Control method, thermal management system and aircraft

Abstract

The invention provides a control method, a thermal management system and an aircraft, relates to the technical field of thermal management systems, and solves the technical problem that the thermal management system cannot meet the cooling and temperature requirements of the aircraft. The heat management system comprises a secondary refrigerant system connected to the rear cabin heat exchanger. The method comprises the steps that the target liquid supply temperature of the secondary refrigerant system before entering the high-power electronic equipment is set; detecting the liquid return temperature of the secondary refrigerant system after heat exchange with the high-power electronic equipment; comparing the detected liquid return temperature with a set target liquid supply temperature; and based on the comparison result, the operation parameters of the secondary refrigerant system are adjusted. The target liquid supply temperature can be set according to the flight stage, the temperature of the electronic equipment and the temperature and humidity of the equipment, the current liquid supply temperature fed back by the temperature sensor is compared, dynamic PI adjustment of the frequency of the bypass valve, the flow proportion adjusting valve and the pump assembly is achieved, and therefore the target liquid supply temperature is achieved; the temperature of the high-power electronic equipment is in a normal range and reliable operation is ensured.

Description

Technical Field

[0001] The present invention relates to the technical field of thermal management systems, and in particular to a control method, a thermal management system and an aircraft. Background Art

[0002] In order to meet the growing mission requirements of aircraft, more and more advanced technologies are being applied to aircraft design, and the number and complexity of systems are increasing. While higher-power electronic devices improve aircraft performance, they also put increasing pressure on aircraft thermal management systems. The thermal management system is one of the important subsystems of modern aircraft. Its design purpose is to ensure that all types of onboard equipment on the aircraft operate within a safe and efficient temperature range. A large amount of heat will be released during the operation of the aircraft. In order to ensure its normal operation, the thermal management system is required to cool the terminal heat loads such as related electronic equipment. For small passenger aircraft, the commonly used thermal management system is a direct cooling method that uses ram air to remove heat.

[0003] The applicant has discovered that the prior art has at least the following technical problems: the existing thermal management system has only one cooling path and cannot meet high-power cooling and temperature requirements. Summary of the invention

[0004] The object of the present invention is to provide a control method, a thermal management system and an aircraft to solve the technical problem that the thermal management system in the prior art cannot meet the cooling and temperature requirements of the aircraft.

[0005] To achieve the above object, the present invention provides the following technical solutions:

[0006] In a first aspect, the present invention provides a control method, which is implemented by applying a thermal management system, wherein the thermal management system includes a coolant system; the coolant system is connected to a rear cabin heat exchanger and is connected to a high-power electronic device; the method includes the following steps:

[0007] Set the target supply temperature of the coolant system before entering the high-power electronic equipment;

[0008] Detect the return liquid temperature of the coolant system after heat exchange with high-power electronic equipment;

[0009] Compare the detected return liquid temperature with the set target liquid supply temperature;

[0010] Based on the comparison results, the operating parameters of the refrigerant system are adjusted.

[0011] The control method of the present invention is a control method for a thermal management system with low energy consumption and wide temperature range. The target liquid supply temperature can be set according to the flight stage, the temperature of the electronic equipment (flight control feedback), and the temperature and humidity at the equipment, and compared with the current liquid supply temperature fed back by the temperature sensor, to achieve dynamic PI adjustment of the bypass valve, flow proportional control valve, and pump component frequency, thereby achieving the target liquid supply temperature and ensuring that the temperature of high-power electronic equipment is within the normal range and operates reliably.

[0012] As a further improvement of the present invention, the setting of the target liquid supply temperature of the coolant system before entering the high-power electronic device includes:

[0013] Calculate the dew point temperature based on ambient temperature and humidity;

[0014] Get the temperature of high-power electronic equipment;

[0015] Determine the flight phase;

[0016] Based on the calculated dew point temperature, the temperature of the power electronics, and the flight phase, a target supply temperature of the coolant system before entering the power electronics is set.

[0017] As a further improvement of the present invention, adjusting the operating parameters of the brine system based on the comparison result includes:

[0018] When the return liquid temperature is ≤ the target supply liquid temperature, the flow rate of the brine participating in the heat exchange in the brine system is adjusted to increase the return liquid temperature;

[0019] When the return liquid temperature is greater than the target supply liquid temperature, the flow rate of the refrigerant participating in the heat exchange in the refrigerant system is adjusted to reduce the return liquid temperature.

[0020] As a further improvement of the present invention, the method of adjusting the flow rate of the brine participating in heat exchange in the brine system to increase the return liquid temperature includes:

[0021] Determine whether the bypass valve is fully open;

[0022] When the bypass valve is fully open, the flow ratio regulating valve is controlled to perform dynamic regulation;

[0023] When the bypass valve is not fully opened, the bypass valve is controlled to be fully opened, and the comparison between the return liquid temperature and the target supply liquid temperature is continued.

