Device and method for measuring electromagnetic compatibility of unmanned aerial vehicle

Abstract

The invention relates to the technical field of unmanned aerial vehicle detection, in particular to an unmanned aerial vehicle electromagnetic compatibility measuring device and method, and the device comprises a measuring box body which is internally provided with a multi-band shielding cabin for measuring the electromagnetic compatibility of an unmanned aerial vehicle, and is internally provided with a supporting part for placing the unmanned aerial vehicle; the multi-band shielding cabin comprises a memory alloy box, and the top of the memory alloy box is connected with a supporting piece through a composite beam. Wherein the memory alloy box is provided with two layers, and the middle part and two outer walls of the two layers of memory alloy boxes are provided with shielding layers for shielding different frequency bands; and an integrated probe group for measuring the electromagnetic compatibility of the unmanned aerial vehicle is arranged on the inner wall of the memory alloy box. Deformation is triggered through current heating, the memory alloy box is dynamically adjusted, the memory alloy box can be adjusted according to the size of the unmanned aerial vehicle, convenience and rapidness are achieved, autonomous deformation of the cabin is achieved through the memory alloy box, and an external driving mechanism is not needed.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicle detection, in particular to a device and method for measuring electromagnetic compatibility of unmanned aerial vehicle. Background Art

[0002] UAV electromagnetic compatibility measurement is an important test link to ensure that the UAV can work normally in the electromagnetic environment and does not interfere with other equipment. The main purpose of UAV electromagnetic compatibility measurement is to evaluate the performance of the UAV in the electromagnetic environment, including its immunity and emission limits. This helps to ensure that the UAV can operate stably in a complex electromagnetic environment while reducing interference with other electronic equipment.

[0003] There are many types of drones, which can be divided into military drones, civilian drones, industrial drones, etc. Different types of drones have different working environments. When drones are flying in the air, they may be subject to electromagnetic interference from the ground or other aerial equipment. Through electromagnetic compatibility measurement, it can be ensured that drones can still maintain stable flight when they are interfered with, avoiding safety accidents such as crashes. Drones may generate electromagnetic radiation when working. If the radiation intensity exceeds the standard, it may interfere with or damage other electronic equipment.

[0004] Through electromagnetic compatibility measurement, the electromagnetic radiation intensity of drones can be limited to protect the normal operation of other electronic equipment. Due to the differences in the types, sizes and shapes of drones, during the measurement process, the traditional method is to place the drone in a fixed box for testing, which cannot be adjusted according to the model of the drone and has a limited scope of application. Secondly, the detector is mostly fixed inside the box, and the measurement result may be affected by the distance between the detector and the drone. Summary of the invention

[0005] In view of the problems in the prior art, the present invention provides an electromagnetic compatibility measurement device and method for an unmanned aerial vehicle.

[0006] The technical solution adopted by the present invention to solve the technical problem is: a UAV electromagnetic compatibility measurement device, comprising a measurement box, a multi-band shielding cabin for UAV electromagnetic compatibility measurement is arranged in the measurement box, and a support for placing the UAV is arranged in the measurement box; The multi-band shielding cabin includes a memory alloy box, the top of which is connected to a support member via a composite beam; The memory alloy box is provided with two layers, and the middle part and two outer walls of the two layers of memory alloy box are provided with shielding layers for shielding different frequency bands; The inner wall of the memory alloy box is provided with an integrated probe group for UAV electromagnetic compatibility measurement.

[0007] Preferably, a composite layer is provided in the middle of the two-layer shape memory alloy box. The composite layer is used for high-frequency band shielding and includes a plasma-enhanced chemical vapor deposition-grown multi-layer graphene and boron nitride heterojunction.

[0008] Preferably, a copper mesh is provided on the inner wall of the shape memory alloy box. A layer of permalloy with a thickness of 0.1 mm is provided on the side of the copper mesh close to the shape memory alloy box. The joint between the copper mesh and the permalloy is filled with liquid metal indium gallium alloy.

[0009] Preferably, an absorbing material is provided on the outer wall of the multi-band shielding cabin.

[0010] Preferably, a substrate is connected to the inner wall of the multi-band shielding cabin. The substrate is made of aluminum nitride ceramic material with a thermal expansion coefficient of 4.5×10⁻ 6 / °C. The surface of the substrate is gold-plated, and an integrated probe group is provided on one side of the substrate.

