A drone-borne ecosystem sensible heat flux measurement device

Abstract

The present invention relates to a device for measuring the sensible heat flux of an unmanned aerial vehicle (UAV) ecosystem, comprising a wind speed measurement sensing part, a probe sleeve, a connecting cone, a conversion pipe section, a temperature collection component, a sensor module, a tail pipe, a preset pipe, a buffer component and an angle adjustment component; the wind speed measurement sensing part, the probe sleeve, the connecting cone, the conversion pipe section and the tail pipe are connected in sequence; the wind speed measurement sensing part is connected via a pressure-guiding pipe group in the probe sleeve and a pressure-guiding joint at the end of the connecting cone, and the pressure-guiding joint is connected via a pneumatic pipe group in the connecting cone and a sensor module in the tail pipe; the free end of the tail pipe is rotatably connected to the free end of the preset pipe; a buffer component is provided at the connection between the tail pipe and the preset pipe; the angle adjustment component is installed on the preset pipe, and the angle adjustment component is transmission-connected to the tail pipe to drive the tail pipe to rotate in a horizontal plane to achieve angle fine-tuning. The beneficial effect is that the device can not only meet monitoring needs, but also be applicable to a variety of UAV flight postures.

Description

Technical Field

[0001] The present invention relates to the field of atmospheric measurement technology, and in particular to a device for measuring sensible heat flux of an unmanned aerial vehicle (UAV)-borne ecosystem. Background Art

[0002] Ecosystem sensible heat flux (SEH) is the primary form of heat exchange between terrestrial ecosystems and the atmosphere. It is also a crucial feedback process after terrestrial ecosystems absorb solar radiation and is a key factor in Earth's surface energy balance. Monitoring and estimating SEH is crucial for research on global climate change, the heat island effect, and Earth's surface energy balance. Currently, monitoring of SEH is primarily done through ground-based tower-based eddy covariance observations, which cover a limited spatial area of ​​only a few hundred meters, making it difficult to obtain regionally representative SEH data. Satellite remote sensing inversion methods can provide quantitative information on ecosystem SEH at large spatial scales. However, model-based methods are often developed based on assumptions and require verification of their simulations with ground-based observations at the same observation scale. However, due to the discrepancy in the spatial scales between ground-based monitoring and remote sensing methods, direct comparisons between the two are difficult, hindering research and development on ecosystem energy cycles at national and watershed scales.

[0003] Currently, new ecosystem flux observation technologies using drones as observation platforms have the characteristics of high observation accuracy, large spatial coverage, low cost, and high flexibility. They can achieve direct observation of regional ecosystem sensible heat flux. However, at this stage, there are still many problems with drone ecosystem sensible heat flux observation equipment. On the one hand, most of the observation equipment on the market is imported, and its wind speed and temperature measurement are split structures with low integration, complex structure, and high failure rate. In addition, the observation equipment for three-dimensional wind speed and temperature pulsation is heavy, costly, and inefficient, making it unsuitable for drone installation. On the other hand, there are no mature technical solutions or relevant patent reports in China to realize ecosystem sensible heat flux observation equipment based on drone platforms, which cannot meet the growing demand for autonomous and controllable monitoring. Summary of the Invention

[0004] (1) Technical issues to be resolved

[0005] In view of the above-mentioned shortcomings and deficiencies of the prior art, the present invention provides a device for measuring the sensible heat flux of an ecosystem carried by an unmanned aerial vehicle, which solves the technical problem that the prior art is not suitable for being carried by an unmanned aerial vehicle and cannot meet the monitoring needs.

