An adjustable temperature control system for an energy-saving and environmentally friendly aircraft battery pack and an aircraft thereof

Abstract

The present invention provides an adjustable temperature control system for an aircraft battery pack and an aircraft thereof, belonging to the technical field of battery temperature control. It includes a cold liquid storage bin for storing coolant and a battery circulating temperature control system. The battery circulating temperature control system includes a battery heat exchange system, a hot liquid storage bin, and a duct cooling system that are connected in a loop through pipelines. The cold liquid storage bin is connected between the duct cooling system and the battery heat exchange system through pipelines. The battery heat exchange system is arranged inside the battery pack of the aircraft, and the pipelines in the battery heat exchange system are in contact with the outer walls of the batteries inside the battery pack. The duct cooling system is arranged inside the turbofan engine of the aircraft, and the pipelines in the duct cooling system are in contact with the inner walls of the ducts of the turbofan engine. By using coolant to exchange heat and cool down the battery pack, and then transporting the coolant into the duct cooling system for recooling and continuing to circulate to cool down the battery pack, the temperature of the battery pack can be effectively controlled to ensure the safety of the battery pack.

Description

Technical Field

[0001] The present invention relates to the technical field of battery temperature control, and particularly to an adjustable temperature control system for an aircraft battery pack with energy conservation and environmental protection and an aircraft thereof. Background Art

[0002] All-electric aircraft have attracted much attention. However, all-electric aircraft based on lithium-ion batteries are restricted by the flight environment and battery performance and it is difficult to achieve safe flight. This project proposes an all-weather intelligent temperature control system (including hardware and software) for an aviation hybrid power battery pack, which uses a hydrogen fuel cell / lithium-ion battery as an electric-electric hybrid power battery module, designs an embedded integrated liquid flow pipeline and an automatic temperature control system, and combines with a battery management system to realize the external heat exchange of the two types of batteries, so that the battery pack is in an optimal working state, ensuring the stability, safety and durability of the electric energy output of the all-electric aircraft.

[0003] Currently, the thermal management solutions for batteries at home and abroad usually include air cooling and temperature control board cooling. Air cooling is to introduce outside cold air into the battery and use the convection of air on the surface of the power battery to take away heat, with limited cooling efficiency. Temperature control board cooling is a component that uses liquid as a heat conduction fluid to control the temperature of the power battery. Generally, an alloy with good thermal conductivity and small density is used as the main material, which has the advantages of making the temperature distribution between battery monomers more uniform and being easy to control the heating and cooling rates.

[0004] However, on an aircraft, the battery module is relatively large, and the amount of coolant required for cooling and heat exchange in the temperature control heat dissipation board is large. However, due to the limited installation space on the aircraft, the re-cooling efficiency of the coolant after heat exchange is low, the cooling effect on the battery module is insufficient, and the thermal control ability for the battery module needs to be improved. Summary of the Invention

[0005] In view of the above problems in the prior art, the present invention provides an adjustable temperature control system for an aircraft battery pack with energy conservation and environmental protection and an aircraft thereof.

[0006] To achieve the above invention purpose, in the first aspect, the present application provides an adjustable temperature control system for an aircraft battery pack with energy conservation and environmental protection, and the technical solution adopted is as follows:

[0007] An adjustable temperature control system for an energy-saving and environment-friendly aircraft battery pack, including a cold liquid storage tank for storing coolant and a battery circulation temperature control system. The battery circulation temperature control system includes a battery heat exchange system, a hot liquid storage tank, and a duct cooling system connected in a circulating pipeline. Coolant flows in the pipeline. The cold liquid storage tank is connected between the duct cooling system and the battery heat exchange system through a pipeline. The hot liquid storage tank is used for storing the coolant after heat exchange by the battery heat exchange system. The pipeline is also provided with a valve assembly for controlling the on-off of the pipeline between the cold liquid storage tank and the battery circulation temperature control system and the pipeline in the battery circulation temperature control system, and a pumping assembly for pumping the coolant.

[0008] Among them, the battery heat exchange system is arranged in the battery pack of the aircraft, and the pipeline in the battery heat exchange system is attached to the outer wall of the battery in the battery pack.

[0009] The duct cooling system is arranged in the turbofan engine of the aircraft, and the pipeline in the duct cooling system is attached to the inner wall of the duct of the turbofan engine.

