Ground heat management system, electric aircraft and electric aircraft system

Abstract

The utility model provides a ground heat management system, an electric aircraft and an electric aircraft system. The ground heat management system is used for being arranged on the ground. The ground heat management system comprises a water inlet pipe, a water outlet pipe, a compressor, a condenser, a heat exchanger, a control part and a heater. The water inlet pipe and the water outlet pipe are used for being connected to the electric aircraft, so that the heat exchange medium can circulate between the ground heat management system and the electric aircraft and is used for heating or cooling operation of the electric aircraft. The water inlet pipe communicates with the water outlet pipe through the heat exchanger and the heater so that heat exchange media can exchange heat through the heat exchanger or the heater. The compressor, the condenser and the heat exchanger are sequentially connected, a refrigerant is led into the heat exchanger to exchange heat with a heat exchange medium after being cooled in the condenser, the heat exchanger is connected with the compressor, and the refrigerant can flow back to the compressor to form circulation of the refrigerant. The control part is connected with the compressor, the condenser, the heat exchanger and the heater so as to control work of the ground heat management system.

Description

Technical Field

[0001] The present application relates to the technical field of thermal management of electric aircraft, and in particular to a ground thermal management system, an electric aircraft, and an electric aircraft system. Background Art

[0002] Electric Vertical Takeoff and Landing (eVTOL) aircraft have gradually entered commercial operation, with applications including, but not limited to, low-altitude sightseeing, urban and regional passenger transport, cargo transportation, personal use, and emergency medical services. Both the powertrain and battery systems of eVTOL aircraft generate significant amounts of heat during operation. Failure to effectively manage and dissipate this heat can affect the aircraft's functionality and performance.

[0003] Existing battery thermal management for electric aircraft is onboard thermal management, whereby a heat sink is integrated into the aircraft. This includes both air-cooling and liquid-cooling methods. Air-cooled heat sinks are large, have high ambient temperature requirements, and have low heat dissipation efficiency, making them incapable of meeting the high-power, high-current requirements of electric aircraft batteries. Liquid-cooled heat sinks are more efficient, more flexible in layout, have lower ambient temperature requirements, and offer high reliability compared to air-cooled heat sinks. However, liquid-cooled heat sinks consume significant amounts of electricity during operation, which reduces the aircraft's endurance and increases its charging time, making them incapable of meeting the commercial operational requirements of electric aircraft. Utility Model Content

[0004] This application is made in view of the above-mentioned state of the prior art. The purpose of this application is to provide a ground thermal management system, which is used to be set on the ground and can heat or cool down an electric aircraft, especially a battery.

[0005] The present application also provides an electric aircraft that can be adapted to the above-mentioned ground thermal management system and an electric aircraft system including the ground thermal management system and the electric aircraft.

[0006] The present application provides a ground thermal management system, which is used to be set on the ground.

[0007] The ground thermal management system includes a water inlet pipe, a water outlet pipe, a compressor, a condenser, a heat exchanger, a control unit and a heater.

[0008] The water inlet pipe and the water outlet pipe are used to be connected to the electric aircraft, so that the heat exchange medium can circulate between the ground thermal management system and the electric aircraft for heating or cooling the electric aircraft.

[0009] The water inlet pipe is connected to the water outlet pipe via the heat exchanger and the heater, so that the heat exchange medium can exchange heat via the heat exchanger or the heater.

[0010] The compressor, the condenser and the heat exchanger are connected in sequence, so that the refrigerant passes into the heat exchanger after dissipating heat in the condenser to exchange heat with the heat exchange medium. The heat exchanger is connected to the compressor so that the refrigerant can flow back to the compressor to form a refrigerant cycle.

[0011] The control unit is connected to the compressor, the condenser, the heat exchanger, and the heater to control the operation of the ground thermal management system.

[0012] In at least one possible embodiment, the ground thermal management system further includes one or more cooling fans, which are arranged adjacent to the condenser. The cooling fans can draw air from the condenser to the outside to improve the heat exchange effect of the condenser.

