EVTOL thermal management system and aircraft

Abstract

The utility model discloses an eVTOL heat management system and an aircraft, and relates to the field of aircrafts, the heat management system comprises a motor loop, a battery loop and a control mechanism, the motor loop comprises a heat dissipation mechanism and at least one motor, the heat dissipation mechanism and the motor can be connected in series through a first pipeline, and the first pipeline is used for circulating a heat carrying medium; when the number of the motors is at least two, the at least two motors are connected in parallel through the first pipeline, the heat dissipation mechanism is used for cooling the motors, the battery loop comprises at least one battery pack, and when the number of the battery packs is at least two, the at least two battery packs are connected in parallel through the second pipeline. The second pipeline is used for circulating a heat-carrying medium, the control mechanism is used for controlling the on-off of the motor loop and the battery loop and connecting the motor loop and the battery loop in series, the overall structure is simple, and the heat management efficiency is high.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, and in particular to an eVTOL thermal management system and an aircraft. Background Technology

[0002] eVTOL (Electric Vertical Take-off and Landing, hereinafter referred to as the aircraft) is an electrically powered aerial transportation device capable of vertical take-off and landing like a helicopter. It can operate within limited urban spaces without a runway, offering significant advantages for short-distance point-to-point transportation, especially in disaster or emergency situations, enabling efficient and rapid access to areas inaccessible by traditional means of transportation. The aircraft is powered by a battery pack and motors. Both the battery pack and motors generate heat during operation. Overheating of these components can easily lead to safety issues and pose a safety hazard. Utility Model Content

[0003] In view of this, the purpose of this utility model is to provide an eVTOL thermal management system and an aircraft, which can control the temperature of the aircraft's motor and battery pack, thereby improving the safety of the aircraft.

[0004] This utility model provides an eVTOL thermal management system, comprising:

[0005] The motor circuit includes a heat dissipation mechanism and at least one motor. The heat dissipation mechanism and the motor are connected in series via a first pipe for flowing a heat transfer medium. When there are at least two motors, the at least two motors are connected in parallel via the first pipe. The heat dissipation mechanism is used to cool the motors.

[0006] The battery circuit includes at least one battery pack. When there are at least two battery packs, the at least two battery packs are connected in parallel via a second conduit for flowing a heat transfer medium.

[0007] A control mechanism for controlling the on / off state of the motor circuit and the battery circuit, and for connecting the motor circuit and the battery circuit in series.

[0008] In one embodiment, the motor circuit includes a first pump body, which is connected in series with the motor through the first pipe and can also be connected in series with the heat dissipation mechanism through the first pipe. The first pump body is used to drive the flow of the heat transfer medium in the first pipe.

[0009] In one embodiment, the motor circuit includes a first valve, which is connected in series with the heat dissipation mechanism to either connect or disconnect the heat dissipation mechanism from the motor.

[0010] In one embodiment, the battery circuit includes a second pump body that is connected in series with the battery pack via the second pipe, and the second pump body is used to drive the flow of a heat transfer medium within the second pipe.

[0011] In one embodiment, the battery circuit further includes a second valve, which is connected in parallel with the battery pack via the second pipe. The second valve is used to connect or disconnect the battery pack from the second pump body.

[0012] In one embodiment, a storage mechanism is also included, which is in communication with the first pipe and the second pipe to circulate a heat transfer medium.

[0013] In one embodiment, the storage mechanism includes a first chamber and a second chamber, both of which store a heat transfer medium. The first chamber is connected to a second pipe, and the second chamber is connected to the first pipe.

[0014] In one embodiment, the motor circuit and the battery circuit are connected to the same storage mechanism.

[0015] In one embodiment, the motor circuit and / or the battery circuit includes a temperature measuring device for detecting the temperature of the motor and / or the battery pack.

[0016] This utility model also proposes an aircraft, including an airframe, on which the aforementioned eVTOL thermal management system is provided.

