Unmanned aerial vehicle detection device and system

Abstract

The embodiment of the application relates to the technical field of unmanned aerial vehicle detection, and discloses an unmanned aerial vehicle detection device and an unmanned aerial vehicle detection system, the unmanned aerial vehicle detection device comprising a shell, a first power supply unit, a second power supply unit and a radar fusion unit, the first power supply unit, the second power supply unit and the radar fusion unit are all arranged on a bottom plate, and first heat dissipation channels are formed between the units, an air inlet device and an air outlet device are further arranged on the bottom plate, so that the gas in the external environment enters the shell interior under the driving of the air inlet device and the air outlet device and is discharged after passing through the first heat dissipation channels, thereby dissipating heat for the first power supply unit, the second power supply unit and the radar fusion unit. In the above manner, the unmanned aerial vehicle detection device can maintain good waterproof performance while dissipating heat for the functional units in the accommodating cavity, thereby preventing the temperature inside the shell from being high due to the continuous accumulation of heat generated by the functional units.

Description

Technical Field

[0001] This application relates to the field of unmanned aerial vehicle (UAV) detection technology, specifically to a UAV detection device and a UAV detection system. Background Technology

[0002] With the widespread adoption of drones, while bringing convenience, they also generate new risks such as security threats, privacy violations, and airspace security breaches. Therefore, drone defense systems need to employ defensive measures such as interference blocking, deception takeover, and physical destruction to intercept or destroy drones that are not authorized to fly. Specifically, drone defense systems need to first use radar, radio, and optoelectronic drone detection equipment to detect, identify, and track unauthorized drones, transforming invisible threats into visible and quantifiable information, and then guiding interception equipment such as drone countermeasure guns, laser weapons, and drone interception devices to carry out precise strikes.

[0003] To ensure that drone detection equipment can maximize coverage of the sensitive areas requiring protection, it is typically deployed in outdoor environments such as rooftops, control towers, and mobile vehicles. This necessitates that the equipment possess sufficient protection levels to withstand harsh conditions such as wind, rain, snow, and hail. Consequently, the casing of drone detection equipment is usually sealed, leading to the continuous accumulation of heat generated by the electronic components inside the casing. This can result in high internal temperatures, potentially affecting the normal operation of the drone detection equipment. Utility Model Content

[0004] In view of the above problems, this application provides a drone detection device and a drone detection system to solve the problem of high internal temperature of the casing caused by the continuous accumulation of heat generated by electronic components in the existing drone detection devices.

[0005] According to one aspect of the embodiments of this application, a drone detection device is provided. The drone detection device is used to connect to radar equipment and visual recognition equipment via signal connection, and to perform fusion calculations on data collected by the radar equipment and data collected by the visual recognition equipment. The drone detection device includes: a housing, a first power supply unit, a second power supply unit, and a radar fusion unit. The housing includes a base plate and a cover, the cover including a top wall and multiple side walls. The cover is disposed on the base plate and sealed to the base plate to form a receiving cavity. Multiple radar devices are disposed on the side of each side wall of the cover away from the receiving cavity, and a visual recognition device is disposed on the top wall of the cover away from the receiving cavity. The first power supply unit, the second power supply unit, and the radar fusion unit are all disposed on the side of the base plate facing the receiving cavity. The first power supply unit supplies power to the radar equipment, and the second power supply unit supplies power to the visual recognition equipment. The identification device is powered by a radar fusion unit that is electrically connected to multiple radar devices and performs fusion calculations on the data collected by the multiple radar devices. The first power supply unit, the second power supply unit, and the radar fusion unit are arranged adjacent to each other at intervals, and each unit is separated by a first heat dissipation channel, which are parallel to each other. A first air inlet is provided at one end of the first heat dissipation channel on the base plate, and an air outlet is provided at the other end of the first heat dissipation channel. An air intake device is provided on the base plate opposite to the first air inlet, which is used to drive the gas in the external environment into the receiving cavity from the first air inlet. An air outlet device is provided on the base plate opposite to the air outlet, which is used to drive the gas entering the receiving cavity from the first air inlet through the first heat dissipation channel and then out of the air outlet to dissipate heat from the first power supply unit, the second power supply unit, and the radar fusion unit.

[0006] In one alternative embodiment, the heat generated by the first power supply unit and the second power supply unit is greater than the heat generated by the radar fusion unit; both the first power supply unit and the second power supply unit are attached to the base plate, and the radar fusion unit is stacked on top of the first power supply unit or the second power supply unit.

[0007] In one alternative embodiment, a second heat dissipation channel is formed between the radar fusion unit and the top wall of the cover near the receiving cavity. The second heat dissipation channel is used to allow gas entering the receiving cavity from the first air inlet to pass through, so as to dissipate heat from the side wall and top wall of the cover.

[0008] In one alternative embodiment, the cover flares outward from the end where the top wall is located to the end of the cover near the bottom plate, and the first air inlet is opposite to the side wall of the cover.

[0009] In one alternative embodiment, a plurality of first heat sinks are spaced apart on the side of the base plate away from the receiving cavity where they are in contact with the first power supply unit and the second power supply unit, and a third heat dissipation channel is formed between adjacent first heat sinks; a fan assembly is also provided on the side of the base plate away from the receiving cavity, the fan assembly being used to drive gas from the external environment into the third heat dissipation channel so as to remove heat from the first heat sinks and the base plate through the gas.

[0010] In one alternative configuration, the first power supply unit and the second power supply unit are arranged on the base plate along the extension direction of the first heat sink.

[0011] In one alternative embodiment, the fan assembly includes a shroud and a fan; the shroud covers the side of the first heat sink away from the base plate, and a second air inlet is provided on the shroud; the fan is positioned on the shroud opposite to the second air inlet, and the fan is used to drive the air from the external environment into the interior of the shroud from the second air inlet, and into the third heat dissipation channel under the guidance of the shroud.

[0012] In one alternative embodiment, at least one of the first power supply unit, the second power supply unit, and the radar fusion unit includes a housing and a circuit structure; a sealed accommodating cavity is formed inside the housing, the circuit structure is disposed within the accommodating cavity, and thermally conductive paste is filled between the circuit structure and the inner wall of the housing.

[0013] In one alternative approach, multiple second heat sinks are spaced apart on the outer wall of the enclosure, with the second heat sinks extending from the side where the first air inlet is located toward the side where the air outlet is located.

[0014] According to another aspect of the embodiments of this application, a drone detection system is provided, the system comprising: multiple radar devices, a visual recognition device, and the drone detection device described in any one of the above; the drone detection device is signal-connected to the radar devices and the visual recognition device respectively, and is used to perform fusion calculation on the data collected by the radar devices and the data collected by the visual recognition device; the radar devices are installed on the side wall of the cover of the drone detection device away from the receiving cavity, and are electrically connected to the first power supply unit and the radar fusion unit in the receiving cavity respectively; the visual recognition device is installed on the top wall of the cover away from the receiving cavity, and is electrically connected to the second power supply unit in the receiving cavity.