[0013] In at least one possible embodiment, the ground thermal management system further includes a liquid reservoir, which is arranged in the refrigerant flow path between the heat exchanger and the compressor, so that the refrigerant flows from the heat exchanger through the liquid reservoir and then flows into the compressor. The liquid reservoir can separate the gaseous refrigerant and the liquid refrigerant to protect the compressor.

[0014] In at least one possible embodiment, the ground thermal management system further includes a water pump, wherein the water pump is connected to the water inlet pipe and / or the water outlet pipe to provide flow power to the heat exchange medium.

[0015] In at least one possible embodiment, the ground thermal management system further includes a control panel connected to the control unit and configured to control the operation of the ground thermal management system and monitor its working status and operating parameters.

[0016] In at least one possible embodiment, the ground thermal management system also includes a power interface and a shell, the shell at least partially shields the ground thermal management system, the water inlet pipe, the water outlet pipe, the power interface and the control panel are arranged on a surface of the shell, and at least part of the end portions of the water inlet pipe and the water outlet pipe extend from the inside of the shell to the outside of the shell.

[0017] In at least one possible embodiment, a throttle valve is provided at the refrigerant inlet of the heat exchanger to adjust the pressure and flow of the refrigerant.

[0018] The water inlet pipe and / or the water outlet pipe are provided with a temperature sensor, and the ends of the water inlet pipe and the water outlet pipe are provided with connection joints with disconnect valves.

[0019] In at least one possible embodiment, the heater is a positive temperature coefficient ceramic heater, the heater and the heat exchanger are arranged adjacent to each other, and a temperature sensor is provided inside the heater and / or the heat exchanger.

[0020] The present application also provides an electric aircraft, which includes a battery pack for powering the electric aircraft. The battery pack is provided with a heat exchange system, and the heat exchange system has a heat exchange pipe capable of circulating a heat exchange medium.

[0021] The heat exchange pipe can be connected to the water inlet pipe and the water outlet pipe of the aforementioned ground thermal management system, so that the heat exchange medium can circulate and exchange heat between the electric aircraft and the ground thermal management system.

[0022] The present application also provides an electric aircraft system, which includes an electric aircraft and the aforementioned ground thermal management system.

[0023] The electric aircraft includes a battery pack for powering the electric aircraft. The battery pack is provided with a heat exchange system. The heat exchange system has a heat exchange pipe capable of circulating a heat exchange medium.

[0024] The heat exchange pipe can be connected to the water inlet pipe and the water outlet pipe of the ground thermal management system, so that the heat exchange medium can circulate and exchange heat between the electric aircraft and the ground thermal management system.

[0025] The ground-based thermal management system provided herein can be installed on the ground and can cool or heat the electric aircraft, particularly its batteries, based on actual environmental conditions and operational needs, ensuring the batteries maintain an optimal operating temperature. The electric aircraft and electric aircraft system provided herein are adaptable to this ground-based thermal management system, which can effectively manage heat while conserving internal space and reducing electrical energy consumption. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 Schematic diagram of the external structure of a ground thermal management system according to one embodiment of the present application.

[0027] Figure 2 This is a schematic diagram of the external structure of a ground thermal management system from another perspective according to an embodiment of the present application.

[0028] Figure 3 Schematic diagram of the internal structure of a ground thermal management system according to one embodiment of the present application.

[0029] Figure 4 Schematic diagram of a cooling fan of a ground thermal management system according to one embodiment of the present application.

[0030] Figure 5 This is a schematic diagram of the internal structure of a ground thermal management system from another perspective according to an embodiment of the present application.

[0031] Figure 6 It is a schematic diagram of part of the internal structure of a ground thermal management system according to one embodiment of the present application.

