Integrated radar reconnaissance load device, radar equipment and unmanned aerial vehicle

Abstract

The invention discloses an integrated radar reconnaissance load device, radar equipment and an unmanned aerial vehicle. A closed cavity is formed by an upper shell, a lower shell, an antenna cover and a rear shell; the heat conduction pipes are connected with the side face, close to the antenna housing, of the rear shell, and one end of each heat conduction pipe faces the antenna housing. The first heat dissipation plate is connected with at least one of the heat conduction pipes and connected with the side face, close to the lower shell, of the upper shell. The first module is detachably connected with the first heat dissipation plate; the support body is detachably connected with the upper shell, and the bottom of the support body is suspended in the closed cavity. The second module is detachably connected with the bracket main body; the second heat dissipation plate is connected with the lower shell; the third module is detachably connected with the lower shell; according to the module unit, anti-collision protection can be carried out on all the modules, heat in the closed cavity is guided out from the upper shell through the multiple heat conduction pipes, and therefore the waterproof heat conduction effect on the module unit is further achieved.

Description

Technical Field

[0001] The present application relates to the field of integrated radar reconnaissance payload devices, and in particular to an integrated radar reconnaissance payload device, radar equipment and unmanned aerial vehicle. Background Art

[0002] Radar signal reconnaissance payload uses radar equipment to emit electromagnetic waves and receives the reflected echo of the target to detect, identify and locate the target. It plays an extremely important role in electronic information systems. Radar payloads are often widely used in vehicles, ships, airborne and other fields to conduct reconnaissance of targets in different scenarios.

[0003] With the continuous development of science and technology, radar reconnaissance payloads are gradually developing towards system networking and automation. The radar reconnaissance payload structure will be further optimized in the direction of serialization, miniaturization and integration of multiple configurations, and will continue to play an irreplaceable role in the reconnaissance field, providing technical support for national security and strategic decision-making.

[0004] The radar reconnaissance payload is carried on the UAV, and its working environment is harsh. If the radar's heat dissipation performance is not good, the electronic equipment will inevitably be affected under long-term working conditions. Summary of the invention

[0005] The main purpose of this application is to provide an integrated radar reconnaissance payload device, radar equipment and unmanned aerial vehicle, aiming to reduce the difficulty of installing the module unit and improve the waterproof and thermal conductivity of the module unit.

[0006] To achieve the above-mentioned purpose, the present application provides an integrated radar reconnaissance payload device, including: a rear shell, one side of which is detachably connected to an upper shell, a lower shell and a radome, respectively, the upper shell and the lower shell are detachably connected to the radome, and the upper shell, the lower shell and the radome form a closed cavity with the rear shell; a plurality of heat pipes, connected to the side of the rear shell close to the radome, and one end of each of the plurality of heat pipes faces the radome; a first heat sink, connected to at least one of the plurality of heat sinks, and the first heat sink is connected to the side of the upper shell close to the lower shell; a first module, detachably connected to the first heat sink; a bracket body, detachably connected to the upper shell, and the bottom is suspended in the closed cavity; a second module, detachably connected to the rear shell; a second heat sink, connected to the lower shell; a third module, detachably connected to the lower shell; and a fourth module, detachably connected to the side of the rear shell away from the radome.

[0007] Optionally, the bracket body is a trapezoidal block, and the side of the bracket body is connected to a second connecting plate through a first connecting plate and a bracket column in sequence, and the second connecting plate is connected to the upper shell: the side of the bracket body close to the rear shell is connected to the second module through a third heat sink; the side of the bracket body away from the second module is equipped with at least one antenna unit through a first antenna mounting bracket; the two sides of the bracket body adjacent to and opposite to the first antenna mounting bracket and the second module are provided with a second antenna mounting bracket, and the two second antenna mounting brackets are each equipped with at least one antenna unit.

[0008] Optionally, transition gaps between the upper shell, the lower shell and the antenna cover are sealed by sealing strips.

[0009] Optionally, a connector adapter plate is provided on a side of the rear shell away from the antenna cover, and the connector adapter plate is connected to the connector.