[0006] (2) Technical solution

[0007] In order to achieve the above objectives, the main technical solutions adopted by the present invention include:

[0008] The present invention provides a device for measuring the sensible heat flux of an unmanned aerial vehicle (UAV) ecosystem, comprising a wind speed measurement sensing part, a pressure pipe group, a probe sleeve, a connecting cone, a conversion pipe section, a temperature acquisition component, a sensor module, a tail pipe, a preset pipe, a buffer component and an angle adjustment component; the wind speed measurement sensing part, the probe sleeve, the connecting cone, the conversion pipe section and the tail pipe are connected in sequence; the wind speed measurement sensing part is connected through the pressure pipe group inside the probe sleeve and the pressure joint at the end of the connecting cone, and the pressure joint is connected to the sensor module inside the tail pipe through the pneumatic pipe group inside the connecting cone via the conversion pipe section; the temperature acquisition component is arranged on the outside of the connecting cone, and the temperature acquisition component is connected to the sensor module through the conversion pipe section; the preset pipe is fixed on the UAV; the free end of the tail pipe is rotatably connected to the free end of the preset pipe; a buffer component is arranged at the connection between the tail pipe and the preset pipe; the angle adjustment component is installed on the preset pipe, and the angle adjustment component is transmission-connected to the tail pipe to drive the tail pipe to rotate in a horizontal plane to achieve angle fine-tuning.

[0009] Optionally, the wind speed measurement sensing part is provided with two angle of attack differential pressure measuring holes, two sideslip angle differential pressure measuring holes and one total pressure measuring hole; the two angle of attack differential pressure measuring holes are vertically arranged above and below the total pressure measuring hole, and the two sideslip angle differential pressure measuring holes are horizontally arranged on both sides of the total pressure measuring hole; the pressure guiding pipe group is respectively connected to the two angle of attack differential pressure measuring holes, the two sideslip angle differential pressure measuring holes and one total pressure measuring hole.

[0010] Optionally, the angle adjustment assembly includes a servo drive and a transmission assembly; the servo drive is installed in the preset tube, and the servo drive is connected to the tail pipe through the transmission assembly to drive the tail pipe to rotate in the horizontal plane.

[0011] Optionally, the transmission assembly includes a worm and a worm wheel; the worm is connected to the output shaft of the servo drive, the worm wheel is connected to the tail pipe, and the worm transmission is connected to the worm wheel; the servo drive drives the worm to rotate, and the rotation of the worm drives the tail pipe to rotate in the horizontal plane through the worm wheel.

[0012] Optionally, the buffer assembly includes a magnetorheological damper and a universal joint; both ends of the magnetorheological damper are connected to the tail pipe and the conversion tube through the universal joint.

[0013] Optionally, the sensor module includes a conversion unit, a signal conditioning unit, a data calculation unit and a data storage unit; the pneumatic tube group is connected to the conversion unit, the conversion unit is connected to the signal conditioning unit, the signal conditioning unit is connected to the data calculation unit, and the data calculation unit is connected to the data storage unit.

[0014] Optionally, the temperature collection component includes an atmospheric static temperature collection component and an atmospheric total temperature collection component; the atmospheric static temperature collection component and the atmospheric total temperature collection component are arranged on the outside of the connecting cone, and the atmospheric static temperature collection component and the atmospheric total temperature collection component are connected to the sensor module.

[0015] Optionally, the atmospheric static temperature collection component includes a static temperature sensor and a static temperature collection cover; the static temperature collection cover is installed on the outside of the connecting cone, the static temperature sensor is located inside the static temperature collection cover, and the static temperature sensor is connected to the conversion pipe section; a plurality of collection holes are evenly arranged on the static temperature collection cover.

[0016] Optionally, the atmospheric total temperature collection component includes a total temperature sensor and a radiation shield; the radiation shield is installed on the outside of the connecting cone, the total temperature sensor is located inside the radiation shield, and the total temperature sensor is connected to the conversion pipe section.

[0017] Optionally, the radiation shield includes a cylindrical shield body, a conical shield tail and a connecting plate; the cylindrical shield body and the conical shield tail are connected to form a collection channel in the front-to-back direction, and the total temperature sensor is located in the collection channel; the collection channel is fixed to the outside of the connecting cone tube through the connecting plate.