[0032] Description of Reference Numerals

[0033] 11 Water inlet pipe

[0034] 111 Temperature Sensor

[0035] 12 Water outlet pipe

[0036] 13 Power port

[0037] 14 Control Panel

[0038] 15 Housing

[0039] 151 Fan Vent

[0040] 20 compressor

[0041] 30 Condenser

[0042] 40 cooling fans

[0043] 50 heat exchanger

[0044] 51 Throttle valve

[0045] 60 Control Department

[0046] 70 Reservoir

[0047] 80 Heater

[0048] 90 water pump DETAILED DESCRIPTION

[0049] The following describes exemplary embodiments of the present application with reference to the accompanying drawings. It should be understood that these specific descriptions are only used to teach those skilled in the art how to implement the present application, and are not intended to exhaust all possible embodiments of the present application, nor to limit the scope of the present application.

[0050] The embodiments of the present application provide a ground-based thermal management system (hereinafter sometimes referred to as a "thermal management system"), which can be installed on the ground for heating and cooling (i.e., thermal management) the batteries (battery packs, battery systems) of electric aircraft (especially electric vertical take-off and landing aircraft, eVTOL). Figure 1 、 Figure 2 and Figure 3As shown, the thermal management system may include a water inlet pipe 11 , a water outlet pipe 12 , a power interface 13 and a control panel 14 , a compressor 20 , a condenser 30 , a cooling fan 40 , a heat exchanger 50 , a control unit 60 and a heater 80 .

[0051] Specifically, such as Figure 1 and Figure 2 As shown, the water inlet pipe 11 can be used to introduce a heat exchange medium into the thermal management system, and the water outlet pipe 12 can be used for the thermal management system to output the heat exchange medium to the outside. The water inlet pipe 11 can be connected to the water outlet pipe 12 via the heat exchanger 50 and the heater 80, so that the heat exchange medium can exchange heat via the heat exchanger 50 or the heater 80. The battery pack of the electric aircraft can be provided with a heat exchange system, and the heat exchange system may include a heat exchange pipe that can circulate a heat exchange medium. The heat exchange pipe can be connected to the water inlet pipe 11 and the water outlet pipe 12 when the electric aircraft is parked on the ground, and is used to circulate the heat exchange medium between the electric aircraft and the thermal management system to heat or cool the battery of the electric aircraft. The type of heat exchange medium can be selected according to the actual thermal management requirements. For example, the heat exchange medium here can be water, but the type of heat exchange medium is not limited to this.

[0052] Preferably, the water inlet pipe 11 and / or the water outlet pipe 12 may be provided with temperature sensors to monitor the temperature of the heat exchange medium. In particular, the water inlet pipe 11 may be provided with a temperature sensor 111 to monitor the temperature of the heat exchange medium entering the thermal management system, thereby more accurately regulating the operating state of the thermal management system and thereby maintaining the battery of the electric aircraft at an optimal operating temperature.

[0053] Preferably, the water inlet pipe 11 and the water outlet pipe 12 can be provided with a connecting joint for connecting to the heat exchange pipe of the electric aircraft. More preferably, the connecting joint of the water inlet pipe 11 and the water outlet pipe 12 can be a connecting joint with a disconnecting stop valve, which can automatically cut off the flow of the heat exchange medium when the connecting joint is not connected to the heat exchange pipe to prevent the heat exchange medium from leaking, and the connecting joint can allow the heat exchange medium to flow freely when connected to the heat exchange pipe. It can be understood that the heat exchange pipe of the heat exchange system of the electric aircraft can also be provided with a connecting joint (especially a connecting joint with a disconnecting stop valve), that is, the water inlet pipe 11, the water outlet pipe 12 and the heat exchange pipe can be provided with male and female joints respectively. In the actual application of the thermal management system, the water inlet pipe 11 and the water outlet pipe 12 can also be connected to a section of hose to facilitate its connection with the electric aircraft.

[0054] Preferably, the thermal management system may further include a water pump 90, which may be connected to the water inlet pipe 11 and / or the water outlet pipe 12 to provide flow power to the heat exchange medium. For example, in this embodiment, the water pump 90 may be connected to the water inlet pipe 11 to pump the heat exchange medium into the thermal management system.

[0055] The power interface 13 can be used to connect to an external power source (particularly an external high-voltage power source) to provide power to the thermal management system. The power interface 13 can be connected to the control unit 60 via a wire. The control unit 60 can further connect to the various electrical devices of the thermal management system and provide them with the required power.

