CN117578003A - Temperature control system and operation method of electric aircraft - Google Patents
Temperature control system and operation method of electric aircraft Download PDFInfo
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- CN117578003A CN117578003A CN202311485799.3A CN202311485799A CN117578003A CN 117578003 A CN117578003 A CN 117578003A CN 202311485799 A CN202311485799 A CN 202311485799A CN 117578003 A CN117578003 A CN 117578003A
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- 238000000034 method Methods 0.000 title claims abstract description 10
- 239000007788 liquid Substances 0.000 claims abstract description 210
- 230000001105 regulatory effect Effects 0.000 claims abstract description 14
- 238000001704 evaporation Methods 0.000 claims abstract description 11
- 230000008020 evaporation Effects 0.000 claims abstract description 11
- 239000000110 cooling liquid Substances 0.000 claims description 55
- 238000012544 monitoring process Methods 0.000 claims description 15
- 230000000087 stabilizing effect Effects 0.000 claims description 10
- 230000005855 radiation Effects 0.000 claims description 7
- 239000003507 refrigerant Substances 0.000 claims description 7
- 238000005057 refrigeration Methods 0.000 claims description 7
- 238000007599 discharging Methods 0.000 claims description 6
- 238000010438 heat treatment Methods 0.000 claims description 4
- 230000001276 controlling effect Effects 0.000 claims description 3
- 230000002159 abnormal effect Effects 0.000 claims description 2
- 239000002826 coolant Substances 0.000 claims description 2
- 230000003247 decreasing effect Effects 0.000 claims description 2
- 238000009834 vaporization Methods 0.000 claims description 2
- 230000008016 vaporization Effects 0.000 claims description 2
- 230000001502 supplementing effect Effects 0.000 claims 1
- 238000001816 cooling Methods 0.000 abstract description 6
- 230000017525 heat dissipation Effects 0.000 abstract description 5
- 238000005265 energy consumption Methods 0.000 abstract description 3
- 230000007613 environmental effect Effects 0.000 abstract description 3
- 230000010354 integration Effects 0.000 abstract description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 5
- 229910052799 carbon Inorganic materials 0.000 description 5
- 238000010586 diagram Methods 0.000 description 5
- 230000005856 abnormality Effects 0.000 description 1
- 230000002238 attenuated effect Effects 0.000 description 1
- 239000012809 cooling fluid Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 230000008014 freezing Effects 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- 238000013021 overheating Methods 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
Classifications
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K9/00—Arrangements for cooling or ventilating
- H02K9/19—Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D23/00—Control of temperature
- G05D23/19—Control of temperature characterised by the use of electric means
- G05D23/30—Automatic controllers with an auxiliary heating device affecting the sensing element, e.g. for anticipating change of temperature
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M10/00—Secondary cells; Manufacture thereof
- H01M10/60—Heating or cooling; Temperature control
- H01M10/61—Types of temperature control
- H01M10/613—Cooling or keeping cold
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M10/00—Secondary cells; Manufacture thereof
- H01M10/60—Heating or cooling; Temperature control
- H01M10/61—Types of temperature control
- H01M10/615—Heating or keeping warm
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M10/00—Secondary cells; Manufacture thereof
- H01M10/60—Heating or cooling; Temperature control
- H01M10/63—Control systems
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M10/00—Secondary cells; Manufacture thereof
- H01M10/60—Heating or cooling; Temperature control
- H01M10/63—Control systems
- H01M10/637—Control systems characterised by the use of reversible temperature-sensitive devices, e.g. NTC, PTC or bimetal devices; characterised by control of the internal current flowing through the cells, e.g. by switching
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M10/00—Secondary cells; Manufacture thereof
- H01M10/60—Heating or cooling; Temperature control
- H01M10/65—Means for temperature control structurally associated with the cells
- H01M10/656—Means for temperature control structurally associated with the cells characterised by the type of heat-exchange fluid
- H01M10/6569—Fluids undergoing a liquid-gas phase change or transition, e.g. evaporation or condensation
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Electrochemistry (AREA)
- General Chemical & Material Sciences (AREA)
- Automation & Control Theory (AREA)
- Power Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Control Of Temperature (AREA)
Abstract
The invention relates to a temperature control system and an operation method of an electric airplane, and belongs to the field of airborne environmental control. The device comprises a liquid storage component (1), a main pipeline (2), a battery temperature control branch (3), a motor temperature control branch (4) and a controller temperature control branch (5); according to the invention, the four-way valve is connected with each temperature control branch in parallel, and the temperature of each temperature control branch is regulated under the combined action of the temperature pressure sensor and the liquid pump of each temperature control branch, so that the heat dissipation problem of the three-electric battery, the motor and the motor controller system of the electric aircraft is solved in an integrated manner. Meanwhile, the heater is connected in parallel on the battery temperature control branch, so that heat dissipation of the motor and the controller is not affected under the condition that the battery is effectively protected in a low-temperature environment. In addition, the reliability of the system is improved by the parallel connection of the liquid pumps; and the cooling capacity of the temperature control system is improved by radiating through the evaporation circulation refrigerating system. The temperature control system has the characteristics of high system integration degree, accurate temperature control, low energy consumption and high reliability.
