An unmanned aerial vehicle-mounted radar mounting stabilizing device, a stabilizing method and an unmanned aerial vehicle

Abstract

This invention relates to the technical field of UAV installation, specifically to a UAV-borne radar mounting and stabilizing device, stabilizing method, and UAV. It includes a radar mounting component, an outer annular air guide ring, an electric slide rail assembly, and a frame-type shell stabilizing assembly. The outer annular air guide ring is fixedly mounted on the radar mounting component and surrounds the outer periphery of the radar body; the electric slide rail assembly is mounted on the inner side of the outer annular air guide ring; the frame-type shell stabilizing assembly is located on the inner side of the outer annular air guide ring and is used to engage the radar body from the outside; wherein, in the engaged state, the frame-type shell stabilizing assembly forms an engaging frame adapted to the outer periphery of the radar body and engages with the slide block, thereby limiting the displacement of the radar body during flight. After assembly, the frame-type shell stabilizing assembly forms an engaging frame surrounding the radar body from multiple directions, and its end positions are fixed accordingly, suppressing radar body displacement and connection loosening caused by flight vibrations, achieving rapid assembly and disassembly and multi-directional stabilization.

Description

Technical Field

[0001] This invention relates to the technical field of drone installation, specifically to a drone-borne radar mounting and stabilizing device, stabilizing method, and drone. Background Technology

[0002] As a core sensor for UAVs performing tasks such as mapping, reconnaissance, and obstacle avoidance, the reliability of the UAV-borne radar's installation structure directly determines the operational accuracy and flight safety of the entire system. Because UAVs are continuously subjected to complex multi-spectral and multi-directional vibration loads during flight, the radar installation device not only needs to bear the weight of the equipment but also needs to maintain the long-term stability of the radar measurement reference in a dynamic mechanical environment. Currently, UAV-borne radar installation methods generally employ either rigid bolts for direct fastening or simple clamp fixation. Rigid bolt connections use multiple distributed bolts to lock the radar housing to the fuselage support, relying on bolt preload for mechanical fixation; simple clamp fixation uses a clamp structure to hold the radar housing at one or more points, making operation relatively simple.

[0003] In practical applications, while rigid bolt connections provide strong static locking force, the disassembly and assembly of bolts at multiple points is cumbersome, hindering rapid field maintenance. Furthermore, due to manufacturing tolerances and assembly errors, the preload of each bolt is difficult to maintain uniformly, easily leading to localized stress concentrations in flight vibration environments and accelerating fatigue and loosening of the connectors. While simple clamp fixation is quick to operate, its limited constraint points make it difficult to effectively suppress radial displacement and angular deflection of the radar housing during flight from multiple directions. None of the above installation methods can achieve a balance between the requirements of rapid disassembly and multi-directional vibration suppression. Rapid disassembly requires loose clearances and simple operation, while multi-directional stability requires the structure to maintain rigid constraints without gaps under vibration. This inherent contradiction leads to widespread reliability issues in existing installation structures during long-term service, such as loose connections, radar measurement reference misalignment, and structural fatigue, severely impacting the continuous operational capability and mission accuracy of UAV radar platforms. Summary of the Invention

[0004] This invention provides a device, method, and drone for mounting and stabilizing a drone-borne radar, which solves the problem that the drone-borne radar mounting structure cannot achieve a balance between rapid assembly and disassembly and multi-directional vibration suppression, resulting in loosening of connectors, radar measurement reference deviation, and structural fatigue under flight vibration environment.

[0005] To address the aforementioned problems, the present invention provides a device for stabilizing and mounting unmanned aerial vehicle (UAV) radar, comprising: A radar mounting component, which is mounted on a UAV, has a socket for inserting into the radar body; An outer annular air guide ring is fixedly mounted on the radar mounting component and surrounds the outer periphery of the radar body. An electric slide rail assembly is installed on the inner side of the outer annular air guide ring. The electric slide rail assembly includes a slide rail arranged circumferentially along the outer annular air guide ring and a slide seat slidably connected to the slide rail. A frame-type shell fixing assembly is located inside the outer annular air guide ring and is used to engage the radar body from the outside of the radar body. In the locked state, the frame-type shell fixing component forms a locking frame that is adapted to the outer periphery of the radar body and engages with the sliding seat to limit the displacement of the radar body in flight.

[0006] Preferably, the frame-type shell assembly includes: Top crossbar; Two vertical rods, the upper ends of which are respectively hinged to the two ends of the top horizontal rod; Two bottom crossbars, with one bottom crossbar fixedly connected to the lower end of each of the vertical bars; When the two bottom crossbars are retracted relative to the two vertical bars, their ends are engaged in the grooves of the slide block to complete the positioning.