[0056] The control panel 14 can be connected to the control unit 60. The operator can use the control panel 14 to control the operation of the thermal management system and monitor its operating status and operating parameters. For example, the control panel 14 can display the real-time temperature of the heat exchange medium (particularly, the real-time temperature of the heat exchange medium can be monitored by temperature sensors provided on the water inlet pipe 11 and / or the water outlet pipe 12).

[0057] The control unit 60 can be connected (including electrically and communicatively) to the various devices and components of the thermal management system to control the operation of the devices and components of the thermal management system to achieve heating or cooling of the battery of the electric aircraft. The control panel 14 can be connected to the control unit 60 to regulate the operation of the thermal management system and monitor its operating status and operating parameters.

[0058] Preferably, the control unit 60 can automatically or in response to instructions control the thermal management system to heat or cool the batteries of the electric aircraft. The heating and cooling functions can each be configured with multiple gears to correspond to different operating times, temperature control efficiencies, and other factors. More preferably, the control unit 60 can also automatically or in response to instructions adjust its operating gear based on the specific water temperature of the water inlet pipe 11 and / or the water outlet pipe 12 as monitored by the temperature sensor.

[0059] Preferably, the thermal management system may further include a shell 15, which may shield at least part of the device of the thermal management system to at least partially isolate the thermal management system from the outside world. At least part of the ends of the water inlet pipe 11 and the water outlet pipe 12 (especially the connecting joints) may extend from the inside of the shell 15 to the outside of the shell, so as to facilitate the connection of the thermal management system with the heat exchange pipe of the electric aircraft. The power interface 13 and the control panel 14 may be arranged on the surface of the shell 15. In particular, the water inlet pipe 11, the water outlet pipe 12, the power interface 13 and the control panel 14 may be jointly arranged on a surface of the shell 15 to facilitate the use of the thermal management system. The shell 15 may form a fan heat dissipation port 151 at the corresponding position of the heat dissipation fan 40 to facilitate the heat dissipation of the heat dissipation fan 40.

[0060] like Figure 3 、 Figure 4 and Figure 5 As shown, the compressor 20 can compress the refrigerant to generate work, thereby increasing the medium- and low-pressure gaseous refrigerant to a high-pressure gaseous refrigerant. By discharging the high-pressure gaseous refrigerant, the compressor 20 can also provide power for the flow of the refrigerant, allowing the refrigerant to circulate among the various devices in the thermal management system.

[0061] Preferably, tetrafluoroethane (R134a) can be selected as the refrigerant. It is understood that the thermal management system in this embodiment can also use other types of refrigerants, and the type of refrigerant is not particularly limited.

[0062] The condenser 30 can be connected to the compressor 20, and the refrigerant can enter the condenser 30 from the compressor 20 via a refrigeration pipeline. The refrigerant can exchange heat in the condenser 30. Specifically, the high-temperature and high-pressure gaseous refrigerant can be condensed into liquid refrigerant in the condenser 30, releasing heat during the phase change. The heat released by the refrigerant phase change can be discharged into the air. The condenser 30 can include a sheet-like heat exchange plate, and the refrigerant can enter the heat exchange plate to release heat during the phase change.

[0063] The heat dissipation fan 40 can be arranged adjacent to the condenser 30. The heat dissipation fan 40 can extract the airflow near the condenser 30 to the outside to accelerate the heat exchange between the condenser and the outside (air) and improve the heat exchange effect of the condenser 30. The heat dissipation fan 40 can be aligned with the fan vent 151 of the housing 15 to facilitate airflow. Preferably, the thermal management system can include multiple heat dissipation fans 40 to enhance the heat dissipation effect. Exemplarily, two heat dissipation fans 40 are provided in the embodiment of the present application.

[0064] Optionally, the thermal management system provided in this embodiment may also adopt other condenser heat dissipation methods. For example, a liquid cooling device may be used instead of a cooling fan to dissipate heat for the condenser.

