Electrical air conditioning temperature regulation system, control method and aircraft

Abstract

This application discloses an electric air conditioning temperature regulation system, control method, and aircraft, belonging to the technical field of air conditioning systems. The electric air conditioning temperature regulation system includes an air supply system and a circulation system. The air supply system provides compressed airflow; the air inlet of the circulation system is connected to the air outlet of the air supply system, and the circulation system includes a refrigeration module and a heating pipeline connected in parallel; wherein, the circulation system also includes a shut-off valve and a temperature control valve, the shut-off valve being used to connect or disconnect the airflow flowing through the refrigeration module, and the temperature control valve being located in the heating pipeline and used to control the flow rate of the airflow in the heating pipeline. By setting the shut-off valve and temperature control valve, in heating mode, the electric air conditioning temperature regulation system of this application, by closing the shut-off valve and opening the temperature control valve, allows the air supply system to directly supply heat to the cabin, reducing power consumption in low-temperature environments and thus reducing energy consumption.

Description

Technical Field

[0001] This application relates to the field of air conditioning system technology, and in particular to an electric air conditioning temperature regulation system, control method, and aircraft. Background Technology

[0002] With the global aviation industry placing increasing emphasis on energy conservation, emission reduction, and green aviation technologies, new energy aircraft have become a crucial direction for aviation technology development. New energy aircraft typically use battery power as their primary energy source, and their onboard systems are gradually evolving towards electrification and intelligence. Among these systems, the electric air conditioning system, as a core component ensuring cabin comfort, directly impacts flight safety and passenger experience. This system uses an electric compressor as its air source, and its operational power relies entirely on the onboard battery.

[0003] However, the electrochemical activity of batteries is extremely sensitive to ambient temperature, especially at low temperatures, where their discharge capacity decreases sharply, severely impacting power supply stability. Taking lithium iron phosphate batteries as an example, based on their activity at room temperature (25°C), their activity drops to only 65% ​​when the ambient temperature falls to 0°C; at extreme low temperatures of -40°C, the activity is even less than 20%, severely affecting their power supply capability. In hot weather, when the air conditioning system is in cooling mode, the electric compressor needs to provide higher air pressure to enhance cooling performance. In cold weather, when the air conditioning system is in heating mode, the electric compressor needs to provide an air temperature of no less than 120°C to ensure the thermal bypass performance of the temperature control valve. Insufficient air supply temperature not only affects heating efficiency but may also lead to excessively low speeds in the air circulation cooling system or even equipment damage. Electric air conditioning systems have high power requirements under different ambient temperatures, creating a significant contradiction with the temperature sensitivity of batteries.

[0004] In related technologies, battery heating technology is used to improve battery activity in low-temperature environments. However, pursuing higher heating temperatures under extreme low-temperature conditions will lead to higher costs and operating expenses. Furthermore, due to limitations such as the structural complexity of the battery thermal management system, equipment weight, and power consumption, practical applications typically only allow batteries to be heated to 0°C or above to ensure basic power supply performance. Even so, the activity provided by lithium batteries in low-temperature environments is only 50% to 60% of that at room temperature, which is insufficient to meet the power requirements of electric air conditioning systems. Summary of the Invention

[0005] This application provides an electric air conditioning temperature regulation system, control method, and aircraft, which can reduce the power consumption of the electric air conditioning temperature regulation system in low-temperature environments, thereby reducing power consumption.

[0006] To achieve the above objectives, according to a first aspect of this application, an electric air conditioning temperature control system is provided, comprising:

[0007] An air supply system, wherein the air supply system is used to provide compressed airflow;

[0008] A circulation system, wherein the air inlet of the circulation system is connected to the air outlet of the air supply system, and the circulation system includes a refrigeration module and a heating pipeline connected in parallel.

[0009] The circulation system further includes a shut-off valve and a temperature control valve. The shut-off valve is used to connect or disconnect the airflow through the refrigeration module, and the temperature control valve is installed in the heating pipeline to control the flow rate of the airflow in the heating pipeline.

