Lifting air-cooled device and method for aircraft battery cooling

Abstract

The application discloses a lifting type air cooling equipment for aircraft battery heat dissipation in the field of battery heat dissipation, which comprises an air cooling host, a flow guide assembly and a lifting centering system, and a cooling method.The air cooling host provides a cold air source for aircraft battery heat dissipation through a condensing structure.The air inlet end of the flow guide assembly is connected with the air outlet end of the air cooling host.The flow guide assembly sends the hot air dissipated by the aircraft battery back to the air cooling host for cooling, and sends the cooled air back to the aircraft battery for heat dissipation.The lifting centering system is used for lifting the flow guide assembly and aligning and sealingly connecting the flow guide assembly with the aircraft battery.The application has the beneficial effects that: the heat dissipation device is divided into two parts, so that the weight of the aircraft can be prevented from being increased, the air cooling device has a simple structure, is safer than liquid cooling heat dissipation, and has a longer service life.

Description

Technical Field

[0001] This invention relates to the field of battery heat dissipation, and more specifically to a lift-type air-cooling device and method for heat dissipation of aircraft batteries. Background Technology

[0002] During flight, especially during vertical takeoff and landing, eVTOL aircraft experience extremely high battery discharge rates and generate a large amount of heat, leading to a rapid increase in battery temperature. After flight, eVTOL aircraft typically require rapid charging on the ground (to 90% charge within 40 minutes). This high-power charging process also generates a significant amount of heat, necessitating effective battery thermal management to control battery temperature. Existing technologies face the following major technical challenges that urgently need to be addressed: (1) Onboard cooling devices increase aircraft weight, reducing payload and endurance; (2) Ground-based liquid cooling equipment is complex and costly, and the liquid cooling system carries a risk of leakage. Currently, there is a lack of solutions that enable precise integration of ground-based cooling with the aircraft's battery pack structure, convenient operation, and automated air cooling.

[0003] To address this, we propose a lift-type air-cooling device and method for heat dissipation of aircraft batteries. Summary of the Invention

[0004] To address the aforementioned shortcomings of the prior art, the present invention provides a lift-type air-cooling device and method for heat dissipation of aircraft batteries.

[0005] To achieve the above-mentioned objectives, the technical solution adopted by this invention is as follows: A liftable air-cooling device for heat dissipation of aircraft batteries includes: an air-cooling main unit that provides a cold air source for heat dissipation of the aircraft battery through a condensation structure; a flow guide component whose air inlet is connected to the air outlet of the air-cooling main unit, the flow guide component sending the hot air dissipated from the aircraft battery back into the air-cooling main unit for cooling and sending the cooled air back into the aircraft battery for heat dissipation; and a lift-alignment system located at the bottom of the flow guide component, the lift-alignment system being used to lift the flow guide component to align it with the aircraft battery and seal it in place.

[0006] By setting up an air-cooled main unit, hot and cold air are exchanged to generate cooling air. This cooling air is then precisely delivered into the aircraft's battery through a flow guide component for heat dissipation. Simultaneously, the hot air generated by the aircraft's battery is also sent back into the air-cooled main unit through the flow guide component for heat exchange, continuously generating cooling air and achieving continuous heat dissipation for the aircraft's battery. Compared to directly introducing cold air, this method has a better heat dissipation effect, and the independent heat dissipation device does not affect the aircraft's weight or range. eVTOL aircraft are short-haul flights with frequent takeoffs and landings, so heat dissipation during landing is sufficient to meet the aircraft's heat dissipation requirements. The lift-and-alignment system can raise and lower the flow guide component, sealing its connection and disconnection from the aircraft's battery. This ensures effective heat dissipation without requiring structural disassembly and assembly, making it convenient to use.