[0065] The heat exchanger 50 can be connected to the condenser 30, and the refrigerant (liquid refrigerant condensed by heat dissipation in the condenser 30) can enter the heat exchanger 50 from the condenser 30 via the refrigeration pipeline. The water inlet pipe 11 and the water outlet pipe 12 can be connected (directly or indirectly) to the heat exchanger 50 to pass the heat exchange medium into the heat exchanger 50. The refrigerant and the heat exchange medium can exchange heat in the heat exchanger 50, and the heat of the heat exchange medium can be transferred to the refrigerant. The refrigerant is then recirculated to the condenser to release the heat to the air. It is understood that the liquid refrigerant can be vaporized into a gaseous refrigerant after absorbing the heat of the heat exchange medium.

[0066] Preferably, a throttle valve 51 (or expansion valve) may be provided at the refrigerant inlet of the heat exchanger 50. The liquid refrigerant flowing out of the condenser 30 may be throttled and depressurized by the throttle valve 51 (e.g., depressurized to form a mist-like liquid refrigerant, i.e., wet steam), thereby facilitating the refrigerant to absorb heat and vaporize within the heat exchanger 50.

[0067] Preferably, the refrigerant inlet of the heat exchanger 50 may be adjacent to the heat exchange medium outlet of the heat exchanger 50 . This arrangement may maximize the cooling effect (heat exchange effect) of the heat exchanger 50 .

[0068] The refrigerant (in gaseous form) that has absorbed heat in the heat exchanger 50 can return to the compressor 20 for compression before entering the condenser 30 to dissipate heat, thereby forming a refrigerant cycle. The accumulator 70 can be disposed in the refrigerant flow path between the heat exchanger 50 and the compressor 20. That is, after flowing out of the heat exchanger 50, the refrigerant can flow through the accumulator 70 before entering the compressor 20. The accumulator 70 (low-pressure accumulator) can separate the gaseous refrigerant from the liquid refrigerant (it will be understood that some liquid refrigerant droplets will still be present in the refrigerant flowing out of the heat exchanger 50), thereby preventing liquid hammer (abnormal shock caused by the compressor sucking in liquid) in the compressor and protecting the compressor 20.

[0069] like Figure 5 and Figure 6 As shown, the heater 80 can be positioned adjacent to the heat exchanger 50. For example, the heat exchanger 50 can be positioned above the heater 80, meaning the heat exchanger 50 and heater 80 can overlap. The heat exchange medium can pass through the heater 80, which can heat the heat exchange medium using electrical heating. Placing the heater 80 and heat exchanger 50 adjacent to each other can reduce the length of the heat exchange piping, thereby conserving internal space within the thermal management system. After flowing out of the heat exchanger 50, the heat exchange medium can flow into the heater 50, where heating can be selected based on the actual function of the thermal management system. It will be appreciated that the heater 80 and heat exchanger 50 perform heating and cooling functions, respectively, and typically do not operate simultaneously. Specifically, when the thermal management system is in the heating mode, only the heater 80 operates, while the heat exchanger 50 does not. When the thermal management system is in the cooling mode, only the heat exchanger 50 operates, while the heater 80 does not.

[0070] Preferably, heater 80 may be a PTC ceramic (positive temperature coefficient ceramic) heater. The resistance of PTC ceramics is very low at room temperature, but increases suddenly by a factor of a thousand to a million as the temperature rises to a certain point (the transition temperature), returning to its original value as the temperature drops. Furthermore, PTC ceramic heaters offer excellent safety features, effectively preventing overheating and preventing thermal runaway.

[0071] Preferably, a temperature sensor may also be provided inside the heat exchanger 50 and / or the heater 80 to facilitate monitoring of the temperature control effect thereof.

[0072] It is understood that the specific configuration of the thermal management system provided in this embodiment is not particularly limited. The "ground" in the ground thermal management system is relative to the electric aircraft, that is, the ground thermal management system is not set on the electric aircraft and will not fly with the electric aircraft. Exemplarily, the thermal management system can be a fixed device set on the electric aircraft landing pad, which can be set on the ground surface or semi-buried underground. The thermal management system can also be a movable device, which can be set on a wheeled movable platform. The thermal management system can also be integrated with other ground support equipment of the electric aircraft to form a comprehensive ground support equipment with rich functions.