Description
Technical Field
The invention relates to a temperature control system and an operation method of an electric airplane, and belongs to the field of airborne environmental control.
Background
With the explosive development of the aviation industry, the carbon emissions of aircraft rise year by year. The carbon emissions of civil aviation are statistically 2.5% -4% of the total carbon emissions in the world, and it is expected that the traffic of civil aviation will increase at a rate of 4.6% per year within 20 years thereafter [1]. The International Air Transport Association (IATA) promises that the aviation industry should achieve net zero emissions in 2050, 18 hundred million tons of carbon reduction. Electric aircraft are receiving increasing attention as low carbon, zero emission solutions. However, the working environment of the electric aircraft is more changeable and more severe than the ground, and meanwhile, the power density requirement on a three-electric (battery, motor and electric control) system is higher, so the requirement on a thermal management system is also more severe.
The battery of the electric aircraft bears the important task of storing and providing energy, and long-time high-power discharge can cause the temperature rise of the battery, which can cause safety problems such as overheating and thermal runaway. In addition, when the temperature is too low, the battery capacity may be greatly attenuated; the motor and its controller affect the power, efficiency, comfort, etc. of the electric aircraft. The motor windings and mechanical friction generate a lot of heat, and with the recent rise of power density, the heat generated by the motor and its controller also rises sharply, and the requirements for heat management are also more stringent. Therefore, the reasonable thermal management system can maintain the three-electric system of the electric aircraft to work in a proper temperature range, improve the service life and performance of the system and ensure the safe and safe operation of the system.
[1] Sun Xiasheng, cheng Wenyuan, mu Zuodong, etc. electric aircraft developed white book [ J ]. Aviation science, 2019, 30 (11): 1-7.
The invention comprises the following steps:
the purpose of the invention is that:
the invention solves the problem of thermal protection of the three-electric system of the electric aircraft in a complex environment through a temperature control system with parallel temperature control branches, temperature and pressure sensors and a liquid pump for regulating the functions together. In addition, the reliability of the system is improved through the parallel motor; and the cooling capacity of the temperature control system is improved by adopting the evaporation circulation refrigerating system to dissipate heat. The temperature control system has the characteristics of high system integration degree, accurate temperature control, low energy consumption and high reliability.
The technical scheme of the invention is as follows: the temperature control system of the electric aircraft comprises a liquid storage component 1, a main pipeline 2, a battery temperature control branch 3, a motor temperature control branch 4 and a controller temperature control branch 5; the liquid storage tank a is connected with a main pipeline 2, and then is divided into three parallel branches of a battery temperature control branch 3, a motor temperature control branch 4 and a controller temperature control branch 5, and then the three parallel branches are converged on the main pipeline 2 and connected back to the liquid storage component 1; the liquid storage assembly 1 comprises a liquid storage tank a, a liquid discharge valve a101, a liquid level meter a102, a pressure stabilizing tank a104, a heater a105 and a temperature and pressure sensor a106; the liquid discharge valve a101 is positioned at the bottom of the liquid storage tank a, the liquid level meter a102, the heater a105 and the temperature and pressure sensor a106 are immersed in liquid in the liquid storage tank a, and the pressure stabilizing tank a104 is positioned at the top of the liquid storage tank a; the main pipeline 2 comprises a shutoff valve a201, a four-way valve 202, a radiator 203, a heat radiation fan 204 and a temperature and pressure sensor b205; one end of the shutoff valve a201 is connected with the liquid storage tank a, the other end of the shutoff valve a201 is connected with one interface of the four-way valve 202, the other three interfaces of the four-way valve 202 are connected with one ends of the battery temperature control branch 3, the motor temperature control branch 4 and the controller temperature control branch 5, one end of the radiator 203 is connected with one ends of the battery temperature control branch 3, the motor temperature control branch 4 and the controller temperature control branch 5, the other end of the radiator 203 is connected with the liquid storage tank a, the radiator fan 204 is opposite to and is close to the radiator 203, and the temperature pressure sensor b205 is positioned on a pipeline of the radiator 203 connected with the liquid storage tank a; the battery temperature control branch 3 comprises a liquid pump a301, a battery heat exchanger 302, a temperature and pressure sensor c303, a shut-off valve b304, a liquid storage tank b305 and a shut-off valve c311; the battery temperature control branch 3 is formed by connecting two branches in parallel, one branch is formed by connecting a liquid pump a301 with a battery heat exchanger 302 and a temperature and pressure sensor c303 in series in sequence, the other branch is formed by connecting a shut-off valve c311 with a liquid storage tank b305 in series, the liquid pump a301 is connected with the shut-off valve c311 in parallel, the temperature and pressure sensor c303 is connected with the liquid storage tank b305 in parallel and then connected with a shut-off valve b304 in series, and the other end of the shut-off valve b304 is connected with the radiator 203; the liquid storage tank b305 comprises a liquid discharge valve b306, a liquid level meter b307, a pressure stabilizing tank b308, a temperature and pressure sensor d309 and a heater b310; the liquid discharge valve b306 is positioned at the bottom of the