EVTOL thermal management system, temperature control system and temperature control method

Abstract

An eVTOL thermal management system, a temperature control system and a temperature control method relate to the field of aircrafts, the thermal 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] The present invention relates to the technical field of aircraft, and particularly to an eVTOL thermal management system, a temperature control system, and a temperature control method. Background Art

[0002] An eVTOL (Electric Vertical Take-off and Landing, hereinafter all abbreviated as aircraft) is an air traffic device that can be driven by electricity and can take off and land vertically like a helicopter. It can take off and land in limited urban spaces without the need for a runway, and has great advantages in point-to-point short-distance transportation. Especially in disasters or emergencies, it can reach areas that are difficult for traditional means of transportation to reach efficiently and quickly. The aircraft is powered by a battery pack and an electric motor, and both the battery pack and the electric motor generate heat during operation. If the temperature of the electric motor and the battery pack is too high, it is very easy to cause safety problems for the aircraft, presenting potential safety hazards. Summary of the Invention In view of this, the purpose of the present invention is to provide an eVTOL thermal management system, a temperature control system, and a temperature control method, which can control the temperature of the electric motor and the battery pack of the aircraft, and is beneficial to improving the safety of the aircraft.

[0003] The present invention provides an eVTOL thermal management system, including: An electric motor circuit, including a heat dissipation mechanism and at least one electric motor. The heat dissipation mechanism and the electric motor can be connected in series through a first pipeline. The first pipeline is used for circulating a heat-carrying medium. When the number of electric motors is at least two, at least two electric motors are connected in parallel through the first pipeline. The heat dissipation mechanism is used to cool the electric motor. A battery circuit, including at least one battery pack. When the number of battery packs is at least two, at least two battery packs are connected in parallel through a second pipeline. The second pipeline is used for circulating a heat-carrying medium. And a control mechanism, which is used to control the on-off of the electric motor circuit and the battery circuit, and to connect the electric motor circuit and the battery circuit in series.

[0004] In one embodiment, the electric motor circuit includes a first pump. The first pump is connected in series with the electric motor through the first pipeline and can be connected in series with the heat dissipation mechanism through the first pipeline. The first pump is used to drive the heat-carrying medium in the first pipeline to flow.

[0005] In one embodiment, the electric motor circuit includes a first valve member. The first valve member is connected in series with the heat dissipation mechanism and is used to connect or disconnect the heat dissipation mechanism and the electric motor.

[0006] In one embodiment, the battery circuit includes a second pump body, which can be connected in series with the battery pack through the second pipeline, and the second pump body is used to drive the heat-carrying medium in the second pipeline to flow.

[0007] In one embodiment, the battery circuit further includes a second valve member, which is connected in parallel with the battery pack through the second pipeline, and the second valve member is used to connect or disconnect the battery pack in series with the second pump body.

[0008] In one embodiment, a storage mechanism is further included, and the storage mechanism is communicated with the first pipeline and the second pipeline to circulate the heat-carrying medium.

[0009] The present invention further provides an eVTOL temperature control system, which is applied to the above-mentioned eVTOL thermal management system, and includes: A control unit, which is communicatively connected with the control mechanism, is used to send control instructions to the control mechanism to control the on-off of the motor circuit and the battery circuit, and to connect the motor circuit in series with the battery circuit. A detection unit, which is communicatively connected with the control unit, is used to detect the real-time relevant temperature of the motor, and to detect the real-time relevant temperature of the battery pack, and send them to the control unit.

[0010] In one embodiment, a protection unit is further included, and the protection unit is communicatively connected with the second valve member, and the protection unit is used to control the switch of the second valve member based on the real-time relevant temperature of the battery pack.

[0011] The present invention further provides an eVTOL temperature control method, which is applied to the above-mentioned eVTOL thermal management system, and / or applied to the above-mentioned eVTOL temperature control system, and includes at least one of the following steps: S1. Based on the aircraft being in a ground state, the battery pack has a charging requirement, and the temperature of the battery pack is greater than the first set temperature T1, the control mechanism connects the motor circuit and the battery circuit in series, and the heat dissipation mechanism is connected in series with the motor to cool the battery pack. S2. Based on the aircraft being in a state after landing during flight, the battery pack has a charging requirement, and the temperature of the battery pack is less than or equal to the first set temperature T1, the control mechanism connects the motor circuit and the battery circuit in series, disconnects the heat dissipation mechanism from the motor, and the motor works to generate heat to heat or keep warm the battery pack. S3. Based on the aircraft being in a state of waiting for flight, and the temperature of the battery pack is greater than the second set temperature T2, the control mechanism connects the motor circuit and the battery circuit in series, and the heat dissipation mechanism is connected in series with the motor to cool the battery pack. S4. Based on the aircraft being in a state of waiting for flight and the temperature of the battery pack being less than or equal to the second set temperature T2, the control mechanism connects the motor circuit and the battery circuit in series, disconnects the heat dissipation mechanism from the motor, and the motor operates to generate heat to heat or keep warm the battery pack. S5. Based on the aircraft being in a flight state, the control mechanism forms an independent closed heat-carrying medium circuit for the motor circuit and the battery circuit. The heat-carrying medium in the first pipeline circulates to cool the motor, and the heat-carrying medium in the second pipeline circulates to cool the battery pack.