[0007] Further defined, the air-cooled main unit includes an air-cooled housing, an electrical control box, a condenser fan, a condenser, an expansion valve, a compressor, an evaporator, an evaporator fan, a return air interface, an air duct, and an air outlet interface; The air-cooled housing is rectangular. The electrical control box is located inside the front wall of the air-cooled housing. The condenser fan is embedded in the right side wall of the air-cooled housing. The condenser is located inside the air-cooled housing in the direction of the condenser fan's air outlet. The compressor's outlet end is connected to one end of the condenser's pipe and is fixed to the bottom surface of the air-cooled housing. The expansion valve is connected to the other end of the condenser's pipe. Both the return air inlet and the outlet air inlet are located on the right side wall of the air-cooled housing, with the outlet air inlet located above the return air inlet. The evaporator is located inside the air-cooled housing in the direction of the return air outlet, with both ends of the pipe connected to the expansion valve and the compressor's inlet end, respectively. The evaporator fan is located inside the air-cooled housing in the direction of the evaporator's air outlet. The evaporator fan and the outlet air inlet are connected in a sealed manner through an air duct. The air-cooled housing is equipped with an air outlet structure.

[0008] The condenser fan delivers ambient air to the condenser, while the compressor compresses the low-temperature, low-pressure refrigerant into a high-temperature, high-pressure gas. The refrigerant dissipates heat as it passes through the condenser, becoming a high-pressure liquid. It then passes through the expansion valve to reduce its pressure before entering the evaporator. Simultaneously, the evaporator fan sends the hot air generated by the aircraft battery into the evaporator. The depressurized refrigerant absorbs heat in the evaporator, cooling the hot air and generating a cooling airflow. The refrigerant, after absorbing heat, is then circulated again by the compressor. The cooling airflow is then sent into the air guide assembly through the air duct and outlet to continuously dissipate heat from the aircraft battery.

[0009] Further defining the features, the air-cooled housing is divided into an evaporation chamber and a condensation chamber by a partition. The condenser, condenser fan, compressor, and expansion valve are all located in the condensation chamber, while the evaporator, evaporation fan, air duct, and electrical control box are all located in the evaporation chamber. The partition has through holes for refrigerant pipes to pass through, and the front panel of the air-cooled housing corresponding to the condensation chamber has louvered air outlet windows as the air outlet structure.

[0010] This partition separates the interior of the air-cooled housing, preventing cross-flow between cold and hot air and ensuring effective heat dissipation.

[0011] Further specifying, the airflow guiding component includes an air guide box, an air shroud, an air inlet transition port, and an air return transition port; The shape of the air guide box matches the shape of the aircraft battery and has an opening at the top. The air cover is fixed on the top of the air guide box. The air cover has several return air inlets arranged in a rectangular array. The air cover between adjacent return air inlets has an air outlet. The position of the air outlet corresponds to the air inlet position of the aircraft battery. The air inlet transition port and the air outlet interface are connected by an air outlet duct. The return air transition port and the return air interface are connected by a return air duct.

[0012] By setting up an air guide box, the air guide box and the main body of the air cover are attached to the fuselage where the aircraft battery is located. Cooling air that comes in from the air inlet transition port enters the air intake position of the aircraft battery through the air outlet to dissipate heat from the aircraft battery. Meanwhile, the hot air generated inside returns to the air-cooled host through the return air port and return air interface for cooling. The cooled air is then reintroduced into the aircraft battery to achieve circulating heat dissipation.

[0013] Further specifying, the lifting and centering system includes a base frame, a top plate, a push rod, a pressure plate, and a hydraulic control box; The base frame is a rectangular frame with universal wheels with locking function at the four corners. The top plate is located on one side of the base frame via a scissor lift structure, the pressure plate is horizontally located on the other side of the base frame, the push rod is vertically located on the outside of the pressure plate, and the hydraulic control box is located on the pressure plate. The hydraulic control box is connected to the hydraulic rod of the scissor lift structure through pipelines and controls its extension and retraction. A limit switch is located on one side of the hood box. The limit switch, hydraulic control box, and electrical control box are all electrically connected to the control system.

[0014] By setting a scissor-lift structure between the top plate and the base frame, the wind shield box is placed on the top plate. The scissor-lift structure lifts and fixes the wind shield box and the wind shield plate body, allowing the wind shield box to fit snugly against the aircraft fuselage. This serves both to lift and maintain altitude. The structure is simple and easy to use.

