Wind power combined micro aircraft testing device and testing method thereof

Abstract

According to the wind power combined micro aircraft testing device and the testing method thereof, a wind field and an electric field are effectively combined, complex conditions possibly encountered by a micro aircraft in an actual environment are simulated, a more real and accurate experimental environment is provided for performance testing of the micro aircraft, the defects of an existing testing means are overcome, and the testing efficiency is improved. And the development of the micro-robot technology is promoted. The device comprises a transparent pipeline for constructing a test space, and honeycomb conductor rectifying plates at two ends are respectively used as a wind field rectifying device and an electric field polar plate; an external fan forms a wind field in a pipeline, a Van der Graff electrification device between the rectifying plates forms a stable electric field, the positive electrode of the Van der Graff electrification device is connected with the upper rectifying plate through a wire, the lower rectifying plate is grounded, and the Van der Graff electrification device is used for forming the stable electric field between the rectifying plates. A wind speed sensor and an electric field sensor are arranged in the pipeline to monitor intensity in real time, a smoke generating device is arranged on the upstream of the fan to achieve wind field visualization, and the performance evaluation method is suitable for performance evaluation of the miniature aircraft with wind power assistance or electric field response characteristics.

Description

Technical Field

[0001] The present invention relates to the technical field of micro air vehicle testing, and particularly to a testing device and method for a micro air vehicle with combined simulation of wind field and electric field. Background Art

[0002] With the continuous development of micro air vehicle technology, especially the new type of micro air vehicle relying on wind field and electric power as power, it has received wide attention due to its unique flight principle and potential application value. However, at present, the testing means for micro air vehicles are relatively scarce, lacking effective testing devices and methods that can simultaneously simulate wind field and electric field environments. Existing testing equipment often can only simulate the wind field or electric field singly, and cannot truly reflect the complex working conditions faced by micro air vehicles in actual applications, resulting in the accuracy and reliability of test results being affected, and it is difficult to meet the needs of the research and development and performance optimization of such aircraft. With the development of unmanned system technology, micro air vehicles are increasingly widely used in fields such as military reconnaissance, extreme environment detection, and building interior inspection. Such aircraft often need to operate in complex natural environments, such as strong wind interference or high electric field areas. However, traditional wind tunnel testing equipment is difficult to simulate the electric field distribution in the real environment, and the electric field testing platform is difficult to simulate the air flow disturbance, resulting in the fact that the practical performance of the aircraft cannot be fully verified during the indoor testing stage, affecting its engineering implementation and reliability evaluation. Summary of the Invention

[0003] The present invention aims to provide a combined wind and electricity micro air vehicle testing device and its testing method. By effectively combining the wind field and the electric field, it simulates the complex conditions that a micro air vehicle may encounter in the actual environment, provides a more real and accurate experimental environment for its performance testing, solves the deficiencies of existing testing means, and promotes the development of micro robot technology.

[0004] To achieve the above object, the present invention provides the following technical solutions:

[0005] The present invention proposes a combined wind and electricity micro air vehicle testing device, and the testing device includes:

[0006] A transparent pipeline for constructing an aircraft testing space;

[0007] Honeycomb conductor rectifying plates arranged at both ends of the transparent pipeline, serving as a wind field rectifying device and an electric field plate respectively;

[0008] A fan arranged outside the transparent pipeline for forming a wind field inside the pipeline;

[0009] A Van de Graaff electrostatic generator arranged between the rectifying plates, whose positive pole is connected to the upper rectifying plate through a wire, and the lower rectifying plate is grounded, for forming a stable electric field between the rectifying plates;

[0010] An airspeed sensor and an electric field sensor installed inside the pipeline are used to monitor the wind field and the electric field strength in real time;

[0011] A smoke generating device set upstream of the fan is used for visualizing the wind field flow.

[0012] Furthermore, the above honeycomb conductor rectifying plate is a hexagonal structure with a height of 10 mm and a wall thickness of 3 mm, and is uniformly arranged within a circle with a diameter of 290 mm; the adjustable airspeed range of the fan is 0 - 30000 V / m.