[0012] In one embodiment, the following steps are further included: S6. Based on the battery pack being in the charging process, the temperature of the battery pack 21 fails to drop to the first set temperature T1 within the set time t, or the temperature of the heat-carrying medium on the inlet side of the battery pack is greater than or equal to the third set temperature T3, or the temperature of the heat-carrying medium on the outlet side of the battery pack is greater than or equal to the fourth set temperature T4, the heat-carrying medium does not flow in the second pipeline where the battery pack is located.

[0013] The beneficial effects of the present invention are as follows: A motor circuit is provided. The heat-carrying medium flowing in the first pipeline can cool the motor, or the heat dissipation mechanism cooperates with the heat-carrying medium flowing in the first pipeline to cool the motor, so as to avoid the temperature of the motor being too high, which is beneficial to ensuring the service life and working efficiency of the motor; a battery circuit is provided. The heat-carrying medium flowing in the second pipeline can cool the battery pack, which is beneficial to ensuring the service life and working efficiency of the battery pack; the control mechanism is used to realize circuit control. When the motor circuit and the battery circuit are connected in series, the battery pack can be cooled through the heat dissipation mechanism, and the battery pack can be kept warm or heated through the heat generated by the motor. The heat generated by the motor can be recovered and utilized according to needs. The circuit structure is simple and has good thermal management efficiency, which is beneficial to the lightweight of the aircraft. Description of the Drawings

[0014] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following will briefly introduce the drawings required for the embodiments. It should be understood that the following drawings only show some embodiments of the present invention, so they should not be regarded as limiting the scope. For those of ordinary skill in the art, other related drawings can be obtained based on these drawings without creative efforts.

[0015] Figure 1 It is a schematic diagram of the thermal management system according to an embodiment of the present invention; Figure 2 It is a schematic diagram of the independence of the battery circuit and the motor circuit according to an embodiment of the present invention; Figure 3 It is another schematic diagram of the independence of the battery circuit and the motor circuit according to an embodiment of the present invention; Figure 4 Schematic diagram of the series connection of the battery circuit and the motor circuit according to an embodiment of the present invention; Figure 5 Another schematic diagram of the series connection of the battery circuit and the motor circuit according to an embodiment of the present invention; Figure 6 Schematic structural diagram of the short circuit of the battery pack according to an embodiment of the present invention; Figure 7 Schematic diagram of the thermal management system according to another embodiment of the present invention; Figure 8 Schematic diagram of the thermal management system according to yet another embodiment of the present invention; Figure 9 Schematic principle diagram of the temperature control system according to an embodiment of the present invention.

[0016] In the figure: 10. First pipeline; 11. Heat dissipation mechanism; 12. Motor; 13. First pump body; 14. First valve member; 15 - Temperature measuring member; 16. Storage mechanism; 161. First chamber; 162. Second chamber; 20. Second pipeline; 21. Battery pack; 22. Second pump body; 23. Second valve member; 31. Control mechanism; 40. Control unit; 41 - Detection unit; 42 - Protection unit; 43. Input unit. Specific embodiments

[0017] The following will describe in detail specific embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the description of the present invention without creative efforts shall fall within the scope of protection of the present invention.

[0018] Unless otherwise clearly defined and limited, terms such as "set", "installed", "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium. For those of ordinary skill in the art, the specific meanings of the above terms can be understood according to specific situations.

[0019] The orientation or positional relationship indicated by terms such as "upper", "lower", "left", "right", "front", "rear", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the inventive product is customarily placed during use. It is only for the convenience of description and to simplify the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on the present invention.

[0020] Terms such as "first", "second", "third", etc. are only used to distinguish elements with similar attributes, rather than indicating or implying relative importance or a specific order.

