A heat dissipation structure of radar carried by unmanned aerial vehicle

Abstract

The present invention relates to a heat dissipation structure of an unmanned aerial vehicle radar, and belongs to the technical field of thermal control of airborne electronic equipment. An independently closed fin-type heat dissipation structure is used for a T / R component with a relatively high heat flux density and relatively concentrated heat, and the heat of the heat source device on the wave control board is evenly heated through a temperature equalizing plate and the heat is introduced into the front cabin air duct. The two structures form an independent heat dissipation space with the front cabin of the radar chassis for independent heat dissipation; the heat dissipation surface of the frequency integrated module with heat dissipation teeth at the integrated RF front end is placed in the rear cabin of the chassis to complete the module heat dissipation. Combined with the structural space characteristics of the radar whole machine, compartment heat dissipation is adopted, and each unit is subjected to a purposeful, targeted and thermal design work adapted to its own structural characteristics. Through the separate thermal design of the front and rear cabins, the thermal isolation of the heat dissipation system is realized, which greatly improves the working performance and working life of each thermal component, and minimizes the weight of the radar whole machine and the complexity of the structural layout.

Description

Technical Field

[0001] The present invention belongs to the technical field of thermal control of airborne electronic equipment, and adopts a combination of compartment heat dissipation, heat pipe heat conduction, fin heat dissipation and forced air cooling to dissipate the relevant equipment of an unmanned aerial vehicle radar complete machine, so as to meet the requirements of its continuous normal operation. Background Art

[0002] In modern warfare, in order to improve the safety of manned helicopters in battlefield environments and expand the combat range of manned helicopters, the "method of manned / unmanned collaborative combat" has been constantly mentioned. Its main means is to control unmanned aircraft to carry out special tasks such as reconnaissance, detection, target indication, and even firepower precision strikes through manned aircraft. At the same time, with the rapid development of modern weapon system technology, as one of the important development objects of future wars, the rapid replacement of unmanned aircraft will also require the airborne reconnaissance radar equipment installed on it to have the characteristics of miniaturization, integration, serialization, multi-function and generalization. Among them, miniaturization and high integration are its most prominent characteristics, which are the technical basis for achieving serialization, multi-function and generalization.

[0003] According to the system functions, the UAV radar is mainly divided into integrated RF front end, data acquisition and signal processing module and power supply and distribution module. Among them, the integrated RF front end is the front-end component of the airborne radar. It completes the transmission and reception functions of various antenna waveforms according to the instructions of the main station, and transmits the signal to the data acquisition and signal processing. It is the core unit of the radar; the power supply and distribution module completes the power supply and distribution of the radar.

[0004] The integrated RF front end is mainly composed of six parts: antenna cover, flat antenna unit, T / R component, power division network module, wave control board and frequency synthesis module. Among them, the T / R component, wave control board and frequency synthesis module are the main heat-generating components in the integrated RF front end; the data acquisition and signal processing module is composed of data sampling board and signal processing board; the power supply and distribution module is mainly composed of power supply and distribution board; the heat dissipation of the above components will directly affect the performance of the radar as a whole.

[0005] At present, the heat dissipation of heat-generating components is mainly carried out by forced air cooling, liquid cooling and evaporative cooling. The heat dissipation capacity of forced air cooling is limited, and the liquid cooling and evaporative cooling equipment is complex, large in size, heavy in weight, and prone to leakage, and is not suitable for UAV-mounted radars. Summary of the invention

[0006] Technical issues to be solved

[0007] In order to solve the heat dissipation problem of the heat source devices of each component unit in the integrated unmanned aerial vehicle radar, the present invention proposes a heat dissipation structure of the unmanned aerial vehicle radar. According to the different functional components of the radar, a targeted heat dissipation solution combining "compartment heat dissipation, high-efficiency heat pipes, special fins and forced air cooling" is proposed to dissipate the heat of the main heat-generating components of the airborne radar.