[0010] Preferably, U-shaped plates are provided on the outer wall of the battery. The U-shaped plates include several U-shaped tubes sleeved in sequence. Both ends of the several U-shaped tubes are in the same direction and connected to the pipeline. The coolant flows from the same-side end of the several U-shaped tubes on the U-shaped plate to the other end.

[0011] U-shaped plates are provided on both outer walls of the battery, and the coolant flows in opposite directions in the U-shaped tubes of the U-shaped plates on both sides of the battery.

[0012] Preferably, U-A-shaped plates are provided on the outer wall of the battery. The U-A-shaped plates include one A-shaped tube and several U-shaped tubes sleeved on the outside of the A-shaped tube in sequence. Both ends of the A-shaped tube and the several U-shaped tubes are in the same direction and connected to the pipeline. The coolant flows from the same-side end of the A-shaped tube and the several U-shaped tubes on the U-A-shaped plate to the other end.

[0013] U-A-shaped plates are provided on both outer walls of the battery, and the coolant flows in opposite directions in the A-shaped tube and the U-shaped tubes of the U-A-shaped plates on both sides of the battery.

[0014] Preferably, the pipeline in the duct cooling system extends along the axial direction of the duct in the duct and bends back and forth along the circumferential direction of the duct to form a serpentine tube.

[0015] Preferably, finned cold plates are coaxially and fixedly arranged on the inner wall of the duct. The finned cold plates are provided with multiple pieces at intervals along the axial direction of the duct. The serpentine tube passes through the finned cold plates and is fixedly connected to the finned cold plates.

[0016] Preferably, a secondary cooling system is further included. The secondary cooling system includes a telescopic tube. Both ends of the serpentine tube face the same end along the axial direction of the duct. The telescopic tube is arranged on each straight line segment of the serpentine tube parallel to the axial direction of the duct. The telescopic tube is close to the bending part of the serpentine tube far from its own end. A driving member for driving the telescopic part to expand and contract along the axial direction of the duct is arranged in the duct.

[0017] Preferably, the driving member is a driving hydraulic rod. An active fin is provided on the side of the serpentine tube away from the end of the telescopic tube. The active fin is fixedly connected to the serpentine tube. One end of the driving hydraulic rod is fixedly connected to the finned cold plate, and the other end is fixedly connected to the active fin.

[0018] Preferably, the valve assembly includes a first valve, a second valve, and a third valve. The first valve is arranged on the pipeline between the cold liquid tank and the battery circulation temperature control system. The second valve is arranged on the pipeline between the duct cooling system and the cold liquid tank in the battery circulation temperature control system. The third valve is arranged on the pipeline between the battery heat exchange system and the hot liquid tank.

[0019] Preferably, the pumping assembly includes a first water pump and a second water pump. The first water pump is arranged on the pipeline between the cold liquid tank and the battery circulation temperature control system. The second water pump is arranged on the pipeline between the duct cooling system and the cold liquid tank in the battery circulation temperature control system.

[0020] In a second aspect, the present application provides an aircraft, adopting the following technical solution:

[0021] An aircraft includes an aircraft body. Both sides of the aircraft body are provided with ducts. An energy-saving and environment-friendly adjustable temperature control system for an aircraft battery group provided in the first aspect of the present application is applied to the aircraft body. The adjustable temperature control system includes a duct cooling system symmetrically arranged on the ducts on both sides of the aircraft body.

[0022] The beneficial effects of the present invention are as follows: 1. By using a coolant to exchange heat and cool down the battery pack, and then transporting the coolant into the duct cooling system for recooling and continuing to circulate to cool down the battery pack, the temperature of the battery pack can be effectively controlled to ensure the safety of the battery pack;

[0023] 2. By embedding the pipeline in the duct cooling system into the inner wall of the aircraft duct, in the electrically driven duct engine, when the aircraft is flying, the cold air passes through the duct, which can exchange heat and cool down the pipeline in the duct, improve the recooling efficiency of the coolant, and save energy and protect the environment;

[0024] 3. The duct is provided with a telescopic serpentine tube, which can extend the flow length of the coolant in the duct cooling system, achieve a secondary cooling effect, and can cope with complex temperature changes and other situations during the takeoff or landing of the aircraft. Description of the Drawings

[0025] Figure 1 It is a system logic diagram of Embodiment 1 of the present application.