[0010] Optionally, the air supply system includes a compressor, an electric motor, and a motor controller. The compressor is used to compress the intake air, the electric motor is used to drive the compressor, and the motor controller is used to control the speed of the electric motor.

[0011] Optionally, the gas supply system further includes a heating valve, the inlet end of which is connected to the outlet end of the compressor, and the outlet end of which is connected to the inlet end of the compressor. The heating valve is used to control the flow rate of the gas returning to the inlet end of the compressor.

[0012] Optionally, the electric air conditioning temperature control system further includes a one-way valve, the inlet end of which is connected to the outlet end of the compressor, and the outlet end of which is connected to the inlet end of the circulation system. The one-way valve is used to prevent backflow of air.

[0013] Optionally, the electric air conditioning temperature control system further includes a measurement system, which is located between the outlet end of the one-way valve and the inlet end of the circulation system.

[0014] Optionally, the measurement system includes a temperature sensor and a pressure sensor, wherein the temperature sensor is used to detect the temperature of the airflow and the pressure sensor is used to detect the pressure of the airflow.

[0015] Optionally, the measurement system further includes a flow venturi tube and a flow sensor, wherein the flow venturi tube is a contraction-expansion Laval tube, and the flow sensor is used to detect the pressure difference between the inlet end of the flow venturi tube and the contraction-expansion throat.

[0016] Optionally, the electric air conditioning temperature control system further includes an integrated controller, which is communicatively connected to the gas supply system, the circulation system and the measurement system, respectively. The integrated controller is configured to control the operation of the gas supply system and the circulation system based on the detection data of the measurement system.

[0017] Optionally, the number of the cyclic systems is multiple;

[0018] The gas supply system is multiple, and each system corresponds to a specific circulation system; or,

[0019] The number of gas supply systems is less than the number of circulation systems, and at least one of the gas supply systems is connected to two or more of the circulation systems.

[0020] According to a second aspect of this application, a control method for an electric air conditioning temperature regulation system is provided, for controlling the electric air conditioning temperature regulation system as described in any one of the above claims, the control method comprising:

[0021] Detect the ambient temperature;

[0022] When the heating conditions are met, the shut-off valve is closed and the temperature control valve is opened.

[0023] Optionally, the heating condition is: the ambient temperature is ≤0℃ and lasts for more than 10 seconds.

[0024] According to a third aspect of this application, an aircraft is also provided, including an electric air conditioning temperature control system as described in any of the foregoing.

[0025] In the electric air conditioning temperature regulation system, control method, and aircraft of this application embodiment, the electric air conditioning temperature regulation system, by setting a shut-off valve and a temperature control valve, closes the shut-off valve and opens the temperature control valve in heating mode, allowing the air supply system to directly supply heat to the cabin. The target temperature of the air supply system is significantly reduced, which reduces the power consumption of the electric air conditioning temperature regulation system in low-temperature environments. This makes the power demand of the electric air conditioning temperature regulation system match the cold-weather activity characteristics of the battery, thereby improving the environmental adaptability and operational reliability of the electric air conditioning temperature regulation system, and improving the stability of the electric air conditioning temperature regulation system in different temperature environments. At the same time, while ensuring the cabin heating effect, the energy consumption of the electric air conditioning temperature regulation system is reduced, thereby improving the battery's range and reducing the additional battery capacity and weight required due to low-temperature environments, thus reducing the overall weight of the aircraft and reducing the overall energy consumption of the aircraft.

[0026] Other features and advantages of this application will be described in detail in the following detailed description section. Attached Figure Description

[0027] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0028] To gain a more complete understanding of this application and its beneficial effects, the following description will be provided in conjunction with the accompanying drawings, wherein the same reference numerals in the following description denote the same parts.