[0007] Preferably, the slide rail of the electric slide rail assembly is provided with a telescopic rod, and the bottom crossbar has a horizontal end hole at its end; after the bottom crossbar is engaged in the groove of the slide block, the telescopic rod extends out and inserts into the horizontal end hole, locking the bottom crossbar to prevent it from coming out of the groove.

[0008] Preferably, the top crossbar is fixedly connected with an end face support lug. When the frame-type housing assembly is in the engaged state, the top crossbar is attached to the top of the radar body, and the two vertical bars are clamped on opposite sides of the radar body. The end face support lug and the radar body are connected by fasteners.

[0009] Preferably, the radar body is provided with lateral heat dissipation fins on both sides, and the sidewall of the outer annular air guide ring is provided with a heat dissipation channel groove corresponding to the lateral heat dissipation fins.

[0010] Preferably, the heat dissipation channel groove has a structure that is wider on the outside and narrower on the inside, with the outer opening size being larger than the inner opening size.

[0011] Preferably, the system includes a water-blocking connecting plate, which is fitted onto the outside of the radar body and protrudes from the upper surface of the radar mounting component. The outer annular air guide ring and the radar body form a distribution surface flow groove, and the water-blocking connecting plate is located at the bottom of the distribution surface flow groove. The distribution surface flow groove is used to guide airflow to flow around the radar body for heat dissipation.

[0012] Preferably, an air guide opening groove and an air guide outlet groove are respectively provided on the outer annular air guide ring; the air guide opening groove is provided on the air inlet side of the distribution surface flow groove, and the air guide outlet groove is provided on the air outlet side of the distribution surface flow groove, so as to cooperate with the lateral diffuser fins to form a flight air guide heat dissipation channel.

[0013] On the other hand, the present invention provides a method for stabilizing and mounting a UAV-borne radar, applied to the aforementioned UAV-borne radar mounting and stabilizing device, comprising the following steps: Adjust the installation angle of the radar mounting components so that the air intake and heat dissipation end of the outer annular air guide ring faces the direction of the incoming flight flow; The radar body is inserted into the socket of the radar mounting component to complete the positioning of the radar body and the radar mounting component. The frame-type shell fixing assembly is placed outside the radar body, and the frame-type shell fixing assembly is folded together to form a locking frame that fits the outer periphery of the radar body, and is locked and fixed to the slide seat of the electric slide rail assembly.

[0014] In another aspect, the present invention provides a drone, including a body and the aforementioned drone-borne radar mounting and stabilizing device, wherein the radar body is inserted into the socket of the radar mounting component of the stabilizing device, and the radar mounting component is mounted on the top of the body.

[0015] The beneficial effects of this invention are: This invention provides an unmanned aerial vehicle (UAV) radar mounting and stabilizing device. During assembly, the frame-type shell-fixing component retracts and engages with the radar body from the outside. The floating capability of the slide block on the slide rail allows the stabilizing device to achieve an ideal state of seamless fit without internal stress, avoiding local stress concentration caused by forced alignment due to tolerances in traditional rigid connections. After assembly, the frame-type shell-fixing component forms a locking frame surrounding the radar body from multiple directions, including the top, sides, and longitudinal direction. Its ends are fixed to the slide block, establishing a gapless rigid constraint network. This effectively suppresses radar body displacement, connection loosening, and measurement reference offset caused by flight vibrations, achieving a unified approach of rapid assembly and disassembly with multi-directional stabilization.

[0016] In terms of heat dissipation, this invention employs a structural layout where an outer annular air guide ring surrounds the outer periphery of the radar body. The distribution surface flow channel formed by the annular gap between the outer annular air guide ring and the radar body guides the oncoming airflow during flight to flow orderly along the outer periphery of the radar body. This transforms the flight airflow into a continuous cooling airflow passing through the lateral heat dissipation fins, constructing a complete passive heat dissipation airflow channel. The airflow enters through the air guide channel, is distributed through the distribution surface flow channel, undergoes heat exchange through the heat dissipation channel channel, and exits through the air guide channel outlet channel. The heat dissipation channel channel adopts a converging cross-section design that is wider at the outer edge and narrower at the inner edge, accelerating the airflow as it passes through the fin area and enhancing the convective heat transfer effect. The entire heat dissipation system requires no fans or any active devices, does not increase power consumption or electromagnetic interference, and the low-resistance layout that runs through the entire system ensures that the cooling airflow follows the flight direction, without increasing flight drag.

[0017] The method for stabilizing and mounting a UAV-borne radar provided by this invention, and the beneficial effects of the UAV compared to existing technologies, are the same as the aforementioned UAV-borne radar stabilization and mounting device, and will not be repeated here. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the structure of a UAV-borne radar mounting and stabilizing device according to an embodiment of the present invention; Figure 2 yes Figure 1 Enlarged view of point A; Figure 3 This is a schematic diagram of the installation of the radar mounting component and the outer annular air guide ring in one embodiment of the present invention.