[0015] This embodiment of the application forms a receiving cavity by covering the base plate with a cover, and arranges functional units such as the first power supply unit, the second power supply unit, and the radar fusion unit in the receiving cavity, so that a first heat dissipation channel is formed between each unit. Simultaneously, a first air inlet and an air outlet are provided on the base plate, with an air intake device at the first air inlet and an air outlet device at the air outlet. This allows external ambient air to enter the receiving cavity formed by the cover and the base plate through the first air inlet under the drive of the air intake device, and then pass through the first heat dissipation channel under the drive of the air outlet device, finally exiting through the air outlet. This dissipates the heat generated by each unit to the external environment, achieving heat dissipation for each unit. Furthermore, since the cover is placed on the base plate, it can cover the first air inlet and air outlet to prevent rain and snow from entering the receiving cavity during rainy or snowy weather. This achieves effective heat dissipation for the functional units while also providing good waterproof performance.

[0016] The above description is only an overview of the technical solution of this application. In order to better understand the technical means of this application and to implement it in accordance with the contents of the specification, and to make the above and other objects, features and advantages of this application more obvious and understandable, the following are specific embodiments of this application. Attached Figure Description

[0017] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of this application. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings: Figure 1 A perspective view of the unmanned aerial vehicle (UAV) detection system provided in an embodiment of the present invention is shown; Figure 2 This image shows a perspective view of the drone detection device provided in an embodiment of the present invention. Figure 3 A partial structural schematic diagram of the UAV detection device provided in an embodiment of this utility model is shown; Figure 4 A cross-sectional view of the UAV detection device provided in an embodiment of the present invention is shown in one direction; Figure 5 A cross-sectional view of the UAV detection device provided in an embodiment of the present invention is shown from another direction; Figure 6 A perspective view of the housing in the UAV detection device provided in this embodiment of the present invention is shown; Figure 7 An exploded view of the first power supply unit in the UAV detection device provided in this embodiment of the present invention is shown.

[0018] The reference numerals in the detailed embodiments are as follows: 1000. Unmanned Aerial Vehicle (UAV) Detection System; 100. Unmanned aerial vehicle (UAV) detection equipment; 200. Tower; 300. Climbing mechanism; 400. Radar equipment; 500. Visual recognition equipment; 10. Housing; 20. First power supply unit; 30. Second power supply unit; 40. Radar fusion unit; 50. Edge computing unit; 60. Multi-channel temperature acquisition and fusion unit; 70. Third power supply unit; 110. Base plate; 120. Cover; 130. Receiving cavity; 140. Interface; 150. Cable; 160. Bracket; 111. First air inlet; 112. Air outlet; 113. First heat sink; 121. Side wall; 1211. Slot; 1212. Opening; 122. Top wall; 123. Fixing plate; 1231. Locking block; 124. Cover plate; 21. Enclosure; 211. Main body; 212. Top cover; 22. Circuit structure; 23. Receptacle; 24. Thermal paste; 25. Second heat sink; 610, First heat dissipation channel; 620, Second heat dissipation channel; 630, Third heat dissipation channel; 710. Air inlet device; 720. Air outlet device; 730. Fan assembly; 731. Air guide shroud; 732. Fan; 733. Second air inlet. Detailed Implementation

[0019] The embodiments of the technical solution of this application will now be described in detail with reference to the accompanying drawings. These embodiments are only used to more clearly illustrate the technical solution of this application and are therefore merely examples, and should not be used to limit the scope of protection of this application.

[0020] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application pertains; the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the application; the terms “comprising” and “having”, and any variations thereof, in the specification, claims, and foregoing description of the drawings are intended to cover non-exclusive inclusion.

[0021] In the description of the embodiments of this application, technical terms such as "first" and "second" are used only to distinguish different objects and should not be construed as indicating or implying relative importance or implicitly specifying the number, specific order, or primary and secondary relationship of the indicated technical features. In the description of the embodiments of this application, "multiple" means two or more, unless otherwise explicitly defined.

[0022] In this document, the term "embodiment" means that a particular feature, structure, or characteristic described in connection with an embodiment may be included in at least one embodiment of this application. The appearance of this phrase in various places throughout the specification does not necessarily refer to the same embodiment, nor is it a separate or alternative embodiment mutually exclusive with other embodiments. It will be explicitly and implicitly understood by those skilled in the art that the embodiments described herein can be combined with other embodiments.

[0023] In the description of the embodiments in this application, the term "and / or" is merely a description of the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent three cases: A exists, A and B exist simultaneously, and B exists. In addition, the character " / " in this document generally indicates that the related objects before and after it have an "or" relationship.

[0024] In the description of the embodiments of this application, the term "multiple" refers to two or more (including two), similarly, "multiple sets" refers to two or more (including two sets), and "multiple pieces" refers to two or more (including two pieces).

[0025] In the description of the embodiments of this application, the technical terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the embodiments of this application and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the embodiments of this application.

[0026] In the description of the embodiments of this application, unless otherwise expressly specified and limited, technical terms such as "installation," "connection," "joining," and "fixing" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. For those skilled in the art, the specific meaning of the above terms in the embodiments of this application can be understood according to the specific circumstances.

[0027] With the increasing prevalence of drone technology and the growing risks of misuse (such as unauthorized flights, smuggling, espionage, and terrorist attacks), drone detection technology has become a crucial element in low-altitude security. Drone detection equipment is primarily used to detect, identify, locate, and track drones. Drone detection relies mainly on the straight-line propagation of electromagnetic waves (radio waves and light waves). When deploying drone detection systems, it is typically necessary to place the equipment in open, high-altitude outdoor locations, such as rooftops, control towers, or dedicated poles, to avoid obstacles blocking or interfering with the propagation of electromagnetic waves.

[0028] Because drone detection equipment needs to be installed in outdoor environments, its casing is typically assembled using a sealed connection method to create a closed space inside the casing to accommodate the circuitry. This gives the drone detection equipment strong waterproof properties to cope with extreme weather conditions such as rain and snow. However, this also causes heat generated by the internal circuitry to accumulate inside the casing, leading to high internal temperatures. This can affect the normal operation of the circuitry, especially under intense summer sunlight, where the circuitry may overheat and shut down due to excessive internal temperature.