[0015] Further, the air guide box has positioning rings on both sides that cooperate with the positioning pins on the bottom of the aircraft, and the wind shield is covered with a soft sealing gasket. The air inlet and air outlet are both opened through the soft sealing gasket.

[0016] By setting positioning rings on both sides of the air guide box, the positional correspondence between the positioning rings and the positioning pins on the aircraft fuselage can be observed at any time during the air guide box's ascent. The position can be adjusted in real time. Furthermore, the base frame is equipped with casters, making position adjustment very convenient and quick. A soft sealing gasket is set on the wind shield plate, which makes the fit between the wind shield plate and the aircraft fuselage tighter, resulting in better air tightness and ensuring heat dissipation.

[0017] Furthermore, the pressure plate is equipped with positioning stops at intervals to perform initial positioning with the aircraft; the positioning stops enable initial positioning between the lifting and centering system and the aircraft fuselage, facilitating subsequent fine-tuning.

[0018] Further specified, the wind shield plate where the air outlet is located is provided with explosion-proof holes, and the explosion-proof holes are set in the same position as the explosion-proof valve of the aircraft battery. The wind shield plate corresponding to the explosion-proof holes is provided with explosion-proof pipes vertically, and the explosion-proof pipes pass through the air guide box and the top plate and are connected to the atmosphere.

[0019] This design of the explosion-proof vents allows the high-pressure gas inside the aircraft battery to be directionally discharged through the explosion-proof valve, vents, and pipes in the event of thermal runaway, preventing explosions and damage to the heat dissipation device. Furthermore, the explosion-proof pipes also provide a limit between the top plate and the air guide box, preventing the air guide box from sliding on the top plate due to the pressure from the upward movement, thus ensuring a more stable alignment.

[0020] A cooling method, employing the aforementioned lift-type air-cooling device for aircraft battery heat dissipation, includes the following steps: S1. Initial positioning: Move the air-cooled main unit to the side of the aircraft and push the lifting and centering system with the airflow guide components to the rear of the aircraft. Complete the initial positioning with the aircraft fuselage by using the positioning lever. S2. Precise Positioning: After initial positioning, control the hydraulic control box to slowly raise the air guide assembly. During the raising process, observe the relative position of the positioning ring and the positioning pin on the aircraft fuselage. When the positioning ring approaches the positioning pin, control the hydraulic control box to stop raising and lowering, push the push rod to adjust the raising and lowering centering system and the air guide assembly as a whole until the positioning ring is aligned with the positioning pin. Continue to control the hydraulic control box to raise the air guide assembly until the soft sealing gasket is tightly attached to the bottom of the aircraft battery. The limit switch is triggered, and the control system controls the raising and lowering centering system to stop rising, completing the precise positioning. S3. Battery Heat Dissipation: Turn on the control box to start the condenser fan, evaporator fan, and compressor. The compressor compresses the low-temperature, low-pressure refrigerant into a high-temperature, high-pressure gas. After being cooled by the air blown in by the condenser and condenser fan, the gas becomes a high-pressure liquid. It then enters the evaporator after being throttled and depressurized by the expansion valve. The evaporator fan absorbs heat from the hot air generated by the aircraft battery and the cooler in the evaporator, generating a low-temperature cooling airflow. The low-temperature cooling airflow enters the air guide assembly through the air duct from the air outlet and enters the aircraft battery from the air outlet of the air guide assembly to achieve heat dissipation. At the same time, the heat generated by the battery also returns to the evaporator through the return air outlet of the air guide assembly for cooling, thus achieving continuous heat dissipation.

[0021] The beneficial effects of the present invention are as follows: by setting the heat dissipation device separately, the heat dissipation device can avoid increasing the weight of the aircraft, and the air cooling device has a simple structure, is safer than liquid cooling, and has a longer service life. Attached Figure Description

[0022] Figure 1 This is a three-dimensional structural diagram of the present invention; Figure 2 A schematic diagram showing the coordination between the flow guiding component and the lifting and centering system; Figure 3 This is a schematic diagram of the air-cooled main unit with the side panel removed. Figure 4 This is a schematic diagram of the air-cooled main unit with both the side panels and the top panel removed.