[0010] Optionally, the third module is detachably connected to the lower shell via a third heat sink, the fourth module is connected to the rear shell via a fourth heat sink, and the first heat sink, the second heat sink, the third heat sink and the fourth heat sink are all copper heat sinks.

[0011] Optionally, the adjacent upper shell, the lower shell, the rear shell and the antenna cover are connected via the sealing plate.

[0012] Optionally, there are four heat pipes, two of which are L-shaped and have one end each welded to the side of the rear shell in parallel, and the other end is welded to the first heat sink; the other two heat pipes are serpentine-shaped and have one end each welded to the side of the rear shell, and the other end is suspended and facing the antenna cover.

[0013] Optionally, the upper shell, the lower shell, and the antenna cover are all arc-shaped surfaces.

[0014] In addition, to achieve the above-mentioned purpose, the present application also provides a radar device, which is equipped with the integrated radar reconnaissance payload device provided by the above-mentioned embodiments.

[0015] In addition, to achieve the above-mentioned purpose, the present application also provides a drone equipped with the radar device provided in the above-mentioned embodiment.

[0016] The embodiment of the present application proposes an integrated radar reconnaissance payload device, radar equipment and unmanned aerial vehicle, which are detachably connected to the upper shell, the lower shell and the radome through a side of the rear shell, the upper shell and the lower shell are detachably connected to the radome, and the upper shell, the lower shell and the radome form a closed cavity with the rear shell; a plurality of heat pipes are connected to the side of the rear shell close to the radome, and one end of each of the plurality of heat pipes is facing the radome; the first heat sink is connected to at least one of the plurality of heat pipes, and the first heat sink is connected to the side of the upper shell close to the lower shell; the first module is detachably connected to the first heat sink; the bracket body is detachably connected to the upper shell, and the bottom is suspended in the closed cavity; the second module is detachably connected to the bracket body; the second heat sink is connected to the lower shell; the third module is detachably connected to the lower shell; the fourth module is detachably connected to the side of the rear shell away from the radome, and the upper shell, the lower shell and the radome are used to form a closed cavity with the rear shell, so that each module inside can be protected, and the heat inside the closed cavity is extracted from the upper shell by using a plurality of heat pipes, thereby achieving a waterproof and heat-conducting effect on the module unit. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 A schematic diagram of the enclosed payload assembly structure provided for an embodiment of the integrated radar reconnaissance payload device of the present application;

[0018] Figure 2 A schematic diagram of the enclosed payload assembly and disassembly structure provided for an embodiment of the integrated radar reconnaissance payload device of the present application;

[0019] Figure 3 A schematic diagram of the disassembled structure of the housing assembly provided for an embodiment of the integrated radar reconnaissance payload device of the present application;

[0020] Figure 4 A schematic diagram of the disassembled structure of the antenna bracket provided for an embodiment of the integrated radar reconnaissance payload device of the present application;

[0021] Figure 5 A schematic diagram of the disassembled structure of the heat transfer system provided for an embodiment of the integrated radar reconnaissance payload device of the present application.

[0022] Explanation of the accompanying drawings: 1. Shell assembly; 11. Upper shell; 12. Lower shell; 13. Rear shell; 2. Antenna bracket; 21. Second connecting plate; 22. Bracket column; 23. First connecting plate; 24. Bracket body; 25. First antenna mounting bracket; 26. Second antenna mounting bracket; 3. Connector adapter plate; 31. Connector; 41. First module; 42. Second module; 43. Third module; 44. Fourth module; 51. Heat pipe; 52. First heat sink; 6. Antenna cover; 7. Antenna unit; 81. Sealing strip; 82. Sealing plate.

[0023] The realization of the purpose, functional features and advantages of this application will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0024] It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application.