[0021] The term "comprising", "including" or any other variant thereof is intended to cover non-exclusive inclusion. In addition to the listed elements, it may also include other elements not expressly listed.

[0022] As Figure 1 shown, the eVTOL thermal management system proposed by the present invention includes: A motor circuit, including 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 pipeline 10. The first pipeline 10 is used for circulating a heat-carrying medium. When the number of motors 12 is at least two, at least two motors 12 are connected in parallel through the first pipeline 10. The heat dissipation mechanism 11 is used to cool the motor 12. A battery circuit, including at least one battery pack 21. When the number of battery packs 21 is at least two, at least two battery packs 21 are connected in parallel through a second pipeline 20. The second pipeline 20 is used for circulating a heat-carrying medium. And a control mechanism 31, which is used to control the on-off of the motor circuit and the battery circuit, so that the motor circuit and the battery circuit respectively form independent heat-carrying medium cycles, and is used to connect the motor circuit in series with the battery circuit.

[0023] It can be understood that the parallel connection and series connection proposed by the present invention both refer to the connection achieved through a heat-carrying medium, rather than an electrical connection.

[0024] A motor circuit is provided. The heat-carrying medium flowing in the first pipe 10 can cool the motor 12, or the heat dissipation mechanism 11 cooperates with the heat-carrying medium flowing in the first pipe 10 to cool the motor 12, so as to avoid the overheating of the motor 12, which is beneficial to ensuring the service life and working efficiency of the motor 12. A battery circuit is provided. The heat-carrying medium flowing in the second pipe 20 can cool the battery pack 21, which is beneficial to 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 in series, the battery pack 21 can be cooled through the heat dissipation mechanism 11, and the battery pack 21 can be insulated or heated through the heat generated by the motor 12. The heat generated by the motor 12 can be recovered and utilized according to requirements. The circuit structure is simple and has good thermal management efficiency, which is beneficial to the lightweight of the aircraft.

[0025] Exemplarily, the heat-carrying medium adopts a mixture of ethylene glycol and water, and the heat-carrying medium is used to realize the heat transportation and transfer between the battery pack 21, the motor 12, or the battery pack 21, the motor 12 and the heat dissipation mechanism 11.

[0026] Exemplarily, the battery pack 21 is internally provided with battery cells and a liquid cooling plate. The liquid cooling plate includes a liquid inlet and a liquid outlet that can communicate with the second pipe 20, so that the heat-carrying medium can flow inside the liquid cooling plate, and a cycle of the heat-carrying medium is formed through the liquid inlet and the liquid outlet. The liquid cooling plate is used to exchange heat with the battery cells to cool the battery pack 21.

[0027] Exemplarily, 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, which can take away the heat of the heat-carrying medium through air flow.

[0028] 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, and then improve the cooling efficiency of the battery pack 21 and / or the motor 12. Preferably, the cold source is located on the ground.

[0029] Exemplarily, as Figure 1 shown, the number of the heat dissipation mechanisms 11 is matched with the number of the motors 12, and each heat dissipation mechanism 11 is in series with one motor 12 and then in parallel with other motors 12. With such a setting, the heat dissipation efficiency of the motor 12 and the battery pack 21 can be improved, and it is convenient for separate management.

[0030] Exemplarily, as Figure 7 and Figure 8 shown, the number of the heat dissipation mechanisms 11 is set to one. After at least two motors 12 are in parallel and then in series with the heat dissipation mechanism 11, with such a setting, the weight of the entire thermal management system can be reduced, which can not only ensure the thermal management efficiency of the aircraft but also reduce the weight of the aircraft.

[0031] Exemplarily, the heat dissipation mechanism 11 is integrated with the motor 12, which can not only ensure the thermal management efficiency of the aircraft, but also reduce the weight of the aircraft.

[0032] In one embodiment, as Figure 1 shown, the motor circuit includes a first pump body 13. The first pump body 13 is connected in series with the motor 12 through a first pipeline 10 and can be connected in series with the heat dissipation mechanism 11 through the first pipeline 10. The first pump body 13 is used to drive the heat-carrying medium in the first pipeline 10 to flow, so as to cool the motor 12 or cooperate with the heat dissipation mechanism 11 to cool the motor 12.

[0033] Exemplarily, the first pump body 13 adopts an electronic water pump.

[0034] Exemplarily, as Figure 1 shown, the motor circuit further includes a first valve member 14. The first valve member 14 is connected in series with the heat dissipation mechanism 11 and is used to connect or disconnect the heat dissipation mechanism 11 and the motor 12 in series.