liquid storage tank b305, the liquid level meter b307, the temperature and pressure sensor d309 and the heater b310 are immersed in the liquid storage tank b305, and the pressure stabilizing tank b308 is positioned at the top of the liquid storage tank a; the motor temperature control branch 4 comprises a liquid pump b401, a motor heat exchanger 402 and a temperature and pressure sensor e403; one end of the liquid pump b401 is connected with the four-way valve 202, the other end of the liquid pump b is sequentially connected with the motor heat exchanger 402 and the temperature and pressure sensor e403 in series, and the other end of the temperature and pressure sensor e403 is connected with the radiator 203; the controller temperature control branch 5 comprises a liquid pump c501, a controller heat exchanger 502 and a temperature and pressure sensor f503; one end of the liquid pump c501 is connected with the four-way valve 202, the other end of the liquid pump c is sequentially connected with the controller heat exchanger 502 and the temperature and pressure sensor f503 in series, and the other end of the temperature and pressure sensor f503 is connected with the radiator 203;
further, the battery temperature control branch 3, the motor temperature control branch 4 and the controller temperature control branch 5 can adopt a mode that the liquid pump d602 and the liquid pump e603 are connected in parallel through the electric three-way ball valve a601 and the electric three-way ball valve b604, and the cooling liquid 103 is selectively made to pass through the liquid pump d602 or the liquid pump e603 through switching of the electric three-way ball valve a601 and the electric three-way ball valve b604, so that the liquid pump d602 and the liquid pump e603 form a backup relationship.
Further, the heat radiation fan 204 is replaced by an evaporation circulation refrigeration system 7, and the evaporation circulation refrigeration system 7 comprises an evaporator 701, a compressor 702, a condenser 703 and an expansion valve 704; the evaporator 701 exchanges heat with the radiator 203, the refrigerant 705 inside the evaporator 701 absorbs heat and is vaporized, the vaporized refrigerant 705 is sucked by the compressor 702 to be compressed and becomes high-temperature high-pressure gas, the high-temperature high-pressure gas is condensed into medium-temperature high-pressure liquid through the condenser 703, the medium-temperature high-pressure liquid is changed into low-temperature low-pressure liquid after being throttled by the expansion valve 704, and then the low-temperature low-pressure liquid enters the evaporator 701 again to absorb heat of the radiator 203 to be vaporized, so that the heat of the temperature control system can be continuously discharged through continuous circulation.
A method for operating a temperature control system of an electric aircraft,
when the temperature and pressure sensor a106 detects that the temperature is lower than the working temperature range of the cooling liquid, the system heats the cooling liquid to the working temperature range through the heater a105 and then starts working; after starting the operation, the cooling liquid flows from the liquid storage tank a to the main pipeline 2 under the drive of the liquid pump a301, the liquid pump b401 and the liquid pump c501, flows to the four-way valve 202 through the shutoff valve a201, and then flows to the battery temperature control branch 3, the motor temperature control branch 4 and the controller temperature control branch 5 respectively;
when the battery needs to be cooled, the four-way valve 202 is opened to flow to the outlet of the battery temperature control branch 3, the shutoff valve c311 is closed, the shutoff valve b304 is opened, the cooling liquid flows from the four-way valve 202 to the battery heat exchanger 302 under the drive of the liquid pump a301, then flows through the temperature and pressure sensor c303 and the shutoff valve b304, and flows to the main pipeline 2;
when the ambient temperature is lower than the battery working temperature range, firstly, the four-way valve 202 is opened to flow to the battery temperature control branch 3, the shutoff valve c311 is closed, the shutoff valve b304 is closed, the cooling liquid 103 is driven by the liquid pump a301 to flow through the liquid pump a301, the battery heat exchanger 302 and the temperature and pressure sensor c303 respectively by the four-way valve 202, then flows into the liquid storage tank b305, after the liquid level meter b307 detects that the cooling liquid in the liquid storage tank b310 is in a specified range, the four-way valve 202 is closed to flow to the battery temperature control branch 3, and the shutoff valve c311 is opened; when the temperature-pressure sensor c303 monitors that the temperature of the battery temperature control branch 3 exceeds or falls below a prescribed range, the rotational speed of the liquid pump a301 is reduced or increased, or the heating power of the heater b310 is reduced or increased until the battery temperature is within a prescribed interval range;
the cooling liquid 103 flows out from the four-way valve 202, enters the motor heat exchanger 402 through the liquid pump b401 to exchange heat, and then flows to the main pipeline 2 through the temperature and pressure sensor e403; the temperature and pressure sensor e403 monitors the temperature and pressure of the motor temperature control branch 4, and then the temperature of the motor on the aircraft is regulated through the liquid pump b 401;
the cooling liquid 103 flows out from the four-way valve 202, enters the motor heat exchanger 502 through the liquid pump c501 for heat exchange, and then flows to the main pipeline 2 through the temperature and pressure sensor f503; the temperature and pressure sensor f503 monitors the temperature and pressure of the controller temperature control branch 5, and then the temperature of the controller on the aircraft is regulated through the liquid pump c 501;
the cooling liquid 103 flows to the radiator 203 after the main pipes 2 are joined, and after heat is transferred to the air by the heat radiation fan 204, the temperature is lowered, and then flows back to the liquid tank a through the temperature and pressure sensor b 205.