[0025] Reference Figure 1 The integrated radar reconnaissance payload device provided in the first embodiment of the present application may include a rear shell 13, a plurality of heat pipes 51, a first heat sink 52, a first module 41, a bracket body 24, a second module 42, a second heat sink, a third module 43 and a fourth module 44, wherein a side of the rear shell 13 is detachably connected to the upper shell 11, the lower shell 12 and the antenna cover 6, respectively, the upper shell 11 and the lower shell 12 are detachably connected to the antenna cover 6, and the upper shell 11, the lower shell 12 and the antenna cover 6 form a closed cavity with the rear shell 13; a plurality of heat pipes 51 are connected to the rear shell 13 is close to the side of the antenna cover 6, and one end of each of the multiple heat pipes 51 is facing the antenna cover 6; the first heat sink 52 is connected to at least one of the multiple heat pipes 51, and the first heat sink 52 is connected to the side of the upper shell 11 close to the lower shell 12; the first module 41 is detachably connected to the first heat sink 52; the bracket body 24 is detachably connected to the upper shell 11, and the bottom is suspended in the closed cavity; the second module 42 is detachably connected to the rear shell 13; the second heat sink is connected to the lower shell 12; the third module 43 is detachably connected to the lower shell 12; the fourth module 44 is detachably connected to the side of the rear shell 13 away from the antenna cover 6.

[0026] Specifically, the load structure is composed of three parts: the upper part, the middle part, and the lower part. The load is divided into two closed areas, the front and the rear part, through the middle structure with embedded heat pipes. The upper shell is the main air-cooled heat dissipation surface, which bears most of the heat from the module unit introduced by the heat pipe. It should be noted that the first module 41, the second module 42, the third module 43 and the fourth module 44 are all high-energy modules, which will generate a lot of heat when working, so it is necessary to export this heat. A plurality of heat pipes 51 are connected to the side of the rear shell 13 close to the antenna cover 6, and one end of each of the plurality of heat pipes 51 is welded to the upper shell 11, which can realize the internal heat export and the external low temperature is conducted to the closed space, so that the first module 41, the second module 42, the third module 43 can be cooled, and the fourth module 44 is attached to the back of the rear shell 13, and can also dissipate heat through a plurality of heat pipes 51. In this way, the modules arranged inside it can be protected from wind and rain erosion, and the temperature inside the closed cavity can be reduced, so that the radar reconnaissance load can be well protected and the life of the radar reconnaissance load can be extended.

[0027] It is worth noting that the present application can be installed in different positions of different housings by M4 screws according to the size and power consumption of the module unit. In other words, the position of the module unit can be arranged according to the specific wiring method, module size, power consumption and system heat dissipation form. The present application does not impose too many restrictions here.

[0028] It is also worth noting that the connection in the present application can be a fixed connection or a detachable connection, wherein the fixed connection can be welding, one-piece molding, etc., which is not limited here.

[0029] In an embodiment of the present application, the bracket body 24 is a trapezoidal block, and the side of the bracket body 24 is connected to a second connecting plate 21 through a first connecting plate 23 and a bracket column 22 in sequence, and the second connecting plate 21 is connected to the upper shell 11: the side of the bracket body 24 close to the rear shell 13 is connected to the second module 42 through a third heat sink; the side of the bracket body 24 away from the second module 42 is installed with at least one antenna unit 7 through a first antenna mounting bracket 25; the two sides of the bracket body 24 adjacent to and opposite to the first antenna mounting bracket 25 and the second module 42 are provided with a second antenna mounting bracket 26, and the two second antenna mounting brackets 26 are each installed with at least one antenna unit 7.

[0030] refer to Figure 2 Specifically, the first antenna mounting bracket 25 is a round plate, and the second antenna mounting bracket 26 is a square plate. The bracket body 24, the second connecting plate 21, the bracket column 22, the first connecting plate 23, the first antenna mounting bracket 25, and the second antenna mounting bracket 26 are connected by screws to form an antenna bracket 2. The antenna bracket 2 has 8 antenna unit 7 mounting slots and a counterweight structure installation position. The antenna unit 7 is fixed in the embedded groove on the first antenna mounting bracket 25 and the second antenna mounting bracket 26 through an SMA connector or an SMP connector, so that the antenna unit 7 can be quickly plugged in and out. The first connecting plate 23, the bracket column 22, and the second connecting plate 21 are all made of Q690ME steel material to maximize the structural rigidity and ensure that the structural parts are not easily deformed when subjected to vertical impact vibration, so as to avoid structural deformation and displacement leading to damage to the third module 43 below. The antenna unit and each circuit module inside the load adopt a miniaturized design, and the plug-in connection method is easy to disassemble and assemble.