[0023] The symbols for each component are as follows: 1. Air-cooled main unit; 11. Air-cooled housing; 12. Electrical control box; 13. Condenser fan; 14. Condenser; 15. Expansion valve; 16. Compressor; 17. Evaporator; 18. Evaporator fan; 19. Return air interface; 110. Air duct; 111. Air outlet interface; 112. Partition plate; 113. Air outlet structure; 2. Air guide assembly; 21. Air guide box; 22. Air cover plate; 23. Air inlet transition port; 24. Return air transition port; 25. Air outlet; 26. Explosion-proof hole; 27. Explosion-proof pipe; 28. Positioning ring; 29. ​​Soft sealing gasket; 210. Limit switch; 211. Lifting and centering system; 3. Base frame; 31. Top plate; 32. Push rod; 33. Pressure plate; 34. Hydraulic control box; 35. Casters; 36. Positioning stop bar; 37. Aircraft battery; 4. Air outlet duct; 5. Return air duct; 6. Detailed Implementation

[0024] The specific embodiments of the present invention are described below to enable those skilled in the art to understand the present invention. However, it should be understood that the present invention is not limited to the scope of the specific embodiments. For those skilled in the art, various changes are obvious as long as they are within the spirit and scope of the present invention as defined and determined by the appended claims. All inventions utilizing the concept of the present invention are protected.

[0025] Example: like Figures 1-4 As shown, a liftable air-cooling device for heat dissipation of aircraft batteries includes an air-cooling main unit 1, a flow guiding component 2, and a lift-alignment system 3. The air-cooled main unit 1 provides a cold air source for heat dissipation of the aircraft battery 4 through a condensation structure. The air-cooled main unit 1 includes an air-cooled housing 11, an electrical control box 12, a condenser fan 13, a condenser 14, an expansion valve 15, a compressor 16, an evaporator 17, an evaporator fan 18, a return air interface 19, an air duct 110, and an air outlet interface 111. The air-cooled housing 11 is a rectangular housing. The electrical control box 12 is located inside the front side wall of the air-cooled housing 11. The condenser fan 13 is embedded in the right side wall of the air-cooled housing 11. The condenser 14 is located inside the air-cooled housing 11 in the direction of the condenser fan 13's air outlet. The outlet end of the compressor 16 is connected to one end of the pipe of the condenser 14. The expansion valve 15 is connected to the other end of the pipe of the condenser 14. The return air interface 19 and the outlet air interface 111 are both located on the right side wall of the air-cooled housing 11. The outlet air interface 111 is located above the return air interface 19. The evaporator 17 is located in the air-cooled housing 11 in the direction of the return air interface 19, and the two ends of the pipe are respectively connected to the inlet end of the expansion valve 15 and the compressor 16. The evaporator fan 18 is located in the air-cooled housing 11 in the direction of the outlet air of the evaporator 17. The evaporator fan 18 and the outlet air interface 111 are connected in a sealed manner through the air duct 110. The air-cooled housing 11 is provided with an air outlet structure 113. The air-cooled housing 11 is divided into an evaporation chamber and a condensation chamber by a partition 112. The condenser 14, condenser fan 13, compressor 16 and expansion valve 15 are all located in the condensation chamber. The evaporator 17, evaporator fan 18, air duct 110 and electrical control box 12 are all located in the evaporation chamber. The partition 112 has through holes for refrigerant pipes to pass through. The front panel of the air-cooled housing 11 corresponding to the condensation chamber has louvered air outlet windows as air outlet structure 113. The airflow guiding assembly 2 sends the hot air emitted from the aircraft battery 4 back into the air-cooled main unit 1 for cooling, and sends the cooled air back into the aircraft battery 4 for heat dissipation. The airflow guiding assembly 2 includes an airflow guide box 21, an air shroud 22, an air inlet transition port 23, and an air return transition port 24. The shape of the airflow guide box 21 matches the shape of the aircraft battery 4, and it has an opening at the top. The air shroud 22 is fixedly mounted on the top of the airflow guide box 21. The air shroud 22 has several air return ports 25 arranged in a rectangular array. Air outlets 26 are opened on the air shroud 22 between adjacent air return ports 25. The air outlets 26 are located on the air shroud 22. There is an explosion-proof hole 27, which is set in a position corresponding to the explosion-proof valve of the aircraft battery 4. The wind shield plate 22 corresponding to the explosion-proof hole 27 is vertically provided with an explosion-proof pipe 28. The position of the air outlet 26 is set in a position corresponding to the air inlet of the aircraft battery 4. The air inlet transition port 23 and the air outlet interface 111 are connected by the air outlet pipe 5. The return air transition port 24 and the return air interface 19 are connected by the return air pipe 6. The air guide box 21 is provided with positioning rings 29 on both sides that cooperate with the positioning pins at the bottom of the aircraft. The wind shield plate 22 is covered with a soft sealing gasket 210. The air inlet and the air outlet 26 are both opened through the soft sealing gasket 210. The lifting and centering system 3 is used to lift and lower the flow guide assembly 2 to align and seal it with the aircraft battery 4. The lifting and centering system 3 includes a base frame 31, a top plate 32, a push rod 33, a pressure plate 34, and a hydraulic control box 35. The base frame 31 is a rectangular frame with universal wheels 36 with locking function at its four corners. The top plate 32 is located on one side of the base frame 31 via a scissor-type lifting structure. The pressure plate 34 is horizontally located on the other side of the base frame 31, and the push rod 33 is vertically located on the pressure plate. On the outside of 34, the hydraulic control box 35 is located on the pressure plate 34. The hydraulic control box 35 is connected to the hydraulic rod of the scissor lift structure through pipelines and controls its extension and retraction. A limit switch 211 is provided on one side of the wind cover box. The limit switch 211, the hydraulic control box 35, and the electrical control box 12 are all electrically connected to the control system. The pressure plate 34 is provided with positioning stops 37 at intervals for initial positioning of the aircraft. The explosion-proof pipe 28 passes through the air guide box 21 and the top plate 32 and is connected to the atmosphere.