[0011] Preferably, a bionic fractal flow channel is provided inside the multi-band shielding cabin by 3D printing. A nanofluid is injected into the bionic fractal flow channel.

[0012] Preferably, the support member includes a main support beam. The main support beam is fixedly connected to the top of the inner wall of the measurement box body. The lower end of the main support beam extends into the multi-band shielding cabin, and a transverse support member for supporting and fixing the unmanned aerial vehicle is provided on one side of the main support beam.

[0013] Preferably, a slider is connected to the side of the transverse support member close to the main support beam. A vertical groove for receiving and guiding is provided on the side wall of the main support beam. An adjusting screw rod is rotatably provided in the vertical groove, and the slider is threadedly sleeved on the outer wall of the adjusting screw rod.

[0014] Preferably, a motor is fixedly connected to the bottom of the main support beam. The output end of the motor is fixedly connected to the output end of the adjusting screw rod; An anti-interference cover is sleeved outside the motor.

[0015] Preferably, the transverse support member includes a support section and a rotating section. The support section and the rotating section are rotatably connected by a connecting member. An arc-shaped push rod for adjusting the angle is provided on the lower surfaces of the support section and the rotating section.

[0016] Preferably, movable shafts are arranged in an array through the rotating section of the transverse support member. One end of the movable shaft placed in the upper part of the transverse support member is connected with a fixed suction cup; The lower end of the movable shaft placed in the rotating section of the transverse support member is fixedly connected with a limit pad. A return spring is sleeved on the outer wall of the movable shaft. The return spring is placed between the limit pad and the bottom of the rotating section of the transverse support member.

[0017] A method for measuring the electromagnetic compatibility of an unmanned aerial vehicle (UAV) includes an environment construction module. The environment construction module uses a telescopic box that is adapted to UAVs with a volume of 0.5 m³ to 5 m³. A support member is installed on the top for fixing the interference transmitting antenna and the probe. Broadband electric field probes and magnetic field loop probes are arranged on the six inner walls of the box.

[0018] Preferably, the probe includes a pulse probe. A group pulse generator is used to inject 4 kV pulses with a repetition frequency of 5 kHz along the antenna to verify the UAV's anti-transient interference ability.

[0019] Preferably, a continuous wave sweep interference of 80 MHz - 1 GHz is applied to the UAV, and failure modes such as the frame loss rate of the UAV's video transmission, GPS positioning deviation, and flight control malfunction are synchronously monitored.

[0020] Advantages of the present invention: For the electromagnetic compatibility measurement device and method of the UAV described in the present invention, compared with the prior art, in this application, current heating is used to trigger deformation, and the shape memory alloy box is dynamically adjusted, enabling the shape memory alloy box to be adjusted according to the size of the UAV, which is convenient and fast. The shape memory alloy box is used to achieve the autonomous deformation of the cabin without an external driving mechanism. The multi-band shielding cabin can shield different wave bands, avoiding affecting external staff, and at the same time providing a stable detection environment for the electromagnetic compatibility measurement of the UAV. The shielding layer provided in the shape memory alloy box can play an auxiliary role in shielding different wave bands, and shielding of different wave bands is achieved through the characteristics of different materials. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The present invention will be further described below with reference to the drawings and embodiments.

[0022] Figure 1 is a schematic diagram of the overall structure of the present invention; Figure 2 is for the present invention Figure 1 internal view; Figure 3 is a diagram of the shape memory alloy box of the present invention; Figure 4 is a schematic diagram of the three-dimensional structure of the main support beam of the present invention; Figure 5 is for the present invention Figure 4 schematic diagram of the structure at position A; Figure 6 is a schematic diagram of the shielding layer of the present invention; Figure 7 is a diagram of the graphene and boron nitride heterojunction of the present invention; Figure 8 is a diagram of the resistance change of the bent multi-layer graphene and boron nitride heterojunction of the present invention.