[0017] The beneficial effects of this utility model are as follows:

[0018] The motor circuit is designed with a heat transfer medium flowing through the first pipe to cool the motor, or a heat dissipation mechanism that works in conjunction with the heat transfer medium in the first pipe to cool the motor, thus preventing overheating and ensuring the motor's lifespan and operating efficiency. Similarly, the battery circuit is designed with a heat transfer medium flowing through the second pipe to cool the battery pack, ensuring its lifespan and operating efficiency. A control mechanism is used to implement circuit control. When the motor and battery circuits are connected in series, the heat dissipation mechanism can cool the battery pack, and the motor's heat can be used to insulate or heat the battery pack. The heat generated by the motor can be recovered and utilized as needed. The circuit structure is simple and has good thermal management efficiency, contributing to the lightweight design of the aircraft. Attached Figure Description

[0019] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this utility model and should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 This is a schematic diagram of a thermal management system according to an embodiment of the present invention;

[0021] Figure 2 This is a schematic diagram showing that the battery circuit and motor circuit are independent in one embodiment of the present invention;

[0022] Figure 3 This is another schematic diagram showing that the battery circuit and motor circuit are independent according to an embodiment of the present invention;

[0023] Figure 4 This is a schematic diagram showing the battery circuit and motor circuit connected in series according to an embodiment of the present invention;

[0024] Figure 5 This is another schematic diagram showing the battery circuit and motor circuit connected in series according to an embodiment of the present invention;

[0025] Figure 6 This is a schematic diagram of a short circuit in a battery pack according to an embodiment of the present invention;

[0026] Figure 7 This is a schematic diagram of a thermal management system according to another embodiment of the present invention;

[0027] Figure 8 This is a schematic diagram of a thermal management system according to another embodiment of the present invention;

[0028] Figure 9 This is a schematic diagram of a thermal management system according to an embodiment of the present invention.

[0029] In the picture:

[0030] 10. First pipe; 11. Heat dissipation mechanism; 12. Motor; 13. First pump body; 14. First valve; 15. Temperature measuring element; 16. Storage mechanism; 161. First chamber; 162. Second chamber;

[0031] 20. Second pipeline; 21. Battery pack; 22. Second pump body; 23. Second valve;

[0032] 31. Control mechanism;

[0033] 40. Control unit; 41. Detection unit; 42. Protection unit; 43. Input unit. Detailed Implementation

[0034] The specific embodiments of this utility model will now be described in detail with reference to the accompanying drawings. Obviously, the described embodiments are merely some, not all, of the embodiments of this utility model. Based on the description of this utility model, all other embodiments obtained by those skilled in the art without inventive effort are within the scope of protection of this utility model.

[0035] Unless otherwise explicitly specified and limited, the terms "setup," "installation," and "connection" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium. Those skilled in the art can understand the specific meaning of these terms based on the specific circumstances.

[0036] The terms “upper,” “lower,” “left,” “right,” “front,” “back,” “top,” “bottom,” “inner,” and “outer,” etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product is in use. They are used only for the convenience of description and simplification, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0037] The terms “first,” “second,” “third,” etc., are used merely to distinguish elements with similar properties, not to indicate or imply relative importance or a specific order.

[0038] The terms “include,” “comprising,” or any other variation thereof are intended to cover non-exclusive inclusion, which includes not only the elements listed but also other elements not expressly listed.

[0039] like Figure 1 As shown, the eVTOL thermal management system proposed in this utility model includes:

[0040] The motor circuit includes a heat dissipation mechanism 11 and at least one motor 12. The heat dissipation mechanism 11 and the motor 12 can be connected in series through a first pipe 10. The first pipe 10 is used to flow a heat transfer medium. When there are at least two motors 12, the at least two motors 12 are connected in parallel through the first pipe 10. The heat dissipation mechanism 11 is used to cool the motors 12.

[0041] The battery circuit includes at least one battery pack 21. When there are at least two battery packs 21, the at least two battery packs 21 are connected in parallel through a second pipe 20, which is used to circulate a heat transfer medium.

[0042] The control mechanism 31 is used to control the on / off state of the motor circuit and the battery circuit, so that the motor circuit and the battery circuit form independent heat transfer medium circulation, and to connect the motor circuit and the battery circuit in series.