[0008] Technical Solution

[0009] A heat dissipation structure for an unmanned aerial vehicle radar, the unmanned aerial vehicle radar comprising an integrated comprehensive radio frequency front end, a data acquisition and signal processing module and a power supply and distribution and servo control module; characterized in that: a radar chassis is divided into a front cabin and a rear cabin, a middle partition is provided between the two cabins, the integrated comprehensive radio frequency front end is located in the front cabin, a heat dissipation fan unit is provided on the left and right inner sides of the front cabin of the chassis, the integrated comprehensive radio frequency front end is located between the left and right heat dissipation fan units, and the heat on the integrated comprehensive radio frequency front end is taken out of the front cabin of the chassis through the air inlet at the bottom of the chassis and the heat dissipation fan unit; the data acquisition and signal processing module and the power supply and distribution and servo control module are located in the rear cabin, the data acquisition and signal processing module comprises a data sampling board and a signal processing board arranged on the left and right, and one side of the data sampling board is in turn A data sampling cold plate and a first fin, a signal processing cold plate and a second fin are arranged on one side of the signal processing board in sequence. The above modules adopt an integrated design, and a first fan is arranged under the data acquisition and signal processing module; the power supply and servo control module comprises a power supply and distribution module and a servo control module arranged up and down, a heat dissipation tooth is arranged between the power supply and distribution module and the servo control module, and a second fan is arranged on the side of the power supply and distribution module close to the data acquisition and signal processing module. The rear cabin air duct comprises two: the first air duct is from a side wall of the rear cabin where the power supply and distribution and servo control module is installed, through the power supply and distribution and servo control module, the second fan, and the data acquisition and signal processing module, and then discharged from the other side of the chassis; the other air duct enters from the bottom of the chassis, passes through the data acquisition and signal processing module, and then is discharged from the other side of the chassis.

[0010] The technical solution of the present invention further states that: the rear end of the integrated radio frequency front end is provided with local heat dissipation teeth.

[0011] The technical solution of the present invention further states that: a thermal conductive pad is provided under the heat source device on the data sampling board and the signal processing board.

[0012] The technical solution of the present invention further states that a high-efficiency heat pipe is welded on the data sampling cold plate.

[0013] Beneficial Effects

[0014] The present invention combines the structural spatial characteristics of the radar unit, performs purposeful and targeted thermal design work on each component unit that adapts to its own structural characteristics, and separates the thermal design of different functional modules by dividing the radar into front and rear cabins, thereby achieving thermal isolation of the heat dissipation system and greatly improving the working performance and service life of each thermal component. The layout form of compartment heat dissipation allows the chassis and each device to form their own air duct during structural design, thereby minimizing the weight of the radar unit and the complexity of the structural layout.

[0015] The present invention is a "combined thermal control" heat dissipation technology solution based on the combination of "compartment heat dissipation, high-efficiency heat pipes, special fins and forced air cooling". It has the advantages of high heat dissipation efficiency, good reliability, light weight, uniform temperature, etc. It can quickly dissipate the heat of T / R components and data acquisition and signal processing modules with high heat flux density in electronic equipment, while taking into account the heat dissipation requirements of modules with low heat flux density such as power division network modules, wave control boards, frequency synthesis modules, and power supply and distribution and servo control modules, reducing the size of the radar unit while facilitating cable wiring between components and improving the reliability of signal transmission.

[0016] In combination with the structural and spatial characteristics of the radar, compartment heat dissipation is adopted, and thermal design work is carried out on each unit in a purposeful and targeted manner that adapts to its own structural characteristics. Through separate thermal design of the front and rear compartments, thermal isolation of the heat dissipation system is achieved, which greatly improves the working performance and service life of each thermal component and minimizes the weight of the radar and the complexity of the structural layout.

[0017] The integrated data acquisition and data processing module with independent heat dissipation capability is packaged as a whole, and is arranged in the rear cabin of the radar chassis to form an independent heat dissipation space for independent heat dissipation. The heat dissipation design scheme is implemented by adopting a structural composition of high-efficiency heat pipes, special fins and independent fan groups. It has the function of independent full-load debugging after being separated from the radar machine.

[0018] Compared with the prior art, the present invention adopts a "combined thermal control" heat dissipation solution combining "compartment heat dissipation, high-efficiency heat pipes, special fins and forced air cooling", which has the following characteristics:

[0019] 1) This method effectively reduces the size and weight of the whole machine;

[0020] 2) The heat dissipation method of separate heat dissipation in the front and rear compartments has the characteristics of high heat dissipation efficiency and high reliability;

[0021] 3) Compared with the existing common heat dissipation methods, each component heat dissipation structure is relatively independent, has strong environmental adaptability, can be independently debugged, and each component module is small in size and light in weight. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1Schematic diagram of the radar system of the present invention

[0023] Figure 2 (a) and Figure 2 (b) are schematic diagrams of the compartments of the radar chassis of the present invention.