[0023] In the figure: 100, measurement box body; 200, multi-band shielding cabin; 201, shape memory alloy box; 202, carbon fiber graphene composite beam; 203, alloy base; 204, bionic fractal flow channel; 300, support member; 310, main support beam; 311, adjusting screw rod; 312, motor; 320, lateral support member; 321, arc push rod; 322, connecting member; 323, limit pad; 324, return spring; 325, fixed suction cup; 400, copper mesh; 410, permalloy; 420, composite layer; 430, wave-absorbing material; 460, integrated probe group; 461, substrate. Detailed implementation manners

[0024] In order to make the technical means, creative features, achieved purposes and functions of the present invention easy to understand, the present invention will be further described below in conjunction with specific implementation manners. Embodiment 1

[0025] As Figures 1-8 shown, an electromagnetic compatibility measurement device for an unmanned aerial vehicle of the present invention includes a measurement box body 100. A multi-band shielding cabin 200 for measuring the electromagnetic compatibility of the unmanned aerial vehicle is arranged in the measurement box body 100, and a support member 300 for placing the unmanned aerial vehicle is arranged in the measurement box body 100; The multi-band shielding cabin 200 includes a shape memory alloy box 201, and the top of the shape memory alloy box 201 is connected to the support member 300 through a composite beam 202; Among them, the shape memory alloy box 201 is provided with two layers, and shielding layers for shielding different frequency bands are arranged in the middle and on both outer walls of the two layers of shape memory alloy boxes 201; An integrated probe group 460 for measuring the electromagnetic compatibility of the unmanned aerial vehicle is arranged on the inner wall of the shape memory alloy box 201.

[0026] The shape memory alloy box 201 adopts a truss composed of a shape memory alloy (Ni-Ti-SMA, phase change temperature 50°C) and a carbon fiber graphene composite beam (tensile modulus 300 GPa). The shape memory alloy box 201 dynamically adjusts its size (from 1 m³ to 8 m³) by triggering deformation through current heating; it can be adjusted according to the size of the unmanned aerial vehicle, which is convenient and fast. The shape memory alloy box 201 realizes the autonomous deformation of the cabin body without an external driving mechanism; The integrated probe group 460 is divided into a high-frequency electric field probe (1 - 40 GHz) transmitter and a low-frequency electric field probe (30 MHz - 1 GHz), and the state of the unmanned aerial vehicle is detected during this process. The multi - band shielding cabin 200 can shield different wave bands, avoiding affecting external staff, and at the same time providing a stable detection environment for the electromagnetic compatibility measurement of the drone. The shielding layer set in the shape memory alloy box 201 can play an auxiliary role in shielding different wave bands, and realizes the shielding of different frequency bands through the characteristics of different materials.

[0027] As a technical optimization scheme of the present invention, a composite layer 420 is provided in the middle of the two - layer shape memory alloy box 201. The composite layer 420 is used for high - frequency band shielding. The composite layer 420 includes a plasma - enhanced chemical vapor deposition - grown multi - layer graphene and boron nitride heterojunction.

[0028] Figure 7 In (a), w is a schematic diagram of the multi - layer graphene and boron nitride heterojunction, and (b) is the structure resistance diagram after bending; high - frequency band shielding utilizes the multi - layer graphene and boron nitride heterojunction, where the graphene is a five - layer heterojunction with boron nitride, the surface resistance ≤ 1Ω / sq, and the magnetic shielding effectiveness (SE) > 80dB@10GHz; the graphene - boron nitride heterojunction takes into account high - frequency shielding and heat dissipation (thermal conductivity > 2000W / m·K).

[0029] UAVs usually use high - frequency bands for communication, such as 2.4GHz, 5.8GHz, etc. These frequency bands are vulnerable to interference from other wireless devices, such as Wi - Fi, Bluetooth, etc. High - frequency shielding can ensure that the communication link between the UAV and the ground control station is not interfered, guaranteeing the continuity and security of communication.

[0030] As a technical optimization scheme of the present invention, a copper mesh 400 is provided on the inner wall of the shape memory alloy box 201. A layer of permalloy 410 with a thickness of 0.1mm is provided on the side of the copper mesh 400 close to the shape memory alloy box 201. The joint between the copper mesh 400 and the permalloy 410 is filled with liquid metal indium - gallium alloy.

[0031] Through the cooperation of the double - layer structure with the inner layer being permalloy (1J85, thickness 0.1mm) and the outer layer being a copper mesh (mesh aperture λ / 15, corresponding to an aperture of 2cm at 1GHz), and the joint being filled with liquid metal indium - gallium alloy (conductivity 3.4×10 6 S / m), the shielding of the low - frequency band is realized.

[0032] Low - frequency electromagnetic interference may come from the permanent magnet of the UAV's own motor, bus current, etc., or from the external environment. These interferences may affect the communication link and navigation safety of the UAV, resulting in problems such as communication interruption and heading deviation. Through low - frequency shielding, the influence of these interferences on the UAV can be effectively reduced.