[0031] In addition, the antenna bracket 2 is fixed to the upper shell 11. In addition to installing the antenna unit 7 and the counterweight, a wiring area can also be built in, which shortens the wiring length between the antenna unit and other modules and solves the problem of reduced antenna unit performance due to long wiring.

[0032] refer to Figure 3In an embodiment of the present application, the transition gap between the upper shell 11, the lower shell 12, and the antenna cover 6 is sealed by a sealing strip 81, and the transition gap between the upper shell 11, the lower shell 12 or the antenna cover 6 and the rear shell 13 is sealed by a sealing plate 82.

[0033] Among them, the shell assembly 1 is composed of an upper shell 11, a lower shell 12, and a rear shell 13 that are connected into one by screws. A special groove for a sealing strip 81 is provided on the outer edge of each shell contact surface to prevent external rain erosion, greatly reducing the economic and time costs brought by machining. At the same time, the screw connection method is also convenient for operation and installation.

[0034] For example, the present application can cut out a sealing plate 82 of a corresponding shape according to the shape of the contact surface between the radome 6 and the shell assembly 1, ensuring that the sealing plate 82 perfectly fits the contact surface. The radome 6 can be connected to the shell assembly 1 by M1.8 screws, and the sealing plate 82 is compacted to ensure the sealing of the load device.

[0035] It should be noted that the model and thickness of the sealing plate 82 need to be selected according to actual conditions. This application selects silicone rubber plate 04-22-1319-GXJ / AC as the sealing plate 82.

[0036] Continue to refer Figure 1 In an embodiment of the present application, a connector adapter plate 3 is provided on a side of the rear shell 13 away from the antenna cover 6, and the connector adapter plate 3 is connected to the connector 31.

[0037] Among them, after the connector 31 is fixed to the connector adapter plate 3, the connector adapter plate 3 is fixed to the housing assembly 1 by M2 screws. It is worth noting that the front area of ​​the load device includes multiple antenna units 7, each high power consumption module unit, a sealing plate 82, an antenna bracket 2 and a radome 6. The radome 6 presses the upper, middle and lower housings to form a front closed area, and the connector adapter plate 3 is covered on the rear surface of the rear housing 13 by screws to form a rear closed area, and the fourth module 44 is located in the rear closed area.

[0038] Continue to refer Figure 1 In the embodiment of the present application, the third module 43 is detachably connected to the lower housing 12 through the third heat sink, the fourth module 44 is connected to the rear housing 13 through the fourth heat sink, and the first heat sink 52, the second heat sink, the third heat sink and the fourth heat sink are all copper heat sinks. The copper heat sink has strong thermal conductivity and can quickly perform heat exchange.

[0039] Specifically, the edges of the upper shell 11 , the lower shell 12 , the antenna cover 6 and the rear shell 13 are all provided with grooves, and the grooves between adjacent upper shells 11 , lower shells 12 , rear shells 13 and antenna covers 6 are connected by sealing strips 81 .

[0040] refer to Figure 4 In the embodiment of the present application, there are four heat pipes 51, two of which are L-shaped and one end of each is welded in parallel to the side of the rear shell 13, and the other end is welded to the first heat sink 52. The other two heat pipes 51 are serpentine, and one end of each of the two heat pipes 51 is welded to the side of the rear shell 13, and the other end is suspended and faces the antenna cover 6.

[0041] Among them, multiple heat pipes 51 are designed as special shapes for the module structure, which can conduct the heat inside the closed structure to the upper shell. Specifically, after the first heat sink 52 is welded to the shell assembly 1, the first heat sink 52 and the upper end surface of the heat pipe 51 are welded into one. The first module 41 is attached to the surface of the first heat sink 52 by M3 screws to evenly disperse the heat and increase the contact area. The heat pipe 51 conducts the internal heat of the closed load structure to the outer surface of the shell, and realizes the heat dissipation function in the closed space through air cooling.

[0042] refer to Figure 5 In the embodiment of the present application, the upper shell 11, the lower shell 12, and the antenna cover 6 are all arc-shaped surfaces. The arc-shaped surface can reduce the air resistance of the drone during flight, and can also increase the heat dissipation surface. The load device adopts a split design, which divides the difficult-to-process arc into three parts, which is easy to install and process, and reduces machining time and manufacturing costs.