[0024] Figure 3 Schematic diagram of the layout of the front and rear compartments of the radar chassis of the present invention

[0025] Figure 4 Schematic diagram of the air duct flow direction in the front cabin of the radar chassis of the present invention

[0026] Figure 5 Schematic diagram of the air duct flow direction in the rear cabin of the radar chassis of the present invention

[0027] Figure 6 Schematic diagram of the integrated radio frequency front end structure of the present invention

[0028] Figure 7 Schematic diagram of the structure of the integrated data acquisition and data processing module of the present invention

[0029] Figure 8 Schematic diagram of the structure of the dedicated heat sink for the integrated data acquisition and data processing module of the present invention

[0030] Fig. 9 Schematic diagram of the power supply and distribution and servo module structure of the present invention

[0031] Fig.10 Schematic diagram of the structure of the front cabin fan unit of the present invention DETAILED DESCRIPTION

[0032] The present invention will now be further described with reference to the embodiments and the accompanying drawings:

[0033] The present invention combines the structural features of an integrated comprehensive RF front end: an independently closed fin-type heat dissipation structure is adopted for the T / R components with higher heat flux density and relatively concentrated heat; the heat of the heat source devices on the wave control board is evenly heated through a temperature equalizing plate and the heat is introduced into the front cabin air duct. The two structures form an independent heat dissipation space with the front cabin of the radar chassis for independent heat dissipation; the heat dissipation surface of the frequency integration module with heat dissipation teeth of the integrated RF front end is placed in the rear cabin of the chassis to complete the module heat dissipation.

[0034] According to the requirements of the radar machine structure layout, the data acquisition board and signal processing board with high heat flux density are integrally packaged into an integrated data acquisition and data processing module with independent heat dissipation capability, and are arranged in the rear cabin of the radar chassis to form an independent heat dissipation space for independent heat dissipation. The board structure adopts back-to-back fast interconnection. Due to space limitations, in order to meet the heat dissipation requirements, the heat source surface of the board is respectively bonded to a special heat dissipation cold plate designed with high-efficiency heat pipes and special fins, and the heat of the device is transferred to the cold plate. Finally, the heat is taken away by the fan installed at the bottom of the module shell, thereby realizing the heat dissipation of the integrated data acquisition and data processing module. At the same time, the integrated data acquisition and signal processing module will also have the function of independent full-load debugging after being separated from the radar machine. The power supply and distribution module with independent heat dissipation capability is installed in the rear cabin of the radar chassis for independent heat dissipation, and its heat will be discharged from the chassis through the rear cabin air duct.

[0035] With reference to the attached drawings, the specific implementation of the "combined thermal control" heat dissipation structure combining "compartment heat dissipation, high-efficiency heat pipes, special fins and forced air cooling" of the present invention is described in detail. The present invention is applied on a certain unmanned helicopter platform, and is installed in the narrow nose cabin through 6 M5 hole bolts. The cabin of the unmanned aircraft is provided with ventilation and heat dissipation outlets / inlets.

[0036] See also Figure 1 , Figure 2 and Figure 3 The "combined thermal control" heat dissipation structure of the present invention divides the radar chassis 1 into the front cabin 23 (shaded part) in FIG. 2 and the rear cabin 24 (non-shaded part) in FIG. 2, and independently dissipates the heat of the corresponding electronic equipment of the radar. The "compartmental compartment" of the "compartmental compartment heat dissipation" is to divide the internal space of the radar chassis 1 into the front cabin 23 and the rear cabin 24 by the structure of the middle partition 25 and the frequency synthesizer 6 spanning the two cabins. The front cabin 23 and the rear cabin 24 form their own ventilation and heat dissipation ducts through the structural layout, and then form the front cabin 23 and the rear cabin 24 forced air cooling heat dissipation system to complete the heat dissipation of the electronic equipment in each cabin.