[0033] As a technical optimization scheme of the present invention, an absorbing material 430 is provided on the outer wall of the multi - band shielding cabin 200.

[0034] The wave-absorbing material 430 is a gradient-density ferrite / carbon nanotube foam (with a gradient density change of 0.1 - 0.8 g / cm³), having a reflection loss > 35 dB (in the frequency band of 2 - 18 GHz) and a thickness of only 20 mm. The wave-absorbing material 430 can absorb, scatter, or neutralize electromagnetic waves, thereby reducing the impact of electromagnetic interference on other components, ensuring that the UAV can operate normally in a complex electromagnetic environment without being interfered by external electromagnetic waves and at the same time not generating unnecessary electromagnetic interference to other devices.

[0035] Table 1: Radiation emission test data (30 MHz - 6 GHz) Test conditions: Simulating the hovering state of the UAV, environmental temperature 25°C, humidity 50%.

[0036] For the failure frequency points, shielding needs to be increased or the filter parameters need to be adjusted.

[0037] As a technical optimization scheme of the present invention, the inner wall of the multi-band shielding cabin 200 is connected with a substrate 461. The substrate 461 is made of aluminum nitride ceramic material with a thermal expansion coefficient of 4.5×10⁻ 6 / °C. The surface of the substrate 461 is gold-plated, and an integrated probe group 460 is arranged on one side of the substrate.

[0038] Among them, the dielectric loss tanδ of the substrate 461 < 0.001 (@10 GHz), and the gold plating on the surface (thickness 2 μm) ensures conductivity; The array bracket uses a silicon carbide whisker-reinforced aluminum matrix composite material (bending strength 800 MPa, density 2.8 g / cm³), with a field strength measurement resolution of up to 0.1 dB / m and a scanning speed 100 times higher than that of traditional mechanical scanning.

[0039] As a technical optimization scheme of the present invention, a bionic fractal flow channel 204 is provided inside the multi-band shielding cabin 200 by 3D printing, and a nanofluid is injected into the bionic fractal flow channel 204.

[0040] The 3D printed microchannel integrated in the shielding cabin wall has a channel diameter of 0.5 mm. The cooling working medium uses a nanofluid (Al2O3 particle size 50 nm, volume fraction 5%), and the boiling point is increased to 150°C. The piezoelectric micropump (with an adjustable flow rate of 0.1 - 10 mL / min) is used to achieve the spatial and temporal migration of heat. Under a continuous 100 W heat load, the temperature rise inside the cabin < 2°C / h. Example 2

[0041] Basically the same as Example 1, as Figures 2-5As shown in the figure, the difference lies in that the support member 300 includes a main support beam 310, the main support beam 310 is fixedly connected to the top of the inner wall of the measurement box body 100, the lower end of the main support beam 310 extends into the multi-band shielding cabin 200, and a lateral support member 320 for supporting and fixing the drone is arranged on one side of the main support beam 310.

[0042] The combined setting of the main support beam 310 and the lateral support member 320 can support the drone, and at the same time can also adjust the position and angle of the drone. By adjusting the drone at multiple angles, the drone can be detected at multiple angles, and the applicability is wider.

[0043] As a technical optimization scheme of the present invention, a slider is connected to the side of the lateral support member 320 close to the main support beam 310. A vertical groove for receiving and guiding is provided on the side wall of the main support beam 310. An adjusting threaded rod 311 is rotatably arranged in the vertical groove, and the slider is threadedly sleeved on the outer wall of the adjusting threaded rod 311; A motor 312 is fixedly connected to the bottom of the main support beam 310, and the output end of the motor 312 is fixedly connected to the output end of the adjusting threaded rod 311; An anti-interference cover is sleeved outside the motor 312.

[0044] By rotating the adjusting threaded rod 311, the height of the slider can be adjusted. The slider drives the lateral support member 320 to move. The adjusting threaded rods 311 corresponding to the two lateral support members 320 can adjust the slider to different height positions. At this time, the drone is in an inclined state. In the inclined state, according to the specific measurement situation, the drone can be rotated from horizontal to inclined during the measurement of the drone to achieve dynamic measurement.

[0045] The motor 312 provides power for the adjusting threaded rod 311, and the anti-interference cover sleeved outside the motor 312 can prevent the motor 312 from being interfered by the outside world during operation.