[0029] Figure 1 This is a schematic diagram of the structure of the first electric air conditioning temperature regulation system provided in the exemplary embodiments of this disclosure;

[0030] Figure 2 This is a schematic diagram of the structure of the second electric air conditioning temperature control system provided in the exemplary embodiments of this disclosure;

[0031] Figure 3 This is a schematic diagram of the structure of a third type of electric air conditioning temperature control system provided in an exemplary embodiment of this disclosure;

[0032] Figure 4 This is a schematic diagram of the structure of the fourth electric air conditioning temperature regulation system provided in the exemplary embodiments of this disclosure;

[0033] Figure 5 This is a schematic diagram of the structure of the fifth electric air conditioning temperature regulation system provided in the exemplary embodiments of this disclosure.

[0034] Explanation of reference numerals in the attached figures:

[0035] 1. Gas supply system; 11. Compressor; 12. Electric motor; 13. Motor controller; 14. Heating valve; 2. Circulation system; 21. Refrigeration module; 22. Heating pipeline; 23. Shut-off valve; 24. Temperature control valve; 3. One-way valve; 4. Measurement system; 41. Temperature sensor; 42. Pressure sensor; 43. Flow venturi tube; 44. Flow sensor; 5. Integrated controller; 6. Gas supply pipeline; 7. Return pipeline. Detailed Implementation

[0036] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application. In addition, it should be understood that the specific embodiments described herein are only for illustration and explanation of this application and are not intended to limit this application. In this application, unless otherwise stated, directional terms such as "up," "down," "left," and "right" generally refer to up, down, left, and right in the actual use or working state of the device, specifically the drawing directions in the accompanying drawings.

[0037] In this application, unless otherwise expressly specified and limited, the terms "connected," "linked," "stacked," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two elements or the interaction between two elements. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0038] This application provides an electric air conditioning temperature regulation system, control method, and aircraft, which are described in detail below. It should be noted that the order of description of the following embodiments is not intended to limit the preferred order of the embodiments of this application. Furthermore, in the following embodiments, the descriptions of each embodiment have their own emphasis; parts not described in detail in a certain embodiment can be referred to in the relevant descriptions of other embodiments.

[0039] According to the first aspect of this application, referring to Figure 1 One embodiment of this application provides an electric air conditioning temperature regulation system, including an air supply system 1 and a circulation system 2. The air supply system 1 is connected to the circulation system 2 and provides compressed airflow to the circulation system 2.

[0040] Specifically, refer to Figure 1The air supply system 1 is the power source for the electric air conditioning temperature control system, and it provides compressed airflow. As an example, the air supply system 1 may include a compressor 11, an electric motor 12, and a motor controller 13. The electric motor 12 drives the compressor 11, and the motor controller 13 controls the speed of the electric motor 12. The compressor 11 is, for example, an air compressor. The inlet of the compressor 11 can be connected to the external environment. Air enters the compressor 11 through the inlet, and the compressor 11 compresses the intake air, increasing its pressure and temperature. The electric motor 12 is driven by the compressor 11 and drives its operation. Its output power determines the pressure and flow rate of the airflow output by the compressor 11. The motor controller 13 is electrically connected to the electric motor 12 and regulates its speed, thereby controlling the pressure and flow rate of the airflow output by the compressor 11.

[0041] Reference Figure 1 The air inlet of the circulation system 2 is connected to the air outlet of the air supply system 1, that is, the air inlet of the circulation system 2 is connected to the air outlet of the compressor 11. The air inlet of the circulation system 2 and the air outlet of the compressor 11 can be connected through the air delivery pipe 6. The circulation system 2 is used to deliver the treated airflow to the aircraft cabin to achieve temperature regulation. The circulation system 2 may include a refrigeration module 21 and a heating pipe 22 arranged in parallel. The refrigeration module 21 may include components such as a turbine (not shown), a heat exchanger (not shown), and a condenser (not shown). The air inlet of the refrigeration module 21 and the air outlet of the compressor 11 can be connected through the air delivery pipe 6. The air inlet of the heating pipe 22 is connected to the air delivery pipe 6, thereby connecting to the air outlet of the compressor 11. Part of the compressed airflow provided by the air supply system 1 can flow into the refrigeration module 21, which can cool the airflow, and part of it can flow into the heating pipe 22. The airflow cooled by the cooling module 21 can be mixed with the airflow in the heating pipe 22, thereby adjusting the temperature of the airflow output by the circulation system 2.