[0019] Explanation of reference numerals in the attached drawings: 1-Radar mounting component; 2-Outer annular air guide ring; 3-Radar body; 4-Electric slide rail assembly; 41-Slide base; 42-Slide rail; 43-Telescopic rod; 5-Frame-type shell fixing assembly; 51-Top crossbar; 52-Vertical rod; 53-Bottom crossbar; 54-End face support lug; 31-Side heat dissipation fins; 21-Heat dissipation channel groove; 6-Water-blocking connecting plate; 7-Distribution surface flow groove; 71-Air guide opening groove; 72-Air guide outlet groove; 8-Main body. Detailed Implementation

[0020] To make the above-mentioned objects, features, and advantages of the present invention more apparent and understandable, specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings. Although some embodiments of the present invention are shown in the drawings, it should be understood that the present invention can be implemented in various forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided to provide a more thorough and complete understanding of the present invention. It should be understood that the accompanying drawings and embodiments of the present invention are for illustrative purposes only and are not intended to limit the scope of protection of the present invention.

[0021] The term "comprising" and its variations as used herein are open-ended, meaning "including but not limited to"; the term "based on" means "at least partially based on"; the term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one additional embodiment"; the term "some embodiments" means "at least some embodiments"; and the term "optionally" means "optional embodiments". Definitions of other terms will be given in the following description. It should be noted that the concepts of "first," "second," etc., mentioned in this invention are used only to distinguish different devices, modules, or components, and are not intended to limit the order of functions performed by these devices, modules, or components or their interdependencies.

[0022] It should be noted that the terms "a" and "a plurality of" used in this invention are illustrative rather than restrictive. Those skilled in the art should understand that, unless otherwise expressly indicated in the context, they should be understood as "one or more".

[0023] To address the problems existing in the aforementioned related technologies, the present invention provides an unmanned aerial vehicle (UAV) radar mounting and stabilizing device, stabilizing method, and an UAV.

[0024] See Figures 1 to 3 This invention provides a device for mounting and stabilizing an unmanned aerial vehicle (UAV) radar, including a radar mounting component 1, an outer annular air guide ring 2, an electric slide rail assembly 4, and a frame-type shell-fixing assembly 5. The radar mounting component 1 is mounted on the UAV and has an insertion hole for inserting into the radar body 3. The outer annular air guide ring 2 is fixedly mounted on the radar mounting component 1 and surrounds the outer periphery of the radar body 3. The electric slide rail assembly 4 is mounted inside the outer annular air guide ring 2 and includes a slide rail 42 arranged circumferentially along the outer annular air guide ring 2 and a slide seat 41 slidably connected to the slide rail 42. The frame-type shell-fixing assembly 5 is located inside the outer annular air guide ring 2 and is used to engage the radar body 3 from the outside. In the engaged state, the frame-type shell-fixing assembly 5 forms an engaging frame adapted to the outer periphery of the radar body 3 and engages with the slide seat 41, thereby limiting the displacement of the radar body 3 during flight.

[0025] Specifically, the radar mounting component 1 can be a mounting base, typically fixed above the UAV. The radar body 3 is inserted into the socket of the radar mounting component 1, completing the positioning of the radar body 3 and the radar mounting component 1. The outer annular air guide ring 2 is fixed to the upper end of the radar mounting component 1, with its central axis vertically set. It should be noted that during assembly, the frame-type shell fixing assembly 5 is first folded in from the outside, so that it fits and engages with the outer periphery of the radar body 3. At this time, the entire frame-type shell fixing assembly 5 can be slightly adjusted relative to the outer annular air guide ring 2. At the same time, the slide block 41 of the electric slide rail assembly 4 slides freely on the slide rail 42, adaptively accommodating and aligning with the end of the frame-type shell fixing assembly 5 to complete the assembly of the frame-type shell fixing assembly 5 and the radar body 3. After assembly, the frame-type shell fixing assembly 5 fits the radar body 3 without gaps and without internal stress, avoiding the traditional rigidity. The rigid connection causes local stress concentration due to the forced alignment of tolerances. Furthermore, the frame-type shell fixing component 5 forms a locking frame that surrounds the radar body 3 from multiple directions, effectively limiting the radar body 3 from multiple directions. Moreover, when the end of the frame-type shell fixing component 5 is engaged with the slide 41, the position of the slide 41 on the slide rail 42 can be fixed by electronic control to ensure the position of the frame-type shell fixing component 5 and the radar body 3 is fixed, suppressing the displacement of the radar body 3 and the loosening of the connection caused by flight vibration, and achieving a combination of rapid disassembly and assembly and multi-directional stability.