[0037] See also Figure 4 The front cabin 23 heat dissipation system includes the front cabin 23 of the chassis and its front cabin air duct 42, the integrated integrated RF front end 2 and the front cabin 23 heat dissipation fan unit 3. The heat dissipation system is designed to discharge the heat generated by the remaining devices in the integrated integrated RF front end 2 except the frequency synthesis module 6 out of the chassis 1, and complete the heat dissipation of the electronic equipment in the front cabin. The heat dissipation fan unit 3 is located on the left and right inner sides of the chassis 1, and the integrated integrated RF front end 2 is located between the left and right heat dissipation fan units 3. Through the air inlet 30 at the bottom, the heat on the T / R components 9, the power division network module 10 and the wave control board 11 with higher heat density is drawn out through the front cabin heat dissipation fan unit 3 to bring out the heat from the front cabin 23 of the chassis 1.

[0038] See also Figure 5 , Figure 7 The rear cabin heat dissipation system mainly includes the rear cabin 24 of the chassis 1 and its rear cabin air duct 43, the data acquisition and signal processing module 4 and the power supply and servo control module 5. The heat dissipation system is designed to discharge the heat generated by the frequency synthesis module 6, the data acquisition and signal processing module 4 with high-efficiency heat dissipation and the power supply and servo control module 5 out of the chassis 1, and complete the heat dissipation of each electronic device in the rear cabin 24.

[0039] See also Figure 3 , Figure 4 and Figure 6 The integrated RF front end 2 is a stacked high-integration design, consisting of six parts: antenna cover 7, flat antenna unit 8, T / R component 9, power division network module 10, wave control board 11 and frequency synthesis module 6. Each component is hierarchically interconnected by screws. The four T / R components 9 are installed on the rear side of the flat antenna unit by screws 28, the power division network module 10 and the wave control board 11 are installed on the rear side of the T / R component 9 by screws 29, and the frequency synthesis module 6 is fixed to the rear side of the TR component 9 and the power division network module 10 by screws 26. Through reasonable layout, the front cabin air duct 30 and the air outlet 31 of the front cabin of the chassis 1 are formed into a complete front cabin air duct, and the heat on the T / R component 9, the power division network module 10 and the wave control board 11 with high heat density is taken out of the front cabin 23 of the chassis 1 by the front cabin heat dissipation fan unit 3.

[0040] See also Figure 5 , Figure 7 and Figure 8 The data acquisition and signal processing module 4 adopts an integrated design, and is composed of a data sampling board 12, a signal processing board 13, a data sampling board cold plate 14, a signal processing board cold plate 27, a fan 15 and a housing 16. The data sampling board 12 and the signal processing board 13 are installed on the housing 16 by screws 32, and are electrically interconnected by blind plug connectors 33; the data sampling board cold plate 14 and the signal processing board cold plate 27 of the data acquisition board 12 and the signal processing board 13 are respectively installed on the housing 16 by screws 34, and a thermal conductive pad 35 is added between the board heat source device and the data sampling board cold plate 14 and the signal processing board cold plate 27, so as to finally achieve a close fit between the device and the cold plate 14, thereby achieving heat dissipation of the data sampling board 12 and the signal processing board 13; two fans 15 are installed on the bottom of the housing 16 by screws 36, and form a heat dissipation system of the data acquisition and signal processing module 4 with the outer fins 17 and the outer fins 39 of the data sampling board cold plate 14 and the signal processing board cold plate 27; the cold plate 14 is welded with a high-efficiency heat pipe 18, and a special fin 17 is used to improve the heat dissipation capacity. In order to enhance the heat dissipation capability of the data acquisition and signal processing module 4 , the air inlet 37 of the rear cabin 24 is arranged at a position corresponding to the fan 15 below the data acquisition and signal processing module 4 .

[0041] See also Figure 6 Since the heat flux density of the frequency synthesis module 6 is relatively small, local heat dissipation teeth 19 are designed on the corresponding surface of the rear cabin 24 where the frequency synthesis module 6 is located to improve the heat dissipation effect.

[0042] See also Figure 5 , Fig. 9 The power supply and distribution and servo control module 5 is installed in the rear compartment 24 of the chassis 1, and is composed of a power supply and distribution module 20 and a servo control module 21. The heat flux density of the devices on the two modules is relatively small, and only ventilation and heat exchange are required. The heat is conducted to the heat dissipation teeth 22 between the modules through the aluminum alloy shell, and finally discharged into the rear compartment 24 of the chassis 1 by the fan 40 installed on the side wall of the power supply and distribution and servo control module 5, and discharged to the outside of the chassis 1 through the air outlet 38 of the rear compartment 24 to complete the heat dissipation.

