EVTOL aircraft thermal management system and use method

Abstract

The invention discloses an EVTOL aircraft thermal management system and a using method, the system comprises a switching module, a cooling module, a passenger compartment temperature control module, a battery temperature control module, a battery cooling module and a battery pack module, the cooling module is connected with a turboshaft engine lubricating oil module and a power generation control module, the passenger compartment temperature control module is connected with a passenger compartment, and the battery cooling module is connected with a battery cooling module. The temperature of the member cabin, the temperature of the battery pack module, the temperature of the turboshaft engine lubricating oil module and the temperature of the power generation control module can be regulated and controlled through the system, one or more working modes are achieved, through the integrated, redundant and intelligent design, an EVTOL heat management solution which is high in reliability, high in energy efficiency and capable of achieving all-dimensional coverage is provided, and the system is suitable for popularization and application. The flight safety is guaranteed, the experience of passengers is improved, the service life of parts is prolonged, and the endurance of the aircraft is prolonged.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of aircraft, in particular to an EVTOL aircraft thermal management system and a use method. BACKGROUND

[0002] The electric vertical take-off and landing aircraft (EVTOL) integrates the vertical take-off convenience of the helicopter and the low noise and cleanliness of the electric system, and has become one of the promising candidate transportation tools. The high heat dissipation power requirement of the power battery and the variability of the application scene pose a great challenge to the thermal management system. In the prior art, there are also designs about the thermal management system to realize the temperature control of the aircraft. For example, a patent with the publication number CN118238575A discloses a multi-scene electric vertical take-off and landing aircraft integrated thermal management system. This scheme realizes different functional scenes of independent or interrelated operation of the passenger cabin thermal management and the battery thermal management by the mutual correlation and coupling of the refrigerant flow path and the cooling liquid flow path, and utilizes the environmental cold source to achieve the cooling and heating function requirements of the thermal management system. However, this scheme still has the following problems: (1) The passenger cabin thermal management and the battery thermal management do not have a redundancy mechanism. If a certain component is damaged, there is no standby thermal management mode to replace, which will cause the passenger cabin thermal management or the battery thermal management to fail, thereby affecting the comfort experience of the passengers or the flight of the aircraft; (2) When the aircraft is flying, the engine, the electronic control module and the engine oil module will also be heated to generate a large amount of heat. This scheme does not involve the thermal management of the engine, the electronic control module and the engine oil module. When the temperature of the engine, the electronic control module and the engine oil module is too high, it will also affect the flight of the aircraft, and even reduce the service life of the aircraft.

[0003] Therefore, it is necessary to provide an EVTOL aircraft thermal management system to solve the above technical problems. SUMMARY

[0004] The main purpose of the present application is to provide an EVTOL aircraft thermal management system, which provides a high-reliability, high-energy-efficiency, and all-around coverage EVTOL thermal management solution through integrated, redundant, and intelligent design, thereby ensuring flight safety, improving passenger experience, prolonging component life, and increasing aircraft endurance.

[0005] The present application realizes the above-mentioned purpose through the following technical scheme: an EVTOL aircraft thermal management system, comprising: A switching module, comprising a first multi-way valve, a second multi-way valve and a third multi-way valve, the first multi-way valve is provided with a first port, a second port and a third port, the second multi-way valve is provided with a first connecting port, a second connecting port, a third connecting port and a fourth connecting port, the third multi-way valve is provided with a first inlet and outlet, a second inlet and outlet, a third inlet and outlet and a fourth inlet and outlet; A cooling module, comprising a condenser, a low-temperature radiator and a high-temperature radiator, one end of the high-temperature radiator is connected with the fourth inlet and outlet, the other end of the high-temperature radiator is connected with the third inlet and outlet and a fourth electronic water pump and a turboshaft engine lubricating oil module is connected therebetween; one end of the low-temperature radiator is connected with the third connecting port, the other end of the low-temperature radiator is connected with the fourth connecting port and a water-cooled condenser, a power generation control module and a second electronic water pump are connected therebetween; A passenger cabin temperature control module connected with a passenger cabin, comprising a first evaporator core and a warm air core, one end of the warm air core is connected with the first inlet and outlet, the warm air core is connected with the second inlet and outlet and a first port, a third port, a PTC heater and a first electronic water pump are connected therebetween in sequence; A battery temperature control module, comprising a battery heating core, a first battery heat exchanger and a second evaporator core; one end of the condenser is connected with a first compressor, the other end of the condenser is connected with the first evaporator core and one end of the second evaporator core, the other end of the first compressor is connected with the first evaporator core and the other end of the second evaporator core, one end of the battery heating core is connected with the second port and the other end of the battery heating core is connected with the first inlet and outlet; A battery cooling module, comprising a second battery heat exchanger and a third evaporator core, one end of the first battery heat exchanger is connected with the second connecting port and the other end of the first battery heat exchanger is connected with the second battery heat exchanger, one end of the water-cooled condenser is connected with the third evaporator core and the other end of the water-cooled condenser is connected with a second compression motor, the other end of the second compression motor is connected with the third evaporator core; A battery pack module, one end of the battery pack module is connected with the first connecting port and the other end of the battery pack module is connected with the second battery heat exchanger and a third electronic water pump is connected therebetween.

[0006] Further, electronic expansion valves are arranged at the inlets of the first evaporator core, the second evaporator core and the third evaporator core.

[0007] Further, the battery pack module comprises a plurality of batteries, one end of each battery is connected with a flow control valve and the other end of each battery is connected with a first water temperature sensor.

[0008] Further, a second water temperature sensor is arranged between the third electronic water pump and the battery pack module, a third water temperature sensor is arranged between the power generation control module and the second electronic water pump, and a fourth water temperature sensor is arranged between the fourth electronic water pump and the turboshaft engine oil module.

[0009] Further, a first high-pressure sensor is arranged between the condenser and the second evaporator core and close to the condenser, and a second high-pressure sensor is arranged between the water-cooled condenser and the third evaporator core and close to the water-cooled condenser.