[0026] In addition, this embodiment uses the structure of an outer annular air guide ring 2 surrounding the outer periphery of the radar body 3. The annular gap between the outer annular air guide ring 2 and the radar body 3 guides the oncoming airflow in flight to flow orderly along the outer periphery of the radar body 3, transforming the flight airflow into a cooling airflow that continuously flows over the outer surface of the radar body 3. Without setting up additional fans or electrical components or increasing system power consumption, the passive heat dissipation capability of the radar body 3 is enhanced. Moreover, the annular structure of the outer annular air guide ring 2 makes the airflow flow in a low-resistance through flow, without significantly increasing flight drag.

[0027] In one embodiment of the present invention, the frame-type housing assembly 5 includes a top horizontal bar 51, two vertical bars 52, and two bottom horizontal bars 53. The upper ends of the two vertical bars 52 are respectively hinged to the two ends of the top horizontal bar 51; the lower end of each vertical bar 52 is fixedly connected to a bottom horizontal bar 53; wherein, when the two vertical bars 52 are retracted relative to each other, the ends of the two bottom horizontal bars 53 are respectively engaged in the grooves of the slide block 41 to complete the positioning.

[0028] It should be noted that the upper ends of the two vertical rods 52 are respectively hinged to the ends of the top horizontal rod 51, and the hinge axes are perpendicular to the top horizontal rod 51 and the corresponding vertical rod 52 respectively. The two vertical rods 52 can rotate flexibly around the hinge point. During assembly, the operator pulls the two vertical rods 52 inward. The hinge structure allows the vertical rods 52 to fit the outer contour of the radar body 3. The top horizontal rod 51 spans the top of the radar body 3, and the two vertical rods 52 are clamped on both sides of the radar body 3, forming a three-dimensional envelope of the top surface and the two sides, thus completing the initial spatial attitude constraint of the radar body 3. Each vertical rod 52 has a bottom horizontal rod 53 fixedly connected to its lower end. When the vertical rod 52 is retracted into place, the end of the bottom horizontal rod 53 aligns precisely with the groove in the slide block 41, thus locking the end of the bottom horizontal rod 53 into the groove for positioning. Specifically, each bottom horizontal rod 53 corresponds to a slide block 41, and each bottom horizontal rod 53 is inserted into the groove of one slide block 41. By fixing and positioning the two bottom horizontal rods 53 with the two slide blocks 41, the three-dimensional envelope structure formed by the top horizontal rod 51 and the two vertical rods 52 can be stabilized. During this process, the slide block 41 floats on the slide rail 42, allowing the slide block 41 to adaptively accommodate and receive the end of the bottom horizontal rod 53, ensuring a smooth and unobstructed insertion process. After the end of the bottom crossbar 53 is inserted into the groove of the slide block 41, the position of the slide block 41 on the slide rail is fixed. A rigid constraint is established between the entire frame-type shell fixing assembly 5 and the slide block 41. Together with the envelope constraint established at the top and sides by the top crossbar 51 and the two vertical bars 52, a multi-directional gapless locking of the radar body 3 is formed, which effectively suppresses the displacement and loosening of the radar body 3 in various directions during flight, thereby ensuring multi-directional stability while achieving rapid assembly and disassembly.

[0029] In one embodiment of the present invention, a telescopic rod 43 is provided on the slide rail 42 of the electric slide rail assembly 4, and a horizontal end hole is provided at the end of the bottom crossbar 53; after the bottom crossbar 53 is engaged in the groove of the slide block 41, the telescopic rod 43 extends out and inserts into the horizontal end hole, locking the bottom crossbar 53 to prevent it from coming out of the groove.

[0030] It should be noted that when the slide block 41 slides on the slide rail 42 until it aligns with the end of the bottom crossbar 53, and the end of the bottom crossbar 53 is engaged in the groove of the slide block 41, a preliminary engagement relationship is established between the entire frame-type housing assembly 5 and the electric slide rail assembly 4. However, under the continuous action of flight vibration, the simple groove engagement may still result in slight movement due to gaps. At this time, the telescopic rod 43 passing through the slide rail 42 extends out, passes through the slide block 41, and inserts into the horizontal end hole opened at the end of the bottom crossbar 53. The telescopic rod 43 and the horizontal end hole form a shaft hole fit, constituting a mechanical locking pin perpendicular to the axial direction of the bottom crossbar 53, blocking the path of the bottom crossbar 53 to retract from the groove along its axial direction. Because the telescopic rod 43 is mounted on the slide rail 42, its extended position is constrained by the slide rail 42 and cannot be disengaged due to vibration. Therefore, the locking relationship between the bottom crossbar 53 and the slide block 41 remains locked throughout the entire flight process, unaffected by vibration loads, thus improving connection reliability. Furthermore, the extension and retraction of the telescopic rod 43 can be performed synchronously after the slide block 41 is aligned, without increasing the complexity of the disassembly and assembly steps, balancing locking reliability and operational convenience. The telescopic rod 43 can be an electric push rod or a hydraulically driven rod.