[0043] Understandably, the parallel and series connections proposed in this utility model refer to connections achieved through a heat transfer medium, not electrical connections.

[0044] The motor circuit is configured such that the heat transfer medium flowing through the first pipe 10 can cool the motor 12, or the heat dissipation mechanism 11 can cooperate with the heat transfer medium flowing through the first pipe 10 to cool the motor 12, thereby preventing the motor 12 from overheating and ensuring the service life and working efficiency of the motor 12. The battery circuit is configured such that the heat transfer medium flowing through the second pipe 20 can cool the battery pack 21, thereby ensuring the service life and working efficiency of the battery pack 21. The control mechanism 31 is used to realize circuit control. When the motor circuit and the battery circuit are connected in series, the heat dissipation mechanism 11 can cool the battery pack 21, and the heat generated by the motor 12 can be used to keep the battery pack 21 warm or heat it. The heat generated by the motor 12 can be recovered and utilized as needed. The circuit structure is simple and has good thermal management efficiency, which is conducive to the lightweighting of the aircraft.

[0045] For example, the heat transfer medium is a mixture of ethylene glycol and water, which is used to realize the heat transport and transfer between the battery pack 21, the motor 12, or the battery pack 21, the motor 12 and the heat dissipation mechanism 11.

[0046] For example, the battery pack 21 is provided with a battery cell and a liquid cooling plate. The liquid cooling plate includes an inlet and an outlet that can be connected to the second pipe 20 so that a heat transfer medium can circulate inside the liquid cooling plate and form a circulation of the heat transfer medium through the inlet and outlet. The liquid cooling plate is used to exchange heat with the battery cell to cool the battery pack 21.

[0047] For example, the heat dissipation mechanism 11 is used to exchange heat with the outside of the first pipe 10 to dissipate the heat of the heat-carrying medium to the outside of the first pipe 10. Optionally, the heat dissipation mechanism 11 includes a fan that can carry away the heat of the heat-carrying medium through airflow.

[0048] Optionally, the heat dissipation mechanism 11 can cooperate with an external cold source to improve the heat dissipation efficiency of the heat dissipation mechanism 11, thereby improving the cooling efficiency of the battery pack 21 and / or the motor 12. Preferably, the cold source is located on the ground.

[0049] For example, such as Figure 1As shown, the number of heat dissipation mechanisms 11 is matched with the number of motors 12, and each heat dissipation mechanism 11 is connected in series with one motor 12 and then connected in parallel with other motors 12. This arrangement can improve the heat dissipation efficiency of the motors 12 and the battery pack 21, and facilitate separate management.

[0050] For example, such as Figure 7 and Figure 8 As shown, the number of heat dissipation mechanisms 11 is set to one, and at least two motors 12 are connected in parallel and then connected in series with the heat dissipation mechanism 11. This setting can reduce the weight of the entire thermal management system, which can both ensure the thermal management efficiency of the aircraft and reduce the weight of the aircraft.

[0051] For example, the heat dissipation mechanism 11 is integrated into the motor 12, which can both ensure the thermal management efficiency of the aircraft and reduce the weight of the aircraft.

[0052] In one embodiment, such as Figure 1 As shown, the motor circuit includes a first pump body 13, which is connected in series with the motor 12 through a first pipe 10 and can also be connected in series with the heat dissipation mechanism 11 through the first pipe 10. The first pump body 13 is used to drive the flow of the heat-carrying medium in the first pipe 10 to cool the motor 12, or to cooperate with the heat dissipation mechanism 11 to cool the motor 12.

[0053] For example, the first pump body 13 is an electronic water pump.

[0054] For example, such as Figure 1 As shown, the motor circuit also includes a first valve 14, which is connected in series with the heat dissipation mechanism 11 and is used to connect or disconnect the heat dissipation mechanism 11 from the motor 12.