[0042] Among them, reference Figure 1 The circulation system 2 may also include a shut-off valve 23 and a temperature control valve 24. The shut-off valve 23, for example, is an electric ball valve. It can be located upstream of the refrigeration module 21 in the gas supply line 6, or at the gas inlet of the refrigeration module 21. The shut-off valve 23 is used to connect or disconnect the airflow through the refrigeration module 21, enabling or bypassing the refrigeration module 21. The temperature control valve 24, for example, is an electric regulating ball valve. Its opening degree can be continuously adjusted between fully closed (0%) and fully open (100%). The gas inlet of the heating line 22 can be located upstream of the shut-off valve 23. The temperature control valve 24 is located in the heating line 22 and is used to control the flow rate of the airflow in the heating line 22.

[0043] As an example, in hot weather, the electric air conditioning temperature control system can be in cooling mode. The shut-off valve 23 is opened, and the opening of the temperature control valve 24 is closed or reduced. Airflow mainly enters the cooling module 21, which cools the airflow and delivers the cooled airflow to the cabin, achieving a cooling effect. In some embodiments, the temperature of the airflow output from the circulation system 2 can be adjusted by regulating the opening of the temperature control valve 24, thereby improving the stability and comfort of the cabin temperature. In cold weather, the electric air conditioning temperature control system can be in heating mode. The shut-off valve 23 is closed to prevent airflow from entering the cooling module 21. The opening of the temperature control valve 24 can be increased, for example, by opening it fully open, allowing airflow to be delivered to the cabin through the heating pipe 22. This not only reduces heat loss through the cooling module 21, helping to reduce system energy consumption and thus improve battery life, but also significantly lowers the target temperature of the air supply system 1, thereby reducing the power consumption of the electric air conditioning temperature control system in low-temperature environments.

[0044] In this application, the electric air conditioning temperature control system, by setting a shut-off valve 23 and a temperature control valve 24, closes the shut-off valve 23 and opens the temperature control valve 24 in heating mode, allowing the air supply system 1 to directly supply heat to the cabin. This significantly reduces the target temperature of the air supply system 1, thereby reducing the power consumption of the electric air conditioning temperature control system in low-temperature environments. This matches the power requirements of the electric air conditioning temperature control system with the cold-weather activity characteristics of the battery, improving the environmental adaptability and operational reliability of the electric air conditioning temperature control system, enhancing its stability under different temperature conditions, and reducing operational risks caused by power demand mismatch. Simultaneously, while ensuring cabin heating effectiveness, reducing the energy consumption of the electric air conditioning temperature control system improves battery range, reduces battery charge / discharge cycles and energy consumption, and lowers operating costs. Furthermore, it reduces the additional battery capacity and weight required in low-temperature environments, reducing the overall weight of the aircraft, thus lowering overall aircraft energy consumption, battery purchase costs, and maintenance costs. As an example, in a scenario where a circulation system 2 is set on each of the left and right sides, the weight increase of the two sets of shut-off valves 23 and their associated pipelines is only 10kg, while the battery can save 150kg of weight, resulting in a total weight gain of 140kg, reducing the overall weight of the aircraft and improving its range.