[0029] Therefore, to prevent excessively high temperatures inside the casing, this application provides a drone detection device. It considers creating ventilation holes on the casing of the drone detection device to conduct heat from inside the casing to the external environment via air. Simultaneously, to prevent rainwater or snowmelt from entering the casing through the ventilation holes, this application considers placing the ventilation holes at the bottom of the casing. The positions of multiple functional units inside the casing are arranged according to the location of the ventilation holes, allowing air entering the casing through the ventilation holes to pass through the heat dissipation channels formed between the functional units and carry away the heat generated by each functional unit. Furthermore, the ventilation holes are blocked by the casing itself, causing rainwater, snowmelt, and other liquids to flow downwards along the side walls of the casing after falling onto it, thereby preventing rainwater and snowmelt from entering the casing through the ventilation holes at the bottom.

[0030] Specifically, the housing includes a base plate and a cover piece placed on the base plate. The cover piece and the base plate are sealed together to form a cavity. Multiple circuit structures of the UAV detection device are set in the cavity, and heat dissipation channels are formed between the multiple circuit structures. An air inlet and an air outlet are respectively set at both ends of the heat dissipation channels on the base plate. An air inlet device is provided at the air inlet to drive the gas in the external environment into the cavity. An air outlet device is provided at the air outlet to drive the air entering the cavity from the air inlet through the heat dissipation channels between the circuit structures and then exhaust it from the air outlet, thereby carrying away the heat from the circuit structures through the gas.

[0031] This structure allows for the exchange of gas within the containment cavity through the air inlet and outlet, enabling gas flow between the external environment, the containment cavity, and the heat dissipation channel. This facilitates the removal of heat generated by the circuitry from the external environment, thus preventing overheating and system failure. Furthermore, the air inlet and outlet are located on the base plate and can be covered to prevent rainwater and snowmelt from entering the containment cavity, ensuring the waterproof performance of the UAV detection equipment.

[0032] According to one aspect of the embodiments of this application, a drone detection device is provided, which is used to connect to radar equipment and visual recognition equipment for signal connection, and to perform fusion calculation on the data collected by the radar equipment and the data collected by the visual recognition equipment.

[0033] Please see Figure 1 , Figure 2 and Figure 3 , Figure 1 The three-dimensional structure of the UAV detection system is shown. Figure 2 The three-dimensional structure of the drone detection equipment is shown. Figure 3 The partial structure of the UAV detection device is shown. The UAV detection device 100 includes a housing 10, a first power supply unit 20, a second power supply unit 30, and a radar fusion unit 40.

[0034] The drone detection equipment 100 can be like Figure 1 The device is mounted on a tower 200 and fixed to the ground, roof, or other locations via the tower 200. Specifically, the UAV detection device 100 and the tower 200 can be connected via an adapter plate and bolts. The tower 200 can also adopt a modular design, that is, multiple towers 200 are set according to a specific length, and the towers 200 can be detachably connected via nuts, bolts, clips, or other structures. Users can select the corresponding number of towers 200 to stack and fix according to their own needs, so as to install the UAV detection device 100 at a suitable height.

[0035] In addition, a climbing mechanism 300, such as a handrail or ladder, can be installed on the side of the tower 200, allowing users to climb to the top of the tower 200 to inspect and maintain the drone detection equipment 100. The climbing mechanism 300 can be fixed to the tower 200 by welding or bolting, or a portable ladder assembly can be selected as the climbing mechanism 300 of the tower 200.

[0036] Of course, the drone detection device 100 can also be installed on vehicles, ships, aircraft, or other transport vehicles to carry the drone detection device 100 for mobile detection within the target area. The target area can be a core area such as an airport, a sensitive location, or a nuclear power plant, to prevent unauthorized drones from intruding into these core areas.

[0037] The housing 10 is the outer shell of the UAV detection device 100, in conjunction with reference to... Figure 2 and Figure 3 The housing 10 includes a base plate 110 and a cover 120. The cover 120 covers the base plate 110 and forms a receiving cavity 130 through a sealing connection. A sealing connection can be formed between the cover 120 and the base plate 110 by using gaskets or sealing rings, or by applying sealant or adhesive to the connection between the cover 120 and the base plate 110. As an example, such as... Figure 3 As shown, the cover 120 can be concave in shape, and after the cover 120 covers the base plate 110, the side wall 121 of the cover 120 is connected to the edge of the base plate 110, that is, the cover 120 can completely cover the base plate 110.

[0038] Reference Figure 1 and Figure 3 The cover 120 includes a top wall 122 and multiple side walls 121. The side of each side wall 121 furthest from the receiving cavity 130 is used to house multiple radar devices 400. The radar devices 400 can be phased array radars, which employ electronic scanning technology (i.e., a four-sided array). A single device can simultaneously track hundreds of targets, and its adaptive clutter suppression algorithm can suppress ground clutter. The X-band emitted by phased array radars has strong penetration capabilities, enabling them to maintain a long effective detection range even under complex weather conditions such as heavy rain and dense fog. Of course, the radar devices 400 can also be continuous wave radars, pulse Doppler radars, etc.

[0039] Regarding the connection method between radar device 400 and side wall 121, this application embodiment provides a possible method, such as... Figure 2 As shown, a fixing plate 123 can be installed on the side wall 121. The radar device 400 is connected to the fixing plate 123 via detachable structures such as bolts and clips, thereby fixing the radar device 400 to the side wall 121. Furthermore, the fixing plate 123 and the side wall 121 can be connected by welding, gluing, or other fixed methods, or by detachable methods such as clips and bolts. As an example, such as... Figure 4 As shown, Figure 4The cross-sectional structure of the UAV detection device is shown. A slot 1211 can be opened on the side wall 121, and a block 1231 is set on one side of the fixing plate 123. When installing the radar device 400, the radar device 400 is first fixedly connected to the fixing plate 123, and then the block 1231 is inserted into the slot 1211 along the direction from the top wall 122 to the bottom plate 110, so that the block 1231 and the slot 1211 are engaged, thereby realizing the installation of the radar device 400.

[0040] The side of the top wall 122 of the cover 120 away from the receiving cavity 130 is used to house the visual recognition device 500. The visual recognition device 500 can be fixedly installed on the top of the UAV detection device 100 through detachable connection methods such as threaded connection, snap-fit, and pin. The visual recognition device 500 can be a camera, specifically a visible light camera equipped with a high-magnification optical zoom lens, to clearly identify the UAV model and structural features. A thermal imaging unit can also be set in the visual recognition device 500 to detect the heat characteristics of the target UAV, thereby achieving all-time tracking. In this way, the UAV detection device 100 can be equipped with radar equipment 400 and visual recognition device 500, and through the radar-visual recognition collaborative detection mechanism, a "radar warning-visual recognition evidence collection" working mechanism can be formed, effectively shortening the time from target appearance to confirmation.