[0055] When the heat dissipation mechanism 11 is not needed to cool the motor 12, the motor 12 is disconnected from the heat dissipation mechanism 11, that is, the heat transfer medium does not circulate at the heat dissipation mechanism 11. At this time, the motor 12 is cooled only by the circulation of the heat transfer medium in the first pipe 10. When the heat dissipation mechanism 11 is needed to cool the motor 12, the first valve 14 connects the motor 12 and the heat dissipation mechanism 11 in series. The heat transfer medium in the first pipe 10 is cooled by the heat dissipation mechanism 11, thereby cooling the motor 12.

[0056] Optionally, the first valve 14 may be a temperature control valve, an electronic on / off valve, or a mechanical valve.

[0057] Optionally, to ensure that most of the heat transfer medium can flow into the heat dissipation mechanism 11 when it is connected in series with the motor 12, the ratio of the pipe diameter of the first pipe 10 where the heat dissipation mechanism 11 is located to the pipe diameter of the first pipe 10 where the motor 12 is located is 2~3:1.

[0058] Optionally, such as Figure 8As shown, the first valve 14 is a three-way valve with three ports: E, F, and G. Port E is connected to the heat transfer medium inlet side of the heat dissipation mechanism 11 via the first pipe 10. Ports E and F can both be connected to the heat transfer medium outlet side of the heat dissipation mechanism 11. Port G can be connected to the heat transfer medium outlet side of the heat dissipation mechanism 11 and the control mechanism 31. When port E and G are connected, the heat dissipation mechanism 11 is disconnected from the motor 12, and no heat transfer medium flows through the heat dissipation mechanism 11. When port F and G are connected, the heat dissipation mechanism 11 and the motor 12 are connected in series.

[0059] For example, such as Figure 1 As shown, the motor circuit also includes a temperature measuring element 15, which is located on the inlet side and / or outlet side of the heat transfer medium of the motor 12. It is used to detect the temperature of the heat transfer medium flowing into and / or flowing out of the motor 12, so as to detect the temperature status of the motor 12 in real time and facilitate efficient thermal management of the motor 12.

[0060] In one embodiment, such as Figure 1 As shown, the battery circuit includes a second pump body 22, which can be connected in series with the battery pack 21 through a second pipe 20. The second pump body 22 is used to drive the flow of the heat transfer medium in the second pipe 20 to cool, heat or keep the battery pack 21 warm.

[0061] For example, the second pump body 22 is an electronic water pump.

[0062] For example, such as Figure 1 As shown, the battery circuit also includes a second valve 23, which is connected in parallel with the battery pack 21 through the second pipe 20. The second valve 23 is used to connect or disconnect the battery pack 21 from the second pump body 22.

[0063] When the battery circuit and the motor circuit are connected in series, the battery pack 21 is in an overheated state, and the heat dissipation mechanism 11 is unable to cool the battery pack 21, the second valve 23 connects the circuit in which it is located, the battery pack 21 is disconnected from the second pump body 22, and the second pump body 22 drives the heat transfer medium to flow through the second valve 23 to short-circuit the second pipe 20 where the battery pack 21 is located, so that the battery pack 21 does not get hotter and hotter.

[0064] Optionally, the second valve 23 may be a temperature control valve, an electronic on / off valve, or a mechanical valve.

[0065] Optionally, the second valve 23 is in the off state by default, so that the battery pack 21 can be directly connected to the battery circuit or connected in series with the motor circuit through the battery circuit. The second valve 23 will only open when needed, which helps to ensure the thermal management efficiency of the battery pack 21 and reduces the number of times the second valve 23 is used in non-emergency situations, thus ensuring the simplicity and efficiency of the entire thermal management system.

[0066] Optionally, to ensure that when the battery pack 21 is short-circuited by the second valve 23 under overheating conditions, most of the heat transfer medium can flow through the second valve 23 instead of flowing through the battery pack 21, the ratio of the pipe diameter of the second pipe 20 where the second valve 23 is located to the pipe diameter of the second pipe 20 where the battery pack 21 is located is 2~3:1.