[0045] In some embodiments, refer to Figure 1The air supply system 1 may further include a heating valve 14, the inlet of which is connected to the outlet of the compressor 11, and the outlet of which is connected to the inlet of the compressor 11. The heating valve 14 may be installed in a return pipe 7, with both ends of the return pipe 7 connected to the inlet and outlet of the compressor 11, respectively. The heating valve 14 may be, for example, an electrically adjustable butterfly valve, and its opening degree can be continuously adjusted between fully closed (0%) and fully open (100%). The heating valve 14 is used to control the flow rate of air returning to the inlet of the compressor 11. In other words, the heating valve 14 is used to control the flow rate of air returning from the outlet of the compressor 11 to the inlet of the compressor 11, and by adjusting the return ratio, precise control of the airflow temperature at the outlet of the compressor 11 is achieved. The larger the opening of the heating valve 14, the greater the flow rate of air returning to the intake end of the compressor 11, the stronger the internal circulation heating effect of the compressor 11, and the higher the temperature of the airflow provided by the compressor 11. In cold weather, when the electric air conditioning temperature control system is in heating mode, the cabin temperature is adjusted by regulating the opening of the heating valve 14, thereby improving the stability and comfort of the cabin temperature.

[0046] In some embodiments, refer to Figure 1 The electric air conditioning temperature control system may also include a one-way valve 3, such as a spring-loaded one-way valve. The one-way valve 3 can be installed on the air supply pipeline 6 between the air supply system 1 and the circulation system 2. The inlet end of the one-way valve 3 is connected to the outlet end of the compressor 11, and the outlet end of the one-way valve 3 is connected to the inlet end of the circulation system 2. The one-way valve 3 is used to prevent backflow of air. This prevents airflow from flowing back from the circulation system 2 to the air supply system 1, which can improve the stable operation of the air supply system 1 and avoid damage to the compressor 11 or a decrease in its working efficiency due to backflow of air.

[0047] In some embodiments, refer to Figure 1 The electric air conditioning temperature control system may also include a measurement system 4, which is located between the outlet of the one-way valve 3 and the inlet of the circulation system 2. The measurement system 4 is used to detect parameters such as the temperature, pressure, and flow rate of the airflow in real time.

[0048] Specifically, refer to Figure 1The measurement system 4 may include a temperature sensor 41 and a pressure sensor 42. The temperature sensor 41 can be installed at the outlet end of the one-way valve 3. The temperature sensor 41, for example, is a pulsed integrated temperature sensor (PITS) or a platinum resistance temperature sensor. The temperature sensor 41 is used to detect the temperature of the airflow. The detected temperature data is not only an important parameter for flow calculation but also a core feedback signal for temperature regulation. The pressure sensor 42, for example, is a pulsed integrated pressure sensor (PIPS) or a piezoelectric pressure sensor. The pressure sensor 42 is used to detect the pressure of the airflow. The detected pressure data not only provides pressure parameters for flow calculation but also serves as a core feedback signal for pressure regulation.

[0049] Reference Figure 1 The measurement system 4 may also include a flow venturi 43 and a flow sensor 44. The flow venturi 43 is a contraction-expansion Laval conduit, whose special structure can accelerate and depressurize the airflow, providing a stable flow field environment for flow measurement. The flow sensor 44 is, for example, a pulsed integration flow sensor (PIFS). The flow sensor 44 is used to detect the pressure difference between the inlet end of the flow venturi 43 and the contraction-expansion throat. After receiving this pressure difference signal, the integrated controller 5 combines the airflow temperature data detected by the temperature sensor 41 and the airflow pressure data detected by the pressure sensor 42 to accurately calculate the real-time airflow flow rate. In some embodiments, other types of sensors may also be used to obtain the airflow flow rate.

[0050] In some embodiments, refer to Figure 1 The electric air conditioning temperature control system may also include a comprehensive controller 5, which is the control core of the system. The comprehensive controller 5 can be communicatively connected to the gas supply system 1, the circulation system 2, and the measurement system 4, respectively. The comprehensive controller 5 is configured to control the operation of the gas supply system 1 and the circulation system 2 based on the detection data from the measurement system 4. In this embodiment, the comprehensive controller 5 can be communicatively connected to the shut-off valve 23, the temperature control valve 24, the heating valve 14, the temperature sensor 41, the pressure sensor 42, and the flow sensor 44, respectively.