[0013] Furthermore, the above rectifying plates are all made of stainless steel, and have both the functions of rectification and electric field plates.

[0014] Furthermore, a quick disassembly and connection device is provided in the middle of the above transparent pipeline, so that the rectifying plate, the pipeline and the fan assembly can be replaced modularly.

[0015] Furthermore, the above smoke generating device is a water-based atomizing device, and its spray particle size is less than 1 μm, which does not affect the normal operation of electronic devices.

[0016] Furthermore, the distance between the above rectifying plates is adjustable, which is used to optimize the uniformity of the formed electric field, and the deviation of the electric field strength in the central area does not exceed ±5%.

[0017] Furthermore, the above device is applicable to micro air vehicles with a maximum external dimension not exceeding 120 mm × 120 mm × 120 mm.

[0018] Furthermore, the above airspeed and electric field strength can both be dynamically regulated, and the experimental process data is synchronously recorded through an external data acquisition system.

[0019] The present invention also proposes a test method implemented based on the wind-electricity combined micro air vehicle test device proposed in any one of the above, and the test method includes the following steps:

[0020] Device installation: Install the fan, the rectifying plate, the transparent pipeline, the airspeed sensor, the electric field sensor and the electrification device on the bracket in sequence to form a closed test channel;

[0021] Electric field construction: Use a Van de Graaff electrification device to charge the upper rectifying plate and ground the lower rectifying plate to form a stable electric field between the rectifying plates, and the adjustable range of the electric field strength is 15000 - 30000 V / m;

[0022] Wind field adjustment: By adjusting the fan speed, a wind field with a speed range of 0 - 5 m / s is formed in the channel, and after being rectified by the honeycomb rectifying plate, a quasi-laminar flow or controlled turbulence is formed;

[0023] Test preparation: Place the micro air vehicle to be tested in the central area of the test channel, and at the same time start the smoke generating device for air flow visualization;

[0024] Data acquisition: The test environment parameters are recorded in real time through an anemometer and an electric field meter, and the flight state of the aircraft is recorded through images or sensors.

[0025] Parameter change test: During the test, the electric field intensity and wind speed are adjusted to achieve single-variable or multi-variable control, and the response behavior of the aircraft under different working conditions is simulated.

[0026] Test end: Turn off the equipment and export the experimental data for analyzing the flight performance of the aircraft in the wind-electricity combined field.

[0027] Furthermore, the above-mentioned smoke generating device adopts a water-based micro-mist system for flow field visualization analysis through planar laser-induced fluorescence (PLIF) or a high-speed camera.

[0028] Furthermore, the above-mentioned test process adopts a modular parameter control platform, which can synchronously control the fan speed and the generator speed to achieve the coupled regulation of wind-electricity parameters.

[0029] The beneficial effects of the present invention are as follows:

[0030] 1. A wind-electricity combined micro-aircraft test device proposed by the present invention has the advantages of highly controllable wind-electricity combined regulation, experimental visualization and data fusion design, and adapting to the structures of multiple types of micro-aircraft; specifically:

[0031] Highly controllable wind-electricity combined regulation:

[0032] The test device proposed by the present invention realizes the independent and continuously adjustable wind speed and electric field intensity. By adjusting the driving parameters of the fan and the electrification device, multiple typical working conditions (such as high wind speed and weak electric field, low wind speed and strong electric field, etc.) can be constructed, with high repeatability and controllability, which is significantly better than the existing test platforms with only a single regulation dimension.

[0033] Experimental visualization and data fusion design:

[0034] The test device proposed by the present invention integrates a flow field visualization mechanism (smoke + transparent pipeline) and a real-time flight state acquisition function (anemometer + electric field meter + aircraft attitude feedback), making the data in the test process more comprehensive, facilitating the collection of training data for fluid dynamics analysis and control algorithms, and providing a data basis for establishing a digital twin model later.