[0067] For example, the battery circuit also includes a temperature measuring element 15, which is disposed on the inlet side and / or outlet side of the heat transfer medium of the battery pack 21, for detecting the temperature of the heat transfer medium flowing into and / or flowing out of the battery pack 21, so as to monitor the temperature status of the battery pack 21 in real time and facilitate efficient thermal management of the battery pack 21.

[0068] Optionally, the battery pack 21 is equipped with a temperature measuring element 15 at the battery cell to detect the temperature of the battery cell. For ease of understanding, the temperature of the battery pack 21 mentioned in this utility model refers to the temperature of its battery cells (i.e., the temperature inside the pack).

[0069] In one embodiment, such as Figure 1 As shown, the eVTOL thermal management system proposed in this utility model also includes a storage mechanism 16. The storage mechanism 16 includes a first chamber 161 and a second chamber 162. Both the first chamber 161 and the second chamber 162 store heat transfer medium. The first chamber 161 is connected to the second pipe 20, and the second chamber 162 is connected to the first pipe 10. Gas from the battery circuit can enter the first chamber 161, and the first chamber 161 can replenish the heat transfer medium to the battery circuit. Gas from the motor circuit can enter the second chamber 162, and the second chamber 162 can replenish the heat transfer medium to the motor circuit.

[0070] When the motor circuit and the battery circuit are independent heat transfer medium circuits, by setting the first chamber 161 and the second chamber 162, the heat transfer mediums of different temperatures in the battery circuit and the motor circuit can be managed separately, avoiding the flow of heat transfer mediums of different temperatures between the first pipe 10 and the second pipe 20, which would affect the thermal management efficiency. It can also reduce the overall weight of the aircraft, which is beneficial to the lightweighting of the aircraft.

[0071] In another embodiment, such as Figure 7 As shown, a storage mechanism 16 is connected to the motor circuit and the battery circuit respectively. The storage mechanism 16 can realize the exhaust and liquid replenishment of the first pipe 10 and the second pipe 20 respectively.

[0072] In yet another embodiment, such as Figure 8 As shown, the motor circuit and the battery circuit are connected to the same storage mechanism 16, which can realize the exhaust and replenishment of the first pipe 10 and the second pipe 20.

[0073] The storage mechanism 16 can exhaust and replenish liquid for the entire thermal management system, and can absorb the volume change of the heat transfer medium in the first pipe 10 and the second pipe 20 due to temperature changes. This helps to ensure uniform and efficient flow of the heat transfer medium, as well as to ensure the pressure stability of the heat transfer medium in the first pipe 10 and the second pipe 20.

[0074] The aircraft involved in this utility model includes the following states:

[0075] Ground status: refers to the state of an aircraft that is on the ground but has just finished a flight or has been in flight for some time.

[0076] Ready to fly: This refers to the state in which the aircraft is on the ground but about to take off;

[0077] Flight status: refers to the state of an aircraft flying in the air.

[0078] When the aircraft is on the ground, the battery pack 21 needs to be charged in some situations. When the aircraft has just finished flying for a short time, or when the ambient temperature is high and the temperature of the battery pack 21 is high, charging the battery pack 21 will result in low charging efficiency and a high risk of thermal runaway. Therefore, the battery pack 21 needs to be cooled down.

[0079] When the aircraft is on the ground and the flight time is long, the battery pack 21 needs to be charged in some cases. If the ambient temperature of the aircraft is too low, the temperature of the battery pack 21 will be too low, which will affect the charging efficiency and cause energy loss and waste. Therefore, the battery pack 21 needs to be heated or kept warm.

[0080] When the aircraft is in a ready-to-fly state, the temperature of the battery pack 21 needs to be kept at an optimal discharge temperature in preparation for subsequent takeoff;

[0081] When the aircraft is in flight, the temperature of the battery pack 21 and the motor 12 need to be kept at a suitable temperature to avoid affecting the aircraft's range.