[0035] When the heat dissipation mechanism 11 does not need to cool the motor 12, the motor 12 is disconnected from the heat dissipation mechanism 11, that is, the heat-carrying medium does not flow through the heat dissipation mechanism 11. At this time, the motor 12 is cooled only by the circulation of the heat-carrying medium in the first pipeline 10. When the heat dissipation mechanism 11 needs to cool the motor 12, the first valve member 14 connects the motor 12 and the heat dissipation mechanism 11 in series, and the heat-carrying medium in the first pipeline 10 is cooled by the heat dissipation mechanism 11, thereby cooling the motor 12.

[0036] Optionally, the first valve member 14 adopts a temperature control valve, an electronic on-off valve or a mechanical valve.

[0037] Optionally, to ensure that when the heat dissipation mechanism 11 is connected in series with the motor 12, most of the heat-carrying medium can flow into the heat dissipation mechanism 11, the diameter ratio of the first pipeline 10 where the heat dissipation mechanism 11 is located to the diameter of the first pipeline 10 where the motor 12 is located is 2-3:1.

[0038] Optionally, as Figure 8 shown, the first valve member 14 adopts a three-way valve, including three ports E, F, and G. Among them, the E port is connected to the heat-carrying medium inlet side of the heat dissipation mechanism 11 through the first pipeline 10, and both the E port and the F port can be connected to the heat-carrying medium outlet side of the heat dissipation mechanism 11, and the G port can be connected to the heat-carrying medium outlet side of the heat dissipation mechanism 11 and the control mechanism 31. When the EG ports are connected, the heat dissipation mechanism 11 is disconnected from the motor 12, and the heat-carrying medium does not flow through the heat dissipation mechanism 11; when the FG ports are connected, the heat dissipation mechanism 11 is connected in series with the motor 12.

[0039] Exemplarily, as Figure 1As shown, the motor circuit further includes a temperature measuring element 15. The temperature measuring element 15 is arranged on the heat-carrying medium inlet side and / or outlet side of the motor 12, and is used to detect the temperature of the heat-carrying medium flowing into and / or out of the motor 12, so as to detect the temperature state of the motor 12 in real time, which is convenient for efficiently managing the heat of the motor 12.

[0040] In one embodiment, as Figure 1 shown, the battery circuit includes a second pump body 22. The second pump body 22 can be connected in series with the battery pack 21 through the second pipeline 20. The second pump body 22 is used to drive the heat-carrying medium in the second pipeline 20 to flow, so as to cool, heat or keep warm the battery pack 21.

[0041] Exemplarily, the second pump body 22 adopts an electronic water pump.

[0042] Exemplarily, as Figure 1 shown, the battery circuit further includes a second valve member 23. The second valve member 23 is connected in parallel with the battery pack 21 through the second pipeline 20. The second valve member 23 is used to connect or disconnect the battery pack 21 in series with the second pump body 22.

[0043] When the battery circuit is connected in series with the motor circuit, the battery pack 21 is in an overheated state, and the heat dissipation mechanism 11 cannot cool the battery pack 21, the second valve member 23 makes the circuit where it is located connected, the battery pack 21 is disconnected from the second pump body 22, and the second pump body 22 drives the heat-carrying medium to flow through the second valve member 23, so as to short-circuit the second pipeline 20 where the battery pack 21 is located, so that the temperature of the battery pack 21 will not become higher and higher.

[0044] Optionally, the second valve member 23 adopts a temperature control valve, an electronic on-off valve or a mechanical valve.

[0045] Optionally, the second valve member 23 is default in the off state, 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 member 23 will only open when needed, which is beneficial to ensuring the heat management efficiency of the battery pack 21, reducing the working times of the second valve member 23 in non-emergency situations, and ensuring the simplicity and efficiency of the entire heat management system.

[0046] Optionally, to ensure that when the battery pack 21 is short-circuited through the second valve member 23 in the case of overheating, most of the heat-carrying medium can flow through the second valve member 23 instead of flowing through the battery pack 21, the ratio of the pipe diameter size of the second pipeline 20 where the second valve member 23 is located to the pipe diameter size of the second pipeline 20 where the battery pack 21 is located is 2-3:1.

[0047] Exemplarily, the battery circuit further includes a temperature measuring element 15 disposed on the inlet side and / or the outlet side of the heat-carrying medium of the battery pack 21 for detecting the temperature of the heat-carrying medium flowing into and / or out of the battery pack 21 to monitor the temperature state of the battery pack 21 in real time, facilitating efficient thermal management of the battery pack 21.