[0026] By setting up an air-cooled main unit 1, hot and cold air are exchanged to generate cooling air. This cooling air is then precisely delivered into the aircraft battery 4 through the airflow guide component 2 for heat dissipation. Simultaneously, the hot air generated by the aircraft battery 4 is also sent back into the air-cooled main unit 1 through the airflow guide component 2 for heat exchange, continuously generating cooling air and achieving continuous heat dissipation for the aircraft battery 4. Compared to directly introducing cold air, this method has a better heat dissipation effect, and the independent heat dissipation device does not affect the weight and range of the aircraft. The eVTOL aircraft is a short-range flight with frequent takeoffs and landings, so heat dissipation during landing is sufficient to meet the aircraft's heat dissipation requirements. The lift-centering system 3 can raise and lower the airflow guide component 2 to align it with the aircraft battery 4. The sealed connection and disconnection ensure heat dissipation without requiring structural disassembly, making it convenient to use. The condenser fan 13 delivers ambient temperature air to the condenser 14, while the compressor 16 compresses the low-temperature, low-pressure refrigerant into a high-temperature, high-pressure gas. This gas dissipates heat as it passes through the condenser 14, becoming a high-pressure liquid. The liquid then passes through the expansion valve 15 for throttling and pressure reduction before entering the evaporator 17. Simultaneously, the evaporator fan 18 delivers hot air generated by the aircraft battery 4 into the evaporator 17. The depressurized refrigerant absorbs heat within the evaporator 17, cooling the hot air and generating a cooling airflow. The refrigerant then undergoes another cycle through the compressor 16. The cooling airflow is then delivered into the guide assembly 2 through the air duct 110 and the air outlet 111. Continuous heat dissipation is achieved for the aircraft battery 4. A partition 112 separates the interior of the air-cooled housing 11, preventing cross-flow between cold and hot air and ensuring effective heat dissipation. An air guide box 21, along with the main body of the air shield 22, is fitted to the fuselage where the aircraft battery 4 is located. Cooling air entering from the air inlet 23 passes through the air outlet 26 and enters the air intake of the aircraft battery 4 to dissipate heat. Meanwhile, the hot air generated inside returns to the air-cooled main unit 1 through the return air inlet 25 and return air interface 19 for further cooling. The cooled air is then reintroduced into the aircraft battery 4, achieving cyclical heat dissipation. A scissor lift structure is installed between the top plate 32 and the base frame 31, positioning the air shield box... On the top plate 32, a scissor-type lifting structure drives the wind shield box and the wind shield plate 22 body to rise and be fixed, so that the wind shield box can fit closely with the aircraft fuselage. This serves both as a lifting function and as a height maintenance function. The structure is simple and easy to use. By setting positioning rings 29 on both sides of the wind shield box 21, the positional correspondence between the positioning rings 29 and the positioning pins on the aircraft fuselage can be observed at any time during the rise of the wind shield box 21. The position can be adjusted in real time. Furthermore, universal wheels 36 are provided on the base frame 31, making position adjustment very convenient and quick. A soft sealing gasket 210 is set on the wind shield plate 22, which makes the fit between the wind shield plate 22 and the aircraft fuselage tighter, improves air tightness, and ensures heat dissipation.Setting up the positioning lever 37 allows for initial positioning between the lifting and centering system 3 and the aircraft fuselage, facilitating subsequent fine-tuning. The inclusion of the explosion-proof hole 27 ensures that in the event of thermal runaway of the aircraft battery 4, the internal high-pressure gas can be directionally discharged through the explosion-proof valve, explosion-proof hole 27, and explosion-proof pipe 28, preventing explosion and damage to the heat dissipation device. Furthermore, the explosion-proof pipe 28 also provides a limit between the top plate 32 and the air guide box 21, preventing the air guide box 21 from sliding on the top plate 32 due to the pressure exerted during ascent, resulting in more stable alignment.