[0041] The cavity 130 is used to house various functional units of the UAV detection equipment 100, such as power supply units for multiple power sources (i.e., the first power supply unit 20 and the third power supply unit 70), radar fusion unit 40, etc. Furthermore, when the UAV detection equipment 100 needs to perform fusion calculations on data acquired from multiple detection devices, such as... Figure 3 As shown, the UAV detection device 100 may further include an edge computing unit 50, a multi-channel temperature acquisition and fusion unit 60, etc. The power supply unit, which supports multiple power supply models, may also include a third power supply unit 70 for supplying power to the edge computing unit 50. The edge computing unit 50 is electrically connected to the radar device 400 and the visual recognition device 500, respectively, to achieve multi-source data fusion processing and system collaborative control through deep learning algorithms and multi-source sensor fusion technology. The multi-channel temperature acquisition and fusion unit 60 collects the temperature of each functional unit through temperature and humidity sensors, and performs high-temperature early warning and heat dissipation control of the UAV detection device 100 through real-time temperature detection and reporting, thereby ensuring the normal operation of each functional unit in high-temperature environments.

[0042] Specifically, such as Figure 3 and Figure 4As shown, the first power supply unit 20, the second power supply unit 30, and the radar fusion unit 40 are all disposed on the base plate 110 on the side facing the receiving cavity 130. The first power supply unit 20 supplies power to the radar device 400, the second power supply unit 30 supplies power to the visual recognition device 500, and the radar fusion unit 40 is electrically connected to multiple radar devices 400 and performs fusion calculations on the data collected by the multiple radar devices 400.

[0043] Since the first power supply unit 20, the second power supply unit 30, and the radar fusion unit 40 are located inside the housing 10 within the receiving cavity 130, while the radar device 400 and the visual recognition device 500 are located outside the housing 10, multiple interfaces 140 can be provided on the housing 10. The first power supply unit 20, the second power supply unit 30, the radar fusion unit 40, the radar device 400, and the visual recognition device 500 can be connected to their respective interfaces 140 via cables 150, thereby achieving electrical connection between the functional units inside the receiving cavity 130 and the devices outside the housing 10. Simultaneously, to prevent rain and snow from affecting the interfaces 140, [further details can be provided]. Figure 1 These interfaces are shown to be mounted on the base plate 110, and are covered by a cover 120. Furthermore, to meet the lifespan requirements of extreme operating environments, these interfaces 140 may also employ military-grade connectors and shielded wiring harnesses to ensure the reliability of the UAV detection equipment 100.

[0044] In addition, to facilitate the detection and maintenance of abnormalities in the various functional units within the cavity 130, such as Figure 2 and Figure 3 As shown, each side wall 121 of the cover 120 has an opening 1212, and each opening 1212 is detachably covered by a cover plate 124. The cover plate 124 and the side wall 121 can be connected by detachable connection methods such as threaded connection, snap-fit, or pin. In order to ensure the waterproof performance of the cover 120, sealing gaskets, sealing rings, and other components can also be sandwiched between the cover plate 124 and the side wall 121 to form a sealed connection.

[0045] In this structure, when it is necessary to perform abnormal detection and maintenance on the functional unit in the receiving cavity 130, the cover plate 124 closest to the functional unit can be removed from the cover plate 120 according to the position of the functional unit. Thus, the functional unit can be maintained through the opening 1212 on the cover plate 120 without disassembling the cover plate 120 and the base plate 110. This makes abnormal detection and maintenance of each functional unit more convenient.

[0046] The first power supply unit 20, the second power supply unit 30, and the radar fusion unit 40 can be arranged horizontally on the base plate 110, that is, the above-mentioned functional units are arranged along the horizontal direction. Figure 3 The units are arranged in the direction shown by the X-axis or the Y-axis. Alternatively, the first power supply unit 20, the second power supply unit 30, and the radar fusion unit 40 can be stacked, i.e., the aforementioned functional units are arranged along... Figure 3 The components are stacked in the direction indicated by the Z-axis to reduce the area of ​​the base plate 110, thereby reducing the area occupied by the UAV detection device 100 when it is installed.

[0047] Furthermore, in order to improve the heat dissipation efficiency of each functional unit within the receiving cavity 130 while reducing the area of ​​the base plate 110, a stacking structure can be set according to the heat generated by each functional unit. As an example, such as... Figure 3 As shown, the heat generated by the first power supply unit 20 and the second power supply unit 30 is greater than that generated by the radar fusion unit 40. Therefore, the first power supply unit 20 and the second power supply unit 30 can be attached to the base plate 110, thereby conducting the heat generated by the first power supply unit 20 and the second power supply unit 30 to the external environment through the base plate 110, thus improving the heat dissipation efficiency of the first power supply unit 20 and the second power supply unit 30. The radar fusion unit 40 is stacked on top of the first power supply unit 20 or the second power supply unit 30 to reduce the area of ​​the base plate 110 and reduce the area occupied by the UAV detection equipment 100 during installation.

[0048] When the functional units within the accommodating cavity 130 also include components such as an edge computing unit 50, a multi-channel temperature acquisition and fusion unit 60, and a third power supply unit 70, such as Figure 3 As shown, since the edge computing unit 50 generates a relatively large amount of heat, the edge computing unit 50 can be attached to the base plate 110, while the multi-channel temperature acquisition and fusion unit 60 and the third power supply unit 70 are stacked on top of the first power supply unit 20, the second power supply unit 30 and the edge computing unit 50.

[0049] Regarding the arrangement order of functional units on the same floor, in addition to considering the heat generation of the functional units, the height and volume of each functional unit can also be taken into account. For example, consider the radar fusion unit 40, the multi-channel temperature acquisition fusion unit 60, and the third power supply unit 70. Figure 3 and Figure 4 As shown, the cover 120 is outwardly flared from the top wall 122 to the bottom plate 110. That is, the closer the cavity 130 is to the edge of the bottom plate 110, the smaller the height of the object it can accommodate. The height of the multi-channel temperature acquisition and fusion unit 60 and the height of the third power supply unit 70 are both smaller than the height of the radar fusion unit 40. Therefore, the radar fusion unit 40 can be placed in the middle position, while the multi-channel temperature acquisition and fusion unit 60 and the third power supply unit 70 are respectively placed on both sides of the radar fusion unit 40.

[0050] Furthermore, in order to improve the heat dissipation of the various functional units within the cavity 130, such as... Figure 3 and Figure 5 As shown, Figure 5 The diagram shows a cross-sectional view of the UAV detection device from another perspective. The first power supply unit 20, the second power supply unit 30, and the radar fusion unit 40 are arranged adjacent to each other, such that each unit is spaced apart by a first heat dissipation channel 610, and each first heat dissipation channel 610 is parallel to each other. Specifically, each unit is arranged at intervals along the direction shown by the Y-axis or the direction shown by the Z-axis, and the first heat dissipation channel 610 extends along the direction shown by the X-axis.