[0035] Adapting to the structures of multiple types of micro-aircraft:

[0036] The size of the test device proposed by the present invention can be adjusted as needed according to the wind field and electric field, and is applicable to various micro-aircraft forms (including fixed-wing, flapping-wing, parafoil, spinning, etc.), with good versatility and platform compatibility, which is conducive to promoting the further engineering test verification of such aircraft in scientific research, detection and special environment applications.

[0037] 2. The test device proposed by the present invention is applicable to micro-aircraft test objects with a maximum size not exceeding 120mm×120mm×120mm, meeting the space requirements of most current insect bionic or parafoil micro-aircraft.

[0038] The present invention belongs to the cross-technology category related to the design of aircraft experimental verification platforms and the construction of simulation environments. And the present invention is applicable to the performance evaluation of micro-aircraft with wind-assisted or electric field response characteristics, and is widely used in research fields such as aircraft aerodynamic stability testing, attitude control strategy optimization, and electric field interference adaptability analysis. At the same time, the test platform proposed by the present invention is also applicable to the environmental adaptability research of new intelligent material-driven aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following will briefly introduce the drawings required for use in the description of the specific embodiments or the prior art. Obviously, the following drawings are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0040] Figure 1 It is a schematic structural diagram of the flow straightening plate proposed by the present invention, where Fig. (a) is the front view of the flow straightening plate, and Fig. (b) is the side view of the flow straightening plate;

[0041] Figure 2 It is a structural diagram of a wind-electricity combined micro-aircraft test device proposed by the present invention;

[0042] Figure 3 It is a structural diagram of the connecting device proposed by the present invention, where Fig. (a) is the front view of the connecting device, and Fig. (b) is the side view of the connecting device;

[0043] Figure 4 It is an exploded view of the wind-electricity combined micro-aircraft test device proposed by the present invention;

[0044] Figure 5 It is a wind field simulation diagram of the test device described in the present invention.

[0045] Among them, 1 represents the upper honeycomb conductor rectifying plate, 2 represents the anemometer, 3 represents the lower honeycomb conductor rectifying plate, 4 represents the connecting device, 5 represents the fan, 6 represents the bracket, 7 represents the smoke generating device, 8 represents the electric field instrument, and 9 represents the electrifying device. Specific Embodiment

[0046] In the following description, specific details such as specific system structures and technologies are presented for the purpose of illustration rather than limitation, so as to thoroughly understand the embodiments of the present application. However, those skilled in the art should clearly understand that the present application can also be implemented in other embodiments without these specific details. In other cases, detailed descriptions of well-known systems, devices, circuits, and methods are omitted to avoid unnecessary details from interfering with the description of the present application.

[0047] It should be understood that when used in this specification and the appended claims, the term "comprising" indicates the presence of the described features, wholes, steps, operations, elements, and / or components, but does not exclude the presence or addition of one or more other features, wholes, steps, operations, elements, components, and / or their combinations.

[0048] The specific embodiments of the present invention will be further described in detail below with reference to the accompanying drawings. The following embodiments will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present invention, several changes and improvements can still be made, and these all belong to the protection scope of the present invention.

[0049] Embodiment 1. Refer to Figure 2 To describe this embodiment, this embodiment provides a wind-electricity combined micro-aircraft test device, which effectively combines the wind field and the electric field to simulate the complex conditions that a micro-aircraft may encounter in the actual environment, providing a more real and accurate experimental environment for its performance test, so as to solve the deficiencies of existing test means and promote the development of micro-robot technology.

[0050] The test device includes:

[0051] A transparent pipeline for constructing an aircraft test space;

[0052] Honeycomb conductor rectifying plates arranged at both ends of the transparent pipeline, serving as a wind field rectifying device and an electric field plate respectively;

[0053] A fan arranged outside the transparent pipeline for forming a wind field inside the pipeline;

[0054] A Van de Graaff electrifying device arranged between the rectifying plates, whose positive pole is connected to the upper rectifying plate through a wire, and the lower rectifying plate is grounded, for forming a stable electric field between the rectifying plates;

[0055] An airspeed sensor and an electric field sensor installed inside the pipeline are used to monitor the wind field and the electric field intensity in real time;

[0056] A smoke generating device arranged upstream of the fan is used for visualizing the flow of the wind field.