[0048] Optionally, a temperature measuring element 15 is provided at the battery cells of the battery pack 21 to detect the temperature of the battery cells. For ease of understanding, the temperature of the battery pack 21 mentioned in the present invention refers to the temperature of its battery cells (i.e., the internal temperature of the pack).

[0049] In one embodiment, as Figure 1 shown, the eVTOL thermal management system proposed by the present invention further includes a storage mechanism 16. The storage mechanism 16 includes a first chamber 161 and a second chamber 162. Heat-carrying media are stored in both the first chamber 161 and the second chamber 162. The first chamber 161 is connected to the second pipeline 20, and the second chamber 162 is connected to the first pipeline 10. The gas in the battery circuit can enter the first chamber 161, and the first chamber 161 can supplement the heat-carrying medium to the battery circuit. The gas in the motor circuit can enter the second chamber 162, and the second chamber 162 can supplement the heat-carrying medium to the motor circuit.

[0050] When the motor circuit and the battery circuit are independent heat-carrying medium circuits, by providing the first chamber 161 and the second chamber 162, it is possible to separately manage the heat-carrying media at different temperatures in the battery circuit and the motor circuit, avoiding the cross-flow of heat-carrying media at different temperatures between the first pipeline 10 and the second pipeline 20 and affecting the thermal management efficiency, and it can also reduce the overall weight of the aircraft, which is beneficial to the lightweight of the aircraft.

[0051] In another embodiment, as Figure 7 shown, storage mechanisms 16 are respectively connected in the motor circuit and the battery circuit, and the storage mechanism 16 can respectively achieve exhaust and liquid supplement of the first pipeline 10 and the second pipeline 20.

[0052] In yet another embodiment, as Figure 8 shown, the motor circuit and the battery circuit are connected to the same storage mechanism 16, and the storage mechanism 16 can achieve exhaust and liquid supplement of the first pipeline 10 and the second pipeline 20.

[0053] The storage mechanism 16 can achieve exhaust and liquid supplement of the entire thermal management system, and can absorb the volume change of the heat-carrying medium in the first pipeline 10 and the second pipeline 20 due to temperature change, which is beneficial to ensuring uniform and efficient circulation of the heat-carrying medium and ensuring the pressure stability of the heat-carrying medium in the first pipeline 10 and the second pipeline 20.

[0054] The aircraft involved in the present invention includes the following states: Ground state: refers to the state of the aircraft when it is on the ground, but has just finished flying or has been on the ground for some time after the flight ends; Pending flight state: refers to the state of the aircraft when it is on the ground but is about to take off; Flight state: refers to the state of the aircraft when it is flying in the air.

[0055] When the aircraft is in the ground state, in some cases, the battery pack 21 needs to be charged. When the aircraft has just finished flying for a short time or the environmental temperature is high, resulting in a high temperature of the battery pack 21, if the battery pack 21 is charged, the charging efficiency of the battery pack 21 will be low and the risk of thermal runaway will be high. Therefore, the battery pack 21 needs to be cooled down; When the aircraft is in the ground state and has been on the ground for a long time after the flight ends, in some cases, the battery pack 21 needs to be charged. If the environmental temperature where the aircraft is located is too low, the temperature of the battery pack 21 will be too low, affecting the charging efficiency and causing energy loss and waste. Therefore, the battery pack 21 needs to be heated or insulated; When the aircraft is in the pending flight state, the temperature of the battery pack 21 needs to be at a better discharge temperature for subsequent takeoff; When the aircraft is in the flight state, the temperatures of both the battery pack 21 and the motor 12 need to be maintained at appropriate temperatures to avoid affecting the endurance of the aircraft.

[0056] In one embodiment, as Figure 1 shown, the control mechanism 31 includes four ports A, B, C, and D. Among them, port A and port B are provided on the first pipeline 10, and port C and port D are provided on the second pipeline 20. The control mechanism 31 is used to control the on-off between each port to achieve different loop connection methods. When ports AD are connected and ports CB are connected, the motor loop and the battery loop are in series. When ports AB are connected and ports CD are connected, the motor loop and the battery loop are two independent heat-carrying medium loops.

[0057] Exemplarily, the control mechanism 31 adopts a four-way valve.

[0058] Exemplarily, the control mechanism 31 can also adopt several ordinary valves, several three-way valves or a combination thereof.