[0051] Specifically, with Figure 3 and Figure 5 Taking the structure shown as an example, the first power supply unit 20 and the second power supply unit 30 are arranged horizontally at intervals on the base plate 110, so that a first heat dissipation channel 610 is formed between the first power supply unit 20 and the second power supply unit 30. The radar fusion unit 40 is stacked above the first power supply unit 20 and the second power supply unit 30 via a bracket 160, and there is a certain gap between the first power supply unit 20 and the second power supply unit 30 and the bracket 160, so that a first heat dissipation channel 610 is also formed between the first power supply unit 20, the second power supply unit 30 and the radar fusion unit 40.

[0052] like Figure 4 and Figure 5 As shown, a first air inlet 111 is provided on the base plate 110 at one end of the first heat dissipation channel 610, and an air outlet 112 is provided at the other end of the first heat dissipation channel 610. Figure 4 Taking the structure shown as an example, the first heat dissipation channel 610 extends along the X-axis, the first air inlet 111 is set on the base plate 110 and located at the end of the first heat dissipation channel 610 facing the negative X-axis, and the air outlet 112 is set on the base plate 110 and located at the end of the first heat dissipation channel 610 facing the positive X-axis. This allows the gas from the external environment to enter the accommodating cavity 130 through the first air inlet 111, and then flow along the first heat dissipation channel 610 in the positive X-axis direction. When flowing through the first power supply unit 20, the second power supply unit 30, and the radar fusion unit 40, it exchanges heat with each unit and is discharged from the air outlet 112 after absorbing heat.

[0053] Of course, the first air inlet 111 can also be located at the end of the first heat dissipation channel 610 facing the positive X-axis, and the air outlet 112 can be located at the end of the first heat dissipation channel 610 facing the negative X-axis. Furthermore, to increase the gas flow velocity within the receiving cavity 130, such as... Figure 4As shown, multiple first air inlets 111 and multiple air outlets 112 can be opened on the base plate 110, with the multiple first air inlets 111 all located at the same end of the first heat dissipation channel 610, and the multiple air outlets 112 all located at the other end of the first heat dissipation channel 610, so as to... Figure 4 Taking the structure shown as an example, multiple first air inlets 111 are located on the side of the functional unit facing the negative X-axis, while multiple air outlets 112 are located on the side of the functional unit facing the positive X-axis. This ensures that the gas entering the receiving cavity 130 from the first air inlet 111 must first flow through the functional unit in the receiving cavity 130 and then be discharged from the air outlet 112. This ensures that when the gas is discharged from the air outlet 112, it can carry away the heat generated by the functional unit in the receiving cavity 130.

[0054] Furthermore, to prevent dust from entering the receiving cavity 130 through the first air inlet 111 and air outlet 112, such as Figure 2 and Figure 4 As shown, filter screens, dust covers, and other filtration mechanisms can also be covered at the first air inlet 111 and air outlet 112 to prevent dust from entering the containment cavity 130 with the flow of gas, thus preventing dust from affecting the normal operation of functional units such as the first power supply unit 20, the second power supply unit 30, and the radar fusion unit 40.

[0055] In addition, to further improve the heat dissipation efficiency of each functional unit within the cavity 130, such as Figure 5 As shown, a second heat dissipation channel 620 is also formed between the radar fusion unit 40 and the top wall 122 of the cover 120 near the receiving cavity 130, so that the gas entering the receiving cavity 130 from the first air inlet 111 can pass through, thereby allowing the gas to flow through the side wall 121 and top wall 122 of the cover 120 and carry away the heat on the side wall 121 and top wall 122, thus realizing the heat dissipation of the side wall 121 and top wall 122 of the cover 120.

[0056] In this structure, on the one hand, during the hot summer sun, the heat accumulated on the cover 120 can be carried away by airflow to reduce the impact of sunlight on the temperature change inside the cavity 130; on the other hand, the radar device 400 and the visual recognition device 500 installed on the cover 120 can conduct heat to the side wall 121 and top wall 122 of the cover 120, thereby dissipating heat from the side wall 121 and top wall 122 through airflow, thus indirectly achieving heat dissipation for the radar device 400 and the visual recognition device 500.

[0057] like Figure 4 and Figure 5As shown, an air intake device 710 is provided on the base plate 110 at a position opposite to the first air inlet 111 to drive gas from the external environment into the receiving cavity 130 from the first air inlet 111. The air intake device 710 can be a fan, such as an axial flow fan, a centrifugal fan, a mixed flow fan, etc. It is arranged opposite to the first air inlet 111 to draw gas from the external environment into the receiving cavity 130. Specifically, it can be set on the side of the base plate 110 facing the receiving cavity 130, or it can be set on the side of the base plate 110 away from the receiving cavity 130.

[0058] like Figure 4 and Figure 5 As shown, an air outlet device 720 is provided on the base plate 110 opposite to the air outlet 112. This device drives the gas entering the receiving cavity 130 from the first air inlet 111 through the first heat dissipation channel 610 and then exits from the air outlet 112. This airflow carries away the heat generated by the first power supply unit 20, the second power supply unit 30, and the radar fusion unit 40, thereby achieving heat dissipation for these units. Similarly, the air outlet device 720 can be a fan, such as an axial flow fan, a centrifugal fan, or a mixed flow fan. It can be located on the side of the base plate 110 facing the receiving cavity 130 or on the side of the base plate 110 away from the receiving cavity 130.

[0059] Specifically, with Figure 4 and Figure 5 Taking the structure shown as an example, under the drive of the air inlet device 710, the gas from the external environment enters the receiving cavity 130 from the first air inlet 111 along the positive Z-axis direction, and then, under the drive of the air outlet device 720, along... Figure 4 and Figure 5 As shown by the dashed arrow, the gas flows along the positive X-axis and passes through the first power supply unit 20, the second power supply unit 30, and the radar fusion unit 40. Specifically, some gas passes through the first heat dissipation channel 610 formed between the first power supply unit 20, the second power supply unit 30, and the radar fusion unit 40, while another part of the gas passes through the second heat dissipation channel 620 formed between the radar fusion units 40. Finally, the gas converges at the air outlet 112 and is discharged into the external environment. When the gas passes through the first heat dissipation channel 610 and the second heat dissipation channel 620, it absorbs heat from the side walls 121 and top wall 122 of the first power supply unit 20, the second power supply unit 30, the radar fusion unit 40, and the cover 120, and carries the heat out through the air outlet 112, thereby carrying the heat in the containment cavity 130 to the external environment.

[0060] Furthermore, in order to allow more gas to pass through the first heat dissipation channel 610, such as... Figure 2 and Figure 5As shown, the cover 120 flares outward from the end where the top wall 122 is located to the end of the cover 120 near the bottom plate 110, and the first air inlet 111 is opposite to the side wall 121 of the cover 120. Specifically, as shown in the figure, the side wall 121 of the cover 120 is inclined, and gradually moves towards the center as it extends from the end near the bottom plate 110 to the end where the top wall 122 is located.