[0026] Figure 2 It is a structural diagram of the battery heat exchange system of Embodiment 1 of the present application.

[0027] Figure 3 This is a schematic structural diagram of the ducted cooling system of Example 1 of the present application.

[0028] Figure 4 This is a schematic diagram of the structure of the ducted cooling system when the secondary cooling system of Example 1 of the present application is turned on.

[0029] Figure 5 This is a schematic diagram of the overall structure of the temperature control system of Example 2 of the present application.

[0030] Among them, 1. Cold liquid tank; 2. Battery heat exchange system; 3. Hot liquid tank; 4. Ducted cooling system; 5. U-shaped plate; 50. UA-shaped plate; 51. U-shaped tube; 52. A-shaped tube; 6. Serpentine tube; 7. Fin cooling plate; 8. Telescopic tube; 9. Driving hydraulic rod; 10. Movable fin plate; 11. First valve; 12. Second valve; 13. Third valve; 14. First water pump; 15. Second water pump; 16. Duct; 17. Battery pack. DETAILED DESCRIPTION

[0031] In order to better understand the above technical solution, the above technical solution will be described in detail below with reference to the accompanying drawings and specific implementation methods.

[0032] Example 1

[0033] The embodiment of the present invention provides an energy-saving and environmentally friendly aircraft battery pack adjustable temperature control system and the aircraft. Figure 1 , including a cold liquid tank 1 and a battery circulation temperature control system, the cold liquid tank 1 is used to store coolant; the battery circulation system is connected to the battery of the aircraft, and cools the battery by supplying coolant into the battery, and after the battery is cooled, the coolant is dissipated and cooled again. In an embodiment of the present application, the battery circulation temperature control system includes a battery heat exchange system 2, a hot liquid tank 3 and a ducted cooling system 4, and the three are connected through a pipeline circulation, and the cold liquid tank 1 is connected between the ducted cooling system 4 and the battery heat exchange system 2 through a pipeline. Coolant flows between the cold liquid tank 1 and the battery circulation temperature control system, as well as in the pipelines within the battery circulation temperature control system. The pipelines are also provided with valve components for controlling the pipelines between the cold liquid tank 1 and the battery circulation temperature control system and the pipelines within the battery circulation temperature control system, as well as a pumping component for pumping the coolant.

[0034] Among them, the battery heat exchange system 2 is arranged in the battery pack 17 of the aircraft, and the pipes in the battery heat exchange system 2 are in contact with the outer walls of the batteries in the battery pack 17, which are used to exchange heat and cool the batteries; the ducted cooling system 4 is arranged in the turbofan engine of the aircraft, and the pipes in the ducted cooling system 4 are in contact with the inner wall of the duct 16 of the turbofan engine, which are used to drive high-altitude cold air to pass through the duct 16 and exchange heat and cool the coolant in the pipes in the duct 16 when the fan in the duct 16 rotates to propel the aircraft forward.

[0035] After the aircraft is started, by pumping the low-temperature coolant in the cold liquid tank 1 into the battery heat exchange system 2 in the battery cycle temperature control system, the heat exchange and cooling of the aircraft battery begins. When the coolant in the cold liquid tank 1 is completely pumped into the battery cycle temperature control system, the pipeline between the cold liquid tank 1 and the battery cycle temperature control system is closed. In the battery cycle temperature control system, after the coolant passes through the battery heat exchange system 2, it is pumped into the hot liquid tank 3 for storage. According to the battery temperature, the computer controls the high-temperature coolant in the hot liquid tank 3 to be pumped to the duct cooling system 4 at an appropriate rate. The coolant cools down in the duct cooling system 4 and finally returns to the battery heat exchange system 2 to continue cooling the battery pack 17. By circulating in this way to cool the battery pack 17, it can ensure that the battery pack 17 does not undergo thermal runaway.