[0059] Figure 2 and Figure 3 the bold lines in indicate the flow of the heat-carrying medium. As Figure 2 shown, when the aircraft is in the flight state, the battery pack 21 discharges, and the control mechanism 31 works to form two independent heat-carrying medium loops for the motor loop and the battery loop.

[0060] In the motor circuit, the first pump body 13 operates to circulate the heat-carrying medium in the motor circuit. When the temperature of the motor 12 does not reach 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-carrying medium does not flow through the heat dissipation mechanism 11. The motor 12 is cooled only by the circulation of the heat-carrying medium. As Figure 3 shown, when the temperature of the motor 12 is greater than or equal to the limit temperature, the heat dissipation mechanism 11 operates and is connected in series with the motor 12. The heat-carrying medium flows through the heat dissipation mechanism 11 to cool down, and then the motor 12 is cooled by the circulation of the heat-carrying medium; In the battery circuit, the second pump body 22 operates to circulate the heat-carrying medium in the battery circuit. The heat in the battery pack 21 is taken away by the circulating heat-carrying medium to cool the battery pack 21. When the temperature of the battery pack 21 gradually increases, the heat-carrying medium in the first pipeline 10 gradually warms up, so that the temperature of the battery pack 21 changes evenly.

[0061] Figure 4 and Figure 5 The bold lines in

[0062] indicate the flow of the heat-carrying medium. When the aircraft is in the ground state or in the standby flight state, the control mechanism 31 operates to connect the motor circuit and the battery circuit in series to form a complete heat-carrying medium circuit.

[0062] As Figure 4 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 operate. The heat dissipation mechanism 11 can cool down the heat-carrying medium flowing through it, and then the battery pack 21 and the motor 12 are cooled by the circulation of the heat-carrying medium; As Figure 5 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 operate, the heat dissipation mechanism 11 does not operate, and the heat-carrying medium does not flow through the heat dissipation mechanism 11. The battery pack 21 is heated or kept warm by the heat generated by the operation of the motor 12.

[0063] Figure 6 The bold lines in Figure 6 indicate the flow of the heat-carrying medium. As Figure 6 shown, when the heat dissipation mechanism 11 operates and the temperature of the battery pack 21 cannot be reduced to the first set temperature T1 within the set time t, or the temperature of the heat-carrying medium on the inlet side of the battery pack 21 is greater than or equal to the third set temperature T3, or the temperature of the heat-carrying medium on the outlet side of the battery pack 21 is greater than or equal to the fourth set temperature T4, the second valve member 23 is connected, disconnecting the battery pack 21 from the second pump body 22, and the heat-carrying medium does not flow in the second pipeline 20 where the battery pack 21 is located.

[0064] Based on the above eVTOL thermal management system, as Figure 9As shown, the present invention also provides an eVTOL temperature control system, comprising: A control unit 40, communicatively connected to a control mechanism 31, for sending control instructions to the control mechanism 31 to control the on / off of the motor circuit and the battery circuit, and to connect the motor circuit and the battery circuit in series. A detection unit 41, communicatively connected to the control unit 40, for detecting the real-time relevant temperature of the motor 12 and the real-time relevant temperature of the battery pack 21, and sending them to the control unit 40.

[0065] The above-mentioned real-time relevant temperature of the motor 12 can be the temperature of the motor 12 itself, or the temperature of the heat-carrying medium on the inlet side and / or the outlet side of the motor 12.

[0066] The above-mentioned real-time relevant temperature of the battery pack 21 can be the temperature of the battery pack 21 itself, or the temperature of the heat-carrying medium on the inlet side and / or the outlet side of the battery pack 21.

[0067] Exemplarily, the control unit 40 sends control instructions to the control mechanism 31 based on the real-time relevant temperature of the battery pack 21.

[0068] Exemplarily, the control unit 40 is integrated into the overall control of the aircraft.

[0069] Exemplarily, the detection unit 41 is a temperature measuring member 15 with signal transceiver functions.

[0070] In one embodiment, as Figure 9 shown, the control unit 40 is communicatively connected to a first valve member 14, and is used to send control instructions to the first valve member 14 based on the real-time relevant temperature of the motor 12 and the real-time relevant temperature of the battery pack 21, so as to realize the series connection or disconnection control of the heat dissipation mechanism 11 and the motor 12.