[0027] A cooling method, employing the aforementioned lift-type air-cooling device for aircraft battery heat dissipation, includes the following steps: S1. Preliminary positioning: Move the air-cooled main unit 1 to the side of the aircraft and push the lifting and centering system 3 with the air guide component 2 installed to the rear of the aircraft. The preliminary positioning is completed with the aircraft fuselage through the positioning lever 37. S2. Precise Positioning: After initial positioning, control the hydraulic control box 35 to slowly raise the flow guide assembly 2. During the raising process, observe the relative position of the positioning ring 29 and the positioning pin on the aircraft fuselage. When the positioning ring 29 approaches the positioning pin, control the hydraulic control box 35 to stop raising and lowering, push the push rod 33 to drive the raising and lowering centering system 3 and the flow guide assembly 2 to adjust as a whole until the positioning ring 29 is aligned with the positioning pin. Continue to control the hydraulic control box 35 to drive the flow guide assembly 2 to rise until the soft sealing gasket 210 is tightly attached to the bottom of the aircraft battery 4. The limit switch 211 is triggered, and the control system controls the raising and lowering centering system 3 to stop rising, completing the precise positioning. S3. Battery cooling: Turn on the control box 12 to start the condenser fan 13, evaporator fan 18 and compressor 16. The compressor 16 compresses the low-temperature, low-pressure refrigerant into a high-temperature, high-pressure gas. After being cooled by the air blown in by the condenser 14 and condenser fan 13, it becomes a high-pressure liquid. After being throttled and depressurized by the expansion valve 15, it enters the evaporator 17. The evaporator fan 18 absorbs heat from the hot air generated by the aircraft battery 4 and the cooler in the evaporator 17 to generate a low-temperature cooling airflow. The low-temperature cooling airflow enters the air guide assembly 2 through the air outlet 111 of the air duct 110 and enters the aircraft battery 4 through the air outlet 26 of the air guide assembly 2 to achieve heat dissipation. At the same time, the heat generated by the battery also returns to the evaporator 17 through the return air outlet 25 of the air guide assembly 2 for cooling, thereby achieving continuous heat dissipation.