Further, the temperature and pressure sensor b205 is used for monitoring the temperature and pressure of the main pipeline, and regulating the temperature of the cooling liquid 103 flowing back to the liquid storage tank a through the fan rotating speed, the liquid discharge valve a101 is used for discharging the cooling liquid in the liquid storage tank a101, the liquid level meter a102 is used for monitoring the liquid position in the liquid storage tank a101, and when the liquid level is lower than a specified range, the cooling liquid 103 is prompted to be replenished.
Further, the surge tank a104 is used for adjusting the pressure of the stable temperature control system, and the temperature and pressure sensor a106 is used for monitoring the temperature and the pressure in the liquid storage tank a; when the pressure of any place of the temperature control system is abnormal, the temperature control system is closed.
Further, the temperature and pressure sensor c303 is used to monitor the temperature and pressure of the battery temperature control branch 3, and when the temperature exceeds or falls below a prescribed range, increasing or decreasing the rotational speed of the liquid pump a301 adjusts the flow rate of the coolant entering the battery heat exchanger, thereby controlling the amount of heat exchange thereof.
Further, the surge tank b308 is used for adjusting the pressure of the battery temperature control branch 3, the temperature and pressure sensor d309 is used for monitoring the temperature and pressure in the liquid storage tank b305, and the liquid discharge valve b306 is used for discharging the cooling liquid 103 in the liquid storage tank b 305.
The invention has the technical effects that:
according to the invention, the four-way valve is connected with each temperature control branch in parallel, and the temperature of each temperature control branch is regulated under the combined action of the temperature pressure sensor and the liquid pump of each temperature control branch, so that the heat dissipation problem of the three-electric battery, the motor and the motor controller system of the electric aircraft is solved in an integrated manner. Meanwhile, the heater is connected in parallel on the battery temperature control branch, so that heat dissipation of the motor and the controller is not affected under the condition that the battery is effectively protected in a low-temperature environment. In addition, the reliability of the system is improved by the parallel connection of the liquid pumps; and the cooling capacity of the temperature control system is improved by radiating through the evaporation circulation refrigerating system. The temperature control system has the characteristics of high system integration degree, accurate temperature control, low energy consumption and high reliability.
Drawings
FIG. 1 is a schematic diagram of a temperature control system
FIG. 2 is a schematic diagram of the operation of the temperature control system in the low temperature environment
FIG. 3 is a schematic diagram of a backup water pump in parallel
FIG. 4 is a schematic diagram of heat dissipation using an evaporative circulation system
Wherein: 1: a liquid storage component; 101: a liquid discharge valve a;102: a liquid level meter a;103: a cooling liquid; 104: a surge tank a;105: a heater a;106: a temperature and pressure sensor a;2: a main pipeline; 201: a shut-off valve a;202: a four-way valve; 203: a heat sink; 204: a heat radiation fan; 205: a temperature and pressure sensor b;3: a battery temperature control branch; 301: a liquid pump a;302: a battery heat exchanger; 303: a temperature and pressure sensor c;304: a shut-off valve b;305: a liquid storage tank b;306: a drain valve b;307: a liquid level meter b;308: a surge tank b;309: a temperature and pressure sensor d;310: a heater b;311: a shut-off valve c;4: a motor temperature control branch; 401: a liquid pump b;402: a motor heat exchanger; 403: a temperature and pressure sensor e;5: a controller temperature control branch; 501: a liquid pump c;502 a controller heat exchanger; 503: a temperature and pressure sensor f;601: an electric three-way ball valve a;602: a liquid pump d;603: a liquid pump e;604: an electric three-way ball valve b;7: an evaporation cycle refrigeration system; 701: an evaporator; 702: a compressor; 703: a condenser; 704: an expansion valve; 705: and (3) a refrigerant.