[0018] (3) Beneficial effects

[0019] The beneficial effects of the present invention are:

[0020] The present invention provides a device for measuring the sensible heat flux of an unmanned aerial vehicle (UAV) ecosystem. The wind speed sensing element and the probe sleeve cooperate to collect three-dimensional atmospheric wind speed and atmospheric pressure parameters. The wind speed sensing element is connected to a pressure-conducting pipe assembly inside the probe sleeve and a pressure-conducting connector connected to the end of the cone tube. The pressure-conducting pipe assembly then connects to the sensor module via a pneumatic pipe assembly, ensuring accurate transmission of the pressure signal and guaranteeing precise wind speed measurement. The sensor module can calculate, store, and output data based on the collected parameters. The tail pipe is rotatably connected to the preset pipe and, in conjunction with an angle adjustment assembly, can be rotated in the horizontal plane for fine-tuning of the angle. This facilitates adjusting the angle of the measuring device according to the UAV's flight attitude and ensures the accuracy of the measurement direction. The buffer assembly effectively reduces the impact of UAV flight vibration on the measuring device, improves the stability of the measurement process, ensures the quality of the measurement data, and meets the special requirements of UAVs. When the UAV's attitude changes due to unstable airflow, the tail pipe angle can be adjusted through the angle adjustment assembly to maintain measurement accuracy and stability, ensuring reliable operation of the device and supporting long-term, continuous, and stable monitoring of the sensible heat flux of the ecosystem. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a schematic diagram of the overall structure of a device for measuring sensible heat flux of an unmanned aerial vehicle-borne ecosystem according to Example 1 of the present invention;

[0022] Figure 2 This is a partial structural diagram of a device for measuring sensible heat flux of an unmanned aerial vehicle-borne ecosystem according to Example 1 of the present invention;

[0023] Figure 3 1 is a front view of the structure of the wind speed measurement sensing portion of Example 1 of the present invention;

[0024] Figure 4 1 is a schematic structural diagram of a radiation shield according to embodiment 1 of the present invention;

[0025] Figure 5 This is a front view of the structure of the radiation shield according to Example 1 of the present invention;

[0026] Figure 6 Schematic diagram of the overall structure of a drone according to embodiment 2 of the present invention.

[0027] [Description of Reference Numerals]

[0028] 1: Wind speed measurement sensing part; 11: Attack angle differential pressure measurement hole; 12: Sideslip angle differential pressure measurement hole; 13: Total pressure measurement hole; 2: Pressure pipe group; 3: Probe sleeve; 4: Connecting cone tube; 41: Pressure connector; 5: Conversion tube; 6: Sensor module; 7: Tail pipe; 8: Preset tube; 91: Static temperature sensor; 92: Static temperature collection cover; 93: Total temperature sensor; 94: Radiation shield; 95: Cylindrical shield; 96: Conical shield tail; 97: Connecting plate; 10: Flight body. DETAILED DESCRIPTION

[0029] To better understand the above technical solutions, exemplary embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. Although exemplary embodiments of the present invention are shown in the accompanying drawings, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments described herein. Instead, these embodiments are provided to enable a clearer and more thorough understanding of the present invention and to fully convey the scope of the present invention to those skilled in the art.

[0030] Example 1:

[0031] like Figure 1 and Figure 2As shown, a specific embodiment of the present invention provides a device for measuring heat flux of an unmanned aerial vehicle ecosystem, comprising a wind speed measurement sensing portion 1, a pressure pipe group 2, a probe sleeve 3, a connecting cone 4, a conversion pipe section 5, a temperature acquisition component, a sensor module 6, a tail pipe 7, a preset pipe 8, a buffer component and an angle adjustment component; the wind speed measurement sensing portion 1, the probe sleeve 3, the connecting cone 4, the conversion pipe section 5 and the tail pipe 7 are connected in sequence; the wind speed measurement sensing portion 1 is connected to the pressure pipe group 2 inside the probe sleeve 3 and the pressure connector 41 at the end of the connecting cone 4, and the pressure connector The head 41 is connected to the sensor module 6 inside the tail pipe 7 via a pneumatic tube assembly connected to the interior of the cone 4 and a conversion tube section 5. The temperature acquisition assembly is located outside the cone 4 and is connected to the sensor module 6 via a conversion tube section. The preset tube 8 is fixed to the drone. The free end of the tail pipe 7 is rotatably connected to the free end of the preset tube 8. A buffer assembly is provided at the connection between the tail pipe 7 and the preset tube 8. The angle adjustment assembly is mounted on the preset tube 8 and is transmission-connected to the tail pipe 7 to drive the tail pipe 7 to rotate in the horizontal plane, achieving fine-tuning of the angle. In this embodiment, the wind speed measurement sensing portion 1 and the probe sleeve 3 are made of stainless steel, and the surface is polished to improve the data acquisition effect.