[0051] As an example, the integrated controller 5 can receive signals such as temperature, pressure, and differential pressure from the measurement system 4, and calculate the real-time airflow rate through a built-in algorithm; it can also interface with the motor 12 controller of the air supply system 1, and send control commands to the motor 12 controller according to the flow rate requirement, pressure requirement, and temperature adjustment target to adjust the speed of the motor 12, thereby controlling the airflow rate; it can adjust the opening of the heating valve 14 of the air supply system 1, and accurately control the degree of airflow heating according to the difference between the target air supply temperature and the measured temperature to ensure that the air supply temperature meets the cabin heating requirements; it can control the opening and closing of the shut-off valve 23 to enable or bypass the cooling module 21; and it can control the opening of the temperature control valve 24, which on the one hand adjusts the airflow rate in the heating pipeline 22, and on the other hand drives it to the fully open position in the heating mode to provide a smooth heating path, while working with the heating valve 14 to achieve precise adjustment of the cabin temperature.

[0052] In some embodiments, refer to Figures 2 to 5 The number of circulation systems 2 can be multiple. The number of gas supply systems 1 can also be multiple, and each system is configured to correspond one-to-one with a circulation system 2. Alternatively, the number of gas supply systems 1 can be less than the number of circulation systems 2, and at least one gas supply system 1 can be connected to two or more circulation systems 2.

[0053] As an example, refer to Figure 2 When there are two air supply systems 1 and two circulation systems 2, the air supply systems 1 and circulation systems 2 are configured in a one-to-one correspondence, serving the left and right cockpits respectively. The number of measurement systems 4 and the number of integrated controllers 5 can also be two. One air supply system 1, one circulation system 2, one measurement system 4, and one integrated controller 5 serve the left cockpit. The other air supply system 1, another circulation system 2, another measurement system 4, and another integrated controller 5 serve the right cockpit. In some embodiments, refer to... Figure 3 When there are two air supply systems 1 and two circulation systems 2, there can be two measurement systems 4 and one integrated controller 5. One air supply system 1, one circulation system 2 and one measurement system 4 serve the left cockpit, and another air supply system 1, another circulation system 2 and another measurement system 4 serve the right cockpit. The integrated controller 5 communicates with both air supply systems 1, both circulation systems 2 and both measurement systems 4.

[0054] Reference Figure 4 When there is one air supply system 1 and two circulation systems 2, one air supply system 1 can provide airflow to two circulation systems 2, and the two circulation systems 2 are used to serve the left and right cabins respectively. The number of measurement systems 4 and integrated controllers 5 can also both be two. In some embodiments, refer to... Figure 5When there is one gas supply system 1 and two circulation systems 2, there can be two measurement systems 4 and one integrated controller 5.

[0055] According to a second aspect of this application, one embodiment of this application provides a control method for an electric air conditioning temperature regulation system, used to control an electric air conditioning temperature regulation system as described above, the control method comprising the following steps.

[0056] The system detects the ambient temperature. Specifically, it uses an ambient temperature sensor (not shown) to detect the ambient temperature in real time and transmits the detected data to the integrated controller 5. This ambient temperature sensor could be, for example, a sensor installed on an aircraft. The integrated controller 5 continuously monitors and analyzes the temperature data, providing a basis for switching operating modes.

[0057] When the heating conditions are met, the shut-off valve 23 is closed and the temperature control valve 24 is opened. The heating conditions are: the ambient temperature is ≤0℃ and lasts for more than 10 seconds. Setting a 10-second delay for judgment can avoid frequent switching of the operating mode of the electric air conditioning temperature regulation system due to instantaneous fluctuations in the ambient temperature, thereby improving the stability of the electric air conditioning temperature regulation system. It is understood that in other embodiments of this application, the duration of the heating conditions can be set to other values ​​according to actual needs, and is not limited here. Specifically, the integrated controller 5 determines whether the heating conditions are met based on the received ambient temperature data. When the heating conditions are met, the integrated controller 5 sends a control command to the circulation system 2 to close the shut-off valve 23 and bypass the refrigeration module 21; at the same time, it drives the temperature control valve 24 to the fully open position, and the airflow provided by the compressor 11 is delivered to the cabin through the heating passage.