Detailed Description
The invention is further described below with reference to the accompanying drawings:
fig. 1 is a schematic diagram of a temperature control system for an electric aircraft battery, motor and controller thereof. The system mainly comprises a liquid storage tank a, a main pipeline 2, a battery temperature control branch 3, a motor temperature control branch 4 and a controller temperature control 5; the liquid storage tank a comprises a liquid discharge valve a101, a liquid level meter a102, cooling liquid 103, a pressure stabilizing tank a104, a heater a105 and a temperature and pressure sensor a106; the main pipeline 2 comprises a shutoff valve a201, a four-way valve 202, a radiator 203, a heat radiation fan 204 and a temperature and pressure sensor b205; the battery temperature control branch 3 comprises a liquid pump a301, a battery heat exchanger 302, a temperature and pressure sensor c303, a shut-off valve b304, a drain valve b306, a liquid level meter b307, a surge tank b308, a temperature and pressure sensor d309, a heater b310 and a shut-off valve c311; the motor temperature control branch 4 comprises a liquid pump b401, a motor heat exchanger 402 and a temperature and pressure sensor e403; the controller temperature control branch 5 comprises a liquid pump c501, a controller heat exchanger 502 and a temperature and pressure sensor f503; before use, a certain amount of cooling liquid 103 is filled into the system through the liquid storage tank a, and the pressure of the system is regulated through the pressure stabilizing tank a104, so that the pressure of the system is in a proper pressure range before operation.
The working principle of the invention is as follows:
when the temperature and pressure sensor a106 detects that the temperature of the cooling liquid 103 is proper, the system directly starts to start working without low temperature, high viscosity and even freezing caused by low ambient temperature. When the temperature and pressure sensor a106 detects that the temperature of the cooling liquid 103 is too low, the system heats the cooling liquid 103 to a proper temperature through the heater a105, and then starts the operation. After the start-up operation, the cooling liquid 103 flows from the liquid storage tank a to the main pipeline 2, flows to the four-way valve 202 through the shutoff valve a201, and then flows to the battery temperature control branch 3, the motor temperature control branch 4 and the controller temperature control branch 5 under the driving of the liquid pump a301, the liquid pump b401 and the liquid pump c 501.
For battery temperature control branch 3:
when the battery needs to be cooled, the four-way valve 202 is opened to flow to the outlet of the battery temperature control branch 3, the shutoff valve c311 is closed, the shutoff valve b304 is opened, and the cooling liquid flows to the battery heat exchanger 302 from the four-way valve 202 under the drive of the liquid pump a301, so that the purpose of cooling the battery is achieved. Then, the cooling liquid 103 flows through the temperature and pressure sensor c303 and the shut-off valve b304, and then flows to the main pipe 2, and the flow direction of the cooling liquid 103 is shown in fig. 1. The temperature and pressure sensor c303 is used for monitoring the temperature and pressure of the battery temperature control branch 3, and when the temperature exceeds or falls below a specified range, the rotating speed of the liquid pump a301 is increased or reduced to adjust the flow rate of the cooling liquid entering the battery heat exchanger, so that the heat exchange amount is controlled, and the purpose of controlling the battery temperature in a reasonable interval is achieved.
When the environmental temperature is too low and the battery needs to be warmed, the four-way valve 202 is firstly opened to flow to the battery temperature control branch 3, the shutoff valve c311 is closed, the shutoff valve b304 is closed, the cooling liquid flows into the liquid storage tank b305 after passing through the liquid pump a301, the battery heat exchanger 302 and the temperature and pressure sensor c303 respectively through the four-way valve 202 under the drive of the liquid pump a301, and after detecting that enough cooling liquid exists in the liquid storage tank b310 through the liquid level meter b307, the four-way valve 202 is closed to flow to the battery temperature control branch 3, and the shutoff valve c311 is opened. The cooling liquid is heated by the heater b310, the heated cooling liquid flows through the shut-off valve c311 under the action of the liquid pump a301, then flows to the battery heat exchanger 302 to heat the battery, and then flows back to the liquid storage tank b305 to be heated, so that the heating protection of the battery can be completed by continuous circulation, and the flowing direction of the cooling liquid 103 is shown in fig. 2. The temperature and pressure sensor c303 is used to monitor the temperature and pressure of the battery temperature control branch 3, and when the temperature exceeds or falls below a predetermined range, the flow rate of the cooling liquid entering the battery heat exchanger is regulated by reducing or increasing the rotation speed of the liquid pump a301, or the heating power of the heater b310 is reduced or increased, so that the heat exchange amount with the battery is controlled, and the battery temperature is within a reasonable interval range. The surge tank b308 is used for adjusting the pressure of the battery temperature control branch 3, the temperature and pressure sensor d309 is used for monitoring the temperature and pressure in the liquid storage tank b305, and the liquid discharge valve b306 is used for discharging the cooling liquid 103 in the liquid storage tank b 305.