[0010] Further, a first low-pressure sensor is arranged between the first compressor and the second evaporator core and close to the second evaporator core, and a second low-pressure sensor is arranged between the second compression motor and the third evaporator core and close to the third evaporator core.

[0011] Further, the cooling module further comprises an electronic fan, and is a double electronic fan.

[0012] Further, the passenger cabin temperature control module further comprises a blower.

[0013] Further, a plurality of expansion water jugs are further included.

[0014] Another object of the present application is to provide a method for using the EVTOL aircraft thermal management system, which comprises one or more combinations of the following working modes: Working mode one, the PTC heater works to heat the passenger cabin: the coolant flows from the first electronic water pump and sequentially passes through the PTC heater, the third port and the first port of the first multi-way valve, the heating core, the first inlet and outlet and the second inlet and outlet of the third multi-way valve, and then flows back to the first electronic water pump; Working mode two, the waste heat of the turboshaft engine oil module heats the passenger cabin: the coolant flows from the first electronic water pump and sequentially passes through the PTC heater, the third port and the first port of the first multi-way valve, the heating core, the first inlet and outlet and the fourth inlet and outlet of the third multi-way valve, the high-temperature radiator, the fourth electronic water pump, the turboshaft engine oil module, the third inlet and outlet and the second inlet and outlet of the third multi-way valve, and then flows back to the first electronic water pump; Working mode three, the first compressor refrigeration cools the passenger cabin: the refrigerant enters the first compressor and sequentially passes through the condenser and the first evaporator core, and then flows back to the first compressor; Working mode four, the PTC heater works to heat the battery module: the first cooling liquid flows from the first electronic water pump and sequentially passes through the PTC heater, the third port and the second port of the first multi-way valve, the battery heating core, the first inlet and outlet and the second inlet and outlet of the third multi-way valve, and then flows back to the first electronic water pump; the second cooling liquid flows from the first battery heat exchanger and sequentially passes through the second battery heat exchanger, the third electronic water pump, the battery module, the first connecting port and the second connecting port of the second multi-way valve, and then flows back to the first battery heat exchanger, and the battery heating core and the second battery heat exchanger exchange heat; Working mode five, the waste heat of the power generation control module heats the battery module: the cooling liquid flows from the first battery heat exchanger and sequentially passes through the second battery heat exchanger, the third electronic water pump, the battery module, the first connecting port and the fourth connecting port of the second multi-way valve, the second electronic water pump, the power generation control module, the water-cooled condenser, the low-temperature radiator, the third connecting port and the second connecting port of the second multi-way valve, and then flows back to the first battery heat exchanger; Working mode six, the waste heat of the turboshaft engine lubricating module heats the battery module: the first cooling liquid flows from the first electronic water pump and sequentially passes through the PTC heater, the third port and the second port of the first multi-way valve, the battery heating core, the first inlet and outlet and the fourth inlet and outlet of the third multi-way valve, the high-temperature radiator, the fourth electronic water pump, the turboshaft engine lubricating module, the third inlet and outlet and the second inlet and outlet of the third multi-way valve, and then flows back to the first electronic water pump; the second cooling liquid flows from the first battery heat exchanger and sequentially passes through the second battery heat exchanger, the third electronic water pump, the battery module, the first connecting port and the second connecting port of the second multi-way valve, and then flows back to the first battery heat exchanger; the battery heating core and the second battery heat exchanger exchange heat; Working mode seven, the first compressor cools the battery module: the refrigerant enters the first compressor and sequentially passes through the condenser and the second evaporator core, and then flows back to the first compressor; the cooling liquid flows from the first battery heat exchanger and sequentially passes through the second battery heat exchanger, the third electronic water pump, the battery module, the first connecting port and the second connecting port of the second multi-way valve, and then flows back to the first battery heat exchanger; the second evaporator core and the first battery heat exchanger exchange heat; Working mode eight, the second compressor cools the battery module: the refrigerant enters from the second compressor and sequentially passes through the water-cooled condenser, the third evaporator core, and then flows back to the second compressor; the cooling liquid flows from the first battery heat exchanger and sequentially passes through the second battery heat exchanger, the third electronic water pump, the battery module, the first connecting port and the second connecting port of the second multi-way valve, and then flows back to the first battery heat exchanger; the second evaporator core exchanges heat with the first battery heat exchanger; Working mode nine, the turboshaft engine oil module is cooled: the cooling liquid flows from the fourth electronic water pump and sequentially passes through the turboshaft engine oil module, the third inlet and outlet and the fourth inlet and outlet of the third multi-way valve, and the high-temperature radiator, and then flows back to the fourth electronic water pump; Working mode ten, the turboshaft engine oil module is cooled: the cooling liquid flows from the first electronic water pump and sequentially passes through the PTC heater, the third port and the first port of the first multi-way valve, the warm air core, the first inlet and outlet and the fourth inlet and outlet of the third multi-way valve, the turboshaft engine oil module, the high-temperature radiator, the fourth electronic water pump, the third inlet and outlet and the second inlet and outlet of the third multi-way valve, and then flows back to the first electronic water pump; Working mode eleven, the turboshaft engine oil module is cooled: the first cooling liquid flows from the first electronic water pump and sequentially passes through the PTC heater, the third port and the second port of the first multi-way valve, the battery heating core, the first inlet and outlet and the fourth inlet and outlet of the third multi-way valve, the high-temperature radiator, the fourth electronic water pump, the turboshaft engine oil module, the third inlet and outlet and the second inlet and outlet of the third multi-way valve, and then flows back to the first electronic water pump; the second cooling liquid flows from the first battery heat exchanger and sequentially passes through the second battery heat exchanger, the third electronic water pump, the battery module, the first connecting port and the second connecting port of the second multi-way valve, and then flows back to the first battery heat exchanger; the battery heating core exchanges heat with the second battery heat exchanger; Working mode twelve, the power generation control module is cooled: the cooling liquid flows from the second electronic water pump and sequentially passes through the power generation control module, the water-cooled condenser, the low-temperature radiator, the third connecting port and the fourth connecting port of the second multi-way valve, and then flows back to the second electronic water pump.