[0082] In one embodiment, such as Figure 1 As shown, the control mechanism 31 includes four ports: A, B, C, and D. Ports A and B are located on the first pipe 10, and ports C and D are located on the second pipe 20. The control mechanism 31 is used to control the on / off states between the ports to achieve different circuit connection modes. When ports A and D are connected and ports B and C are connected, the motor circuit and the battery circuit are connected in series. When ports A and B are connected and ports C and D are connected, the motor circuit and the battery circuit are two independent heat transfer medium circuits.

[0083] For example, the control mechanism 31 uses a four-way valve.

[0084] For example, the control mechanism 31 may also employ several ordinary valves, several three-way valves, or a combination thereof.

[0085] Figure 2 and Figure 3 The bold lines in the text indicate the flow of the heat transfer medium, such as... Figure 2 As shown, when the aircraft is in flight, the battery pack 21 discharges and the control mechanism 31 operates, so that the motor circuit and the battery circuit form two independent heat transfer medium circuits.

[0086] In the motor circuit, the first pump body 13 operates, circulating the heat transfer medium in the motor circuit. When the temperature of the motor 12 has not reached the limit temperature, the heat dissipation mechanism 11 is disconnected from the motor 12, the heat dissipation mechanism 11 does not operate, and the heat transfer medium does not circulate at the heat dissipation mechanism 11; the motor 12 is cooled only through the circulation of the heat transfer medium. Figure 3 As shown, when the temperature of the motor 12 is greater than or equal to the limit temperature, the heat dissipation mechanism 11 works and is connected in series with the motor 12. The heat transfer medium flows through the heat dissipation mechanism 11 to cool down, and then the motor 12 is cooled by the circulation of the heat transfer medium.

[0087] In the battery circuit, the second pump 22 operates to circulate the heat transfer medium in the battery circuit. The circulating heat transfer medium carries away the heat in the battery pack 21 to cool the battery pack 21. As the temperature of the battery pack 21 gradually increases, the heat transfer medium in the first pipe 10 gradually heats up to make the temperature of the battery pack 21 change uniformly.

[0088] Figure 4 and Figure 5 The bold lines in the text indicate the flow of heat transfer medium. When the aircraft is on the ground or in a state of waiting to fly, the control mechanism 31 works to connect the motor circuit and the battery circuit in series to form a complete heat transfer medium circuit.

[0089] like Figure 4 As shown, when the temperature of the battery pack 21 is greater than the first set temperature T1, the first pump body 13, the second pump body 22 and the heat dissipation mechanism 11 work. The heat dissipation mechanism 11 can cool down the heat transfer medium flowing through it, and then cool the battery pack 21 and the motor 12 through the circulation of the heat transfer medium.

[0090] like Figure 5 As shown, when the temperature of the battery pack 21 is less than or equal to the first preset temperature T1, the motor 12, the first pump body 13 and the second pump body 22 work, the heat dissipation mechanism 11 does not work, and no heat transfer medium flows through the heat dissipation mechanism 11. The heat generated by the operation of the motor 12 heats or keeps the battery pack 21 warm.

[0091] Figure 6The bold lines in the text indicate the flow of the heat transfer medium, such as... Figure 6 As shown, when the heat dissipation mechanism 11 is working, if the temperature of the battery pack 21 cannot be reduced to the first set temperature T1 within the set time t, or if the temperature of the heat transfer medium at the inlet side of the battery pack 21 is greater than or equal to the third set temperature T3, or if the temperature of the heat transfer medium at the outlet side of the battery pack 21 is greater than or equal to the fourth set temperature T4, the second valve 23 is connected, causing the battery pack 21 to be disconnected from the second pump body 22, and the heat transfer medium does not flow in the second pipe 20 where the battery pack 21 is located.

[0092] like Figure 9 As shown, the eVTOL thermal management system of this utility model also includes:

[0093] The control unit 40 is communicatively connected to the control mechanism 31 and is used to send control commands to the control mechanism 31 to control the on / off state of the motor circuit and the battery circuit, and to connect the motor circuit and the battery circuit in series.

[0094] The detection unit 41 is communicatively connected to the control unit 40 and is used to detect the real-time related temperature of the motor 12 and the real-time related temperature of the battery pack 21, and send the data to the control unit 40.