For the motor temperature control branch 4, the cooling liquid 103 flows out from the four-way valve 202, enters the motor heat exchanger 402 through the liquid pump b401 to exchange heat, achieves the purpose of cooling the motor, and then flows to the main pipeline 2 through the temperature and pressure sensor e 403. The temperature and pressure sensor e403 is used for monitoring the temperature and pressure of the motor temperature control branch 4, and then the temperature of the motor is regulated by the liquid pump b401, as the temperature and pressure sensor c 303.
Similarly, for the controller temperature control branch 5, the cooling liquid 103 flows out from the four-way valve 202, enters the motor heat exchanger 502 through the liquid pump c501 for heat exchange, achieves the purpose of cooling the controller, and then flows to the main pipeline 2 through the temperature and pressure sensor f 503. The temperature and pressure sensor e503 is used for monitoring the temperature and pressure of the temperature control branch 5 of the controller and further adjusting the temperature of the controller.
The cooling liquid 103 flows out from the battery temperature control branch 3, the motor temperature control branch 4 and the controller temperature control branch 5 respectively, flows to the radiator 203 after being converged by the main pipeline 2, and flows back to the liquid storage tank a after the temperature is reduced by transferring heat to the air through the action of the radiating fan 204 and then flows back to the liquid storage tank a through the temperature and pressure sensor b 205. The temperature and pressure sensor b205 is used to monitor the temperature and pressure of the main line and regulate the temperature of the cooling fluid 103 flowing back to the reservoir a through the main line 2 by the fan speed. The liquid discharge valve a101 is used for discharging the cooling liquid in the liquid storage tank a101, the liquid level meter a102 is used for monitoring the liquid position in the liquid storage tank a101, and when the liquid level is too low, the supplementary cooling liquid 103 is prompted. The surge tank a104 is used for regulating the pressure of the stabilization system, and the temperature and pressure sensor a106 is used for monitoring the temperature and pressure in the liquid storage tank a. When an abnormality is detected in the pressure anywhere in the system, the system is shut down.
The liquid pumps of the battery temperature control branch 3, the motor temperature control branch 4 and the controller temperature control branch 5 can adopt a mode that a liquid pump d602 and a liquid pump e603 are connected in parallel through an electric three-way ball valve a601 and an electric three-way ball valve b604 as shown in fig. 3, and cooling liquid 103 passes through the liquid pump d602 or the liquid pump e603 through switching of the electric three-way ball valve a601 and the electric three-way ball valve b604, so that the liquid pump d602 and the liquid pump e603 form a backup relationship, and the reliability of the system is enhanced.
Further, in order to increase the temperature difference between the heat dissipating system and the environment, so as to significantly increase the heat dissipating capacity of the system, the heat dissipating fan 204 may be replaced by the evaporation circulation refrigeration system 7 as shown in fig. 4 to dissipate heat to the temperature control system. The evaporator 701 of the evaporation circulation refrigeration system 7 absorbs heat of the radiator 203, the refrigerant 705 in the evaporator 701 absorbs heat and is vaporized, the vaporized refrigerant 705 is sucked by the compressor 702 to be compressed and becomes high-temperature high-pressure gas, the high-temperature high-pressure gas is condensed into medium-temperature high-pressure liquid through the condenser 703, and the medium-temperature high-pressure liquid is throttled by the expansion valve 704 and becomes low-temperature low-pressure liquid; then the heat enters the evaporator 703 again to absorb the heat of the heat radiator 203 for evaporation and vaporization, so that the heat of the temperature control system can be continuously discharged by continuous circulation.