[0073] It will be appreciated that the thermal management system provided in this embodiment can not only provide thermal management for the electric aircraft's batteries, but can also exchange heat with other devices in the electric aircraft that require thermal management. For example, the electric aircraft's cabin and / or cockpit may be equipped with an air conditioning system, and this thermal management system can be connected to and exchange heat with the air conditioning system to help regulate the cabin and / or cockpit temperature.

[0074] The embodiment of the present application also provides an electric aircraft, which can use the above-mentioned thermal management system to perform thermal management of batteries (battery packs, battery systems). The electric aircraft has a battery pack for powering the electric aircraft, and the battery pack is provided with a heat exchange system, and the heat exchange system may include a heat exchange pipe that can circulate a heat exchange medium. The heat exchange pipe may be provided with a joint that can be connected to the water inlet pipe 11 and the water outlet pipe 12 of the thermal management system. It can be understood that the above-mentioned thermal management system can meet at least part of the thermal management requirements of the electric aircraft, so the electric aircraft only needs to be provided with a simple thermal management device. Compared with electric aircraft that need to rely entirely on their own thermal management equipment, the electric aircraft provided in this embodiment can use a thermal management device that takes up less space and consumes less power.

[0075] It is understood that after an electric aircraft returns to the ground after a certain period of operation, it can be connected to a thermal management system and use its cooling function to cool the battery. This prevents the battery from overheating, which could lead to thermal runaway risks and shorten the battery life. When the electric aircraft is used in a lower ambient temperature, it can be connected to a thermal management system before operation and use its heating function to heat the battery. This prevents the battery from overheating and affecting its performance.

[0076] After connecting the heat exchange pipes of the battery pack of the electric aircraft to the thermal management system, the heating or cooling function of the thermal management system can be selected through the control panel 14. When the heating function is selected, the control unit 60 turns on the heater 80 to generate heat and transfer the heat to the heat exchange medium. The operation of the water pump 90 can cause the heat exchange medium to circulate between the electric aircraft and the thermal management system, thereby preheating the batteries of the electric aircraft. When the cooling function is selected, the control unit 60 controls the operation of the compressor 20 to drive the refrigerant to start circulating. The refrigerant enters the condenser 30 to cool down, and then enters the heat exchanger 50 to exchange heat with the heat exchange medium. The operation of the water pump 90 can cause the heat exchange medium to circulate between the electric aircraft and the thermal management system, thereby cooling the batteries of the electric aircraft.

[0077] Embodiments of the present application also provide an electric aircraft system comprising the aforementioned electric aircraft and the aforementioned ground-based thermal management system. The electric aircraft includes a battery pack for powering the electric aircraft, and the battery pack is provided with a heat exchange system comprising heat exchange pipes capable of circulating a heat exchange medium. The heat exchange pipes are capable of connecting to a water inlet pipe 11 and a water outlet pipe 12 of the ground-based thermal management system, allowing the heat exchange medium to circulate between the electric aircraft and the ground-based thermal management system for heat exchange.

[0078] The following briefly describes some of the beneficial effects of the above-mentioned embodiments of the present application.

[0079] The ground-based thermal management system provided in embodiments of the present application can be installed on the ground. It can cool or heat the batteries of an electric aircraft according to actual environmental conditions and operational needs, maintaining the batteries at an optimal operating temperature. The electric aircraft and electric aircraft systems provided in embodiments of the present application are adaptable to this ground-based thermal management system, which effectively manages thermal energy while conserving internal space and reducing electrical energy consumption. Furthermore, it can reduce battery charging time and increase the range of the electric aircraft.

[0080] It is understood that in this application, when the number of parts or components is not specifically limited, the number may be one or more, and the term "plurality" herein refers to two or more. Where the number of parts or components is shown in the drawings and / or described in the specification as a specific number, such as two, three, or four, the specific number is generally illustrative and not restrictive, and may be understood as a plurality, i.e., two or more. However, this does not mean that this application excludes the case of one.