[0043] Based on the above embodiments, the present application also provides a radar device equipped with the integrated radar reconnaissance payload device provided in the above embodiments.

[0044] Based on the above embodiments, the present application also provides a drone equipped with the radar device provided in the above embodiments.

[0045] The above are only preferred embodiments of the present application, and are not intended to limit the patent scope of the present application. Any equivalent structure or equivalent process transformation made using the contents of the present application specification and drawings, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of the present application.

Claims

1. An integrated radar reconnaissance payload device, characterized in that: include: A rear shell (13), one side of which is detachably connected to the upper shell (11), the lower shell (12) and the antenna cover (6), the upper shell (11) and the lower shell (12) are both detachably connected to the antenna cover (6), and the upper shell (11), the lower shell (12) and the antenna cover (6) form a closed cavity with the rear shell (13); A plurality of heat-conducting pipes (51), each having one end connected to a side surface of the rear housing (13) close to the antenna cover (6), and each having the other end facing the antenna cover (6); A first heat dissipation plate (52) connected to at least one of the plurality of heat-conducting pipes (51), and the first heat dissipation plate (52) is arranged on a side surface of the upper shell (11) close to the lower shell (12); A first module (41) detachably connected to the first heat dissipation plate (52); A bracket body (24) is detachably connected to the upper shell (11), and the bottom is suspended in the closed cavity; A second module (42) detachably connected to the rear housing (13); A second heat dissipation plate connected to the lower housing (12); A third module (43) detachably connected to the lower housing (12); The fourth module (44) is detachably connected to the side of the rear housing (13) away from the antenna cover (6).

2. The integrated radar reconnaissance payload device according to claim 1, characterized in that: The support body (24) is a trapezoidal block, and the side surface of the support body (24) is connected to the second connecting plate (21) through the connected first connecting plate (23) and the support column (22), and the second connecting plate (21) is connected to the upper shell (11): The side surface of the bracket body (24) close to the rear housing (13) is connected to the second module (42) via a third heat sink; At least one antenna unit (7) is installed on the side of the bracket body (24) away from the second module (42) via a first antenna installation bracket (25); A second antenna mounting bracket (26) is provided on two side surfaces of the bracket body (24) adjacent to and opposite to the first antenna mounting bracket (25) and the second module (42), and the two second antenna mounting brackets (26) are each installed with at least one antenna unit (7).

3. The integrated radar reconnaissance payload device according to claim 1, characterized in that: The transition gaps between the upper shell (11), the lower shell (12) and the antenna cover (6) are all sealed by sealing strips (81).

4. The integrated radar reconnaissance payload device according to claim 1, characterized in that: A connector adapter plate (3) is provided on a side of the rear shell (13) away from the antenna cover (6), and the connector adapter plate (3) is connected to the connector (31).

5. The integrated radar reconnaissance payload device according to claim 1, characterized in that: The third module (43) is detachably connected to the lower housing (12) via a third heat sink, the fourth module (44) is connected to the rear housing (13) via a fourth heat sink, and the first heat sink (52), the second heat sink, the third heat sink and the fourth heat sink are all copper heat sinks.

6. The integrated radar reconnaissance payload device according to claim 3, characterized in that: The adjacent upper shell (11), the lower shell (12), the rear shell (13) and the antenna cover (6) are connected via the sealing plate (82).

7. The integrated radar reconnaissance payload device according to claim 1, characterized in that: The plurality of heat-conducting tubes (51) are four in number, two of the heat-conducting tubes (51) are L-shaped and one end of each is welded in parallel to the side of the rear shell (13), and the other end of each is welded to the first heat sink (52); the other two heat-conducting tubes (51) are serpentine-shaped and one end of each is welded to the side of the rear shell (13), and the other end of each is welded to the upper shell (11).

8. The integrated radar reconnaissance payload device according to claim 1, characterized in that: The upper shell (11), the lower shell (12) and the antenna cover (6) are all arc-shaped surfaces.

9. A radar device, characterized in that: An integrated radar reconnaissance payload device as described in any one of claims 1-8 is installed.

10. A drone, characterized in that: The radar device according to claim 9 is installed.

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