Ground heat management system, electric aircraft and electric aircraft system

Abstract

The invention 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 been put into commercial operation, and their application scenarios include but are not limited to low-altitude sightseeing, urban passenger transport, regional passenger transport, cargo transportation, personal use and emergency medical rescue services. A large amount of heat will be generated during the operation of the power system and battery system of the electric aircraft. If this heat cannot be effectively managed and dissipated, it will affect the normal function and operating performance of the electric aircraft.

[0003] The existing form of battery thermal management for electric aircraft is onboard thermal management, that is, the heat sink is integrated into the electric aircraft, which includes air cooling and liquid cooling. Among them, the air-cooled heat sink is large in size, has high requirements for ambient temperature, and has low heat dissipation efficiency, and cannot meet the high-power and high-current application scenarios of electric aircraft batteries. Compared with air-cooled heat sinks, liquid-cooled heat sinks are more efficient, more flexible in layout, have lower requirements for ambient temperature, and are more reliable. However, the liquid-cooled heat sink consumes a lot of electricity during operation, which will reduce the endurance of the electric aircraft and increase the charging time of the electric aircraft, and cannot meet the commercial operation requirements of the electric aircraft. Summary of the invention

[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 arranged 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 arranged 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 the condenser dissipates heat to exchange heat with the heat exchange medium, and 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 disposed adjacent to the condenser and are capable of drawing air from the condenser to the outside to enhance the heat exchange effect of the condenser.

[0013] In at least one possible embodiment, the ground thermal management system also 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 implementation, 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 implementation, the ground thermal management system further 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.

[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 ends 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 connecting joints with disconnect stop valves.

[0019] In at least one possible implementation, the heater is a positive temperature coefficient ceramic heater, the heater and the heat exchanger are disposed adjacent to each other, and a temperature sensor is disposed 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, wherein the battery pack is provided with a heat exchange system, wherein 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 above-mentioned 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 thermal management system provided by the present application can be set on the ground, and it can cool down or heat the electric aircraft, especially the battery, according to the actual environmental conditions and operating needs, so that the battery of the electric aircraft is at a better working temperature. The electric aircraft and electric aircraft system provided by the present application can be adapted to the above-mentioned ground thermal management system, which can save the internal space of the aircraft and reduce the power consumption of the aircraft while performing effective thermal management. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0027] Figure 2 It 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 It is a 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 an embodiment of the present application.

[0030] Figure 5 It 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 a 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 connector

[0037] 14 Control Panel

[0038] 15 Housing

[0039] 151 Fan vents

[0040] 20 Compressor

[0041] 30 Condenser

[0042] 40 Cooling fan

[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 exemplary embodiments of the present application are described below 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 methods of the present application, nor to limit the scope of the present application.

[0050] The embodiments of the present application provide a ground thermal management system (hereinafter, sometimes referred to as a "thermal management system"), which can be set on the ground for heating and cooling operations (i.e. thermal management operations) of 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, 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. 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. Exemplarily, the heat exchange medium here can be water, but the type of heat exchange medium is not limited thereto.

[0052] Preferably, the water inlet pipe 11 and / or the water outlet pipe 12 may be provided with a temperature sensor 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, so as to more accurately regulate the working state of the thermal management system, thereby enabling the battery of the electric aircraft to be at an optimal working temperature.

[0053] Preferably, the water inlet pipe 11 and the water outlet pipe 12 may be provided with a connecting joint for connecting 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 may 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 may 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 may 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 may also be connected to a section of hose to facilitate its connection with the electric aircraft.

[0054] Preferably, the thermal management system may also be provided with 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. Exemplarily, 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 an external power source (especially 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 wires, and the control unit 60 can further connect to various electrical devices of the thermal management system and provide the required power to them.

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

[0057] The control unit 60 can be connected (including electrical connection and communication connection) to various devices and components of the thermal management system to control the operation of the various devices and components of the thermal management system to achieve the operation of heating or cooling 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 the working status and operating parameters through the control panel 14.

[0058] Preferably, the control unit 60 can automatically or according to instructions control the thermal management system to heat or cool the battery of the electric aircraft. The heating and cooling functions can be set to multiple gears to correspond to different working hours, temperature control efficiencies, etc. More preferably, the control unit 60 can also automatically or according to instructions adjust its working gear according to the specific water temperature of the water inlet pipe 11 and / or the water outlet pipe 12 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. 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 pipes 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 do work, so as to increase the medium and low pressure gaseous refrigerant to high pressure gaseous refrigerant. The compressor 20 can also provide power for the flow cycle of the refrigerant by discharging the high pressure gaseous refrigerant, so that the refrigerant circulates between the various devices of the thermal management system.