[0032] Specifically, the wind speed measurement sensing part 1 and the probe sleeve 3 cooperate to collect atmospheric three-dimensional wind speed and atmospheric pressure parameters. The wind speed measurement sensing part 1 is connected to the pressure pipe group 2 inside the probe sleeve 3 and the pressure joint 41 connected to the end of the cone tube 4, and then connected to the sensor module 6 through the pneumatic tube group to ensure accurate transmission of the pressure signal, providing a guarantee for accurate wind speed measurement. The sensor module 6 can calculate, store and output data based on the collected parameters. The tail pipe 7 is rotatably connected to the preset pipe 8, and cooperates with the angle adjustment component to achieve rotation in the horizontal plane for angle fine-tuning, making it convenient to adjust the angle of the measuring device according to the flight attitude of the drone and ensure the accuracy of the measurement direction. The buffer component can effectively reduce the impact of drone flight vibration on the measuring device, improve the stability of the measurement process, ensure the quality of the measurement data, and meet the special requirements of drones. When the drone attitude changes due to unstable airflow, the angle of the tail pipe 7 can be adjusted through the angle adjustment component to maintain the accuracy and stability of the measurement, ensure the reliable operation of the device, and provide support for long-term, continuous and stable monitoring of the sensible heat flux of the ecosystem.

[0033] Furthermore, if Figure 1-Figure 3As shown, the wind speed measurement sensing part 1 has two angle of attack differential pressure measurement holes 11, two sideslip angle differential pressure measurement holes 12 and a total pressure measurement hole 13, which can comprehensively and accurately measure the wind speed and wind direction information of the atmosphere. The two angle of attack differential pressure measurement holes 11 are vertically arranged above and below the total pressure measurement hole 13, and the two sideslip angle differential pressure measurement holes 12 are horizontally arranged on both sides of the total pressure measurement hole 13. The angle of attack differential pressure measurement hole 11 can measure the wind speed difference in the vertical direction, the sideslip angle differential pressure measurement hole 12 can measure the wind speed difference in the horizontal direction, and the total pressure measurement hole 13 can obtain the total pressure of the atmosphere. The pressure pipe group 2 is respectively connected to the two angle of attack differential pressure measurement holes 11, the two sideslip angle differential pressure measurement holes 12 and the total pressure measurement hole 13. Furthermore, in this embodiment, the probe sleeve 3 and the wind speed measurement sensing part 1 are sealed to prevent external air leakage from affecting the measurement results, ensuring the reliability and stability of the measurement data. The multiple atmospheric static pressure measurement holes evenly distributed on the side of the probe sleeve 3 can be used to measure the static pressure of the atmosphere.

[0034] Furthermore, the angle of attack differential pressure measurement hole 11 located above the total pressure measurement hole 13 is the first measurement hole, the sideslip angle differential pressure measurement hole 12 located to the right of the total pressure measurement hole 13 is the second measurement hole, the angle of attack differential pressure measurement hole 11 located below the total pressure measurement hole 13 is the third measurement hole, and the sideslip angle differential pressure measurement hole 12 located to the left of the total pressure measurement hole 13 is the second measurement hole. The origin of the relative wind speed measurement coordinate system is the total pressure measurement hole 13, the y-axis points to the second measurement hole, and the z-axis points to the first measurement hole, forming a right-handed coordinate system. The incoming wind speed angle of attack is positive when it points to the second measurement hole, and the incoming wind speed sideslip angle is positive when it points to the fourth measurement hole. In this embodiment, two angle of attack differential pressure measurement holes 11, two sideslip angle differential pressure measurement holes 12, and one total pressure measurement hole 13 are set at the probe of the wind speed measurement hand-feeling part. The diameter of the probe is 11 mm, and the diameters of the angle of attack differential pressure measurement hole 11 and the sideslip angle differential pressure measurement hole 12 are 0.8 mm.