[0095] The real-time related temperature of the motor 12 mentioned above can be the temperature of the motor 12 itself, or the temperature of the heat transfer medium on the inlet side and / or outlet side of the motor 12.

[0096] The real-time related temperature of the battery pack 21 mentioned above can be the temperature of the battery pack 21 itself, or the temperature of the heat transfer medium on the inlet side and / or outlet side of the battery pack 21.

[0097] For example, the control unit 40 sends control commands to the control mechanism 31 based on the real-time relevant temperature of the battery pack 21.

[0098] For example, the control unit 40 is integrated into the aircraft's central control unit.

[0099] For example, the detection unit 41 is a temperature measuring device 15 with signal transmission and reception functions.

[0100] In one embodiment, such as Figure 9 As shown, the control unit 40 is communicatively connected to the first valve 14 and is used to send control commands to the first valve 14 based on the real-time related temperature of the motor 12 and the real-time related temperature of the battery pack 21, so as to realize the series or disconnection control of the heat dissipation mechanism 11 and the motor 12.

[0101] In one embodiment, such as Figure 9As shown, the eVTOL thermal management system proposed in this utility model also includes a protection unit 42, which is communicatively connected to the second valve 23. The protection unit 42 is used to control the opening and closing of the second valve 23 based on the real-time related temperature of the battery pack 21, thereby realizing the series or disconnection control of the battery pack 21 and the second pump body 22.

[0102] In one embodiment, such as Figure 9 As shown, the eVTOL thermal management system proposed in this utility model also includes an input unit 43, which is communicatively connected to the control unit 40. The input unit 43 can manually input control commands and send them to the control unit 40, and then the control unit 40 sends control commands to the control mechanism 31.

[0103] For example, such as Figure 9 As shown, when the eVTOL thermal management system includes a protection unit 42, the input unit 43 is communicatively connected to at least one of the control unit 40 and the protection unit 42. The input unit 43 can manually input control commands and send them to the control unit 40 and / or the protection unit 42 to manually control the opening and closing of the second valve 23 based on the real-time relevant temperature of the battery pack 21.

[0104] The working principle of the eVTOL thermal management system proposed in this utility model is as follows:

[0105] Since the aircraft is on the ground, the battery pack 21 has a charging requirement, and the temperature of the battery pack 21 is greater than the first set temperature T1, the control mechanism 31 connects the motor circuit and the battery circuit in series, and the heat dissipation mechanism 11 is connected in series with the motor 12 to cool the battery pack 21.

[0106] Since the aircraft is on the ground, the battery pack 21 has a charging requirement, and the temperature of the battery pack 21 is less than or equal to the first set temperature T1, the control mechanism 31 connects the motor circuit and the battery circuit in series, the heat dissipation mechanism 11 is disconnected from the motor 12, the motor 12 works, and generates heat to heat or keep the battery pack 21 warm.

[0107] Since the aircraft is in a ready-to-fly state and the temperature of the battery pack 21 is greater than the second set temperature T2, the control mechanism 31 connects the motor circuit and the battery circuit in series, and the heat dissipation mechanism 11 is connected in series with the motor 12 to cool the battery pack 21.

[0108] Based on the aircraft being in a ready-to-fly state and the temperature of the battery pack 21 being less than or equal to the second set temperature T2, the control mechanism 31 connects the motor circuit and the battery circuit in series, disconnects the heat dissipation mechanism 11 from the motor 12, and the motor 12 operates to generate heat to heat or keep the battery pack 21 warm.

[0109] While the aircraft is in flight, the control mechanism 31 establishes independent closed heat transfer medium circuits for the motor circuit and the battery circuit. The heat transfer medium circulates in the first pipe 10 to cool the motor 12, and the heat transfer medium circulates in the second pipe 20 to cool the battery pack 21. Furthermore, based on the cooling requirements of the motor 12, the heat dissipation mechanism 11 is connected in series with or disconnected from the motor 12.