[0015] Compared with the prior art, the EVTOL aircraft thermal management system and the use method have the advantages that: the thermal management system of the scheme effectively solves the core problems of the lack of redundancy and limited management range of the existing scheme in the prior art through integrated, redundant and intelligent design, provides an EVTOL thermal management solution with high reliability, high energy efficiency and full coverage, which is of great value to ensure flight safety, improve passenger experience, prolong component life and increase aircraft endurance, and specifically: 1. High system integration and functional coupling are achieved: through ingenious flow path design and precise control of multiple valves, the passenger cabin thermal management, battery thermal management, engine oil thermal management and electric control system thermal management are highly integrated, the temperature of the passenger cabin, battery module, turboshaft engine oil module and power generation control module can be controlled using the system, and each has one or more working modes. The thermal management system can intelligently distribute cold and hot resources according to the needs of the aircraft in different working conditions, realize the cooperation and linkage of each component thermal management, and improve the overall energy efficiency; 2. A comprehensive redundancy backup mechanism is built, which significantly improves system reliability and flight safety, including the following redundancy designs: (1) Heating redundancy: multiple heating sources are provided for the passenger cabin and the battery, in addition to the main PTC heater, the waste heat generated by the turboshaft engine oil module and the power generation control module during operation is also used as a backup heat source; When the PTC heater fails, the system can automatically switch to the waste heat recovery mode to ensure the comfort of the passenger cabin and the working temperature of the battery in critical conditions, avoiding the loss of function caused by single point failure; (2) Refrigeration redundancy: two independent compressor refrigeration circuits (first compressor and second compressor) are provided for battery cooling; When one of the compressors fails, the other can still work independently or at reduced capacity to provide necessary cooling for the battery, giving the aircraft time to safely land, greatly enhancing the safety margin of the aircraft; (3) Heat dissipation path redundancy: multiple cooling path options are provided for key components such as the turboshaft engine oil module, further ensuring the continuous operation of the system when some components fail; 3. The thermal management range is expanded, and the temperature control of the key components of the whole vehicle is realized: compared with the prior art, the system not only covers the passenger cabin and the battery, but also includes the turboshaft engine oil module, the power generation control module and other flight core power and control systems, which effectively prevents these components from performance degradation, damage or shortened life due to overheating, ensuring stable, efficient and long-lasting operation of the aircraft power system; 4. Improved energy utilization efficiency: The system utilizes the waste heat generated by the engine oil and electronic control system for cabin heating and battery heating through waste heat recovery design, reducing the dependence on high-power electric heating equipment such as PTC heaters, and reducing the overall energy consumption of the system, which is crucial for electric aircraft with long endurance mileage; 5. Precise and balanced temperature control: In battery thermal management, by equipping each battery monomer with an independent flow control valve and temperature sensor, the internal temperature of the battery pack can be finely managed, ensuring the temperature uniformity between each monomer battery, effectively prolonging the overall life of the battery pack and improving safety; The pressure and temperature sensors at each key node provide sufficient data support for intelligent control and fault diagnosis of the system, making temperature control more accurate and reliable; 6. Enhanced system adaptability and flexibility: The multiple control modes listed show that the system can flexibly respond to the thermal management needs of EVTOL aircraft in various complex scenarios (such as vertical take-off and landing, cruising, ground standby, different environmental temperatures, etc.), achieving efficient, energy-saving, and safe multi-objective optimization operation. BRIEF DESCRIPTION OF DRAWINGS

[0016] Figure 1 Schematic diagram of the EVTOL aircraft thermal management system of the present application embodiment; Numerals in the figure represent: 100-EVTOL aircraft thermal management system; 1-First multi-way valve, 11-First port, 12-Second port, 13-Third port; 2-Second multi-way valve, 21-First connection port, 22-Second connection port, 23-Third connection port, 24-Fourth connection port; 3-Third multi-way valve, 31-First inlet and outlet, 32-Second inlet and outlet, 33-Third inlet and outlet, 34-Fourth inlet and outlet; 4-Cooling module, 41-Condenser, 42-Low-temperature radiator, 43-High-temperature radiator, 44-Electronic fan; 5-Cabin temperature control module, 51-First evaporator core, 52-Heating core, 53-Blower; 6-Battery temperature control module, 61-Battery heating core, 62-First battery heat exchanger, 63-Second evaporator core; 7-Battery cooling module, 71-Second battery heat exchanger, 72-Third evaporator core; 8-Battery pack module, 81-Battery, 82-Flow control valve, 83-First water temperature sensor; 9-Turboshaft engine oil module; 101 - first electronic water pump, 102 - second electronic water pump, 103 - third electronic water pump, 104 - fourth electronic water pump; 201 - first compressor, 202 - second compression motor; 30 - PTC heater, 40 - water-cooled condenser, 50 - power generation control module; 801 - second water temperature sensor, 802 - second low pressure sensor, 803 - first low pressure sensor, 804 - third water temperature sensor, 805 - second high pressure sensor, 806 - first high pressure sensor, 807 - fourth water temperature sensor, 809 - expansion water pot. DETAILED DESCRIPTION