[0031] In one embodiment of the present invention, an end face support lug 54 is fixedly connected to the top crossbar 51. When the frame-type housing assembly 5 is in the locked state, the top crossbar 51 is attached to the top of the radar body 3, and the two vertical bars 52 are clamped on the opposite sides of the radar body 3. The end face support lug 54 and the radar body 3 are connected by fasteners.

[0032] It should be noted that when the two vertical rods 52 are retracted and clamped on opposite sides of the radar body 3, and the top horizontal rod 51 is attached to the top of the radar body 3, the top horizontal rod 51 is kept in contact with the radar body 3 by the clamping force of the two vertical rods 52. However, relying solely on the clamping force, there is still a risk that the top horizontal rod 51 may separate from the top surface of the radar body 3 under flight vibration. At this time, the end face support lug 54 fixedly connected to the top horizontal rod 51 is fastened to the radar body 3 by a threaded connection, locking the top horizontal rod 51 and the radar body 3 in the vertical direction, eliminating the assembly gap between the two, and preventing the top horizontal rod 51 from lifting due to vibration and losing contact with the radar body 3. Since the end face support lug 54 is fixedly connected to the top crossbar 51, and the top crossbar 51 is hinged to the two vertical bars 52, the fastening effect of the end face support lug 54 is transmitted to the entire frame-type shell fixing assembly 5 through the top crossbar 51, so that the frame and the radar body 3 form an integral rigid structure. With the locking of the bottom crossbar 53 end to the slide 41, the radar body 3 is completely constrained from the top, sides and longitudinal direction, which further improves the ability to suppress flight vibration displacement.

[0033] In one embodiment of the present invention, the radar body 3 is provided with lateral heat dissipation fins 31 on both sides, and the side wall of the outer annular air guide ring 2 is provided with a heat dissipation channel groove 21 through the lateral heat dissipation fins 31.

[0034] It should be noted that the sidewall of the outer annular air guide ring 2 has a heat dissipation channel groove 21 that runs through the lateral heat dissipation fins 31. The core design intention is to establish a direct forced convection channel between the airflow and the heat dissipation fins 31, transforming the lateral heat dissipation fins 31 from a passive natural heat dissipation surface into an active heat exchange interface within the air duct. The lateral heat dissipation fins 31 are located on both sides of the radar body 3 and are the main path for heat conduction outward during radar body 3 operation. If there is no directional airflow, the lateral heat dissipation fins 31 can only rely on the natural convection of the surrounding air for heat dissipation, which is inefficient. The heat dissipation channel groove 21 runs through the sidewall of the outer annular air guide ring 2 and corresponds to the lateral heat dissipation fins 31. This allows the airflow in the annular gap between the outer annular air guide ring 2 and the radar body 3 to be guided to the area where the lateral heat dissipation fins 31 are located when flowing circumferentially. The airflow flows quickly along the surface of the lateral heat dissipation fins 31, carrying away the heat on the fins and discharging it downstream in a forced convection manner. By directing the existing oncoming airflow into the fin area during flight, heat dissipation efficiency is improved without the need for a fan or any active device. Furthermore, the heat dissipation channel groove 21 serves as a through opening in the side wall of the air guide ring, without adding additional frontal area or protruding structure, thus keeping the impact on flight drag at a low level.

[0035] In one embodiment of the present invention, the heat dissipation channel groove 21 has a structure that is wider on the outside and narrower on the inside, with the outer opening size being larger than the inner opening size.

