

[0048] The cover plate 32 has a through hole 321 for fixing the carbon fiber rod 12, so that the magnetic component 11 is located directly above the sensor.

[0049] In this embodiment, the detection performance of magnetic sensor 2 with different magnet heights under the same load was tested, aiming to optimize the optimal distance between magnetic component 11 and sensor. Figure 5 As shown, this test was conducted at a distance from the bottom surface of the magnetic component 11 to the magnetic sensor 2 ranging from 3mm to 11mm. The cantilever beam 1 has a diameter of 0.3mm and a length of 65mm.

[0050] Each test applies the same load to the free end of the cantilever beam 1, with the loading direction aligned with the X direction of the magnetic sensor 2. Therefore, the change in the magnetic field of the magnetic sensor 2 along the Y and Z directions is very small.

[0051] Test results are as follows Figure 5 As shown in the figure, the horizontal axis represents the distance between the bottom surface of the magnetic component 11 and the magnetic sensor 2, and the vertical axis represents the magnetic field strength in the X direction measured by the magnetic sensor 2. It can be seen from the figure that the magnetic sensor 2 has the best detection effect when the distance between the magnetic component 11 and the magnetic sensor 2 is 4-6mm. As the distance increases, the magnetic field strength gradually weakens.

[0052] Therefore, in this embodiment, the distance between the magnetic component 11 and the magnetic sensor 2 is preferably 4-6 mm.

[0053] The magnetic sensor 2 requires a power supply line to provide power and a signal line to transmit signals to the flight control system. Therefore, to ensure the sealing of the magnetic sensor 2, this embodiment provides the following structure, as follows: Figure 3 and Figure 4 As shown:

[0054] The magnetic sensor 2 is integrated on the base 21. The base 21 has a wiring module 22 connected to the magnetic sensor 2 on the back side relative to the sensor. This module serves as the power line interface and signal line interface for the magnetic sensor 2. The base 21 is located between the first groove 311 and the cover plate 32. The size of the base 21 is such that it can be fitted into the first groove 311, and the side of the base 21 on which the magnetic sensor 2 is integrated faces the cover plate 32.

[0055] The bolts of the fixed cover plate 32 pass through the four corners of the base 21 and are threaded to the four corners of the first groove 311 of the mounting base 31.

[0056] Furthermore, the cover plate 32 has an inner groove facing the magnetic sensor 2. When the cover plate 32 is subjected to external force by the tightened bolts, it fits against the base 21, so that there is a space between the cover plate 32 and the base 21 to accommodate the magnetic sensor 2.

[0057] Furthermore, when the cover plate 32 is tightened by the bolts and applied external force to fit against the base 21, the base 21 fits against the first groove 311; therefore, the mounting base 31 has a second groove 312 in the first groove 311, forming a space for accommodating the wiring module 22; the side wall of the mounting base 31 has a through groove 313 that communicates with the second groove 312, through which the power line and signal line of the magnetic sensor 2 pass to connect with the wiring module 22.

[0058] The power line and signal line of the magnetic sensor 2 are connected to a flexible flat cable through the through groove 313. The through groove 313 is sealed with 705 silicone rubber. 705 silicone rubber has good fluidity and can fill the entire internal space of the mounting assembly 3 to protect the chip.

[0059] Furthermore, waterproof gaskets are added to the bolt mounting holes and various connections, or 705 silicone rubber is used for sealing, so that the mounting component 3 can achieve a better waterproof effect; at the same time, the sealing shell formed by the mounting component 3 and the cover plate improves the pressure resistance of the device underwater.

[0060] Based on the above, the cross-medium flight magnetic sensing device based on a magnetic cantilever beam provided in this embodiment has the following significant technical advantages:

[0061] Large measuring range: With a cantilever beam length of 65mm and a diameter of 0.4mm, the aerial measurement range is 0-60m / s, and the underwater measurement range is 0-10m / s.

[0062] High-precision measurement: By combining a magnetic cantilever beam with a three-dimensional magnetic field sensor, the speed and direction of the aircraft can be accurately captured in complex fluid environments, providing high-precision flight data. The speed resolution in air can reach 0.8 m / s, and the resolution in water can reach 0.03 m / s.