[0017] Please refer to Figure 1 The embodiment is an EVTOL aircraft thermal management system 100, which comprises: A switching module comprising a first multi-way valve 1, a second multi-way valve 2, and a third multi-way valve 3, the first multi-way valve 1 being provided with a first port 11, a second port 12, and a third port 13, the second multi-way valve 2 being provided with a first connection port 21, a second connection port 22, a third connection port 23, and a fourth connection port 24, the third multi-way valve 3 being provided with a first inlet and outlet 31, a second inlet and outlet 32, a third inlet and outlet 33, and a fourth inlet and outlet 34; A cooling module 4 comprising a condenser 41, a low-temperature radiator 42, and a high-temperature radiator 43, the high-temperature radiator 43 being connected at one end to the fourth inlet and outlet 34, and at the other end to the third inlet and outlet 33, and between the two being connected with the fourth electronic water pump 104 and the turboshaft engine oil module 9; the low-temperature radiator 42 being connected at one end to the third connection port 23, and at the other end to the fourth connection port 24, and between the two being connected with the water-cooled condenser 40, the power generation control module 50, and the second electronic water pump 102; A passenger cabin temperature control module 5 connected to the passenger cabin, the passenger cabin temperature control module 5 comprising a first evaporator core 51 and a warm air core 52, the warm air core 52 being connected at one end to the first inlet and outlet 31, and at the other end to the second inlet and outlet 32, and between the two being connected in sequence with the first port 11, the third port 13, the PTC heater 30, and the first electronic water pump 101; A battery temperature control module 6 comprising a battery heating core 61, a first battery heat exchanger 62, and a second evaporator core 63; the condenser 41 being connected at one end to the first compressor 201, and at the other end to the first evaporator core 51 and one end of the second evaporator core 63, the other end of the first compressor 201 being connected to the other end of the first evaporator core 51 and the second evaporator core 63, one end of the battery heating core 61 being connected to the second port 12, and the other end being connected to the first inlet and outlet 31; A battery cooling module 7, which includes a second battery heat exchanger 71 and a third evaporator core 72, the first battery heat exchanger 62 is connected to the second connection port 22 at one end and to the second battery heat exchanger 71 at the other end, the water-cooled condenser 40 is connected to the third evaporator core 72 at one end and to the second compression motor 202 at the other end, the other end of the second compression motor 202 is connected to the third evaporator core 72; A battery pack module 8, which is connected to the first connection port 21 at one end and to the second battery heat exchanger 71 at the other end, and a third electronic water pump 103 is connected between the two.

[0018] The water-cooled condenser 40 serves as the condenser of the second compression motor 202 refrigeration cycle, and transfers the heat brought by the refrigerant from the second compression motor 202 to the cooling liquid flowing through it. The condenser 41 serves as the condenser of the first compressor 201 refrigeration cycle, and dissipates the heat brought by the refrigerant from the first compressor 201 to the environment.

[0019] The low-temperature radiator 42 is used to dissipate the heat from the power generation control module 50 and the battery cooling module 7, and is a low-temperature heat dissipation terminal in the system. The high-temperature radiator 43 is used to dissipate the heat from the turboshaft engine oil module 9, and is a high-temperature heat dissipation terminal in the system.

[0020] The PTC heater 30 is an electric heater used to directly heat the cooling liquid and provide a stable heat source for the passenger cabin, especially when the engine is not started or there is no waste heat.

[0021] The power generation control module 50 includes a generator and a generator controller, which provides power for the aircraft thermal management system and generates heat when working, and is also an important heat source in the system, and its waste heat can be recycled for heating the battery.

[0022] The first evaporator core 51 serves as the evaporator of the first compressor 201 refrigeration cycle, in which the refrigerant vaporizes and absorbs heat, cooling the air flowing through it, thereby cooling the passenger cabin. The second evaporator core 63 serves as the evaporator for battery refrigeration in the first compressor 201 refrigeration cycle, and exchanges heat with the first battery heat exchanger 62 to remove heat from the battery circulation loop. The third evaporator core 72 serves as the evaporator of the second compression motor 202 refrigeration cycle, and exchanges heat with the second battery heat exchanger 71 to remove heat from the battery circulation loop.

[0023] The heater core 52 is a heating element that allows high-temperature cooling liquid heated by the PTC heater 30 or the turboshaft engine oil module 9 to flow through it, and the air blown by the blower 53 exchanges heat with it and is heated to provide heating for the passenger cabin.

[0024] The battery heating core 61 is a liquid-liquid heat exchanger, which allows the high-temperature coolant from the PTC heater 30 or the waste heat of the turboshaft engine oil module 9 to flow through, and transfers heat to the battery coolant flowing through the first battery heat exchanger 62, thereby indirectly heating the battery module 8.

[0025] The first battery heat exchanger 62 connects the battery cooling circuit and the battery temperature control / cooling circuit, in the heating mode, it obtains heat from the battery heating core 61, in the cooling mode, it releases heat to the second evaporator core 63 or the third evaporator core 72. The second battery heat exchanger 71 connects the battery cooling circuit and the battery cooling circuit, especially the circuit of the second compression motor 202, in the cooling mode, it transfers the battery heat to the third evaporator core 72.

[0026] The turboshaft engine oil module 9 is a high-temperature heat source in the system, the waste heat can be recycled to heat the passenger cabin or the battery module 8, and itself also needs to be cooled.

[0027] The first compressor 201 is a compressor that provides power for passenger cabin refrigeration and battery refrigeration (main circuit), and drives the refrigerant to circulate in the circuit containing the condenser 41, the first evaporator core 51 and the second evaporator core 63. The second compression motor 202 is a compressor that provides power for battery refrigeration (auxiliary circuit), and drives the refrigerant to circulate in the circuit containing the water-cooled condenser 40 and the third evaporator core 72, which constitutes a redundant backup with the first compressor 201.

[0028] The cooling module 4 also includes an electronic fan 44 to force air flow through the condenser 41, the low-temperature radiator 42 and the high-temperature radiator 43, enhancing their heat dissipation efficiency, and using double electronic fans can effectively improve the operation reliability of the air conditioning thermal management system.

[0029] The passenger cabin temperature control module 5 also includes a blower 53, which drives air to flow through the heating core 52 or the first evaporator core 51, and sends the heated or cooled air into the passenger cabin.

[0030] Electronic expansion valves are provided at the first evaporator core 51, the second evaporator core 63 and the third evaporator core 72, and the electronic expansion valves are installed at the inlet of each evaporator core to accurately control the refrigerant flow into the evaporator core, so as to achieve the best heat exchange efficiency and temperature control.