[0061] Preferably, tetrafluoroethane (R134a) can be selected as the refrigerant. It can be 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 may be connected to the compressor 20, and the refrigerant may enter the condenser 30 from the compressor 20 via a refrigeration pipeline. The refrigerant may exchange heat in the condenser 30, that is, the high-temperature and high-pressure gaseous refrigerant may be condensed into a liquid refrigerant in the condenser 30 and release heat during the phase change. The heat released by the phase change of the refrigerant may be discharged into the air. The condenser 30 may have a sheet-shaped heat exchange plate, and the refrigerant may 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, and the heat dissipation fan 40 can draw 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 a plurality of 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 to replace 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 to the heat exchanger 50 (directly or indirectly) 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, and the refrigerant is recirculated to the condenser to discharge the heat into the air. It can be 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) so as to facilitate the refrigerant to absorb heat and vaporize in 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 refrigeration effect (heat exchange effect) of the heat exchanger 50 .

[0068] The refrigerant (gaseous state) that absorbs heat in the heat exchanger 50 can return to the compressor 20 for compression and then enter the condenser 30 to dissipate heat, thereby forming a refrigerant cycle. The accumulator 70 can be arranged in the refrigerant flow path between the heat exchanger 50 and the compressor 20, that is, the refrigerant can flow through the accumulator 70 after flowing out of the heat exchanger 50 and then enter the compressor 20. The accumulator 70 (low-pressure accumulator) can separate the gaseous refrigerant and the liquid refrigerant (it can be understood that there are still some liquid refrigerant droplets in the refrigerant flowing out of the heat exchanger 50) to prevent the compressor from liquid hammer (abnormal shock caused by the compressor sucking in liquid), which is used to protect the compressor 20.

[0069] like Figure 5 and Figure 6 As shown, the heater 80 can be arranged adjacent to the heat exchanger 50. Exemplarily, the heat exchanger 50 can be arranged on the upper part of the heater 80, that is, the heat exchanger 50 and the heater 80 can be arranged overlappingly. The heat exchange medium can pass through the heater 80, and the heat exchanger 80 can heat the heat exchange medium in the form of electric heating. The heater 80 and the heat exchanger 50 are arranged adjacent to each other to reduce the length of the heat exchange pipeline, thereby saving the internal space of the thermal management system. After the heat exchange medium flows out of the heat exchanger 50, it can flow into the heater 50, and the heat exchange medium can be heated according to the actual function of the thermal management system. It can be understood that the heater 80 and the heat exchanger 50 respectively assume the heating and cooling functions, and usually do not operate at the same time. That is, when the thermal management system selects the heating function, only the heater 80 operates and the heat exchanger 50 does not operate; when the thermal management system selects the cooling function, only the heat exchanger 50 operates and the heater 80 does not operate.

[0070] Preferably, the heater 80 can be a PTC ceramic (positive temperature coefficient ceramic) heater. The resistance of PTC ceramics is very small at room temperature, but it will suddenly increase by a thousand to a million times as the temperature rises to a certain temperature (transition temperature), and return to its original state when the temperature drops. Furthermore, the PTC ceramic heater has excellent safety performance, which can effectively avoid excessive heating temperature and is not prone to thermal runaway.

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

[0072] It can be understood that the specific setting form of the thermal management system provided in this embodiment is not particularly limited. The "ground" in which the ground thermal management system is set on the ground 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 apron, which can be set on the surface or half 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 electric aircraft to form a comprehensive ground support equipment with rich functions.

[0073] It can be understood that the thermal management system provided in this embodiment can not only perform thermal management for the battery of the electric aircraft, but also exchange heat with other devices of the electric aircraft that need thermal management. Exemplarily, the cabin and / or cockpit of the electric aircraft can be provided with an air conditioning system, and the thermal management system can also be connected to the air conditioning system and exchange heat with the air conditioning system to help adjust the temperature of the cabin and / or cockpit.

[0074] The embodiments of the present application also provide 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 simple thermal management equipment. Compared with electric aircraft that need to rely entirely on their own thermal management equipment, the electric aircraft provided in this embodiment can use thermal management equipment that occupies less space and consumes less power.