[0063] Rapid response: Using magnetic field signals as the signal source, the response speed is extremely fast, which can reflect fluid changes in real time and ensure that the aircraft can quickly sense when it encounters complex flow.

[0064] Low cost: Compared with traditional sensor systems, it reduces the reliance on multiple high-cost pressure sensors, lowering the overall cost of the system, making it suitable for economical aircraft as well as transcontinental aircraft.

[0065] The above embodiments are merely exemplary embodiments of this application and are not intended to limit this application. The scope of protection of this application is defined by the claims. Those skilled in the art can make various modifications or equivalent substitutions to this application within its substance and scope of protection, and such modifications or equivalent substitutions should also be considered to fall within the scope of protection of this application.

Claims

1. A transmedium flow sensing device based on a magnetic cantilever beam, characterized in that, include: A cantilever beam (1) with a magnetic component (11) deforms under the action of airflow; the magnetic component (11) on the cantilever beam (1) causes the magnetic field around the cantilever beam (1) to change; A magnetic sensor (2) is used to detect the change in magnetic field caused by the deformation of the cantilever beam (1) and convert it into an electrical signal to reflect the intensity and direction of the flow field around the cantilever beam (1); The mounting assembly (3) is used to install and fix the cantilever beam (1) and the magnetic sensor (2). The structure of the mounting assembly (3) makes the environment around the magnetic sensor (2) a sealed environment, so that the entire magnetic sensing device can adapt to both underwater and airborne environments. The main body of the cantilever beam (1) is a carbon fiber rod (12), and the magnetic component (11) is a ring-shaped permanent magnet (13). The permanent magnet (13) is sleeved on the carbon fiber rod (12).

2. The cross-medium flow sensing device according to claim 1, characterized in that, The carbon fiber rod (12) has positioning sleeves (14) at both ends of the permanent magnet (13). The positioning sleeves (14) are in transition with the carbon fiber rod (12) to limit the permanent magnet (13). The permanent magnet (13) is wrapped in a copper tube (15) to protect the permanent magnet (13).

3. The cross-medium flow sensing device according to claim 1 or 2, characterized in that, The mounting assembly (3) includes a mounting base (31) and a cover plate (32). The mounting base (31) has a first groove (311) for mounting the magnetic sensor (2). The cover plate (32) is used to cover the first groove (311), and the cover plate (32) is subjected to an external force to fit against the first groove (311), so that a sealed cavity is formed between the first groove (311) and the cover plate (32). The cover plate (32) is provided with a through hole (321) for fixing the carbon fiber rod (12), so that the magnetic component (11) is located directly above the sensor.

4. The cross-medium flow sensing device according to claim 3, characterized in that, The distance between the magnetic component (11) and the magnetic sensor (2) is 4-6 mm.

5. The cross-medium flow sensing device according to claim 4, characterized in that, The magnetic sensor (2) is integrated on the base (21). The base (21) has a wiring module (22) connected to the magnetic sensor (2) on the back side relative to the sensor. This module serves as the power line interface and signal line interface of the magnetic sensor (2). The base (21) is disposed between the first groove (311) and the cover plate (32). The base (21) is sized to fit within the first groove (311), and the side of the base (21) on which the magnetic sensor (2) is integrated faces the cover plate (32).

6. The cross-medium flow sensing device according to claim 5, characterized in that, The cover plate (32) has an inner groove facing the magnetic sensor (2). When the cover plate (32) is subjected to external force, it fits against the base (21), so that there is a space between the cover plate (32) and the base (21) to accommodate the magnetic sensor (2).

7. The cross-medium flow sensing device according to claim 6, characterized in that, The mounting base (31) has a second groove (312) inside the first groove (311) to form a space for accommodating the wiring module (22); The mounting base (31) has a through groove (313) on its side wall that communicates with the second groove (312), through which the power line and signal line of the magnetic sensor (2) pass to connect to the wiring module (22).

Images