[0057] The test device proposed in this embodiment, as Figure 2 shown, uses an acrylic transparent pipeline as the main structure of the entire test device, providing a relatively enclosed space for the aircraft test, facilitating observation and testing. Its transparent property enables the operator to directly observe the flight state of the aircraft during the test. By replacing pipelines of different lengths, the distance between the upper and lower electrode plates can be adjusted.

[0058] Honeycomb conductor rectifying plates: including an upper honeycomb conductor rectifying plate 1 and a lower honeycomb conductor rectifying plate 3, which are respectively arranged at the front and rear ends of the acrylic transparent pipeline. The main function is to rectify the wind field excited by the fan 5 into a relatively stable wind field. This stable laminar wind field can more accurately simulate the airflow condition in the actual flight environment, providing stable wind field conditions for the aircraft test.

[0059] The wind field area between the two rectifying plates is the working area for testing the aircraft. The distance between the upper and lower honeycomb conductor rectifying plates is adjustable. By adjusting the plate distance and the edge shape, the edge effect of the electric field can be improved, ensuring that the electric field intensity in the central test area is more uniform. Through simplified simulation verification, the error of the electric field intensity in the central area is controlled within ±5%.

[0060] Furthermore, the lower rectifying plate: in addition to playing a rectifying role, can also serve as an experimental platform, facilitating the placement and fixation of the aircraft to be tested. The lower rectifying plate is grounded for better excitation of a stable electric field.

[0061] The Van de Graaff electrostatic generator 9: is used for electrification. Its advantage is that it can excite an electric field with a very high voltage. The electrostatic generator is connected to the upper rectifying plate through a wire to charge the upper rectifying plate, while the lower rectifying plate is grounded, thereby forming a relatively stable electric field area between the two rectifying plates to realize the combination of the wind field and the electric field.

[0062] The anemometer 2 and the electric field meter 8: are both installed inside the pipeline, and are respectively used to measure the airspeed and the electric field intensity. By monitoring the parameters of the wind field and the electric field in real time, accurate data can be provided for the testers to analyze the performance of the aircraft under different wind and electric environments.

[0063] The fan 5: is connected to the lower honeycomb conductor rectifying plate 3 through a connecting device 4, and is located at the bottom of the device, and is used to provide a wind field for the test.

[0064] Smoke generating device 7: Placed at the rear end of the fan, used for the visualization of turbulence inside the device. The smoke generating device 7 adopts a water-based atomization device or a glycerol mist device, with a particle size generated within 1 μm, posing no risk of conductivity or corrosion to electronic components, and facilitating high-contrast visualization imaging.

[0065] A wind-electricity combined micro-aircraft test device proposed in this embodiment has the advantages of highly controllable wind-electricity combined regulation, experimental visualization and data fusion design, and adaptation to the structures of multiple types of micro-aircraft. Specifically:

[0066] Highly controllable wind-electricity combined regulation: The test device realizes independent and continuously adjustable wind speed and electric field intensity. By adjusting the driving parameters of the fan and the electrification device, various typical working conditions (such as high wind speed and weak electric field, low wind speed and strong electric field, etc.) can be constructed, with high repeatability and controllability, significantly superior to existing test platforms with only a single regulation dimension.

[0067] Experimental visualization and data fusion design: The test device integrates a flow field visualization mechanism (smoke + transparent pipeline) and a real-time flight state acquisition function (anemometer + electric field meter + aircraft attitude feedback), making the data in the test process more comprehensive, facilitating the collection of training data for fluid dynamics analysis and control algorithms, and providing a data basis for the subsequent establishment of a digital twin model.