Claims

1. A lift-type air-cooling device for heat dissipation of aircraft batteries, characterized in that, include: The air-cooled main unit (1) provides a cold air source for the aircraft battery (4) to dissipate heat through the condensation structure; The air guide assembly (2) has its air inlet end connected to the air outlet end of the air-cooled host (1). The air guide assembly (2) sends the hot air emitted by the aircraft battery (4) back into the air-cooled host (1) for cooling and sends the cooled air back into the aircraft battery (4) for heat dissipation. The lifting and centering system (3) is located at the bottom of the flow guide assembly (2). The lifting and centering system (3) is used to lift the flow guide assembly (2) and align and seal it with the aircraft battery (4).

2. The lift-type air-cooling device for heat dissipation of aircraft batteries according to claim 1, characterized in that, The air-cooled host (1) includes an air-cooled housing (11), an electrical control box (12), a condenser fan (13), a condenser (14), an expansion valve (15), a compressor (16), an evaporator (17), an evaporator fan (18), a return air interface (19), an air duct (110), and an air outlet interface (111). The air-cooled housing (11) is a rectangular housing. The electrical control box (12) is located inside the front side wall of the air-cooled housing (11). The condenser fan (13) is embedded in the right side wall of the air-cooled housing (11). The condenser (14) is located inside the air-cooled housing (11) in the direction of the air outlet of the condenser fan (13). The outlet end of the compressor (16) is connected to one end of the pipe of the condenser (14) and is fixedly located on the bottom surface of the air-cooled housing (11). The expansion valve (15) is connected to the other end of the pipe of the condenser (14). The return air interface (19) and the outlet air interface (111) are both located in the... On the right side wall of the air-cooled housing (11), the air outlet (111) is located above the return air outlet (19). The evaporator (17) is located inside the air-cooled housing (11) in the air outlet direction of the return air outlet (19), and the two ends of the pipe are respectively connected to the inlet end of the expansion valve (15) and the compressor (16). The evaporation fan (18) is located inside the air-cooled housing (11) in the air outlet direction of the evaporator (17). The evaporation fan (18) and the air outlet (111) are connected in a sealed manner through the air duct (110). The air-cooled housing (11) is provided with an air outlet structure (113).

3. The lift-type air-cooling device for heat dissipation of aircraft batteries according to claim 2, characterized in that, The air-cooled housing (11) is divided into an evaporation chamber and a condensation chamber by a partition (112). The condenser (14), condenser fan (13), compressor (16) and expansion valve (15) are all located in the condensation chamber. The evaporator (17), evaporator fan (18), air duct (110) and electrical control box (12) are all located in the evaporation chamber. The partition (112) has a through hole for the refrigerant pipe to pass through. The front panel of the air-cooled housing (11) corresponding to the condensation chamber is provided with a louvered air outlet window as an air outlet structure (113).

4. The lift-type air-cooling device for aircraft battery heat dissipation according to claim 3, characterized in that, The airflow guiding assembly (2) includes an air guide box (21), an air cover plate (22), an air inlet transition port (23), and an air return transition port (24). The shape of the air guide box (21) matches the shape of the aircraft battery (4) and is set with an opening at the top. The air cover plate (22) is fixedly set on the top of the air guide box (21). The air cover plate (22) has a plurality of return air ports (25) arranged in a rectangular array. The air cover plate (22) between adjacent return air ports (25) has an air outlet (26). The position of the air outlet (26) corresponds to the air inlet position of the aircraft battery (4). The air inlet transition port (23) and the air outlet interface (111) are connected by an air outlet pipe (5). The return air transition port (24) and the return air interface (19) are connected by a return air pipe (6).