[0035] Furthermore, in this embodiment, the angle adjustment assembly includes a servo drive and a transmission assembly; the servo drive is installed in the preset tube 8, and the servo drive is connected to the tail pipe 7 through the transmission assembly to drive the tail pipe 7 to rotate in the horizontal plane. Specifically, the transmission assembly includes a worm and a worm wheel; the worm is connected to the output shaft of the servo drive, the worm wheel is connected to the tail pipe 7, and the worm transmission is connected to the worm wheel; the servo drive drives the worm to rotate, and the rotation of the worm drives the tail pipe 7 to rotate in the horizontal plane through the worm wheel. Through the transmission connection with the tail pipe 7 through the transmission assembly, the tail pipe 7 can be driven to perform precise angular rotation in the horizontal plane. The angle of the tail pipe 7 can be adjusted in real time according to the actual conditions such as the flight attitude and wind direction of the drone to ensure that the wind speed measurement sensing part 1 is always in the best measurement position, thereby improving the accuracy and effectiveness of the measurement. The servo drive is characterized by high precision and precise control. The transmission assembly composed of a worm and a worm gear has the advantages of a large transmission ratio, smooth transmission, and low noise. In addition, the worm and worm gear transmission usually has a self-locking feature. When the tail pipe 7 is adjusted to a suitable angle, the position of the tail pipe 7 can be automatically locked to prevent the tail pipe 7 from angular deviation due to external interference (such as airflow impact), further improving the stability and measurement accuracy of the measuring device.

[0036] Furthermore, in this embodiment, the buffer assembly includes a magnetorheological damper and a universal joint; the two ends of the magnetorheological damper are connected to the tail pipe 7 and the conversion tube section 5 through a universal joint. The magnetorheological damper can adjust the magnitude of the damping force according to the magnitude and frequency of external vibrations by changing the rheological properties of its internal magnetorheological fluid. During the flight of the drone, the magnetorheological damper can effectively absorb and buffer vibration energy, reduce the impact of vibration on the measuring device, protect the internal precision components, and improve the reliability and service life of the device. The universal joint can allow a certain angle of rotation and swing, so that the magnetorheological damper will not restrict the relative movement between the tail pipe 7 and the conversion tube section 5 while buffering vibrations, thereby ensuring the normal operation of the measuring device in different postures.

[0037] Furthermore, in this embodiment, the sensor module 6 includes a conversion unit, a signal conditioning unit, a data calculation unit, and a data storage unit. The pneumatic tube assembly is connected to the conversion unit, which is then connected to the signal conditioning unit, which is then connected to the data calculation unit, and the data calculation unit is then connected to the data storage unit. The temperature acquisition assembly is connected to the signal conditioning unit. The conversion unit is an array of absolute and differential pressure sensors that can convert the pressure signals of total pressure, static pressure, angle of attack pressure difference, and sideslip angle pressure difference transmitted by the pneumatic tube assembly into voltage analog signals and transmit these analog voltage signals to the signal conditioning unit. The signal conditioning unit amplifies, filters, and performs A / D conversion on the voltage analog signals transmitted by the conversion unit and the atmospheric static temperature and total atmospheric temperature analog signals collected by the temperature acquisition assembly, and then transmits them to the data calculation unit. The data calculation unit calculates the collected pressure and differential pressure data into parameters such as dynamic pressure, static pressure, relative wind speed, atmospheric static temperature, wind speed angle of attack, and sideslip angle based on the Bernoulli equation and potential flow theory, combined with wind tunnel calibration results. The data calculation unit stores the calculated results and the original collected data for subsequent reference and further research. In this embodiment, the sensor module 6 is also provided with a data output unit and a system power supply unit. The data calculation unit and the data output unit are connected to facilitate the output of the various data processed by the data calculation unit through the relevant protocol. The system power supply unit is respectively connected to the conversion unit, signal conditioning unit, data calculation unit, and data storage unit to provide power for the stable operation of each unit.