[0043] See Figure 2. Figure 4 The front cabin 23 of the chassis 1 , the integrated RF front end 2 , the air inlet 30 , and the air outlet 31 constitute a front cabin air duct 42 of the front cabin 23 of the chassis 1 .

[0044] See Figure 2. Figure 5 The rear cabin 24 of the chassis 1 , the air inlet 37 , the air inlet 41 , and the air outlet 38 form a rear cabin air duct 43 of the rear cabin 24 of the chassis 1 .

[0045] Through this "combined thermal control" heat dissipation structure that combines "compartment heat dissipation, high-efficiency heat pipes, special fins and forced air cooling", the heat of the T / R components 9 and the data acquisition and signal processing module 4 with higher heat flux density can be quickly dissipated, while taking into account the heat dissipation needs of modules with lower heat flux density such as the power division network module 10, the wave control board 11, the frequency integration module 6 and the power supply and servo control module 5, so that the radar machine can meet the normal operating temperature requirements, saving the layout space of the whole machine and making it more convenient for the reliability of cable wiring and signal transmission between the components.

[0046] A certain unmanned aerial vehicle radar designed according to the unmanned aerial vehicle radar heat dissipation structure of the present invention has been successfully applied to a certain helicopter-borne radar product. The application shows that the thermal control technology of the present invention and its implementation method are reasonable, feasible and applicable, and can ensure the normal operation of the radar. In addition, the heat dissipation method has the advantages of high heat dissipation efficiency, good reliability, light weight, uniform temperature, etc.

Claims

1. A heat dissipation structure of an unmanned aerial vehicle radar, the unmanned aerial vehicle radar comprising an integrated radio frequency front end (2), a data acquisition and signal processing module (4) and a power supply and servo control module (5); characterized in that: The radar chassis (1) is divided into a front cabin (23) and a rear cabin (24), a middle partition (25) is provided between the two cabins, an integrated radio frequency front end (2) is located in the front cabin (23), a heat dissipation fan unit (3) is provided on the left and right inner sides of the front cabin (23) of the chassis (1), the integrated radio frequency front end (2) is located between the left and right heat dissipation fan units (3), and air is drawn outward through an air inlet (30) at the bottom of the chassis (1) by the heat dissipation fan unit (3) to remove heat from the integrated radio frequency front end (2) out of the chassis (1) ) front cabin (23); the data acquisition and signal processing module (4) and the power supply and servo control module (5) are located in the rear cabin (24); the data acquisition and signal processing module (4) comprises a data sampling board (12) and a signal processing board (13) arranged on the left and right; one side of the data sampling board (12) is provided with a data sampling cold plate (14) and a first fin (17); one side of the signal processing board (13) is provided with a signal processing cold plate (27) and a second fin (39); the above modules are integrated The invention discloses a novel integrated radio frequency front end (2) comprising a first fan (15) under the data acquisition and signal processing module (4); the power supply and servo control module (5) comprises a power supply and distribution module (20) and a servo control module (21) arranged in an upper and lower manner; a heat dissipation tooth (22) is provided between the power supply and distribution module (20) and the servo control module (21); a second fan (40) is provided on the side of the power supply and distribution module (20) close to the data acquisition and signal processing module (4); and the rear cabin air duct comprises two air ducts: the first air duct is from a side wall of the rear cabin where the power supply and distribution and servo control module (5) is installed, passes through the power supply and distribution and servo control module (5), the second fan (40), and the data acquisition and signal processing module (4), and then is discharged from the other side of the chassis; the other air duct is from the bottom of the chassis, passes through the data acquisition and signal processing module (4), and then is discharged from the other side of the chassis; the rear end of the integrated radio frequency front end (2) is provided with a local heat dissipation tooth (19); and a heat conductive pad (35) is provided under the heat source device on the data sampling board (12) and the signal processing board (13).

2. The heat dissipation structure of the unmanned aerial vehicle radar according to claim 1 is characterized in that A high-efficiency heat pipe (18) is welded on the data sampling cold plate (14).

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