[0046] As a technical optimization scheme of the present invention, the lateral support member 320 includes a support section and a rotating section. The support section and the rotating section are rotatably connected by a connecting member 322, and an arc-shaped push rod 321 for adjusting the angle is arranged on the lower surfaces of the support section and the rotating section.

[0047] By extending or shortening the telescopic end of the arc-shaped push rod 321, the support section and the rotating section of the lateral support member 320 can be controlled to rotate, further adjusting the angle of the measured drone, realizing the omnidirectional measurement of the drone, and increasing the accuracy and reliability of the measurement data.

[0048] As a technical optimization scheme of the present invention, movable shafts are arranged in an array through the rotating section of the lateral support member 320, and a fixed suction cup 325 is connected to one end of the movable shaft placed on the upper part of the lateral support member 320; The movable shaft is fixedly connected with a limit pad 323 at the lower end of the rotating section of the horizontal support member 320. A return spring 324 is sleeved on the outer wall of the movable shaft. The return spring 324 is arranged between the limit pad 323 and the bottom of the rotating section of the horizontal support member 320.

[0049] The drone can be fixed by the suction cup 325. The setting of the return spring 324 can play a buffering role. When the drone tilts, the fixing suction cup 325 on one side will receive a greater pulling force, and the movable shaft will slide, and the return spring 324 will be compressed to make way.

[0050] A method for measuring the electromagnetic compatibility of a drone, including an environment construction module. The environment construction module uses a telescopic box body, which is adapted to drones with a volume of 1m³ to 5m³. A support member is installed on the top for fixing the interference emission antenna and the probe. Low-frequency electric field probes (30MHz - 1GHz) and high-frequency electric field probes (1 - 40GHz) are arranged on six sides of the inner wall of the box body.

[0051] Combined with the probe position data, reconstruct the spatial distribution of the electromagnetic field around the drone to locate the interference source.

[0052] As a technical optimization scheme of the present invention, the probe includes a pulse probe. A group pulse generator is used to inject 4kV pulses with a repetition frequency of 5kHz along the antenna to verify the anti-transient interference ability of the drone. Compare the emission over-standard frequency band with the immunity failure threshold to identify potential self-interference risks, such as the over-strong emission in the Wi-Fi frequency band causing desensitization of its own receiver.

[0053] As a technical optimization scheme of the present invention, a continuous wave sweep interference of 80MHz - 1GHz is applied to the drone, and the failure modes such as the frame loss rate of the drone's video transmission, the GPS positioning offset, and the misoperation of the flight control are synchronously monitored.

[0054] The above shows and describes the basic principles, main features and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited by the above embodiments. The above embodiments and the descriptions in the specification only illustrate the principles of the present invention. Without departing from the spirit and scope of the present invention, the present invention will have various changes and improvements, and these changes and improvements all fall within the scope of the present invention claimed. The scope of the present invention claimed is defined by the appended claims and their equivalents.

Claims

1. An electromagnetic compatibility measurement device for an unmanned aerial vehicle, characterized in that: It includes a measurement box body (100), and a multi-band shielding chamber (200) for measuring the electromagnetic compatibility of unmanned aerial vehicles is arranged in the measurement box body (100), and a support member (300) for placing the unmanned aerial vehicle is arranged in the measurement box body (100); The multi-band shielding chamber (200) includes a shape memory alloy box (201), and the top of the shape memory alloy box (201) is connected to the support member (300) through a composite beam (202); Among them, the shape memory alloy box (201) is provided with two layers, and shielding layers for shielding different frequency bands are arranged in the middle and on both outer walls of the two layers of shape memory alloy boxes (201); An integrated probe group (460) for measuring the electromagnetic compatibility of unmanned aerial vehicles is arranged on the inner wall of the shape memory alloy box (201).

2. The electromagnetic compatibility measurement device for an unmanned aerial vehicle according to claim 1, characterized in that: A composite layer (420) is arranged in the middle of the two layers of shape memory alloy boxes (201), and the composite layer (420) is used for high-frequency band shielding. The composite layer (420) includes a plasma-enhanced chemical vapor deposition-grown multi-layer graphene and boron nitride heterojunction.