[0036] Refer to Figure 2 , specifically, in the embodiment of the present application, the structure of the battery heat exchange system 2 can be that U-shaped plates 5 are provided on the outer walls on both sides of each battery in the battery pack 17. The U-shaped plate 5 includes a plurality of U-shaped tubes 51 sleeved in sequence. Both ends of the plurality of U-shaped tubes 51 face the same side. Both ends of the U-shaped tube 51 are connected to the pipeline, so that the plurality of U-shaped tubes 51 are simultaneously connected in parallel to the pipeline. The coolant flows in the U-shaped tube 51. In the U-shaped tubes 51 on each U-shaped plate 5, the coolant flows in the same direction, but the coolant flow directions in the two U-shaped plates 5 on both sides of the battery are opposite, so that the coolant can comprehensively cool and exchange heat with the battery.

[0037] Refer to Figure 3 , the pipeline in the duct cooling system 4 is specifically located in the wall of the duct 16 of the aircraft. Specifically, the pipeline extends along the axis of the duct 16 in the duct 16. At the same time, the pipeline bends back and forth to form a serpentine tube 6, and the serpentine tube 6 bends circumferentially along the duct 16 to cover. By adopting the serpentine tube 6, the routing length of the pipeline in the inner wall of the duct 16 can be increased, thereby prolonging the flow time of the coolant in the serpentine tube 6 and improving the cooling effect of the cold air on the coolant.

[0038] In an electric aircraft, the duct 16 is driven electrically. Different from a fuel engine, the turbofan consumes electrical energy, resulting in the temperature at the duct 16 being much lower than that of a fuel engine. As the aircraft moves forward, the rotation of the turbofan drives the cold air in the high altitude to flow through the entire duct 16. Under the flow of the low-temperature and high-speed air flow, the temperature of the duct 16 is extremely low. At this time, the liquid cooling pipeline transfers the temperature to the inner and outer walls of the duct 16 through radiation heat transfer and then conducts it to the atmospheric environment, thereby meeting the cooling of the coolant. Utilizing heat transfer with cold air to achieve the cooling of the coolant greatly reduces the energy loss and achieves the effect of zero pollution.

[0039] In the embodiment of the present application, the valve assembly includes a first valve 11 and a second valve 12, and the pumping assembly includes a first water pump 14 and a second water pump 15. The first valve 11 and the first water pump 14 are both arranged on the pipeline between the cold liquid tank 1 and the battery circulation temperature control system. The first water pump 14 can pump bidirectionally to pump the coolant out of or back into the cold liquid tank 1, and the first valve 11 is used to open and close the pipeline between the cold liquid tank 1 and the battery circulation temperature control system. The second water pump 15 is arranged on the pipeline between the duct cooling system 4 and the cold liquid tank 1 in the battery circulation temperature control system and is used to pump the coolant unidirectionally from the hot liquid tank 3 to the duct cooling system 4. The second valve 12 is arranged on the pipeline between the duct cooling system 4 and the cold liquid tank 1 in the battery circulation temperature control system, and the third valve 13 is arranged on the pipeline between the battery heat exchange system 2 and the hot liquid tank 3. The second valve 12 and the third valve 13 are used to open and close their respective pipelines.

[0040] When the cold liquid tank 1 transports the coolant to the battery circulation temperature control system, the second valve 12 is closed, the first valve 11 and the third valve 13 are opened, and the first water pump 14 is opened and pumps from the cold liquid tank 1 to the battery heat exchange system 2; when the battery circulation temperature control system operates in a cycle, the second water pump 15 is opened, the first valve 11 is closed, and the second valve 12 and the third valve 13 are opened; when the battery pack 17 stops cooling down and pumps the coolant back to the cold liquid tank 1, the third valve 13 is closed, the first valve 11 and the second valve 12 are opened, and the first water pump 14 is opened and pumps from the duct cooling system 4 to the cold liquid tank 1.

[0041] In order to meet the structural strength and heat exchange efficiency of the pipelines in the battery pack 17 and the serpentine tubes 6 in the duct 16 during high-altitude operation, the pipelines in the battery pack 17 and the serpentine tubes 6 in the duct 16 can both be made of aluminum material. Further, in order to stably install the serpentine tubes 6, in the embodiment of the present application, the two ends of the serpentine tubes 6 face the same direction, and finned cold plates 7 are fixedly welded on the inner wall of the duct 16. The finned cold plates 7 are annular. The serpentine tubes 6 pass through the finned cold plates 7 and are fixedly connected with the finned cold plates 7 by interference fit. A plurality of finned cold plates � are arranged at intervals along the axial direction of the duct 16, which can not only improve the installation stability of the serpentine tubes 6 but also utilize the fast heat conduction efficiency between metals to increase the heat conduction effect between the serpentine tubes 6 and the wall of the duct 16, thereby improving the heat exchange and cooling efficiency of the coolant.