[0058] Subsequently, the integrated controller 5 adjusts the opening of the heating valve 14 based on the difference between the target air supply temperature and the measured value from the temperature sensor 41 in the measurement system 4. A larger opening of the heating valve 14 results in a greater flow rate of air returning to the compressor 11's inlet, stronger internal circulation heating within the compressor 11, and a higher air supply temperature. The target air supply temperature can be dynamically adjusted based on the ambient temperature and the system's transient operating characteristics to ensure the cabin temperature remains stable within a comfortable range. For example, when the measured temperature is lower than the target temperature, the opening of the heating valve 14 is increased to increase the flow rate of air returning to the compressor 11's inlet, thus raising the air supply temperature; conversely, when the measured temperature is higher than the target temperature, the opening of the heating valve 14 is decreased to lower the air supply temperature.

[0059] Simultaneously, the integrated controller 5 receives pressure and differential pressure signals from the measurement system 4, calculates the real-time airflow, and sends instructions to the motor 12 controller according to the flow demand to adjust the motor 12 speed and control the air supply flow of the compressor 11, ensuring the stability of the heating effect. For example, when the measured flow is lower than the target flow, the motor controller 13 increases the speed of the motor 12 to increase the air supply flow; when the measured flow is higher than the target flow, it decreases the speed to reduce the air supply flow.

[0060] When the ambient temperature rises, if the integrated controller 5 detects that the ambient temperature is >0℃ for more than 10 seconds, it determines that the heating conditions are no longer met and sends a control command to exit the heating mode. At this time, the integrated controller 5 controls the shut-off valve 23 to open, connecting the cooling module 21, and simultaneously adjusts the temperature control valve 24 to the normal operating position. The electric air conditioning temperature regulation system switches to cooling mode or normal ventilation mode according to the actual temperature requirements.

[0061] As an example, when the cooling conditions are met, the integrated controller 5 sends an opening command to the shut-off valve 23, which opens and connects the cooling module 21; it also sends a command to the temperature control valve 24 to reduce the opening of the temperature control valve 24 or close the temperature control valve 24; the heating valve 14 remains closed.

[0062] The integrated controller 5 adjusts the speed of the motor 12 through the motor controller 13 according to the cabin set temperature and the outside ambient temperature, controls the air supply pressure and flow of the compressor 11, and the refrigeration module 21 starts the air circulation refrigeration to deliver the cooled air to the cabin to achieve the refrigeration effect.

[0063] According to a third aspect of this application, one embodiment of this application also provides an aircraft including an electric air conditioning temperature control system as described above. The electric air conditioning temperature control system can be integrated into the aircraft's environmental control system to provide stable and efficient temperature control services for the aircraft cabin, thereby improving the reliability and economy of aircraft operation in low-temperature environments.

[0064] The implementation schemes of this application will be described in detail below with reference to the embodiments. However, those skilled in the art will understand that the following embodiments are only used to illustrate this application and should not be regarded as limiting the scope of this application.

[0065] Test conditions: The test environment temperature was set to -40℃, -30℃, -20℃, -10℃, and 0℃ to simulate different low-temperature operating conditions. In the embodiments of this application, the shut-off valve 23 is in the closed state. The comparative example does not have a shut-off valve 23 as in this application. The other test conditions of the comparative example are the same as those of the embodiments.

[0066] Test results: See Table 1.