[0068] Adaptation to the structures of multiple types of micro-aircraft: The size of the test device, the wind field, and the electric field can all be adjusted as needed, suitable for various micro-aircraft forms (including fixed-wing, flapping-wing, wing-parachute, spin type, etc.), with good versatility and platform compatibility, which is conducive to promoting further engineering test verification of such aircraft in scientific research, detection, and special environment applications.

[0069] Embodiment 2. Refer to Figure 1 To describe this embodiment, this embodiment further specifically describes a wind-electricity combined micro-aircraft test device proposed in the above Embodiment 1.

[0070] As Figure 1 shown, the above honeycomb-shaped conductor rectifying plate is evenly distributed with hexagonal grids with a height of 10 mm, the grid wall thickness is 3 mm, and the grids are evenly distributed within a circle with a diameter of 290 mm.

[0071] Furthermore, the upper and lower rectifying plates are made of stainless steel, with good electrical conductivity, and can simultaneously act as the plates for generating an electric field. The electrification device is connected to the upper plate through a wire, and the lower plate is grounded.

[0072] Furthermore, the rectifying plate is divided into upper and lower parts, located at both ends of the channel respectively. The channel part is made of acrylic transparent material because the transparent material is convenient for observing the internal experimental object.

[0073] Furthermore, by adjusting the rotational speed of the regulator motor, the magnitude of the applied voltage can be adjusted within the range of 0 - 6 kV, thereby forming a peak electric field of 15000 - 30000 V / m inside the pipeline.

[0074] Furthermore, the fan can provide a wind speed range of 0 - 5 m / s. When the wind speed passes through the rectifying plate, a turbulent wind field will be formed.

[0075] Furthermore, a wind speed sensor and an electric field sensor are arranged inside the pipeline for monitoring experimental data.

[0076] Furthermore, a smoke generating device is placed at the rear end of the fan for visualizing the turbulence inside the device. The smoke generating device adopts a water-based atomization device or a glycerol mist device, and the particle size it generates is within 1 μm, which does not pose a risk of conduction or corrosion to electronic components and is convenient for achieving high-contrast visual imaging.

[0077] Furthermore, to facilitate the smooth intake of wind by the device, the entire device is supported by an aluminum profile bracket, leaving the fan 20 cm above the ground.

[0078] Furthermore, the test device proposed in this embodiment is applicable to micro-aircraft test objects with a maximum size not exceeding 120 mm × 120 mm × 120 mm, meeting the space requirements of most current insect bionic or wing-parachute micro-aircraft.

[0079] Embodiment 3. Refer to Figure 2 and Figure 4 To describe this embodiment, this embodiment proposes a test method implemented based on the wind-electricity combined micro-aircraft test device described in any one of the above embodiments. The test method includes the following steps:

[0080] Device installation: Install the fan, rectifying plate, transparent pipeline, wind speed sensor, electric field sensor, and electrification device on the bracket in sequence to form a closed test channel;

[0081] Electric field construction: Use the Van de Graaff electrification device to charge the upper rectifying plate and ground the lower rectifying plate to form a stable electric field between the rectifying plates, and the adjustable range of the electric field intensity is 15000 - 30000 V / m;

[0082] Wind field adjustment: By adjusting the rotational speed of the fan, a wind field with a wind speed range of 0 - 5 m / s is formed in the channel, and after being rectified by the honeycomb rectifying plate, a quasi-laminar flow or controlled turbulence is formed;

[0083] Test preparation: Place the micro-aircraft to be tested in the central area of the test channel, and at the same time start the smoke generating device for airflow visualization;

[0084] Data acquisition: The test environment parameters are recorded in real time by an anemometer and an electric field meter, and the flight state of the aircraft is recorded by images or sensors.

[0085] Parameter change test: During the test, the electric field strength and wind speed are adjusted to achieve single-variable or multi-variable control, and the response behavior of the aircraft under different working conditions is simulated.

[0086] Test end: Turn off the equipment and export the experimental data for analyzing the flight performance of the aircraft in the wind-electricity combined field.