[0038] Furthermore, in this embodiment, the temperature acquisition assembly includes an atmospheric static temperature acquisition assembly and an atmospheric total temperature acquisition assembly; these are disposed outside the connecting cone 4 and are connected to the sensor module 6. Specifically, the atmospheric static temperature acquisition assembly and the atmospheric total temperature acquisition assembly are connected to the signal conditioning unit in the sensor module 6. The atmospheric static temperature reflects the temperature of the atmosphere at rest, while the atmospheric total temperature includes the heat energy converted from the kinetic energy of atmospheric motion. Simultaneously acquiring these two types of temperature information provides a more comprehensive understanding of the thermal state of the atmosphere and more accurate temperature data for calculating the sensible heat flux of the ecosystem. Placing the atmospheric static temperature acquisition assembly and the atmospheric total temperature acquisition assembly outside the connecting cone 4 allows them to directly contact the atmosphere, more accurately reflecting the atmospheric temperature.

[0039] Specifically, if Figure 1 and Figure 2As shown, the atmospheric static temperature collection assembly includes a static temperature sensor 91 and a static temperature collection cover 92. The static temperature collection cover 92 is mounted on the outside of the connecting cone 4, with the static temperature sensor 91 located inside the static temperature collection cover 92 and connected to the conversion pipe section 5. Multiple collection holes are evenly distributed on the static temperature collection cover 92, allowing the outside air to flow evenly into the static temperature collection cover 92 and fully contact the static temperature sensor 91. The static temperature collection cover 92 can reduce the impact of external factors on the static temperature measurement, ensuring that the static temperature sensor 91 can accurately measure the atmospheric static temperature. It also provides a certain degree of protection for the static temperature sensor 91, preventing it from being hit or damaged by external objects, thereby extending its service life.

[0040] Furthermore, if Figure 1 and Figure 2 As shown, the total atmospheric temperature collection assembly includes a total temperature sensor 93 and a radiation shield 94. The radiation shield 94 is mounted on the outside of the connecting cone 4, and the total temperature sensor 93 is located inside the radiation shield 94. The total temperature sensor 93 is connected to the conversion tube section 5. The radiation shield 94 provides a relatively stable measurement environment for the total temperature sensor 93, effectively blocking the effects of solar radiation and other external radiation on the total temperature sensor 93. This allows the total temperature sensor 93 to accurately measure the total atmospheric temperature, thereby improving the stability and reliability of the total atmospheric temperature measurement.

[0041] Specifically, if Figure 4 and Figure 5 As shown, the radiation shield 94 includes a cylindrical shield body 95, a conical shield tail 96, and a connecting plate 97. The cylindrical shield body 95 and the conical shield tail 96 are connected to form a front-to-back collection channel, in which the total temperature sensor 93 is located. The collection channel is fixed to the outside of the connecting cone 4 via the connecting plate 97. The front-to-back collection channel guides the atmosphere smoothly through the total temperature sensor 93, improving measurement accuracy. The collection channel also reduces the impact of radiation interference on measurement results. The design of the conical shield tail 96 helps reduce air resistance, minimizing the aerodynamic impact on the measuring device during drone flight, thereby improving the device's adaptability and stability in flight environments.

[0042] The measurement frequency of the drone-mounted ecosystem sensible heat flux measurement device provided in this embodiment is 50 Hz. By measuring the relative wind speed, incoming wind speed angle of attack, and sideslip angle, combined with the three-dimensional ground speed and attitude output by the drone itself, the relative three-dimensional wind speed measured in the coordinate system of the wind speed measurement sensing part 1 is converted into a three-dimensional wind speed in the earth coordinate system. The three-dimensional wind speed in the earth coordinate system is used, combined with the total atmospheric temperature measurement value, and based on the eddy covariance principle, to calculate the ecosystem sensible heat flux value.