Claims (8)
1. The temperature control system of the electric aircraft is characterized by comprising a liquid storage component (1), a main pipeline (2), a battery temperature control branch (3), a motor temperature control branch (4) and a controller temperature control branch (5); the liquid storage assembly (1) is connected with a main pipeline (2), and then is divided into three parallel branches of a battery temperature control branch (3), a motor temperature control branch (4) and a controller temperature control branch (5), and the three parallel branches are converged on the main pipeline (2) and connected back to the liquid storage assembly (1); the liquid storage assembly (1) comprises a liquid storage tank a, a liquid discharge valve a (101), a liquid level meter a (102), a pressure stabilizing tank a (104), a heater a (105) and a temperature and pressure sensor a (106); the liquid discharge valve a (101) is positioned at the bottom of the liquid storage tank a, the liquid level meter a (102), the heater a (105) and the temperature and pressure sensor a (106) are immersed in liquid in the liquid storage tank a, and the pressure stabilizing tank a (104) is positioned at the top of the liquid storage tank a; the main pipeline (2) comprises a shutoff valve a (201), a four-way valve (202), a radiator (203), a heat radiation fan (204) and a temperature and pressure sensor b (205); one end of the shutoff valve a (201) is connected with the liquid storage tank a, the other end of the shutoff valve a is connected with one interface of the four-way valve (202), the other three interfaces of the four-way valve (202) are connected with one end of the battery temperature control branch circuit (3), one end of the motor temperature control branch circuit (4) and one end of the controller temperature control branch circuit (5), one end of the radiator (203) is connected with one end of the battery temperature control branch circuit (3), one end of the motor temperature control branch circuit (4) and one end of the controller temperature control branch circuit (5), the other end of the radiator is connected with the liquid storage tank a, the radiating fan (204) is opposite to and is close to the radiator (203), and the temperature and pressure sensor b (205) is positioned on a pipeline connected with the liquid storage tank a through the radiator (203); the battery temperature control branch circuit (3) comprises a liquid pump a (301), a battery heat exchanger (302), a temperature and pressure sensor c (303), a shut-off valve b (304), a liquid storage tank b (305) and a shut-off valve c (311); the battery temperature control branch circuit (3) is formed by connecting two branches in parallel, one branch is formed by connecting a liquid pump a (301) with a battery heat exchanger (302) and a temperature and pressure sensor c (303) in series, the other branch is formed by connecting a shut-off valve c (311) with a liquid storage tank b (305) in series, the liquid pump a (301) is connected with the shut-off valve c (311) in parallel, the temperature and pressure sensor c (303) is connected with the liquid storage tank b (305) in parallel and then connected with the shut-off valve b (304) in series, and the other end of the shut-off valve b (304) is connected with the radiator (203); the liquid storage tank b (305) comprises a liquid discharge valve b (306), a liquid level meter b (307), a pressure stabilizing tank b (308), a temperature and pressure sensor d (309) and a heater b (310); the liquid discharge valve b (306) is positioned at the bottom of the liquid storage tank b (305), the liquid level meter b (307), the temperature and pressure sensor d (309) and the heater b (310) are immersed in the liquid storage tank b (305), and the pressure stabilizing tank b (308) is positioned at the top of the liquid storage tank a; the motor temperature control branch circuit (4) comprises a liquid pump b (401), a motor heat exchanger (402) and a temperature and pressure sensor e (403); one end of the liquid pump b (401) is connected with the four-way valve (202), the other end of the liquid pump b is sequentially connected with the motor heat exchanger (402) and the temperature and pressure sensor e (403) in series, and the other end of the temperature and pressure sensor e (403) is connected with the radiator (203); the controller temperature control branch circuit (5) comprises a liquid pump c (501), a controller heat exchanger (502) and a temperature and pressure sensor f (503); one end of the liquid pump c (501) is connected with the four-way valve (202), the other end of the liquid pump c is connected with the controller heat exchanger (502) and the temperature and pressure sensor f (503) in series, and the other end of the temperature and pressure sensor f (503) is connected with the radiator (203).
2. The temperature control system of an electric aircraft according to claim 1, wherein the battery temperature control branch (3), the motor temperature control branch (4) and the controller temperature control branch (5) are connected in parallel by the electric three-way ball valve a (601) and the electric three-way ball valve b (604), and the cooling liquid (103) is selectively passed through the liquid pump d602 or the liquid pump e (603) by switching the electric three-way ball valve a (601) and the electric three-way ball valve b (604), so that the liquid pump d (602) and the liquid pump e (603) are in a backup relationship.
3. The temperature control system of an electric aircraft according to claim 1, characterized in that the heat radiation fan (204) is replaceable with an evaporation cycle refrigeration system (7), the evaporation cycle refrigeration system (7) comprising an evaporator (701), a compressor (702), a condenser (703), an expansion valve (704); the evaporator (701) exchanges heat with the radiator (203), the refrigerant (705) in the evaporator (701) absorbs heat and then is vaporized, the vaporized refrigerant (705) is sucked by the compressor (702) to be compressed and becomes high-temperature high-pressure gas, the high-temperature high-pressure gas is condensed into medium-temperature high-pressure liquid through the condenser (703), the medium-temperature high-pressure liquid is throttled by the expansion valve (704) and becomes low-temperature low-pressure liquid, and then the low-temperature low-pressure liquid enters the evaporator (701) again to absorb heat of the radiator (203) for vaporization, and the heat of the temperature control system can be continuously discharged through continuous circulation.