[0031] The battery module 8 includes a plurality of batteries 81, and one end of each battery 81 is connected with a flow control valve 82, and the other end is connected with a first water temperature sensor 83, which is used for monitoring the cooling liquid temperature at the outlet of each battery, and providing key data for battery thermal management control; the flow control valve 82 is installed at the inlet of each battery monomer, and accurately allocates the cooling liquid flow to each battery, to ensure the uniform temperature in the battery pack, and the flow control valve 82 is connected with one end of each battery 81 and is individually controllable, and when the flow control valve 82 fails, it only affects the corresponding battery 81 of the flow control valve, and does not affect the work of other batteries.

[0032] The third electronic water pump 103 is provided with a second water temperature sensor 801 between the battery module 8, and the second water temperature sensor 801 is used for monitoring the cooling liquid temperature before entering the battery module 8.

[0033] The power generation control module 50 is provided with a third water temperature sensor 804 between the second electronic water pump 102, and the third water temperature sensor 804 is used for monitoring the cooling liquid temperature at the outlet of the power generation control module 50. The fourth electronic water pump 104 is provided with a fourth water temperature sensor 807 between the turboshaft engine oil module 9, and the fourth water temperature sensor 807 is used for monitoring the cooling liquid temperature at the outlet of the turboshaft engine oil module 9.

[0034] The condenser 41 is provided with a first high-pressure sensor 806 between the second evaporator core 63 and close to the condenser 41, and the first high-pressure sensor 806 is used for monitoring the high-pressure side pressure of the first compressor 201 refrigeration circuit, for system protection and efficiency control. The water-cooled condenser 40 is provided with a second high-pressure sensor 805 between the third evaporator core 72 and close to the water-cooled condenser 40, and the second high-pressure sensor 805 is used for monitoring the high-pressure side pressure of the second compression motor 202 refrigeration circuit, for system protection and efficiency control.

[0035] The first compressor 201 is provided with a first low-pressure sensor 803 between the second evaporator core 63 and close to the second evaporator core 63, and the first low-pressure sensor 803 is used for monitoring the low-pressure side pressure of the first compressor 201 refrigeration circuit, for system protection and efficiency control. The second compression motor 202 is provided with a second low-pressure sensor 802 between the third evaporator core 72 and close to the third evaporator core 72, and the second low-pressure sensor 802 is used for monitoring the low-pressure side pressure of the second compression motor 202 refrigeration circuit, for system protection and efficiency control.

[0036] The EVTOL aircraft thermal management system 100 further comprises a plurality of expansion water pots 809. When the temperature of the cooling liquid changes, the volume of the cooling liquid changes, and the expansion water pots provide space for expansion. When the temperature decreases, the cooling liquid in the expansion water pots replenishes the air conditioning thermal management system, accommodates the volume expansion and contraction of the cooling liquid due to temperature changes, provides buffer space and a cooling liquid replenishment source for the system, and discharges gas in the circulating liquid. The number and installation position of the plurality of expansion water pots 809 are not limited here and can be adjusted according to actual conditions.

[0037] The embodiment also provides a method for using the EVTOL aircraft thermal management system 100, which comprises one or a combination of the following working modes, but is not limited to the following listed working modes and can be adjusted according to actual conditions.

[0038] Working mode one: The PTC heater 30 works to heat the passenger cabin. The cooling liquid flows from the first electronic water pump 101, passes through the PTC heater 30, the third port 13 and the first port 11 of the first multi-way valve 1, the warm air core 52, the first inlet and outlet 31 and the second inlet and outlet 32 of the third multi-way valve 3 in turn, and then flows back to the first electronic water pump 101, to complete the circulation of the cooling liquid and realize the heating function of the passenger cabin. At this time, the PTC heater 30 is normally working.

[0039] Working mode two: The waste heat of the turboshaft engine oil module 9 is used to heat the passenger cabin. The cooling liquid flows from the first electronic water pump 101, passes through the PTC heater 30, the third port 13 and the first port 11 of the first multi-way valve 1, the warm air core 52, the first inlet and outlet 31 and the fourth inlet and outlet 34 of the third multi-way valve 3, the high-temperature radiator 43, the fourth electronic water pump 104, the turboshaft engine oil module 9, the third inlet and outlet 33 and the second inlet and outlet 32 of the third multi-way valve 3 in turn, and then flows back to the first electronic water pump 101, to complete the circulation of the cooling liquid. At this time, the PTC heater 30 is not working, but only functions as a conductor.

[0040] Both working mode one and working mode two can realize the heating function of the passenger cabin, and a redundant design is adopted. If the PTC heater 30 fails, working mode two is used to heat the passenger cabin by using the waste heat of the turboshaft engine oil module 9.

[0041] Working mode three: The first compressor 201 is used to cool the passenger cabin. The refrigerant flows from the first compressor 201, passes through the condenser 41 and the first evaporator core 51 in turn, and then flows back to the first compressor 201, to complete the circulation of the refrigerant. The refrigerant vaporizes in the first evaporator core 51 to absorb heat from the air passing through the surface of the first evaporator core 51, thereby reducing the temperature of the air to cool the passenger cabin.

[0042] Working mode four, PTC heater 30 works to heat battery module 8: the first cooling liquid flows from the first electronic water pump 101 and sequentially passes through the PTC heater 30, the third port 13 and the second port 12 of the first multi-way valve 1, the battery heating core 61, the first inlet and outlet 31 and the second inlet and outlet 32 of the third multi-way valve 3, and then flows back to the first electronic water pump 101, realizing the circulation of the first cooling liquid; the second cooling liquid flows from the first battery heat exchanger 62 and sequentially passes through the second battery heat exchanger 71, the third electronic water pump 103, the battery module 8, the first connecting port 21 and the second connecting port 22 of the second multi-way valve 2, and then flows back to the first battery heat exchanger 62, realizing the circulation of the second cooling liquid; heat is exchanged between the battery heating core 61 and the second battery heat exchanger 71, realizing the heating of the battery module 8.