[0036] It should be noted that the heat dissipation channel 21 adopts a cross-sectional shape that is wider on the outside and narrower on the inside. Utilizing the airflow acceleration effect generated by the cross-sectional contraction, it enhances the forced convection heat transfer capability of the lateral diffuser fins 31, while also considering the requirements of low drag and prevention of foreign object ingress. The outer opening size of the heat dissipation channel 21 is larger than the inner opening size. When the oncoming airflow during flight flows along the annular gap between the outer annular guide ring 2 and the radar body 3 and enters the heat dissipation channel 21, the airflow enters from the wider outer opening and exits from the narrower inner opening. The gradual narrowing of the flow cross-section increases the airflow velocity as it flows through the channel. According to the principle of convection heat transfer, a higher airflow velocity means a larger heat transfer coefficient, thus enabling the airflow flowing over the surface of the lateral diffuser fins 31 to more efficiently remove heat from the fins and improve heat dissipation efficiency. Meanwhile, the design of the outer opening being larger than the inner opening makes the heat dissipation channel 21 a convergent flow channel. Compared to a straight channel with a constant cross-section, the convergent flow channel has lower aerodynamic drag, and the airflow is less likely to generate vortices or separation when entering the channel, which helps to control the increase in flight drag while ensuring heat dissipation effect. In addition, the smaller inner opening also provides a certain degree of shielding and protection for the lateral heat dissipation fins 31, reducing the risk of foreign objects directly impacting the fins from the side. This makes the heat dissipation channel 21 have multiple functions, including airflow acceleration, low-resistance flow, and structural protection, further optimizing the overall performance of the passive heat dissipation system without adding any active devices or additional frontal area.

[0037] In one embodiment of the present invention, the water-blocking connecting plate 6 is further included. The water-blocking connecting plate 6 is fitted on the outside of the radar body 3 and protrudes from the upper end face of the radar mounting component 1. The outer annular air guide ring 2 and the radar body 3 form a distribution surface flow groove 7. The water-blocking connecting plate 6 is located at the bottom of the distribution surface flow groove 7. The distribution surface flow groove 7 is used to guide the airflow to flow around the radar body 3 for heat dissipation.

[0038] It should be noted that the water-blocking connecting plate 6 is fitted onto the outside of the radar body 3 and protrudes from the upper surface of the radar mounting part 1. Structurally, it forms a raised baffle ring surrounding the radar body 3. When the UAV operates in precipitation or humid environments, water droplets flowing downwards along the outer shell of the radar body 3 are blocked and guided to the surrounding areas upon encountering the protruding water-blocking connecting plate 6, preventing them from further seeping into the connection gap between the radar body 3 and the radar mounting part 1, thus providing a waterproof and sealing protection. At the same time, the distribution surface flow groove 7 formed between the outer annular air guide ring 2 and the radar body 3 constitutes an annular airflow channel surrounding the radar body 3. The water-blocking connecting plate 6 is located at the bottom of the distribution surface flow groove 7, narrowing the lower half of the distribution surface flow groove 7. This causes the oncoming airflow entering from the front during flight to be squeezed towards the outer surface of the radar body 3 when flowing through this area. The airflow flows closer to the outer wall of the radar body 3, enhancing the convective heat transfer effect between the airflow and the radar body 3, and continuously carrying away the heat generated by the radar body 3 during operation. The distribution surface flow channel 7 utilizes the existing space between the outer annular air guide ring 2 and the radar body 3 to form an airflow channel without adding additional flow guiding components. The water-blocking connecting plate 6 serves as both a waterproof baffle and an airflow guiding structure at the bottom of the distribution surface flow channel 7, enabling the device to simultaneously achieve environmental protection and passive heat dissipation functions within a limited space, thereby improving the integration and overall efficiency of the structure.

[0039] In one embodiment of the present invention, an air guide opening groove 71 and an air guide outlet groove 72 are respectively provided on the outer annular air guide ring 2; the air guide opening groove 71 is provided on the air inlet side of the distribution surface flow groove 7, and the air guide outlet groove 72 is provided on the air outlet side of the distribution surface flow groove 7, so as to cooperate with the lateral diffuser fin heat sink 21 to form a flight air guide heat dissipation channel.

[0040] It should be noted that the air guide slot 71 and the air guide outlet slot 72 are respectively located on the air inlet and outlet sides of the distribution surface flow channel 7. This establishes a clear airflow inlet and outlet for the distribution surface flow channel 7, organizing the airflow, which originally relied solely on the natural flow of the annular gap, into a complete heat dissipation duct with a defined direction and running the entire length. The air guide slot 71 is located on the air inlet side of the distribution surface flow channel 7, that is, the upstream end in the flight direction. The oncoming airflow during flight is captured by the air guide slot 71 and concentrated into the distribution surface flow channel 7. Under the annular constraint of the distribution surface flow channel 7, it flows orderly along the outer periphery of the radar body 3, and completes heat exchange in the heat dissipation flow channel slot 21 area where the lateral diffuser fins 31 are located. The heated airflow continues to flow downstream along the distribution surface flow channel 7 and finally is smoothly discharged from the air guide outlet slot 72 located on the outlet side. This arrangement of two slots, one inlet and one outlet, makes the entire air duct form a complete closed-loop airflow of inlet capture, annular gap distribution, fin heat exchange, and outlet discharge, with an orderly airflow direction. The opening of the air guide slot 71 increases the windward capture area and improves the air intake, while the opening of the air guide outlet slot 72 provides a smooth outlet channel for the heated airflow, preventing the airflow from accumulating and becoming congested downstream of the annular gap, which would cause the flow velocity to decrease. Together with the annular structure of the outer annular air guide ring 2, the convergent section of the heat dissipation channel slot 21, and the circumferential guidance of the distribution surface flow slot 7, they form a passive heat dissipation system that is controlled throughout the entire process from air intake to air exhaust. Without the need for a fan or increased power consumption, it achieves efficient thermal management of the radar body 3 by utilizing the airflow of flight. Furthermore, the low-resistance layout that runs through the front and rear allows the heat dissipation airflow to follow the flight direction without generating additional aerodynamic drag.