[0071] In one embodiment, as Figure 9 shown, the eVTOL temperature control system proposed by the present invention further includes a protection unit 42. The protection unit 42 is communicatively connected to a second valve member 23, and the protection unit 42 is used to control the switch of the second valve member 23 based on the real-time relevant temperature of the battery pack 21, so as to realize the series connection or disconnection control of the battery pack 21 and the second pump body 22.

[0072] In one embodiment, as Figure 9 shown, the eVTOL temperature control system proposed by the present invention further includes an input unit 43. The input unit 43 is communicatively connected to the control unit 40. The input unit 43 can manually input control instructions and send them to the control unit 40, and then send control instructions to the control mechanism 31 through the control unit 40.

[0073] Exemplarily, as Figure 9As shown, when the eVTOL temperature control 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 a control instruction and send it to the control unit 40 and / or the protection unit 42 to manually control the opening and closing of the second valve member 23 based on the real-time relevant temperature of the battery pack 21.

[0074] The present invention also proposes an eVTOL temperature control method, which is applied to the aforementioned eVTOL thermal management system and / or the aforementioned eVTOL temperature control system, and includes at least one of the following steps: S1. Based on the aircraft being in a ground state, 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 makes the motor circuit and the battery circuit in series, and the heat dissipation mechanism 11 is in series with the motor 12 to cool the battery pack 21. S2. Based on the aircraft being in a ground state, 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 makes the motor circuit and the battery circuit in series, and the heat dissipation mechanism 11 is disconnected from the motor 12, and the motor 12 operates to generate heat to heat or keep warm the battery pack 21. S3. Based on the aircraft being in a state of waiting to fly, and the temperature of the battery pack 21 is greater than the second set temperature T2, the control mechanism 31 makes the motor circuit and the battery circuit in series, and the heat dissipation mechanism 11 is in series with the motor 12 to cool the battery pack 21. S4. Based on the aircraft being in a state of waiting to fly, and the temperature of the battery pack 21 is less than or equal to the second set temperature T2, the control mechanism 31 makes the motor circuit and the battery circuit in series, and the heat dissipation mechanism 11 is disconnected from the motor 12, and the motor 12 operates to generate heat to heat or keep warm the battery pack 21. S5. Based on the aircraft being in a flying state, the control mechanism 31 makes the motor circuit and the battery circuit form an independent closed heat carrier medium circuit, the heat carrier medium in the first pipeline 10 circulates to cool the motor 12, and the heat carrier medium in the second pipeline 20 circulates to cool the battery pack 21.

[0075] It can be understood that there is no order limit for the above S1, S2, S3, S4, and S5.

[0076] Exemplarily, the above first set temperature T1 is set according to the preferred charging temperature of the battery pack 21, and the above second set temperature T2 is set according to the preferred discharging temperature of the battery pack 21.

[0077] Exemplarily, the above step S5 further includes: based on the cooling requirement of the motor 12, the heat dissipation mechanism 11 is in series with or disconnected from the motor 12.

[0078] In one embodiment, the above eVTOL temperature control method further includes the following steps: S6. Based on the fact that during the charging process of the battery pack 21, the temperature of the battery pack 21 fails to drop to the first set temperature T1 within the set time t, or the temperature of the heat-carrying medium on the inlet side of the battery pack 21 is greater than or equal to the third set temperature T3, or the temperature of the heat-carrying medium on the outlet side of the battery pack 21 is greater than or equal to the fourth set temperature T4, no heat-carrying medium flows in the second pipeline 20 where the battery pack 21 is located.

[0079] Exemplarily, step S6 further includes: stopping the charging of the battery pack 21.

[0080] More specifically, referring to Figure 6 , step S6 further includes: the second valve member 23 is connected, disconnecting the battery pack 21 from the second pump body 22, and the heat-carrying medium flows through the second pipeline 20 where the second valve member 23 is located, that is, the heat-carrying medium no longer flows through the battery pack 21, so as to prevent the temperature of the battery pack 21 from continuously increasing due to the too high temperature of the heat-carrying medium, which is beneficial to protecting the charging safety of the battery pack 21.

[0081] The above is only the specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed by the present invention should be covered by the protection scope of the present invention.

Claims

1. An eVTOL thermal management system, characterized in that: include: A motor circuit comprises a heat dissipation mechanism (11) and at least one motor (12), wherein the heat dissipation mechanism (11) and the motor (12) can be connected in series via a first pipe (10), the first pipe (10) being used to circulate a heat-carrying medium, and when the number of the motors (12) is at least two, at least two of the motors (12) are connected in parallel via the first pipe (10), and the heat dissipation mechanism (11) is used to cool the motors (12). A battery circuit, comprising at least one battery pack (21), wherein when the number of the battery packs (21) is at least two, at least two of the battery packs (21) are connected in parallel via a second pipe (20), and the second pipe (20) is used to circulate a heat carrier medium. and a control mechanism (31) for controlling the on / off of the motor circuit and the battery circuit, and for connecting the motor circuit and the battery circuit in series.