[0081] It should be understood that the above embodiments are merely exemplary and are not intended to limit the present application. Those skilled in the art may make various modifications and changes to the above embodiments based on the teachings of the present application without departing from the scope of the present application.

Claims

1. A ground thermal management system, characterized in that: The ground thermal management system is used to be arranged on the ground, The ground thermal management system includes a water inlet pipe, a water outlet pipe, a compressor, a condenser, a heat exchanger, a control unit and a heater. The water inlet pipe and the water outlet pipe are used to be connected to the electric aircraft, so that the heat exchange medium can circulate between the ground thermal management system and the electric aircraft for heating or cooling the electric aircraft. The water inlet pipe is connected to the water outlet pipe via the heat exchanger and the heater, so that the heat exchange medium can exchange heat via the heat exchanger or the heater. The compressor, the condenser and the heat exchanger are connected in sequence, so that the refrigerant passes into the heat exchanger after dissipating heat in the condenser to exchange heat with the heat exchange medium. The heat exchanger is connected to the compressor so that the refrigerant can flow back to the compressor to form a refrigerant cycle. The control unit is connected to the compressor, the condenser, the heat exchanger, and the heater to control the operation of the ground thermal management system.

2. The ground thermal management system according to claim 1, characterized in that: It also includes one or more cooling fans, which are arranged adjacent to the condenser. The cooling fans can draw air from the condenser to the outside to improve the heat exchange effect of the condenser.

3. The ground thermal management system according to claim 1, characterized in that: It also includes a liquid accumulator, which is arranged in the refrigerant flow path between the heat exchanger and the compressor, so that the refrigerant flows from the heat exchanger through the liquid accumulator and then flows into the compressor. The liquid accumulator can separate the gaseous refrigerant and the liquid refrigerant to protect the compressor.

4. The ground thermal management system according to claim 1, characterized in that: It also includes a water pump, which is connected to the water inlet pipe and / or the water outlet pipe to provide flow power to the heat exchange medium.

5. The ground thermal management system according to claim 1, characterized in that: It also includes a control panel, which is connected to the control unit and is used to control the operation of the ground thermal management system and monitor its working status and operating parameters.

6. The ground thermal management system according to claim 5, characterized in that: It also includes a power interface and a shell, the shell at least partially shields the ground thermal management system, the water inlet pipe, the water outlet pipe, the power interface and the control panel are arranged on a surface of the shell, and at least part of the end portions of the water inlet pipe and the water outlet pipe extend from the inside of the shell to the outside of the shell.

7. The ground thermal management system according to claim 1, characterized in that: The refrigerant inlet of the heat exchanger is provided with a throttle valve to adjust the pressure and flow of the refrigerant. The water inlet pipe and / or the water outlet pipe are provided with a temperature sensor, and the ends of the water inlet pipe and the water outlet pipe are provided with connection joints with disconnect valves.

8. The ground thermal management system according to claim 1, characterized in that: The heater is a positive temperature coefficient ceramic heater. The heater and the heat exchanger are arranged adjacent to each other. A temperature sensor is arranged inside the heater and / or the heat exchanger.

9. An electric aircraft, characterized in that: The invention comprises a battery pack for powering an electric aircraft, wherein the battery pack is provided with a heat exchange system, and the heat exchange system has a heat exchange pipe capable of circulating a heat exchange medium. The heat exchange pipe can be connected to the water inlet pipe and the water outlet pipe of the ground thermal management system according to any one of claims 1 to 8, so that the heat exchange medium can circulate between the electric aircraft and the ground thermal management system for heat exchange.

10. An electric aircraft system, characterized in that: comprising an electric aircraft and a ground thermal management system according to any one of claims 1 to 8, The electric aircraft includes a battery pack for powering the electric aircraft. The battery pack is provided with a heat exchange system. The heat exchange system has a heat exchange pipe capable of circulating a heat exchange medium. The heat exchange pipe can be connected to the water inlet pipe and the water outlet pipe of the ground thermal management system, so that the heat exchange medium can circulate and exchange heat between the electric aircraft and the ground thermal management system.

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