[0043] Example 2:

[0044] like Figure 6 As shown, this embodiment provides a drone, which includes a flight body 10 and the drone-borne ecosystem sensible heat flux measuring device described in Example 1, and a preset tube 8 is installed on the flight body 10.

[0045] In this embodiment, the connecting cone 4, the static temperature collection cover 92 and the radiation shield 94 are made of lightweight aviation aluminum to significantly reduce the overall weight of the measurement equipment.

[0046] Furthermore, in this embodiment, the outer diameter of the tail pipe 7 is 22 mm, and it is made of carbon fiber material.

[0047] The flight body 10 provided in this embodiment is made of high-strength, lightweight carbon fiber composite materials. While ensuring the structural strength of the body, it effectively reduces the overall weight of the drone and improves flight performance. Its fuselage is designed to be streamlined to reduce air resistance during flight and improve flight efficiency, allowing the drone to fly more stably under different weather conditions and ensuring that the onboard measuring device can continuously and reliably obtain data. Inside the flight body 10, the line connections between various electronic devices and measuring devices are rationally planned and laid out. Independent power supply lines and data transmission lines are specially set up for the measuring device to reduce electromagnetic interference with other equipment. At the same time, it is equipped with a redundant power supply system. When the main power supply fails, the backup power supply can be immediately started to ensure uninterrupted operation of the measuring device and avoid data loss.

[0048] In the description of the present invention, it should be understood that the terms "first" and "second" are used for descriptive purposes only and should not be understood to indicate or imply relative importance or implicitly specify the number of the technical features indicated. Therefore, a feature specified as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, "plurality" means two or more, unless otherwise specifically defined.

[0049] In the present invention, unless otherwise expressly specified or limited, the terms "mounted," "connected," "connect," "fixed," etc. should be understood broadly. For example, they may refer to fixed connection, detachable connection, or integration; mechanical connection or electrical connection; direct connection or indirect connection through an intermediate medium; and internal communication between two components or interaction between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0050] In the present invention, unless otherwise expressly specified or limited, when a first feature is "above" or "below" a second feature, it may mean that the first and second features are in direct contact, or that the first and second features are in indirect contact through an intermediate medium. Furthermore, when a first feature is "above," "above," or "above" a second feature, it may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is at a higher level than the second feature. When a first feature is "below," "below," or "below" a second feature, it may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is at a lower level than the second feature.

[0051] In the description of this specification, the terms "one embodiment", "some embodiments", "embodiments", "examples", "specific examples" or "some examples" refer to the specific features, structures, materials or characteristics described in conjunction with the embodiment or example and included in at least one embodiment or example of the present invention. In this specification, the schematic expressions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine different embodiments or examples described in this specification and features of different embodiments or examples, unless they are mutually inconsistent.

[0052] Although the embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are illustrative and are not to be construed as limitations on the present invention. A person skilled in the art may alter, modify, replace and modify the above embodiments within the scope of the present invention.