2. The eVTOL thermal management system according to claim 1, characterized in that: The motor circuit comprises a first pump body (13), the first pump body (13) being connected in series with the motor (12) via the first pipe (10), and being capable of being connected in series with the heat dissipation mechanism (11) via the first pipe (10), the first pump body (13) being used to drive the heat carrier medium in the first pipe (10) to flow.

3. The eVTOL thermal management system according to claim 2, characterized in that: The motor circuit comprises a first valve component (14), the first valve component (14) being connected in series with the heat dissipation mechanism (11) and being used to connect or disconnect the heat dissipation mechanism (11) and the motor (12) in series.

4. The eVTOL thermal management system according to claim 1, characterized in that: The battery circuit comprises a second pump body (22), the second pump body (22) being able to be connected in series with the battery pack (21) via the second pipe (20), and the second pump body (22) being used to drive the heat carrier medium in the second pipe (20) to flow.

5. The eVTOL thermal management system according to claim 4, characterized in that: The battery circuit further comprises a second valve component (23), the second valve component (23) being connected in parallel with the battery pack (21) via the second pipeline (20), the second valve component (23) being used to connect or disconnect the battery pack (21) and the second pump body (22) in series.

6. The eVTOL thermal management system according to claim 1, characterized in that: It also includes a storage mechanism (16), wherein the storage mechanism (16) is in communication with the first pipeline (10) and the second pipeline (20) to allow the heat carrier medium to flow through.

7. An eVTOL temperature control system, characterized in that: The eVTOL thermal management system applied to claims 1 to 6 comprises: A control unit (40) is communicatively connected to the control mechanism (31) and is used to send a control instruction to the control mechanism (31) to control the on / off of the motor circuit and the battery circuit, and to connect the motor circuit and the battery circuit in series. A detection unit (41) is connected to the control unit (40) for detecting the real-time relevant temperature of the motor (12) and for detecting the real-time relevant temperature of the battery pack (21) and sending the temperature to the control unit (40).

8. The eVTOL temperature control system according to claim 7, characterized in that: It also includes a protection unit (42), the protection unit (42) being communicatively connected to the second valve component (23), the protection unit (42) being used to control the switch of the second valve component (23) based on the real-time relevant temperature of the battery pack (21).

9. An eVTOL temperature control method, characterized in that: The eVTOL thermal management system as claimed in any one of claims 1 to 6, and / or the eVTOL temperature control system as claimed in claim 7 or 8, comprises at least one of the following steps: S1, based on the aircraft being in a ground state, the battery pack (21) needs to be charged, and the temperature of the battery pack (21) is greater than a first set temperature T1, the control mechanism (31) connects the motor circuit and the battery circuit in series, and the heat dissipation mechanism (11) and the motor (12) in series, to cool the battery pack (21); S2, based on the aircraft being in a ground state, the battery pack (21) having a charging demand, and the temperature of the battery pack (21) being less than or equal to a first set temperature T1, 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; S3, based on the aircraft being in a ready-to-fly state and the temperature of the battery pack (21) being greater than a second set temperature T2, the control mechanism (31) connects the motor circuit and the battery circuit in series, and the heat dissipation mechanism (11) and the motor (12) in series, to cool the battery pack (21); S4, 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 operates the motor (12) to generate heat to heat or keep the battery pack (21) warm; S5. Based on the aircraft being in flight, the control mechanism (31) causes the motor circuit and the battery circuit to form an independent closed heat medium circuit, the heat medium in the first pipe (10) circulates to cool the motor (12), and the heat medium in the second pipe (20) circulates to cool the battery pack (21).

10. The eVTOL temperature control method according to claim 9, characterized in that: The following steps are also included: S6: Based on the battery pack (21) being in the charging process, the temperature of the battery pack 21 fails to drop to the first set temperature T1 within the set time t, or the temperature of the heat medium at the inlet side of the battery pack (21) is greater than or equal to the third set temperature T3, or the temperature of the heat medium at the outlet side of the battery pack (21) is greater than or equal to the fourth set temperature T4, and the heat medium does not flow in the second pipe (20) where the battery pack (21) is located.

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