[0087] For the test method proposed in this embodiment, first, the fan 5 and the connecting device 4 are fixed on the bracket 6. An anemometer 2 and an electric field meter 8 are installed inside the pipeline and connected to external data acquisition equipment to ensure normal data acquisition. Then, the lower honeycomb conductor rectifying plate 3, the pipeline, and the upper honeycomb conductor rectifying plate 1 are connected in sequence to ensure firm installation and good sealing. The Van de Graaff electrostatic generator 9 is placed in a suitable position and connected to the upper rectifying plate through a wire, and at the same time, the lower rectifying plate is grounded. Finally, the smoke generating device 7 is installed to form the Figure 2 wind-electricity combined micro-aircraft test device as shown in Figure 4 is an exploded view of the wind-electricity combined micro-aircraft test device, which details the specific installation structure of the test device.

[0088] Parameter setting stage:

[0089] According to the test requirements, the electric field strength between the two rectifying plates is adjusted by the Van de Graaff electrostatic generator 9 to reach the preset test value.

[0090] Adjust the rotation speed of the fan 5 to control the wind speed of the wind field to meet the test requirements. At the same time, the parameters of the wind field and the electric field are monitored in real time by the anemometer 2 and the electric field meter 8 to ensure that they are stable within the preset range.

[0091] Test stage:

[0092] Place the aircraft to fly in the environment combined with the wind field and the electric field. The tester observes the flight state of the aircraft, such as flight attitude, flight trajectory, flight stability, etc., and records the relevant data.

[0093] During the test, the parameters of the wind field and the electric field can be adjusted as needed to simulate different actual working conditions and further test the performance of the aircraft.

[0094] During the test, single-variable control experiments (keeping the wind speed constant and only adjusting the electric field strength) or dual-variable experiments (simultaneously regulating the wind speed and the electric field) can be adopted to study the key performance parameters of the micro-aircraft, such as lift change, attitude disturbance, anti-interference ability, etc. A high-frame-rate camera can be used in the experiment for motion trajectory reconstruction and dynamic analysis.

[0095] After the test, the exported experimental data can be stored in a computer device for analyzing the flight performance of the aircraft in the wind-power combined field. For the computer device, the hardware device in this part is of a general model and is not shown in the form of a diagram. The system includes a processor and a memory. The processor and the memory can be connected through a bus or other means. The memory, as a non-transitory computer-readable storage medium, can be used to store non-transitory software programs, non-transitory computer-executable programs, and modules, as well as corresponding program instructions / modules. The processor executes various functional applications and data processing of the processor by running the non-transitory software programs, instructions, and modules stored in the memory.

[0096] Furthermore, this embodiment also explains the simulation effect of the wind-power combined micro-aircraft test device; as Figure 5 shown, it can be seen from the figure that when the inlet wind speed is about 1.2 m / s, a wind field environment of about 0.7 m / s can be formed inside.

[0097] In summary, the wind-power combined micro-aircraft test device of the present invention has many advantages. In terms of the highly controllable wind-electricity combined regulation, the device can independently and continuously adjust the wind speed and electric field intensity. By changing the driving parameters of the fan and the electrification device, it can construct various typical working conditions such as high wind speed and weak electric field, low wind speed and strong electric field, and has extremely high repeatability and controllability, which is much better than the existing test platforms with a single regulation dimension. In terms of the experimental visualization and data fusion design, the device incorporates a flow field visualization mechanism, that is, it is equipped with smoke and transparent pipes, and also has a real-time acquisition function of the flight state. Data such as the wind speed meter, electric field meter, and aircraft attitude feedback can be obtained in real time. As a result, the test data is more comprehensive, which is conducive to subsequent fluid dynamics analysis, and also helps in the acquisition of training data for control algorithms, laying a solid data foundation for building a digital twin model.

[0098] In terms of adapting to the structures of multiple types of micro-aircraft, the size of the device, as well as the wind field and electric field, can be adjusted according to needs, and it can be applicable to various micro-aircraft forms such as fixed-wing, flapping-wing, parafoil, and spinning types. It has excellent versatility and platform compatibility, which is of great benefit to promoting in-depth engineering test verification of such micro-aircraft in the fields of scientific research, detection, and special environment applications.