[0075] It is understandable that when the electric aircraft returns to the ground after running for a certain period of time, it can be connected to the thermal management system and use the cooling function of the thermal management system to cool the battery of the electric aircraft to prevent the battery temperature from being too high and causing the risk of thermal runaway and affecting the battery life, etc. When the temperature of the electric aircraft is low, it can be connected to the thermal management system before the electric aircraft is operated and use the heating function of the thermal management system to heat the battery of the electric aircraft to prevent the battery temperature from being too low and affecting its working performance.

[0076] After connecting the heat exchange pipe 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 achieving battery preheating 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 achieving battery cooling of the electric aircraft.

[0077] The embodiment of the present application also provides an electric aircraft system, which includes the aforementioned electric aircraft and the aforementioned ground 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, and the heat exchange system has 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 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.

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

[0079] The ground thermal management system provided by the embodiment of the present application can be set on the ground, which can cool or heat the battery of the electric aircraft according to the actual environmental conditions and operating needs, so that the battery of the electric aircraft is at an optimal operating temperature. The electric aircraft and electric aircraft system provided by the embodiment of the present application can be adapted to the above-mentioned ground thermal management system, which can save the internal space of the aircraft and reduce the power consumption of the aircraft while performing effective thermal management. It can also reduce the battery charging time of the electric aircraft and increase its cruising range.

[0080] It is understood that in the present application, when the number of parts or components is not particularly limited, the number may be one or more, and the multiple here means two or more. For the case where the number of parts or components shown in the drawings and / or described in the specification is a specific number such as two, three, four, etc., the specific number is usually exemplary and not restrictive, and it can be understood as multiple, that is, two or more, but this does not mean that the present 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 under the guidance 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 comprises a water inlet pipe (11), a water outlet pipe (12), a compressor (20), a condenser (30), a heat exchanger (50), a control unit (60) and a heater (80). The water inlet pipe (11) and the water outlet pipe (12) 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 (11) is 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 compressor (20), the condenser (30) and the heat exchanger (50) are connected in sequence, so that the refrigerant, after dissipating heat in the condenser (30), passes into the heat exchanger (50) to exchange heat with the heat exchange medium, and the heat exchanger (50) is connected to the compressor (20) so that the refrigerant can flow back to the compressor (20) to form a refrigerant cycle. The control unit (60) is connected to the compressor (20), the condenser (30), the heat exchanger (50) and the heater (80) 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 heat dissipation fans (40), which are arranged adjacent to the condenser (30). The heat dissipation fans (40) are capable of extracting airflow from the condenser (30) to the outside to improve the heat exchange effect of the condenser (30).

3. The ground thermal management system according to claim 1, characterized in that: The invention also includes a liquid accumulator (70), which is arranged in the refrigerant flow path between the heat exchanger (50) and the compressor (20), so that the refrigerant flows from the heat exchanger (50) through the liquid accumulator (70) and then flows into the compressor (20). The liquid accumulator (70) can separate the gaseous refrigerant and the liquid refrigerant, so as to protect the compressor (20).

4. The ground thermal management system according to claim 1, characterized in that: It also includes a water pump (90), which is connected to the water inlet pipe (11) and / or the water outlet pipe (12) to provide flow power for the heat exchange medium.

5. The ground thermal management system according to claim 1, characterized in that: It also comprises a control panel (14), which is connected to the control unit (60) and is used to control the operation of the ground thermal management system and monitor its working state and operating parameters.

6. The ground thermal management system according to claim 5, characterized in that: It also comprises a power interface (13) and a shell (15), wherein the shell (15) at least partially shields the ground thermal management system, the water inlet pipe (11), the water outlet pipe (12), the power interface (13) and the control panel (14) are arranged on a surface of the shell (15), and at least part of the ends of the water inlet pipe (11) and the water outlet pipe (12) extend from the inside of the shell (15) to the outside of the shell (15).

7. The ground thermal management system according to claim 1, characterized in that: The refrigerant inlet of the heat exchanger (50) is provided with a throttle valve (51) to adjust the pressure and flow of the refrigerant. The water inlet pipe (11) and / or the water outlet pipe (12) are provided with a temperature sensor, and the ends of the water inlet pipe (11) and the water outlet pipe (12) are provided with connection joints with disconnection stop valves.

8. The ground thermal management system according to claim 1, characterized in that: The heater (80) is a positive temperature coefficient ceramic heater. The heater (80) and the heat exchanger (50) are arranged adjacent to each other. A temperature sensor is arranged inside the heater (80) and / or the heat exchanger (50).

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 (11) and the water outlet pipe (12) of the ground thermal management system described in 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: The invention comprises 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 (11) and the water outlet pipe (12) 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.

Images