[0042] Refer to Figure 4 , during the takeoff, cruise, landing, and emergency states of the electric aircraft, the battery discharge rate fluctuates, resulting in a certain difference in the battery heat generation. Therefore, in the embodiment of the present application, a secondary cooling system is also provided. The secondary cooling system includes a telescopic tube 8. The telescopic tube 8 is arranged on each straight segment of the serpentine tube 6 parallel to the axial direction of the duct 16, especially at the bending part on the side of the serpentine tube 6 far from its own end. A driving member for driving the telescopic part to expand and contract along the axial direction of the duct 16 is arranged in the duct 16.

[0043] When the ambient temperature is relatively high, the external environment has a relatively poor cooling effect on the coolant. For example, when the aircraft is in a low-altitude state during takeoff or landing, the driving member elongates the telescopic tube 8, increasing the cooling path of the coolant in the duct 16, thereby increasing the cooling time and achieving the effect of secondary refrigeration. When the flight altitude of the aircraft is relatively high and the ambient temperature is relatively low, the external environment has a better cooling effect on the coolant at this time. The driving member then drives the telescopic tube 8 to be in a contracted state, shortening the circulation period of the coolant and reducing the energy consumption of the pumping assembly in the system. The telescopic tube 8 that can be telescoped can more flexibly respond to the environmental impact during the flight of the aircraft. During the entire process of secondary refrigeration, considering the problem that the telescopic tube 8 sways around under force, in order to reduce the loss of kinetic energy, the telescopic tube 8 will be in a fully retracted or fully extended state, and no other intermediate states will exist.

[0044] In the embodiment of the present application, the driving member can be a driving hydraulic rod 9. An active wing plate 10 is fixedly connected to the side of the serpentine tube 6 away from the end of the serpentine tube 6 on the telescopic tube 8. The active wing plate 10 can move in the duct 16 along the axial direction of the duct 16. One end of the driving hydraulic rod 9 is fixed on the wing cooling plate 7 closest to the active wing plate 10 in the duct 16, and the other end is fixedly connected to the active wing plate 10. The telescopic direction of the driving hydraulic rod 9 is the same as the moving direction of the active wing plate 10. In other embodiments, the driving member can also be a telescopic structure such as an electric push rod.

[0045] When the aircraft is taking off, landing, and in case of an emergency, the battery generates a large amount of heat, causing the temperature of the coolant to be relatively high after cooling the battery. At this time, the driving hydraulic rod 9 elongates, the active wing plate 10 slides forward, the telescopic tube 8 elongates, and the liquid cooling path increases, achieving cooling at high temperatures and making the temperature of the coolant after cooling reach the preset temperature. When the aircraft is in a cruising state, the heat generated by the battery is relatively low compared to the previous cases, and the temperature of the liquid after cooling the battery is in a medium and low temperature state. At this time, the driving hydraulic rod 9 contracts, the active wing plate 10 slides backward, the telescopic tube 8 contracts, and the liquid can be quickly input into the aircraft for cooling tasks after being cooled.

[0046] The working process of the present invention is as follows: In an electric aircraft, the ducted fan engine is driven by electricity. Different from a fuel engine, the turbofan consumes electrical energy, resulting in a temperature at the duct 16 that is much lower than that of a fuel engine. As the aircraft moves forward, the rotation of the turbofan drives the cold air in the high altitude to flow through the entire duct 16. By embedding the pipes in the duct cooling system 4 into the inner wall of the duct 16, under the flow of the low-temperature and high-speed air flow, the temperature of the duct 16 is extremely low. At this time, the pipes transfer the temperature to the inner and outer walls of the duct 16 through radiative heat transfer, and then conduct it to the atmospheric environment, thereby meeting the cooling of the coolant, similar to film cooling. Utilizing heat transfer with cold air to achieve the cooling of the coolant greatly reduces energy loss and achieves the effect of zero pollution.