[0099] The above is only the embodiment of the present invention and does not limit the present invention. For those skilled in the art, the present invention can have various changes and modifications. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the scope of the claims of the present invention.

Claims

1. A wind power combined micro air vehicle testing device, characterized in that, include: Transparent pipes for constructing aircraft test spaces; The honeycomb conductor rectifier plates arranged at both ends of the transparent pipe serve as wind field rectifiers and electric field plates respectively; A fan disposed outside the transparent pipe is used to form a wind field inside the pipe; A Van de Graaff electrification device is arranged between the rectifier plates, the positive electrode of which is connected to the upper rectifier plate through a wire, and the lower rectifier plate is grounded, and is used to form a stable electric field between the rectifier plates; Wind speed sensors and electric field sensors installed inside the pipeline are used to monitor wind and electric field strength in real time; A smoke generating device is installed upstream of the fan to visualize the wind flow.

2. The wind power combined micro air vehicle testing device according to claim 1, wherein The honeycomb conductor rectifier plate is a hexagonal structure with a height of 10 mm and a wall thickness of 3 mm, and is evenly arranged in a circle with a diameter of 290 mm; the fan has an adjustable wind speed range of 0 to 30,000 V / m.

3. The wind-electricity combined micro air vehicle testing device according to claim 1, wherein, The rectifier plate is made of stainless steel and has both rectifier and electric field plate functions.

4. A wind power combined micro air vehicle testing device according to claim 1, characterized in that, A quick-disassembly connection device is provided in the middle of the transparent pipe, so that the rectifier plate, pipe and fan assembly can be replaced modularly.

5. The wind-electricity combined micro air vehicle testing device according to claim 1, characterized in that The smoke generating device is a water-based atomizing device, and the spray particle size thereof is less than 1 μm.

6. The wind-electricity combined micro air vehicle testing device according to claim 1, wherein The spacing between the rectifier plates is adjustable to optimize the uniformity of the formed electric field, with the deviation of the electric field strength in the central area not exceeding ±5%.

7. A wind power combined micro air vehicle testing device according to claim 1, characterized in that, Both wind speed and electric field intensity can be dynamically controlled, and the experimental process data can be synchronously recorded through an external data acquisition system.

8. A test method implemented by a wind-electricity combined micro-aircraft test device according to any one of claims 1-7, characterized in that The method is: Device installation: install the fan, rectifier plate, transparent pipe, wind speed sensor, electric field sensor and electrification device on the bracket in sequence to form a closed test channel; Electric field construction: Using the Van de Graaff electrification device, the upper rectifier plate is charged and the lower rectifier plate is grounded, forming a stable electric field between the rectifier plates. The electric field strength can be adjusted in the range of 15000 to 30000 V / m. Wind field regulation: By adjusting the fan speed, a wind field with a wind speed range of 0 to 5 m / s is formed in the channel, and quasi-laminar flow or controlled turbulence is formed after rectification by the honeycomb rectifier plate; Test preparation: Place the micro-aircraft to be tested in the center area of ​​the test channel and start the smoke generating device to visualize the airflow; Data collection: record the test environment parameters in real time through anemometers and electric field meters, and record the flight status of the aircraft through images or sensors; Parameter change test: adjust the electric field strength and wind speed during the test to achieve single variable or multi-variable control and simulate the aircraft response behavior under different working conditions; End of test: Shut down the equipment and export the experimental data for analyzing the flight performance of the aircraft in the wind farm.

9. The test method according to claim 8, characterized in that, The smoke generation device adopts a water-based micro-mist system, which is used to realize flow field visualization analysis through laser tomography or high-speed camera.

10. The test method according to claim 8, characterized in that The test process uses a modular parameter control platform, which can synchronously control the fan speed and the starting motor speed to achieve coupled adjustment of wind power parameters.

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