[0061] When the gas in the external environment enters the receiving cavity 130 along the positive Z-axis under the drive of the air intake device 710, it will continue to flow along the positive Z-axis and directly impact the side wall 121. This can change the flow path of some gas, so that it no longer continues to flow in the positive Z-axis direction. Instead, it enters the first heat dissipation channel 610 under the drive of the air outlet device 720 and flows along the positive X-axis direction and passes through the first heat dissipation channel 610. The other part of the gas continues to flow in the positive Z-axis direction under the guidance of the side wall 121, and gradually deviates to flow in the positive X-axis direction to the second heat dissipation channel 620. This allows the gas to enter and pass through the second heat dissipation channel 620, and finally merges with the gas that passed through the first heat dissipation channel 610 and is discharged from the air outlet 112 under the drive of the air outlet device 720.

[0062] In this structure, by setting the sidewall 121 at an angle, on the one hand, the flow path of the gas entering the receiving cavity 130 from the first air inlet 111 can be changed, allowing more gas to pass through the first heat dissipation channel 610, thereby improving the heat dissipation efficiency of the first power supply unit 20, the second power supply unit 30, and the radar fusion unit 40. On the other hand, the sidewall 121 can also guide the gas to flow more smoothly from the side where the first air inlet 111 is located to the side where the air outlet 112 is located, increasing the gas flow speed in the receiving cavity 130 and helping to improve the gas replacement speed in the receiving cavity 130. In addition, the sidewall 121 can also guide the water flow, allowing rainwater to flow outward with the sidewall 121 at an angle, preventing water from flowing along the sidewall 121 onto the base plate 110, further improving the waterproof performance of the UAV detection equipment 100.

[0063] In the above embodiment, by covering the base plate 110 with the cover 120 to form a receiving cavity 130, and arranging functional units such as the first power supply unit 20, the second power supply unit 30, and the radar fusion unit 40 in the receiving cavity 130, a first heat dissipation channel 610 is formed between each unit. At the same time, by setting a first air inlet 111 and an air outlet 112 on the base plate 110, and setting an air intake device 710 at the first air inlet 111 and an air outlet device 720 at the air outlet 112, the gas in the external environment can enter the receiving cavity 130 formed by the cover 120 and the base plate 110 from the first air inlet 111 under the drive of the air intake device 710, and pass through the first heat dissipation channel 610 under the drive of the air outlet device 720, and finally be discharged from the air outlet 112, so as to dissipate the heat generated by each unit to the external environment and achieve heat dissipation of each unit. Moreover, the cover 120 is installed on the base plate 110, and the first air inlet 111 and the air outlet 112 can be covered by the cover 120 to prevent rain and snow from entering the housing cavity 130 from the first air inlet 111 and the air outlet 112 on rainy or snowy days. This achieves effective heat dissipation for the functional unit while also having good waterproof performance.

[0064] Furthermore, in order to improve the heat dissipation efficiency of the first power supply unit 20 and the second power supply unit 30, such as... Figure 2 , Figure 3 and Figure 6 As shown, Figure 6 The diagram illustrates the three-dimensional structure of the housing in a drone detection device. On the base plate 110, a plurality of first heat sinks 113 are spaced apart on the side away from the receiving cavity 130, where they are attached to the first power supply unit 20 and the second power supply unit 30. A third heat dissipation channel 630 is formed between adjacent first heat sinks 113. As an example, such as… Figure 6 As shown, the base plate 110 has a plurality of first heat sinks 113 extending along the Y-axis on the side facing the external environment, and the plurality of first heat sinks 113 are spaced apart along the X-axis so that a third heat dissipation channel 630 is formed between two adjacent first heat sinks 113. Of course, the first heat sinks 113 can also extend along the X-axis and be spaced apart along the Y-axis.

[0065] like Figure 2 , Figure 3 and Figure 6 As shown, a fan assembly 730 is also provided on the side of the base plate 110 away from the receiving cavity 130. This fan assembly 730 is used to drive air from the external environment into the third heat dissipation channel 630, so as to remove heat from the first heat sink 113 and the base plate 110 through the air. Figure 6Taking the structure of the first heat sink 113 as an example, the fan assembly 730 can be disposed at the end of the first heat sink 113 and drive the gas to flow in the direction shown by the Y-axis, so that the gas enters the third heat dissipation channel 630 and flows along the extension direction of the third heat dissipation channel 630. Specifically, the fan assembly 730 can be disposed on the side of the first heat sink 113 facing the positive direction of the Y-axis to drive the gas to flow in the negative direction of the Y-axis and enter the third heat dissipation channel 630, or the fan assembly 730 can be disposed on the side of the first heat sink 113 facing the negative direction of the Y-axis to drive the gas to flow in the positive direction of the Y-axis and enter the third heat dissipation channel 630.

[0066] Alternatively, the fan assembly 730 can be positioned on the side of the first heatsink 113 away from the base plate 110, driving gas to flow toward the base plate 110. As an example, such as... Figure 2 and Figure 5 As shown, the fan assembly 730 includes an air guide shroud 731 and a fan 732. The air guide shroud 731 covers the side of the first heat sink 113 facing away from the base plate 110, and a second air inlet 733 is provided on the air guide shroud 731. The fan 732 is positioned on the air guide shroud 731 opposite to the second air inlet 733. The fan 732 drives the air from the external environment to enter the interior of the air guide shroud 731 from the second air inlet 733, and then into the third heat dissipation channel 630 under the guidance of the air guide shroud 731.

[0067] by Figure 2 and Figure 5 Taking the structure shown as an example, the second air inlet 733 is located on the surface of the air guide shroud 731 parallel to the base plate 110, and drives the gas from the external environment along... Figure 5 As shown by the dashed line, the air flows in the positive Z-axis direction and enters the interior of the air guide shroud 731. Under the guidance of the side wall of the air guide shroud 731, the air enters the third heat dissipation channel 630, allowing the air to flow along the third heat dissipation channel 630 and carry away the effects on the first heat sink 113 and the base plate 110.

[0068] In this structure, the air guide shroud 731 can guide the airflow, ensuring that all the gas entering the air guide shroud 731 driven by the fan 732 needs to enter the third heat dissipation channel 630 to exchange heat with the first heat sink 113 and the base plate 110 before returning to the external environment through the third heat dissipation channel 630. This ensures that the gas has sufficient contact with the first heat sink 113 and the base plate 110, which helps to improve the heat dissipation efficiency of the first heat sink 113 and the base plate 110, thereby improving the heat dissipation efficiency of the first power supply unit 20 and the second power supply unit 30.