[0041] On the other hand, embodiments of the present invention provide a method for stabilizing and mounting a UAV-borne radar, applied to the aforementioned UAV-borne radar mounting and stabilizing device, comprising the following steps: Step 1: Adjust the installation angle of radar mounting component 1 so that the air intake and heat dissipation end of the outer annular air guide ring 2 faces the direction of the incoming flight flow; The installation angle of radar mounting component 1 directly determines whether the air intake direction is aligned with the air duct inlet. After the angle is adjusted to the correct position, the subsequent frame-type shell fixing component 5 and electric slide rail component 4 are all based on this angle. It is not necessary to perform overall attitude calibration after assembly, which reduces the difficulty of operation and ensures the effectiveness of the heat dissipation air duct throughout the entire flight phase.

[0042] Step 2: Insert the radar body 3 into the socket of the radar mounting part 1 to complete the positioning of the radar body 3 and the radar mounting part 1. Step 3: Place the frame-type shell fixing component 5 outside the radar body 3, and fold the frame-type shell fixing component 5 to form a locking frame that fits the outer periphery of the radar body 3, and lock it into the slide seat 41 of the electric slide rail component 4; so that the radar body 3 is subject to multi-directional limiting by the frame-type shell fixing component 5 in the UAV flight state, so as to suppress the radial sway and displacement of the radar body 3.

[0043] The floating capability of the slide block 41 on the slide rail 42 adaptively absorbs assembly tolerances, so that the snap-in action does not require forced alignment, the operation is smooth and there is no internal stress. The entire frame and the radar body 3 form a seamless whole structure, and the assembly of multi-directional locking is completed in a single retraction action, which simplifies the operation process of quick disassembly and assembly in the field.

[0044] The top crossbar 51 and two vertical bars 52 clamp the radar body 3 from the top and sides. The bottom crossbar 53 provides longitudinal constraint through the slide block 41. The telescopic rod 43 is inserted into the horizontal end hole to achieve geometric locking. The constraints at all points together form a complete multi-directional gapless rigid network. After the flight vibration is transmitted from the body 8 to the radar mounting part 1, it is attenuated and blocked in all directions by the constraint network. The measurement reference of the radar body 3 remains stable, and radial sway and displacement are effectively suppressed. At the same time, based on the air intake direction established in step one, the flight airflow continues to flow through the heat dissipation duct to passively dissipate heat from the radar body 3, realizing the parallel operation of stabilization and heat dissipation.

[0045] In another aspect, embodiments of the present invention provide a drone, including a body 8 and the aforementioned drone-borne radar mounting and stabilizing device, wherein the radar body 3 is inserted into the socket of the radar mounting component 1 of the stabilizing device, and the radar mounting component 1 is mounted on the top of the body 8.

[0046] Specifically, the radar mounting component 1 serves as the mounting base for the stabilizing device. One end is fixed to the top of the body 8 via bolts or a quick-release mechanism, while the other end has a socket for inserting the radar body 3. The inner wall contour of the socket matches the shape of the insertion section at the lower end of the radar body 3, typically featuring a circular or polygonal cross-section with a guide bevel, allowing the radar body 3 to automatically align itself during insertion, reducing assembly difficulty. An elastic retaining ring or radial locking screw can be further installed inside the socket. After the radar body 3 is inserted, the elastic retaining ring engages with a pre-set annular groove on the insertion section of the radar body 3, or the locking screw tightens it from the side, thus initially fixing the radar body 3 axially to the radar mounting component 1, preventing it from accidentally dislodging when the frame-type housing assembly 5 is not installed.

[0047] While the present invention has been disclosed above, its scope of protection is not limited thereto. Those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention, and all such changes and modifications will fall within the scope of protection of the present invention.