[0110] Since the battery pack 21 is in the charging process, if the temperature of the battery pack 21 fails to drop to the first set temperature T1 within the set time t, or if the temperature of the heat transfer medium at the inlet side of the battery pack 21 is greater than or equal to the third set temperature T3, or if the temperature of the heat transfer medium at the outlet side of the battery pack 21 is greater than or equal to the fourth set temperature T4, the heat transfer medium does not flow in the second pipe 20 where the battery pack 21 is located.

[0111] Furthermore, charging of battery pack 21 stops.

[0112] Furthermore, the second valve 23 is connected, disconnecting the battery pack 21 from the second pump body 22. The heat transfer medium flows through the second pipe 20 where the second valve 23 is located, meaning the heat transfer medium no longer flows through the battery pack 21. This prevents the temperature of the heat transfer medium from becoming too high and causing the temperature of the battery pack 21 to continue to increase, which is beneficial to protecting the charging safety of the battery pack 21.

[0113] For example, the first set temperature T1 is set according to the preferred charging temperature of the battery pack 21, and the second set temperature T2 is set according to the preferred discharging temperature of the battery pack 21.

[0114] This utility model also proposes an aircraft, including an airframe, on which the aforementioned eVTOL thermal management system is provided.

[0115] The above description is only a specific embodiment of this utility model, but the protection scope of this utility model is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this utility model should be included within the protection scope of this utility model.

Claims

1. An eVTOL thermal management system, characterized in that, include: The motor circuit includes a heat dissipation mechanism (11) and at least one motor (12). The heat dissipation mechanism (11) and the motor (12) can be connected in series through a first pipe (10). The first pipe (10) is used to flow a heat transfer medium. When there are at least two motors (12), at least two motors (12) are connected in parallel through the first pipe (10). The heat dissipation mechanism (11) is used to cool the motors (12). The battery circuit includes at least one battery pack (21). When the number of battery packs (21) is at least two, the at least two battery packs (21) are connected in parallel through a second pipe (20) for flowing a heat transfer medium. The control mechanism (31) is used to control the on / off state of the motor circuit and the battery circuit, and to connect the motor circuit and the battery circuit in series.

2. The eVTOL thermal management system of claim 1, wherein, The motor circuit includes a first pump body (13), which is connected in series with the motor (12) through the first pipe (10) and can be connected in series with the heat dissipation mechanism (11) through the first pipe (10). The first pump body (13) is used to drive the flow of the heat transfer medium in the first pipe (10).

3. The eVTOL thermal management system of claim 2, wherein, The motor circuit includes a first valve (14), which is connected in series with the heat dissipation mechanism (11) to connect or disconnect the heat dissipation mechanism (11) from the motor (12).

4. The eVTOL thermal management system of claim 1, wherein, The battery circuit includes a second pump body (22), which is connected in series with the battery pack (21) through the second pipe (20). The second pump body (22) is used to drive the flow of the heat transfer medium in the second pipe (20).

5. The eVTOL thermal management system of claim 4, wherein, The battery circuit also includes a second valve (23), which is connected in parallel with the battery pack (21) through the second pipe (20). The second valve (23) is used to connect or disconnect the battery pack (21) from the second pump body (22).

6. The eVTOL thermal management system of claim 1, wherein, It also includes a storage mechanism (16) connected to the first pipe (10) and the second pipe (20) to circulate a heat transfer medium.

7. The eVTOL thermal management system of claim 6, wherein, The storage mechanism (16) includes a first chamber (161) and a second chamber (162), both of which store a heat transfer medium. The first chamber (161) is connected to the second pipe (20), and the second chamber (162) is connected to the first pipe (10).

8. The eVTOL thermal management system of claim 6, wherein, The motor circuit and the battery circuit are connected to the same storage mechanism (16).

9. The eVTOL thermal management system of claim 1, wherein, The motor circuit and / or the battery circuit include a temperature measuring element (15) for detecting the temperature of the motor (12) and / or the battery pack (21).

10. An aircraft characterized by, It includes a body, on which is provided the eVTOL thermal management system as described in any one of claims 1 to 9.

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