[0043] Working mode five, the waste heat of the power generation control module 50 heats the battery module 8: the cooling liquid flows from the first battery heat exchanger 62 and sequentially passes through the second battery heat exchanger 71, the third electronic water pump 103, the battery module 8, the first connecting port 21 and the fourth connecting port 24 of the second multi-way valve 2, the second electronic water pump 102, the power generation control module 50, the water-cooled condenser 40, the low-temperature radiator 42, the third connecting port 23 and the second connecting port 22 of the second multi-way valve 2, and then flows back to the first battery heat exchanger 62, realizing the heating function of the battery module 8. The second multi-way valve 2 switches the flow direction of the cooling liquid, so that the power generation control module 50 and the battery module 8 are connected in series.

[0044] Working mode six, the waste heat of the turboshaft engine oil module 9 heats the battery module 8: the first cooling liquid flows from the first electronic water pump 101 and sequentially passes through the PTC heater 30, the third port 13 and the second port 12 of the first multi-way valve 1, the battery heating core 61, the first inlet and outlet 31 and the fourth inlet and outlet 34 of the third multi-way valve 3, the high-temperature radiator 43, the fourth electronic water pump 104, the turboshaft engine oil module 9, the third inlet and outlet 33 and the second inlet and outlet 32 of the third multi-way valve 3, and then flows back to the first electronic water pump 101, completing the circulation of the first cooling liquid, at this time the PTC heater 30 does not work; the second cooling liquid flows from the first battery heat exchanger 62 and sequentially passes through the second battery heat exchanger 71, the third electronic water pump 103, the battery module 8, the first connecting port 21 and the second connecting port 22 of the second multi-way valve 2, and then flows back to the first battery heat exchanger 62, realizing the circulation of the second cooling liquid; heat is transferred between the battery heating core 61 and the second battery heat exchanger 71, realizing the heating function of the battery module 8.

[0045] Working mode four, working mode five, working mode six can realize heating of the battery module 8, if the PTC heater 30 fails, working mode five or working mode six is used to heat the battery module 8, the waste heat of the power generation control module 50 is used to heat the battery module 8, or the waste heat of the turboshaft engine oil module 9 is used to heat the battery module 8.

[0046] Working mode seven, the first compressor 201 cools the battery module 8: the refrigerant flows into the first compressor 201 and sequentially passes through the condenser 41, the second evaporator core 63, and then flows back to the first compressor 201, realizing refrigerant circulation; the cooling liquid flows into the first battery heat exchanger 62 and sequentially passes through the second battery heat exchanger 71, the third electronic water pump 103, the battery module 8, the first connecting port 21 and the second connecting port 22 of the second multi-way valve 2, and then returns to the first battery heat exchanger 62, realizing cooling liquid circulation. The second evaporator core 63 and the first battery heat exchanger 62 exchange heat, reducing the temperature of the cooling liquid circulation system, realizing battery cooling function, and the two media circulating at the same time can realize battery cooling function.

[0047] Working mode eight, the second compressor 202 cools the battery module 8: the refrigerant flows into the second compressor 202 and sequentially passes through the water-cooled condenser 40 and the third evaporator core 72, and then returns to the second compressor 202, realizing refrigerant circulation cooling; the cooling liquid flows into the first battery heat exchanger 62 and sequentially passes through the second battery heat exchanger 71, the third electronic water pump 103, the battery module 8, the first connecting port 21 and the second connecting port 22 of the second multi-way valve 2, and then returns to the first battery heat exchanger 62, realizing cooling liquid circulation. The second evaporator core 63 and the first battery heat exchanger 62 exchange heat, reducing the temperature of the cooling liquid circulation system, realizing battery cooling function, and the two media circulating at the same time can realize battery cooling function.

[0048] Among them, working mode seven and working mode eight are independent of each other, that is, they can work alone to cool the battery module 8, or they can work together to cool the battery module 8. The system adopts a double-compressor refrigerant system with redundant design. When the first compressor 201 or the second compressor 202 fails, although the refrigeration performance is reduced, there is enough time to make the aircraft land safely, improving the safety of the aircraft.

[0049] Working mode nine, cooling the turboshaft engine oil module 9: the cooling liquid flows into the fourth electronic water pump 104 and sequentially passes through the turboshaft engine oil module 9, the third inlet and outlet 33 and the fourth inlet and outlet 34 of the third multi-way valve 3, and the high-temperature radiator 43, and then returns to the fourth electronic water pump 104, realizing cooling of the turboshaft engine oil module 9.

[0050] Working mode ten, cooling the turboshaft engine oil module 9: the cooling liquid flows from the first electronic water pump 101, and sequentially passes through the PTC heater 30, the third port 13 and the first port 11 of the first multi-way valve 1, the warm air core 52, the first inlet and outlet 31 and the fourth inlet and outlet 34 of the third multi-way valve 3, the turboshaft engine oil module 9, the high-temperature radiator 43, the fourth electronic water pump 104, the third inlet and outlet 33 and the second inlet and outlet 32 of the third multi-way valve 3, and finally flows back to the first electronic water pump 101, so as to cool the turboshaft engine oil module 9, and at this time the PTC heater 30 does not work, but only plays a role of conduction.

[0051] Working mode eleven, cooling the turboshaft engine oil module 9: the first cooling liquid flows from the first electronic water pump 101, and sequentially passes through the PTC heater 30, the third port 13 and the second port 12 of the first multi-way valve 1, the battery heating core 61, the first inlet and outlet 31 and the fourth inlet and outlet 34 of the third multi-way valve 3, the high-temperature radiator 43, the fourth electronic water pump 104, the turboshaft engine oil module 9, the third inlet and outlet 33 and the second inlet and outlet 32 of the third multi-way valve 3, and finally flows back to the first electronic water pump 101, so as to complete the circulation of the first cooling liquid, and at this time the PTC heater 30 does not work; the second cooling liquid flows from the first battery heat exchanger 62, and sequentially passes through the second battery heat exchanger 71, the third electronic water pump 103, the battery module 8, the first connecting port 21 and the second connecting port 22 of the second multi-way valve 2, and then flows back to the first battery heat exchanger 62, so as to realize the circulation of the second cooling liquid; heat is transferred between the battery heating core 61 and the second battery heat exchanger 71, so as to realize the heating function of the battery module 8.