[0069] Furthermore, to ensure that the first heat sink 113 can evenly dissipate heat from the first power supply unit 20 and the second power supply unit 30, such as... Figure 4 and Figure 6 As shown, the first power supply unit 20 and the second power supply unit 30 can be arranged on the base plate 110 along the extending direction of the first heat sink 113. Figure 4 and Figure 6 Taking the structure shown as an example, multiple first heat sinks 113 extend along the Y-axis, and the third heat dissipation channel 630 formed by the multiple first heat sinks 113 also extends along the Y-axis. Therefore, the first power supply unit 20 and the second power supply unit 30 can also be arranged along the Y-axis. This structure allows the first heat sinks 113 to uniformly conduct the heat generated by the first power supply unit 20 and the second power supply unit 30, so that when the gas passes through the third heat dissipation channel 630, it can uniformly carry away the heat generated by the first power supply unit 20 and the second power supply unit 30, ensuring that both the first power supply unit 20 and the second power supply unit 30 can receive effective heat dissipation.

[0070] In the above embodiment, by providing a first heat sink 113 on the base plate 110, the contact area between the base plate 110 and the gas is increased, and the gas flow is driven by the fan assembly 730 to increase the gas flow speed, thereby improving the heat dissipation efficiency of the base plate 110 and the first heat sink 113, and further improving the heat dissipation efficiency of the base plate 110 for the first power supply unit 20 and the second power supply unit 30.

[0071] Regarding the structure of each functional unit within the housing cavity 130, the circuit structure of each functional unit can be directly placed within the housing cavity 130, or the circuit structure of each functional unit can be placed separately in a sealed enclosure to further improve the waterproof and dustproof performance of the UAV detection equipment 100 and prevent dust entering the housing cavity 130 from the first air inlet 111 or air outlet 112 from affecting the circuit structure of each functional unit.

[0072] The following uses the first power supply unit 20 as an example to briefly describe the structure of each functional unit of the receiving cavity 130. For example... Figure 7 As shown, Figure 7 The exploded structure of the first power supply unit in the UAV detection device is shown. The first power supply unit 20 includes a housing 21 and a circuit structure 22. A sealed accommodating cavity 23 is formed inside the housing 21. The circuit structure 22 is disposed in the accommodating cavity 23, and thermal conductive paste 24 is filled between the circuit structure 22 and the inner wall of the housing 21.

[0073] The enclosure 21 includes a main body 211 and a top cover 212. The main body 211 has a receiving groove. The top cover 212 forms a receiving cavity 23 by covering the opening of the receiving groove. The top cover 212 and the main body 211 can be sealed by clamping a gasket or a sealing ring to form a sealed receiving cavity 23. Alternatively, the receiving cavity 23 can be filled with potting compound (such as silicone potting compound, epoxy resin potting compound, polyurethane potting compound, etc.) to achieve sealed protection for the circuit structure 22.

[0074] The heat generated by the circuit structure 22 can be conducted to the wall of the housing 21 by filling the space between the circuit structure 22 and the inner wall of the housing 21 with thermally conductive paste 24. The heat can then be conducted through the wall of the housing 21 to the receiving cavity 130, or to the base plate 110. The thermally conductive paste 24 can be thermally conductive gel, thermally conductive silicone grease, etc. If the receiving cavity 130 is sealed and protected by filling with potting compound, a high thermal conductivity potting compound (such as silicone potting compound) can also be used, allowing the potting compound to act as the thermally conductive paste 24 to conduct the heat generated by the circuit structure 22 to the housing 21. In the above embodiments, the first power supply unit 20 sets the circuit structure 22 in the accommodating cavity 23 inside the housing 21, so as to seal and protect the circuit structure 22 through the housing 21, thereby improving the waterproof and dustproof performance of the UAV detection equipment 100. Moreover, the space between the circuit structure 22 and the inner wall of the housing 21 is filled with thermally conductive paste 24, so that the heat generated by the circuit structure 22 can be conducted to the housing 21 through the thermally conductive paste 24, thereby realizing heat dissipation of the circuit structure 22 inside the housing 21 by heat exchange between the gas and the housing 21.

[0075] Besides the first power supply unit 20, the second power supply unit 30 and the radar fusion unit 40 can both adopt the same structure as the first power supply unit 20. That is, the second power supply unit 30 and the radar fusion unit 40 can also adopt the design of a housing 21 and a circuit structure 22, so as to seal and protect the circuit structure of each functional unit through the housing, and at the same time realize the modular design of each functional unit within the housing cavity 130. Specifically, at least one of the first power supply unit 20, the second power supply unit 30 and the radar fusion unit 40 includes a housing and a circuit structure. A sealed housing cavity is formed inside the housing, the circuit structure is placed in the housing cavity, and thermal conductive paste is filled between the circuit structure and the inner wall of the housing.

[0076] Furthermore, in order to improve the heat dissipation efficiency of circuit structure 22, such as Figure 7As shown, multiple second heat sinks 25 can be spaced apart on the outer wall of the housing 21 to increase the contact area between the housing 21 and the gas in the containment cavity 130. This allows the heat generated by the circuit structure 22 to be conducted more quickly to the inside of the containment cavity 130 through the housing 21 and the second heat sinks 25. The gas in the containment cavity 130 can then be replaced through the first air inlet 111 and the air outlet 112 to dissipate heat from the circuit structure 22.

[0077] Furthermore, the second heat sink 25 can also be designed to extend from the side where the first air inlet 111 is located towards the side where the air outlet 112 is located, so that a first heat dissipation channel 610 is also formed between the multiple second heat sinks 25. In this way, the second heat sinks 25 can guide the gas in the receiving cavity 130, so that the gas can quickly pass through the first heat dissipation channel 610 under the drive of the air outlet device 720, thereby improving the heat dissipation efficiency of the circuit structure 22.

[0078] It should be noted that the various functional units in the housing 130 can adopt the same structure as the first power supply unit 20, or different methods can be selected to achieve the same function according to the characteristics of each functional unit. Taking the sealing method of the housing 23 as an example, the first power supply unit 20, the second power supply unit 30, the radar fusion unit 40, and the third power supply unit 70 can be sealed and protected by filling the housing 23 with potting compound. The edge computing unit 50 and the multi-channel temperature acquisition and fusion unit 60 can be sealed by fixing with waterproof sealing rings and bolts, so that the housing 21 forms a sealed housing 23. Similarly, the structure of the second heat sink 25 can be designed according to the heat dissipation requirements of each functional unit. If the heat dissipation requirements of the functional unit are not high, the second heat sink 25 may not be installed on the outer wall of the housing 21.