Claims

1. A device for mounting and stabilizing unmanned aerial vehicle (UAV) radar, characterized in that, include: Radar mounting component (1), which is mounted on the UAV, has a socket for insertion into the radar body (3); An outer annular air guide ring (2) is fixedly mounted on the radar mounting component (1) and surrounds the outer periphery of the radar body (3); Electric slide rail assembly (4), the electric slide rail assembly (4) is installed on the inner side of the outer annular air guide ring (2), the electric slide rail assembly (4) includes a slide rail (42) arranged circumferentially along the outer annular air guide ring (2) and a slide seat (41) slidably connected to the slide rail (42). A frame-type shell fixing assembly (5) is located inside the outer annular air guide ring (2) and is used to engage the radar body (3) from the outside of the radar body (3). In the case of the frame-type shell fixing component (5), when the frame is engaged, a locking frame is formed that is adapted to the outer periphery of the radar body (3) and is engaged with the slide (41) to realize the displacement limit of the radar body (3) in flight state.

2. The UAV-borne radar mounting and stabilizing device according to claim 1, characterized in that, The frame-type shell fixing component (5) includes: Top crossbar (51); Two vertical rods (52), the upper ends of which are respectively hinged to the two ends of the top horizontal rod (51); Two bottom crossbars (53), and the lower end of each of the vertical bars (52) is fixedly connected to one of the bottom crossbars (53); When the two bottom horizontal bars (53) are retracted relative to the two vertical bars (52), their ends are respectively engaged in the groove of the slide block (41) to complete the positioning.

3. The UAV-borne radar mounting and stabilizing device according to claim 2, characterized in that, The electric slide rail assembly (4) has a retractable telescopic rod (43) threaded through the slide rail (42), and the bottom crossbar (53) has a horizontal end hole at its end; after the bottom crossbar (53) is inserted into the groove of the slide block (41), the telescopic rod (43) extends out and inserts into the horizontal end hole, locking the bottom crossbar (53) to prevent the bottom crossbar (53) from coming out of the groove.

4. The UAV-borne radar mounting and stabilizing device according to claim 2, characterized in that, The top crossbar (51) is fixedly connected with an end face support lug (54). When the frame-type shell fixing assembly (5) is in the locked state, the top crossbar (51) is attached to the top of the radar body (3), and the two vertical bars (52) are clamped on the opposite sides of the radar body (3). The end face support lug (54) and the radar body (3) are connected by fasteners.

5. The UAV-borne radar mounting and stabilizing device according to claim 1, characterized in that, The radar body (3) is provided with lateral heat dissipation fins (31) on both sides, and the side wall of the outer annular air guide ring (2) is provided with heat dissipation channel grooves (21) through the lateral heat dissipation fins (31).

6. The UAV-borne radar mounting and stabilizing device according to claim 5, characterized in that, The heat dissipation channel groove (21) has a structure that is wider on the outside and narrower on the inside, with the outer opening size being larger than the inner opening size.

7. The UAV-borne radar mounting and stabilizing device according to claim 5, characterized in that, It also includes a water-blocking connecting plate (6), which is fitted on the outside of the radar body (3) and protrudes from the upper end face of the radar mounting part (1). The outer annular air guide ring (2) and the radar body (3) form a distribution surface flow groove (7). The water-blocking connecting plate (6) is located at the bottom of the distribution surface flow groove (7). The distribution surface flow groove (7) is used to guide the airflow to flow around the radar body (3) for heat dissipation.

8. The UAV-borne radar mounting and stabilizing device according to claim 7, characterized in that, The outer annular air guide ring (2) is provided with an air guide opening groove (71) and an air guide outlet groove (72); the air guide opening groove (71) is located on the air inlet side of the distribution surface flow groove (7), and the air guide outlet groove (72) is located on the air outlet side of the distribution surface flow groove (7) to cooperate with the lateral diffuser heat fin (21) to form a flight air guide heat dissipation channel.

9. A drone, characterized in that, The device includes a body (8) and an unmanned aerial vehicle (UAV) radar mounting and stabilizing device as described in any one of claims 1 to 8, wherein the radar body (3) is inserted into the socket of the radar mounting component (1) of the stabilizing device, and the radar mounting component (1) is mounted on the top of the body (8).

10. A method for stabilizing and mounting a UAV-borne radar, applied to the UAV-borne radar mounting and stabilizing device according to any one of claims 1 to 8, characterized in that, Includes the following steps: Adjust the installation angle of the radar mounting component (1) so that the air intake and heat dissipation end of the outer annular air guide ring (2) faces the direction of the incoming flight flow; Insert the radar body (3) into the socket of the radar mounting component (1) to complete the positioning of the radar body (3) and the radar mounting component (1); The frame-type shell fixing assembly (5) is placed outside the radar body (3), and the frame-type shell fixing assembly (5) is folded up to form a snap-fit ​​frame that fits the outer periphery of the radar body (3), and is snapped and fixed to the slide seat (41) of the electric slide rail assembly (4).

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