[0047] Embodiment 2

[0048] Referring to Figure 5 , the difference between Embodiment 2 and Embodiment 1 lies in the different structures in the battery heat exchange system 2.

[0049] In the embodiment of the present application, the battery heat exchange system 2 includes a U-A type plate 50. The U-A type plate 50 is stacked at intervals with the batteries in the battery pack 17, and it is ensured that the outer walls on both sides of each battery are attached with the U-A type plate 50. The U-A type plate 50 includes an A-type pipe 52 and a plurality of U-type pipes 51 sequentially sleeved outside the A-type pipe 52. The two ends of the A-type pipe 52 and the plurality of U-type pipes 51 are in the same direction and connected to the pipes. The flow directions of the coolant in the A-type pipe 52 and the plurality of U-type pipes 51 on the same U-A type plate 50 are the same, and the flow directions of the coolant in the U-A type plates 50 on both sides of the battery are opposite.

[0050] Due to structural constraints of the U-shaped pipes, there is a phenomenon of heat accumulation in the middle part of the battery, and it cannot be improved by controlling the liquid flow rate. Using only U-type pipes 51 in the battery heat exchange system 2 will cause heat accumulation in the middle part of the battery, affecting the battery service life. Adding an A-type pipe in the U-A type plate can effectively cool the middle part of the battery, making the battery heat dissipation more uniform, reducing the risk of thermal runaway, and ensuring the battery safety and output stability. Specifically, the U-A type plate 50 is filled with high-thermal-conductivity carbon materials in the gaps between the pipes, basically covering the areas where the heat released during the battery operation is relatively high.

[0051] Embodiment 3

[0052] The embodiment of the present application also discloses an aircraft, which includes an aircraft body. A battery pack 17 is provided inside the aircraft. Ducts 16 are symmetrically arranged on the wings on both sides of the aircraft. A turbofan thruster is installed in the duct 16. An energy-saving and environment-friendly adjustable temperature control system for the aircraft battery pack provided in any one of Embodiment 1 or 2 of the present application is applied to the aircraft body, which includes a cold liquid tank 1, a battery heat exchange system 2, a hot liquid tank 3, and a duct cooling system 4. Both the cold liquid tank 1 and the hot liquid tank 3 are arranged inside the aircraft body. The battery heat exchange system 2 is installed in the battery pack 17 of the aircraft. The duct cooling system 4 is symmetrically installed in the inner wall of the duct 16 on the ducts 16 on both sides of the aircraft body. By using the ducts 16 on both sides of the aircraft body, when the turbofan thruster drives cold air to pass through the ducts 16, the coolant in the pipeline of the duct cooling system 4 can be heat-exchanged and cooled down, greatly reducing the energy loss and achieving the effect of zero pollution.

[0053] Those skilled in the art should understand that although the preferred embodiments of the present invention have been described, once the basic creative concepts are known to those skilled in the art, additional changes and modifications can be made to these embodiments. Therefore, the appended claims are intended to be construed as including the preferred embodiments and all changes and modifications falling within the scope of the present invention. Obviously, those skilled in the art can make various changes and variations to the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalent technologies, the present invention is also intended to include these modifications and variations.

Claims

1. An adjustable temperature control system for an energy-saving and environmentally-friendly aircraft battery pack, characterized in that, It includes a cold liquid storage tank (1) for storing coolant and a battery cycle temperature control system. The battery cycle temperature control system includes a battery heat exchange system (2), a hot liquid storage tank (3), and a duct cooling system (4) that are connected in a circulating pipeline. Coolant flows in the pipeline. The cold liquid storage tank (1) is connected between the duct cooling system (4) and the battery heat exchange system (2) through a pipeline. The hot liquid storage tank (3) is used for storing the coolant that has exchanged heat through the battery heat exchange system (2). The pipeline is also provided with a valve assembly for controlling the on-off of the pipeline between the cold liquid storage tank (1) and the battery cycle temperature control system and the pipeline inside the battery cycle temperature control system, and a pumping assembly for pumping the coolant. Among them, the battery heat exchange system (2) is arranged inside the battery pack (17) of the aircraft, and the pipeline in the battery heat exchange system (2) is attached to the outer wall of the battery inside the battery pack (17). The duct cooling system (4) is arranged inside the turbofan engine of the aircraft, and the pipeline in the duct cooling system (4) is attached to the inner wall of the duct (16) of the turbofan engine. The pipeline in the duct cooling system (4) extends axially along the duct and bends back and forth circumferentially along the duct (16) to form a serpentine tube (6). On the inner wall of the duct (16), finned cooling plates (7) are coaxially and fixedly arranged. A plurality of finned cooling plates (7) are arranged at intervals along the axial direction of the duct (16). The serpentine tube (6) passes through the finned cooling plates (7) and is fixedly connected to the finned cooling plates (7).