[0079] According to another aspect of the embodiments of this application, a drone detection system is also provided, such as... Figure 1As shown, the UAV detection system 1000 includes multiple radar devices 400, a visual recognition device 500, and the UAV detection device 100 described in any of the above embodiments. The UAV detection device 100 is signal-connected to both the radar devices 400 and the visual recognition device 500, and is used to perform fusion calculations on the data collected by the radar devices 400 and the visual recognition device 500. The radar devices 400 are installed on the side wall 121 of the cover 120 of the UAV detection device 100 away from the receiving cavity 130, and are electrically connected to the first power supply unit 20 and the radar fusion unit 40 within the receiving cavity 130, so that the power supply unit supplies power to the radar devices 400, and the radar fusion unit 40 performs fusion calculations on the data collected by the multiple radar devices 400. The visual recognition device 500 is installed on the top wall 122 of the cover 120 away from the receiving cavity 130, and is electrically connected to the second power supply unit 30 within the receiving cavity 130, so that the second power supply unit 30 supplies power to the visual recognition device 500.

[0080] As an example, radar device 400 can be a long-range two-dimensional phase-scanning radar, and visual recognition device 500 can be a multispectral target recognition and tracking servo payload optoelectronic system to achieve an effective detection radius of greater than or equal to 5 km and stably acquire an RCS of 0.01 m. 2 It can guide, identify, track and locate micro and small drone targets, meeting the needs of long-distance early warning. At the same time, it can intelligently classify and identify multiple types of targets such as drones, personnel and vehicles, and accurately determine the target attributes.

[0081] In addition, the UAV detection device 100 may also include an edge computing unit 50 disposed within the receiving cavity 130. The edge computing unit 50 is electrically connected to the radar device 400 and the visual recognition device 500 respectively. The edge computing unit 50 performs fusion calculation on the multimodal data collected by the radar device 400 and the visual recognition device 500, so that the UAV detection system 1000 forms a working mechanism of "radar early warning - optical / thermal imaging identification and evidence collection". Through the radar-visual collaborative detection mechanism, the time required from target appearance to confirmation is effectively shortened. Combined with countermeasure capabilities, a countermeasure closed loop can also be formed.

[0082] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application, and not to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. These modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this application, and they should all be covered within the scope of the claims and specification of this application. In particular, as long as there is no structural conflict, the various technical features mentioned in the embodiments can be combined in any way. This application is not limited to the specific embodiments disclosed herein, but includes all technical solutions falling within the scope of the claims.

Claims

1. A drone detection device, characterized in that, The UAV detection equipment is used to connect with radar equipment and visual recognition equipment, and to perform fusion calculations on the data collected by the radar equipment and the data collected by the visual recognition equipment. The UAV detection device includes: a shell, a first power supply unit, a second power supply unit, and a radar fusion unit; The housing includes a base plate and a cover, the cover including a top wall and multiple side walls; the cover is disposed on the base plate and is sealed to the base plate to form a receiving cavity; The sidewalls of the cover member away from the receiving cavity are used to house multiple radar devices, and the top wall of the cover member away from the receiving cavity is used to house the visual recognition device. The first power supply unit, the second power supply unit, and the radar fusion unit are all disposed on the base plate on the side facing the receiving cavity; the first power supply unit is used to supply power to the radar device, the second power supply unit is used to supply power to the visual recognition device, and the radar fusion unit is used to electrically connect with multiple radar devices and perform fusion calculation on the data collected by multiple radar devices; The first power supply unit, the second power supply unit, and the radar fusion unit are arranged adjacent to each other, and each unit is spaced apart by a first heat dissipation channel, and each of the first heat dissipation channels is parallel to each other. The base plate has a first air inlet at one end of the first heat dissipation channel and an air outlet at the other end of the first heat dissipation channel. An air intake device is provided on the base plate at a position opposite to the first air inlet. The air intake device is used to drive gas from the external environment into the accommodating cavity from the first air inlet. An air outlet device is provided on the base plate at a position opposite to the air outlet. The air outlet device is used to drive the gas entering the accommodating cavity from the first air inlet through the first heat dissipation channel and then discharge it from the air outlet to dissipate heat from the first power supply unit, the second power supply unit and the radar fusion unit.

2. The UAV detection device according to claim 1, characterized in that, The heat generated by the first power supply unit and the second power supply unit is greater than the heat generated by the radar fusion unit; Both the first power supply unit and the second power supply unit are attached to the base plate, and the radar fusion unit is stacked on top of the first power supply unit or the second power supply unit.

3. The UAV detection device according to claim 2, characterized in that, A second heat dissipation channel is formed between the radar fusion unit and the top wall of the cover near the receiving cavity. The second heat dissipation channel is used to allow gas entering the receiving cavity from the first air inlet to pass through, so as to dissipate heat from the side wall and top wall of the cover.

4. The UAV detection device according to claim 3, characterized in that, The cover extends outward from the end where the top wall is located to the end of the cover near the bottom plate, and the first air inlet is opposite to the side wall of the cover.

5. The UAV detection device according to claim 2, characterized in that, On the bottom plate, a plurality of first heat sinks are provided at intervals on the side away from the receiving cavity where they are in contact with the first power supply unit and the second power supply unit, and a third heat dissipation channel is formed between adjacent first heat sinks. A fan assembly is also provided on the side of the base plate away from the receiving cavity. The fan assembly is used to drive the gas in the external environment into the third heat dissipation channel so as to remove the heat from the first heat sink and the base plate through the gas.

6. The UAV detection device according to claim 5, characterized in that, The first power supply unit and the second power supply unit are arranged on the base plate along the extension direction of the first heat sink.

7. The UAV detection device according to claim 5, characterized in that, The fan assembly includes an air guide and a fan; The air guide cover is disposed on the side of the first heat sink away from the base plate, and the air guide cover is provided with a second air inlet; The fan is positioned on the air guide shroud opposite the second air inlet. The fan drives the gas from the external environment to enter the interior of the air guide shroud from the second air inlet, and then into the third heat dissipation channel under the guidance of the air guide shroud.

8. The UAV detection device according to any one of claims 1-7, characterized in that, At least one of the first power supply unit, the second power supply unit, and the radar fusion unit includes a housing and a circuit structure; The box has a sealed cavity inside, the circuit structure is disposed in the cavity, and the space between the circuit structure and the inner wall of the box is filled with thermally conductive paste.

9. The UAV detection device according to claim 8, characterized in that, Multiple second heat sinks are spaced apart on the outer wall of the housing, and the second heat sinks extend from the side where the first air inlet is located toward the side where the air outlet is located.

10. A drone detection system, characterized in that, The system includes: multiple radar devices, visual recognition devices, and unmanned aerial vehicle detection devices as described in any one of claims 1-9; The UAV detection device is connected to the radar device and the visual recognition device respectively, and is used to perform fusion calculation on the data collected by the radar device and the data collected by the visual recognition device; The radar device is installed on the side wall of the cover of the UAV detection device away from the receiving cavity, and is electrically connected to the first power supply unit and the radar fusion unit inside the receiving cavity, respectively. The visual recognition device is installed on the top wall of the cover on the side away from the receiving cavity and is electrically connected to the second power supply unit inside the receiving cavity.

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