5. The lift-type air-cooling device for aircraft battery heat dissipation according to claim 4, characterized in that, The lifting and centering system (3) includes a base frame (31), a top plate (32), a push rod (33), a pressure plate (34), and a hydraulic control box (35). The base frame (31) is a rectangular frame. The four corners of the base frame (31) are equipped with universal wheels (36) with locking function. The top plate (32) is set on one side of the base frame (31) through a scissor lifting structure. The pressure plate (34) is set horizontally on the other side of the base frame (31). The push rod (33) is set vertically on the outside of the pressure plate (34). The hydraulic control box (35) is set on the pressure plate (34). The hydraulic control box (35) is connected to the hydraulic rod of the scissor lifting structure through a pipeline and controls its extension and retraction. A limit switch (211) is set on one side of the hood box. The limit switch (211), the hydraulic control box (35), and the electrical control box (12) are all electrically connected to the control system.

6. The lift-type air-cooling device for heat dissipation of aircraft batteries according to claim 5, characterized in that, The air guide box (21) has positioning rings (29) on both sides that cooperate with the positioning pins at the bottom of the aircraft. The wind shield (22) is covered with a soft sealing gasket (210). The air inlet and the air outlet (26) are both opened through the soft sealing gasket (210).

7. The lift-type air-cooling device for aircraft battery heat dissipation according to claim 6, characterized in that, The pressure plate (34) is provided with positioning stops (37) at intervals on the upper part for initial positioning of the aircraft.

8. The lift-type air-cooling device for aircraft battery heat dissipation according to claim 7, characterized in that, An explosion-proof hole (27) is provided on the wind cover plate (22) where the air outlet (26) is located. The explosion-proof hole (27) and the explosion-proof valve of the aircraft battery (4) are positioned correspondingly. The wind cover plate (22) corresponding to the explosion-proof hole (27) is provided with an explosion-proof pipe (28) vertically. The explosion-proof pipe (28) passes through the air guide box (21) and the top plate (32) and communicates with the atmosphere.

9. A cooling method, comprising using the lift-type air-cooling device for aircraft battery heat dissipation as described in claim 8 to dissipate heat from the aircraft battery, characterized in that, The steps include the following: S1. Preliminary positioning: Move the air-cooled main unit (1) to the side of the aircraft and push the lifting centering system (3) with the air guide component (2) to the rear of the aircraft. The initial positioning is completed with the aircraft fuselage by the positioning lever (37). S2. Precise positioning: After initial positioning, control the hydraulic control box (35) to slowly raise the flow guide assembly (2). During the raising process, observe the relative position of the positioning ring (29) and the positioning pin on the aircraft body. When the positioning ring (29) approaches the positioning pin, control the hydraulic control box (35) to stop raising and lowering, push the push rod (33) to drive the raising and lowering centering system (3) and the flow guide assembly (2) to adjust as a whole until the positioning ring (29) is aligned with the positioning pin. Continue to control the hydraulic control box (35) to drive the flow guide assembly (2) to rise until the soft sealing gasket (210) is tightly attached to the bottom of the aircraft battery (4). The limit switch (211) is triggered, and the control system controls the raising and lowering centering system (3) to stop rising, thus completing the precise positioning. S3. Battery heat dissipation: Turn on the control box (12) to start the condenser fan (13), evaporator fan (18) and compressor (16). The compressor (16) compresses the low-temperature and low-pressure refrigerant into a high-temperature and high-pressure gas. After being cooled by the air blown in by the condenser (14) and condenser fan (13), it becomes a high-pressure liquid. After being throttled and depressurized by the expansion valve (15), it enters the evaporator (17). The evaporator fan (18) absorbs heat from the hot air generated by the aircraft battery (4) and the cooler in the evaporator (17) to generate a low-temperature cooling airflow. The low-temperature cooling airflow enters the guide assembly (2) from the air outlet (111) through the air duct (110) and enters the aircraft battery (4) from the air outlet (26) of the guide assembly (2) to achieve heat dissipation. At the same time, the heat generated by the battery also returns to the evaporator (17) through the return air outlet (25) of the guide assembly (2) for cooling, thereby achieving continuous heat dissipation.

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