[0052] Working mode nine, working mode ten and working mode eleven can all realize the cooling of the turboshaft engine oil module 9, and the redundancy design improves the safety of the aircraft.

[0053] Working mode twelve, cooling the generator control module 50: the cooling liquid flows from the second electronic water pump 102, and sequentially passes through the generator control module 50, the water-cooled condenser 40, the low-temperature radiator 42, the third connecting port 23 and the fourth connecting port 24 of the second multi-way valve 2, and then flows back to the second electronic water pump 102, so as to cool the generator / electronic control system 50.

[0054] Working mode thirteen, battery module 8 and passenger cabin cooling at the same time: the refrigerant from the first compressor 201 into and after the condenser 41 into two ways, one into the first evaporator core 51, the other into the second evaporator core 63, and then flow back to the first compressor 201, can realize the battery module 8 and passenger cabin cooling at the same time; the refrigerant from the second compressor 202 into and in turn through the water-cooled condenser 40, the second evaporator core 63, and then flow back to the second compressor 202, realize the refrigerant cycle refrigeration, because the circuit can only implement battery cooling, so the refrigerant circuit according to whether the demand to start the battery cooling system.

[0055] Working mode fourteen, battery module 8 and passenger cabin heating at the same time: the high temperature cooling liquid through the first port 11 and the second port 12 of the first multi-way valve 1 opening degree proportional adjustment, so that the high temperature cooling liquid passes through the heater core 52 and the battery heating core 61 respectively, wherein the heater core 52 exchanges heat with the air to heat the passenger cabin, and the battery heater core 61 exchanges heat with the first battery heater 62 to heat the battery pack, realizing the heating of the passenger cabin and the battery pack; wherein the high temperature cooling liquid can be the cooling liquid heated by the PTC heater 30, or the high temperature cooling liquid of the turboshaft engine oil module 9.

[0056] Working mode fifteen, battery module 8 and passenger cabin heating at the same time: the battery module 8 heating adopts working mode five, and the passenger cabin heating adopts working mode one or working mode two.

[0057] Working mode fourteen and working mode fifteen can realize the heating of the battery module 8 and the passenger cabin at the same time, and the redundancy design improves the safety of the aircraft.

[0058] Working mode sixteen, battery module 8 cooling and passenger cabin heating: the passenger cabin heating according to working mode one or working mode two, and the battery module 8 cooling according to working mode seven or working mode eight, realizing the heating of the passenger cabin and the cooling of the battery module 8.

[0059] The above only describes some embodiments of the present application. For those skilled in the art, without departing from the inventive concept, several modifications and improvements can be made, which are all within the protection scope of the present application.

Claims

1. An EVTOL aircraft thermal management system, characterized in that, It includes: Switching module, including a first multi-way valve, a second multi-way valve and a third multi-way valve, the first multi-way valve is provided with a first port, a second port and a third port, the second multi-way valve is provided with a first connecting port, a second connecting port, a third connecting port and a fourth connecting port, the third multi-way valve is provided with a first inlet and outlet, a second inlet and outlet, a third inlet and outlet and a fourth inlet and outlet; Cooling module, including a condenser, a low temperature radiator and a high temperature radiator, one end of the high temperature radiator is connected with the fourth inlet and outlet, the other end of the high temperature radiator is connected with the third inlet and outlet and the fourth electronic water pump and the turboshaft engine lubricating oil module is connected between the two; one end of the low temperature radiator is connected with the third connecting port, the other end of the low temperature radiator is connected with the fourth connecting port and the water-cooled condenser, the power generation control module and the second electronic water pump are connected between the two; Passenger compartment temperature control module connected with the passenger cabin, the passenger compartment temperature control module includes a first evaporator core and a warm air core, one end of the warm air core is connected with the first inlet and outlet, the warm air core is connected with the second inlet and outlet and the first port, the third port, the PTC heater and the first electronic water pump are connected between the two in turn; Battery temperature control module, including a battery heating core, a first battery heat exchanger and a second evaporator core; one end of the condenser is connected with a first compressor, the other end is connected with the first evaporator core and one end of the second evaporator core, the other end of the first compressor is connected with the first evaporator core and the other end of the second evaporator core, one end of the battery heating core is connected with the second port and the other end is connected with the first inlet and outlet; Battery cooling module, including a second battery heat exchanger and a third evaporator core, one end of the first battery heat exchanger is connected with the second connecting port, the other end is connected with the second battery heat exchanger, one end of the water-cooled condenser is connected with the third evaporator core, the other end is connected with the second compression motor, the other end of the second compression motor is connected with the third evaporator core; Battery module, one end of which is connected with the first connecting port and the other end is connected with the second battery heat exchanger and the third electronic water pump is connected between the two.

2. An EVTOL aircraft thermal management system as claimed in claim 1, characterized in that: Electronic expansion valves are arranged at the entrances of the first evaporator core, the second evaporator core and the third evaporator core.

3. An EVTOL aircraft thermal management system as claimed in claim 1, characterized in that: The battery module includes a plurality of batteries, one end of each battery is connected with a flow control valve and the other end is connected with a first water temperature sensor.

4. An EVTOL aircraft thermal management system as claimed in claim 1, characterized in that: A second water temperature sensor is arranged between the third electronic water pump and the battery module, a third water temperature sensor is arranged between the power generation control module and the second electronic water pump, and a fourth water temperature sensor is arranged between the fourth electronic water pump and the turboshaft engine lubricating oil module.

5. An EVTOL aircraft thermal management system as claimed in claim 1, characterized by: A first high pressure sensor is arranged between the condenser and the second evaporator core and close to the condenser, and a second high pressure sensor is arranged between the water-cooled condenser and the third evaporator core and close to the water-cooled condenser.

6. An EVTOL aircraft thermal management system as claimed in claim 1, characterized by: A first low pressure sensor is arranged between the first compressor and the second evaporator core near the second evaporator core, and a second low pressure sensor is arranged between the second compressor motor and the third evaporator core near the third evaporator core.