3. The electromagnetic compatibility measurement device for an unmanned aerial vehicle according to claim 1, wherein: A copper mesh (400) is arranged on the inner wall of the shape memory alloy box (201), a layer of permalloy (410) with a thickness of 0.1 mm is arranged on one side of the copper mesh (400) close to the shape memory alloy box (201), and the joint between the copper mesh (400) and the permalloy (410) is filled with a liquid metal indium-gallium alloy.

4. An electromagnetic compatibility measurement device for an unmanned aerial vehicle according to claim 3, characterized in that: An absorbing material (430) is arranged on the outer wall of the multi-band shielding chamber (200).

5. The electromagnetic compatibility measurement device for an unmanned aerial vehicle according to claim 1, wherein: The inner wall of the multi-band shielding chamber (200) is connected with a substrate (461), the substrate (461) is made of aluminum nitride ceramic material, and the coefficient of thermal expansion is 4.5×10⁻ 6 / °C. The surface of the substrate (461) is gold-plated, and an integrated probe group (460) is arranged on one side of the substrate (461).

6. The electromagnetic compatibility measurement device for an unmanned aerial vehicle according to claim 1, characterized in that: A bionic fractal flow channel (204) is arranged inside the multi-band shielding chamber (200) by 3D printing, and a nanofluid is injected into the bionic fractal flow channel (204).

7. An electromagnetic compatibility measurement device for an unmanned aerial vehicle according to claim 1, characterized in that: The support member (300) includes a main support beam (310), the main support beam (310) is fixedly connected to the top of the inner wall of the measurement box body (100), the lower end of the main support beam (310) extends into the multi-band shielding chamber (200), and a transverse support member (320) for supporting and fixing the unmanned aerial vehicle is arranged on one side of the main support beam (310).

8. An electromagnetic compatibility measurement device for an unmanned aerial vehicle according to claim 7, characterized in that: A slider is connected to one side of the transverse support member (320) close to the main support beam (310). A vertical groove for receiving and guiding is opened on the side wall of the main support beam (310), and an adjusting threaded rod (311) is rotatably arranged in the vertical groove. The slider is threadedly sleeved on the outer wall of the adjusting threaded rod (311).

9. The electromagnetic compatibility measurement device for an unmanned aerial vehicle according to claim 8, characterized in that: A motor (312) is fixedly connected to the bottom of the main support beam (310), and the output end of the motor (312) is fixedly connected to the output end of the adjusting threaded rod (311); An anti-interference cover is sleeved outside the motor (312).

10. An electromagnetic compatibility measurement device for an unmanned aerial vehicle according to claim 8, characterized in that: The transverse support member (320) includes a support section and a rotating section, the support section and the rotating section are rotatably connected through a connecting member (322), and an arc-shaped push rod (321) for adjusting the angle is arranged on the lower surfaces of the support section and the rotating section.

11. An electromagnetic compatibility measurement device for an unmanned aerial vehicle according to claim 10, characterized in that: The rotating section of the transverse support member (320) is arrayed with movable shafts penetrating through, and a fixed suction cup (325) is connected to one end of the movable shaft placed in the upper part of the transverse support member (320); The movable shaft is fixedly connected with a limit pad (323) at the lower end of the rotating section of the transverse support member (320). A return spring (324) is sleeved on the outer wall of the movable shaft. The return spring (324) is arranged between the limit pad (323) and the bottom of the rotating section of the transverse support member (320).

12. A method for measuring the electromagnetic compatibility of an unmanned aerial vehicle, which is applied to the device for measuring the electromagnetic compatibility of an unmanned aerial vehicle according to any one of claims 1-11 above, and is characterized in that: It includes an environment construction module. The environment construction module adopts a telescopic box body, which is adapted to drones with a volume of 0.5 m³ to 5 m³. A support member is installed at the top for fixing the interference transmitting antenna and the probe; Broadband electric field probes and magnetic field loop probes are arranged on six sides of the inner wall of the box body.

13. According to a method for measuring the electromagnetic compatibility of a drone described in claim 12, the probe includes a pulse probe. A 4 kV pulse with a repetition frequency of 5 kHz is injected along the antenna using a group pulse generator to verify the anti-transient interference ability of the drone.

14. According to a method for measuring the electromagnetic compatibility of a drone described in claim 12, a continuous wave sweep interference of 80 MHz - 1 GHz is applied to the drone, and failure modes such as the frame loss rate of the drone video transmission, GPS positioning offset, and incorrect operation of the flight control are synchronously monitored.

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