[0067] Table 1

[0068]

[0069] As shown in Table 1, the power consumption of the embodiment is reduced by 51.6% to 85.0% compared with the comparative embodiment, achieving a reduction of more than 50% in heating energy consumption, improving the battery's range, thus eliminating the need to increase battery capacity and weight, reducing battery weight by 50%, thereby reducing the overall weight of the aircraft and improving its range.

[0070] In the description of this application, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include one or more features. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0071] In the above embodiments, the descriptions of each embodiment have different focuses. For parts not described in detail in a certain embodiment, please refer to the relevant descriptions in other embodiments.

[0072] The embodiments, implementation methods, and related technical features of this application can be combined and substituted for each other without conflict.

[0073] The above are merely preferred embodiments of this application and are not intended to limit this application in any way. Any simple modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of this application without departing from the scope of the technical solution of this application shall still fall within the scope of the technical solution of this application.

Claims

1. An electric air conditioner temperature regulating system characterized by, include: An air supply system, wherein the air supply system is used to provide compressed airflow; A circulation system, wherein the air inlet of the circulation system is connected to the air outlet of the air supply system, and the circulation system includes a refrigeration module and a heating pipeline connected in parallel. The air supply system includes a compressor, an electric motor, a motor controller, and a heated valve. The compressor is used to compress the intake air, the electric motor is used to drive the compressor, the motor controller is used to control the speed of the electric motor, the air inlet of the heated valve is connected to the air outlet of the compressor, the air outlet of the heated valve is connected to the air inlet of the compressor, and the heated valve is used to control the flow rate of air returning to the air inlet of the compressor. The circulation system also includes a shut-off valve and a temperature control valve. The shut-off valve is used to connect or disconnect the airflow through the refrigeration module, and the temperature control valve is located in the heating pipeline and is used to control the flow rate of the airflow in the heating pipeline.

2. The electrical air conditioning temperature regulating system of claim 1, wherein, The electric air conditioning temperature control system also includes a one-way valve, the air inlet of which is connected to the air outlet of the compressor, and the air outlet of which is connected to the air inlet of the circulation system. The one-way valve is used to prevent airflow backflow.

3. The electrical air conditioner temperature regulation system of claim 2, wherein, The electric air conditioning temperature control system also includes a measurement system, which is located between the outlet end of the one-way valve and the inlet end of the circulation system.

4. The electrical air conditioning temperature regulating system of claim 3, wherein, The measurement system includes a temperature sensor and a pressure sensor. The temperature sensor is used to detect the temperature of the airflow, and the pressure sensor is used to detect the pressure of the airflow.

5. The electrical air conditioner temperature regulating system of claim 3, wherein, The measurement system also includes a flow venturi tube and a flow sensor. The flow venturi tube is a contraction-expansion Laval tube, and the flow sensor is used to detect the pressure difference between the inlet end of the flow venturi tube and the contraction-expansion throat.

6. The electrical air conditioner temperature regulating system of claim 3, wherein, The electric air conditioning temperature control system also includes an integrated controller, which is communicatively connected to the gas supply system, the circulation system and the measurement system. The integrated controller is configured to control the operation of the gas supply system and the circulation system based on the detection data of the measurement system.

7. The electrical air conditioner temperature regulation system of claim 1, wherein, The number of the cyclic systems is multiple; The gas supply system is multiple, and each system corresponds to a specific circulation system; or, The number of gas supply systems is less than the number of circulation systems, and at least one of the gas supply systems is connected to two or more of the circulation systems.

8. A control method of an electric air conditioner temperature regulating system, characterized by, The control method for controlling the electric air conditioning temperature regulation system as described in any one of claims 1 to 7 includes: Detect the ambient temperature; When the heating conditions are met, the shut-off valve is closed and the temperature control valve is opened.

9. The control method of an electric air conditioner temperature regulation system according to claim 8, characterized in that, The heating conditions are: the ambient temperature is ≤0℃ and lasts for more than 10 seconds.

10. An aircraft, characterized in that Includes the electric air conditioning temperature control system as described in any one of claims 1 to 7.

Images