7. An EVTOL aircraft thermal management system as claimed in claim 1, characterized by: The cooling module further comprises two electronic fans.

8. An EVTOL aircraft thermal management system as claimed in claim 1, characterized by: The passenger cabin temperature control module further comprises a blower.

9. An EVTOL aircraft thermal management system as claimed in claim 1, characterized by: A plurality of expansion water jugs are further included.

10. A method for using the aircraft thermal management system according to any one of claims 1 to 9, comprising one or more combinations of the following working modes: Working mode one, the PTC heater works to heat the passenger cabin: the coolant flows from the first electronic water pump and sequentially passes through the PTC heater, the third port and the first port of the first multi-way valve, the heating core, the first inlet and outlet and the second inlet and outlet of the third multi-way valve, and then flows back to the first electronic water pump; Working mode two, the waste heat of the turboshaft engine oil module heats the passenger cabin: the coolant flows from the first electronic water pump and sequentially passes through the PTC heater, the third port and the first port of the first multi-way valve, the heating core, the first inlet and outlet and the fourth inlet and outlet of the third multi-way valve, the high-temperature radiator, the fourth electronic water pump, the turboshaft engine oil module, the third inlet and outlet and the second inlet and outlet of the third multi-way valve, and then flows back to the first electronic water pump; Working mode three, the first compressor refrigeration cools the passenger cabin: the refrigerant flows from the first compressor and sequentially passes through the condenser and the first evaporator core, and then flows back to the first compressor; Working mode four, the PTC heater works to heat the battery module: the first path of the coolant flows from the first electronic water pump and sequentially passes through the PTC heater, the third port and the second port of the first multi-way valve, the battery heating core, the first inlet and outlet and the second inlet and outlet of the third multi-way valve, and then flows back to the first electronic water pump; the second path of the coolant flows from the first battery heat exchanger and sequentially passes through the second battery heat exchanger, the third electronic water pump, the battery module, the first connection port and the second connection port of the second multi-way valve, and then flows back to the first battery heat exchanger, the battery heating core and the second battery heat exchanger exchange heat; Working mode five, the waste heat of the power generation control module heats the battery module: the coolant flows from the first battery heat exchanger and sequentially passes through the second battery heat exchanger, the third electronic water pump, the battery module, the first connection port and the fourth connection port of the second multi-way valve, the second electronic water pump, the power generation control module, the water-cooled condenser, the low-temperature radiator, the third connection port and the second connection port of the second multi-way valve, and then flows back to the first battery heat exchanger; Working mode six, the waste heat of the turboshaft engine oil module heats the battery module: the first cooling liquid flows from the first electronic water pump, sequentially passes through the PTC heater, the third port and the second port of the first multi-way valve, the battery heating core, the first inlet and outlet and the fourth inlet and outlet of the third multi-way valve, the high-temperature radiator, the fourth electronic water pump, the turboshaft engine oil module, the third inlet and outlet and the second inlet and outlet of the third multi-way valve, and flows back to the first electronic water pump; the second cooling liquid flows from the first battery heat exchanger, sequentially passes through the second battery heat exchanger, the third electronic water pump, the battery module, the first connection port and the second connection port of the second multi-way valve, and flows back to the first battery heat exchanger; the battery heating core and the second battery heat exchanger exchange heat; Working mode seven, the first compressor cools the battery module: the refrigerant enters from the first compressor, sequentially passes through the condenser and the second evaporator core, and flows back to the first compressor; The cooling liquid flows from the first battery heat exchanger, sequentially passes through the second battery heat exchanger, the third electronic water pump, the battery module, the first connection port and the second connection port of the second multi-way valve, and flows back to the first battery heat exchanger; The second evaporator core exchanges heat with the first battery heat exchanger; Working mode eight, the second compressor cools the battery module: the refrigerant enters from the second compressor, sequentially passes through the water-cooled condenser and the third evaporator core, and flows back to the second compressor; The cooling liquid flows from the first battery heat exchanger, sequentially passes through the second battery heat exchanger, the third electronic water pump, the battery module, the first connection port and the second connection port of the second multi-way valve, and flows back to the first battery heat exchanger; The second evaporator core exchanges heat with the first battery heat exchanger; Working mode nine, the turboshaft engine oil module is cooled: the cooling liquid flows from the fourth electronic water pump, sequentially passes through the turboshaft engine oil module, the third inlet and outlet and the fourth inlet and outlet of the third multi-way valve, and the high-temperature radiator, and flows back to the fourth electronic water pump; Working mode ten, the turboshaft engine oil module is cooled: the cooling liquid flows from the first electronic water pump, sequentially passes through the PTC heater, the third port and the first port of the first multi-way valve, the warm air core, the first inlet and outlet and the fourth inlet and outlet of the third multi-way valve, the turboshaft engine oil module, the high-temperature radiator, the fourth electronic water pump, the third inlet and outlet and the second inlet and outlet of the third multi-way valve, and flows back to the first electronic water pump; Eleventh working mode, cooling the turboshaft engine oil module: the first cooling liquid flows from the first electronic water pump, and sequentially passes through the PTC heater, the third port and the second port of the first multi-way valve, the battery heating core, the first inlet and outlet and the fourth inlet and outlet of the third multi-way valve, the high-temperature radiator, the fourth electronic water pump, the turboshaft engine oil module, the third inlet and outlet and the second inlet and outlet of the third multi-way valve, and then flows back to the first electronic water pump; the second cooling liquid flows from the first battery heat exchanger, and sequentially passes through the second battery heat exchanger, the third electronic water pump, the battery pack module, the first connecting port and the second connecting port of the second multi-way valve, and then flows back to the first battery heat exchanger; the battery heating core and the second battery heat exchanger exchange heat; Twelfth working mode, cooling the power generation control module: the cooling liquid flows from the second electronic water pump, and sequentially passes through the power generation control module, the water-cooled condenser, the low-temperature radiator, the third connecting port and the fourth connecting port of the second multi-way valve, and then flows back to the second electronic water pump.

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