Claims

1. A device for measuring the sensible heat flux of an unmanned aerial vehicle ecosystem, characterized in that: It includes a wind speed measurement sensing part (1), a pressure pipe group (2), a probe sleeve (3), a connecting cone (4), a conversion pipe section (5), a temperature acquisition component, a sensor module (6), a tail pipe (7), a preset pipe (8), a buffer component and an angle adjustment component; The wind speed measurement sensing part (1), the probe sleeve (3), the connecting cone (4), the conversion pipe section (5) and the tail pipe (7) are connected in sequence; the wind speed measurement sensing part (1) is connected through the pressure pipe group (2) inside the probe sleeve (3) and the pressure guide joint (41) at the end of the connecting cone (4); the pressure guide joint (41) is connected to the sensor module (6) inside the tail pipe (7) through the pneumatic pipe group inside the connecting cone (4) and the conversion pipe section (5); The temperature acquisition component is arranged on the outside of the connecting cone (4), and the temperature acquisition component is connected to the sensor module (6) via the conversion pipe section (5); The preset tube (8) is fixed on the drone; the free end of the tail tube (7) is rotatably connected to the free end of the preset tube (8); a buffer assembly is provided at the connection between the tail tube (7) and the preset tube (8); the angle adjustment assembly is mounted on the preset tube (8), and the angle adjustment assembly is transmission-connected to the tail tube (7) to drive the tail tube (7) to rotate in a horizontal plane to achieve angle fine-tuning; The wind speed measurement sensing part (1) is provided with two attack angle differential pressure measurement holes (11), two sideslip angle differential pressure measurement holes (12) and a total pressure measurement hole (13); Two attack angle differential pressure measuring holes (11) are vertically arranged above and below the total pressure measuring hole (13), and two sideslip angle differential pressure measuring holes (12) are horizontally arranged on both sides of the total pressure measuring hole (13); The pressure guiding pipe group (2) is respectively connected to two attack angle differential pressure measuring holes (11), two sideslip angle differential pressure measuring holes (12) and one total pressure measuring hole (13); The buffer assembly includes a magnetorheological damper and a universal joint; Both ends of the magnetorheological damper are connected to the tail pipe (7) and the conversion pipe section (5) through universal joints; The temperature collection component includes an atmospheric static temperature collection component and an atmospheric total temperature collection component; The atmospheric static temperature collection component and the atmospheric total temperature collection component are arranged on the outside of the connecting cone (4), and the atmospheric static temperature collection component and the atmospheric total temperature collection component are connected to the conversion pipe section (5); The atmospheric total temperature collection component includes a total temperature sensor (93) and a radiation shield (94); The radiation shield (94) is installed on the outside of the connecting cone (4), the total temperature sensor (93) is located inside the radiation shield (94), and the total temperature sensor (93) is connected to the conversion pipe section (5).

2. The device for measuring the sensible heat flux of an unmanned aerial vehicle ecosystem according to claim 1, wherein: The angle adjustment assembly includes a servo drive and a transmission assembly; The servo drive is installed in the preset tube (8), and the servo drive is connected to the tail pipe (7) through the transmission component to drive the tail pipe (7) to rotate in the horizontal plane.

3. The device for measuring the sensible heat flux of an unmanned aerial vehicle ecosystem according to claim 2, wherein: The transmission assembly includes a worm and a worm wheel; The worm is connected to the output shaft of the servo driver, the worm wheel is connected to the tail pipe (7), and the worm drive is connected to the worm wheel; The servo driver drives the worm to rotate, and the rotation of the worm drives the tail pipe (7) to rotate in the horizontal plane through the worm gear.

4. The device for measuring the sensible heat flux of an unmanned aerial vehicle ecosystem according to claim 1, wherein: The sensor module (6) includes a conversion unit, a signal conditioning unit, a data calculation unit and a data storage unit; The pneumatic tube group is connected to the conversion unit, the conversion unit is connected to the signal conditioning unit, the signal conditioning unit is connected to the data calculation unit, and the data calculation unit is connected to the data storage unit.

5. The device for measuring sensible heat flux of an unmanned aerial vehicle ecosystem according to claim 1, wherein: The atmospheric static temperature collection component includes a static temperature sensor (91) and a static temperature collection cover (92); The static temperature collection cover (92) is installed on the outside of the connecting cone (4), the static temperature sensor (91) is located inside the static temperature collection cover (92), and the static temperature sensor (91) is connected to the conversion pipe section (5); A plurality of collection holes are evenly arranged on the static temperature collection cover (92).

6. The device for measuring heat flux of an unmanned aerial vehicle ecosystem according to claim 1, wherein: The radiation shield (94) includes a cylindrical shield body (95), a conical shield tail (96) and a connecting plate (97); The cylindrical cover body (95) and the conical cover tail (96) are connected to form a collection channel in the front-to-back direction, and the total temperature sensor (93) is located in the collection channel; the collection channel is fixed to the outside of the connecting cone tube (4) through a connecting plate (97).

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