2. The adjustable temperature control system for the aircraft battery pack with energy conservation and environmental protection according to claim 1, characterized in that, A U-shaped plate (5) is provided on the outer wall of the battery. The U-shaped plate (5) includes a number of U-shaped tubes (51) sleeved in sequence. Both ends of the number of U-shaped tubes (51) are in the same direction and are connected to the pipeline. The coolant flows from the same-side end of the number of U-shaped tubes (51) on the U-shaped plate (5) to the other end. U-shaped plates (5) are provided on both outer walls of the battery. The coolant flow directions in the U-shaped tubes (51) of the U-shaped plates (5) on both sides of the battery are opposite.

3. An adjustable temperature control system for an aircraft battery pack with energy conservation and environmental protection according to claim 1, characterized in that, A U-A-shaped plate (50) is provided on the outer wall of the battery. The U-A-shaped plate (50) includes an A-shaped tube (52) and a number of U-shaped tubes (51) sleeved outside the A-shaped tube (52) in sequence. Both ends of the A-shaped tube (52) and the number of U-shaped tubes (51) are in the same direction and are connected to the pipeline. The coolant flows from the same-side end of the A-shaped tube (52) and the number of U-shaped tubes (51) on the U-A-shaped plate (50) to the other end. U-A-shaped plates (50) are provided on both outer walls of the battery. The coolant flow directions in the A-shaped tube (52) and the U-shaped tubes (51) of the U-A-shaped plates (50) on both sides of the battery are opposite.

4. An adjustable temperature control system for an aircraft battery pack with energy conservation and environmental protection according to claim 1, characterized in that, It further includes a secondary cooling system. The secondary cooling system includes a telescopic tube (8). Both ends of the serpentine tube (6) face the same end along the axial direction of the duct (16). The telescopic tube (8) is arranged on each straight segment of the serpentine tube (6) parallel to the axial direction of the duct (16). The telescopic tube (8) is close to the bending part of the serpentine tube (6) away from its own end. A driving member for driving the telescopic part to expand and contract along the axial direction of the duct (16) is arranged inside the duct (16).

5. An adjustable temperature control system for an aircraft battery pack with energy conservation and environmental protection according to claim 4, characterized in that, The driving member is a driving hydraulic rod (9). An active fin (10) is arranged on the side of the telescopic tube (8) away from the end of the serpentine tube (6) on the serpentine tube (6). The active fin (10) is fixedly connected to the serpentine tube (6). One end of the driving hydraulic rod (9) is fixedly connected to the fin cooling plate (7), and the other end is fixedly connected to the active fin (10).

6. An adjustable temperature control system for an aircraft battery pack with energy conservation and environmental protection according to claim 1, characterized in that, The valve assembly includes a first valve (11), a second valve (12) and a third valve (13). The first valve (11) is arranged on the pipeline between the cold liquid chamber (1) and the battery circulation temperature control system. The second valve (12) is arranged on the pipeline between the duct cooling system (4) in the battery circulation temperature control system and the cold liquid chamber (1). The third valve (13) is arranged on the pipeline between the battery heat exchange system (2) and the hot liquid chamber (3).

7. An adjustable temperature control system for an aircraft battery pack with energy conservation and environmental protection according to claim 1, characterized in that, The pumping assembly includes a first water pump (14) and a second water pump (15). The first water pump (14) is arranged on the pipeline between the cold liquid chamber (1) and the battery circulation temperature control system. The second water pump (15) is arranged on the pipeline between the duct cooling system (4) in the battery circulation temperature control system and the cold liquid chamber (1).

8. An aircraft, characterized in that, It includes an aircraft body, and the aircraft body includes an adjustable temperature control system for an energy-saving and environmentally friendly aircraft battery pack as described in any one of claims 1-7.

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