4. The method for operating a temperature control system for an electric aircraft according to claim 1, wherein the system directly starts the operation when the temperature and pressure sensor a (106) detects that the temperature is within the operating temperature range of the cooling liquid, and the system heats the cooling liquid to the operating temperature range through the heater a (105) and then starts the operation again when the temperature and pressure sensor a (106) detects that the temperature is lower than the operating temperature range of the cooling liquid; after starting, the cooling liquid flows from the liquid storage tank a to the main pipeline (2) under the drive of the liquid pump a (301), the liquid pump b (401) and the liquid pump c (501), flows to the four-way valve (202) through the shutoff valve a (201), and then flows to the battery temperature control branch circuit (3), the motor temperature control branch circuit (4) and the controller temperature control branch circuit (5) respectively;
when the battery needs to be cooled, opening the four-way valve (202) to flow to the outlet of the battery temperature control branch (3), closing the shutoff valve c (311), opening the shutoff valve b (304), enabling the cooling liquid to flow from the four-way valve (202) to the battery heat exchanger (302) under the drive of the liquid pump a (301), enabling the cooling liquid to flow through the temperature and pressure sensor c (303) and the shutoff valve b (304), and then flowing to the main pipeline (2);
when the ambient temperature is lower than the battery working temperature range, firstly, opening the four-way valve (202) to flow to the battery temperature control branch (3), closing the shutoff valve c (311), closing the shutoff valve b (304), enabling the cooling liquid (103) to flow through the liquid pump a (301), the battery heat exchanger (302) and the temperature and pressure sensor c (303) respectively by the four-way valve (202) under the driving of the liquid pump a (301), then flow into the liquid storage tank b (305), detecting that the cooling liquid in the liquid storage tank b (310) is in a specified range by the liquid level meter b (307), closing the four-way valve (202) to flow to the battery temperature control branch (3), and opening the shutoff valve c (311); when the temperature and pressure sensor c (303) monitors that the temperature of the battery temperature control branch circuit (3) exceeds or is lower than a specified range, the rotating speed of the liquid pump a (301) is reduced or increased, or the heating power of the heater b (310) is reduced or increased until the battery temperature is within a specified interval range;
the cooling liquid (103) flows out from the four-way valve (202), enters the motor heat exchanger 402 through the liquid pump b (401) to exchange heat, and then flows to the main pipeline (2) through the temperature and pressure sensor e (403); a temperature and pressure sensor e (403) monitors the temperature and pressure of the motor temperature control branch (4), and then the temperature of the motor on the aircraft is regulated through a liquid pump b (401);
the cooling liquid (103) flows out from the four-way valve (202), enters the motor heat exchanger 502 through the liquid pump c (501) to exchange heat, and then flows to the main pipeline (2) through the temperature and pressure sensor f (503); the temperature and pressure sensor f (503) monitors the temperature and pressure of the temperature control branch (5) of the controller, and then the temperature of the controller on the aircraft is regulated through the liquid pump c (501);
the cooling liquid (103) flows to the radiator (203) after the main pipelines (2) are combined, and after heat is transferred to the air by the action of the radiating fan (204), the temperature is reduced, and then the cooling liquid flows back to the liquid storage tank a through the temperature and pressure sensor b (205).
5. The method according to claim 4, wherein the temperature and pressure sensor b (205) is used for monitoring the temperature and pressure of the main pipeline, and regulating the temperature of the cooling liquid (103) flowing back to the liquid storage tank a through the fan rotation speed, the liquid discharge valve a (101) is used for discharging the cooling liquid in the liquid storage tank a, the liquid level meter a (102) is used for monitoring the liquid position in the liquid storage tank a, and when the liquid level is lower than a specified range, the supplementing cooling liquid (103) is indicated.
6. The method of operating a temperature control system for an electric aircraft according to claim 4, wherein the surge tank a (104) is used for regulating the pressure of the stabilized temperature control system, and the temperature and pressure sensor a (106) is used for monitoring the temperature and pressure in the liquid storage tank a; when the pressure of any place of the temperature control system is abnormal, the temperature control system is closed.
7. The method according to claim 4, wherein the temperature and pressure sensor c (303) is used for monitoring the temperature and pressure of the battery temperature control branch (3), and when the temperature exceeds or falls below a prescribed range, increasing or decreasing the rotation speed of the liquid pump a (301) adjusts the flow rate of the coolant entering the battery heat exchanger, thereby controlling the heat exchange amount thereof.
8. The method according to claim 4, wherein the surge tank b (308) is used for adjusting the pressure of the battery temperature control branch (3), the temperature and pressure sensor d (309) is used for monitoring the temperature and pressure in the liquid storage tank b (305), and the liquid discharge valve b (306) is used for discharging the cooling liquid (103) in the liquid storage tank b (305).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311485799.3A CN117578003A (en) | 2023-11-09 | 2023-11-09 | Temperature control system and operation method of electric aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311485799.3A CN117578003A (en) | 2023-11-09 | 2023-11-09 | Temperature control system and operation method of electric aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN117578003A true CN117578003A (en) | 2024-02-20 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202311485799.3A Pending CN117578003A (en) | 2023-11-09 | 2023-11-09 | Temperature control system and operation method of electric aircraft |
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| Country | Link |
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| CN (1) | CN117578003A (en) |
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- 2023-11-09 CN CN202311485799.3A patent/CN117578003A/en active Pending
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