[0024] As a further improvement of the present invention, the method of adjusting the flow rate of the brine participating in heat exchange in the brine system to reduce the return liquid temperature includes:

[0025] Determine whether the flow ratio regulating valve is fully closed;

[0026] When the flow ratio regulating valve is fully closed, the frequency of the control pump assembly is dynamically adjusted;

[0027] When the flow ratio regulating valve is not fully closed, the flow ratio regulating valve is controlled to be fully closed, and the return liquid temperature is returned to continue to compare the target liquid supply temperature.

[0028] As a further improvement of the present invention, after the frequency of the control pump assembly is dynamically adjusted, the method further comprises:

[0029] Determine whether the pump component frequency is the maximum;

[0030] When the pump assembly frequency is not the maximum, return to continue to compare the return liquid temperature with the target supply liquid temperature;

[0031] When the pump assembly frequency is at a maximum, the bypass valve is controlled to be dynamically adjusted.

[0032] As a further improvement of the present invention, when the pump assembly frequency is at a maximum, controlling the bypass valve to perform dynamic adjustment comprises:

[0033] Obtain a new liquid return temperature again;

[0034] Compare the obtained new return liquid temperature with the target supply liquid temperature;

[0035] When the new return liquid temperature = target supply liquid temperature, the adjustment is ended;

[0036] When the new return liquid temperature is not equal to the target supply liquid temperature, the process returns to continue comparing the return liquid temperature with the target supply liquid temperature.

[0037] In a second aspect, the present invention provides a thermal management system for executing the control method, comprising a coolant system and a ram air system; wherein:

[0038] The coolant system is connected to the rear cabin heat exchanger and is connected to the high-power electronic equipment;

[0039] After the ram air system exchanges heat with the radiator, it is connected to a high-power electronic device.

[0040] As a further improvement of the present invention, the brine system includes a brine flow path, a brine branch, a brine bypass flow path, a bypass valve, a pump assembly, a flow ratio regulating valve, and a temperature sensor; wherein:

[0041] The coolant flow path is connected in series with the high-power electronic equipment, the rear cabin heat exchanger and the radiator in sequence;

[0042] One end of the coolant branch is connected to the coolant flow path between the radiator and the rear cabin heat exchanger through the bypass valve, and the other end is connected to the coolant flow path between the radiator and the high-power electronic equipment;

[0043] The pump assembly is arranged on the coolant flow path between the bypass valve and the rear cabin heat exchanger;

[0044] The brine bypass flow path is arranged on the brine flow path between the inlet and outlet of the rear cabin heat exchanger;

[0045] The flow ratio regulating valve is arranged on the coolant bypass flow path;

[0046] The temperature sensors are respectively arranged on the coolant flow path at both sides of the inlet and outlet of the high-power electronic device and on the inlet side of the pump component.

[0047] The thermal management system of the present invention can meet the cooling demand without phase change refrigeration equipment, greatly reducing energy consumption, and can meet the cooling demand under all temperature conditions; on the basis of meeting the cooling demand of high-power electronic equipment such as electric hydraulic pump controllers, electric fan controllers, and power transformer rectifiers, it can realize fully automatic dynamic adjustment according to the target liquid supply temperature. Equipped with ambient temperature and humidity detection equipment, the system can calculate the dew point temperature and automatically control the liquid supply temperature range, thereby avoiding the generation of condensed water from the equipment and greatly improving the system reliability. The system can automatically control the priority of the heat exchanger based on the feedback results of the detection element, thereby reducing the impact of the operation of the thermal management system on the performance of the environmental control system.

[0048] In a third aspect, the present invention provides an aircraft, comprising the thermal management system. BRIEF DESCRIPTION OF THE DRAWINGS

[0049] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0050] Figure 1 It is a logic control diagram of the control method of the present invention;

[0051] Figure 2 is a control flow chart of an embodiment of the control method of the present invention;

[0052] Figure 3 It is a system composition diagram of the thermal management system of the present invention.

[0053] In the figure, 1, refrigerant flow path; 2, refrigerant branch; 3, refrigerant bypass flow path; 4, pump assembly; 5, bypass valve; 6, flow ratio control valve; 7, high-power electronic equipment; 8, rear cabin heat exchanger; 9, radiator; 10, temperature sensor; 11, one-way valve. DETAILED DESCRIPTION

[0054] To make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be described in detail below. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other implementation methods obtained by ordinary technicians in this field without creative work belong to the scope of protection of the present invention.

[0055] like Figure 1 As shown, the present invention provides a control method for a thermal management system, which is implemented by applying a thermal management system on an aircraft, wherein the thermal management system includes a coolant system; the coolant system is connected to a rear cabin heat exchanger and is connected to a high-power electronic device; specifically, the coolant system uses the rear cabin heat exchanger to perform heat exchange, thereby using the coolant to control the temperature of the high-power electronic device 7;

[0056] In this embodiment, the control method includes the following steps:

[0057] Step S1, setting a target liquid supply temperature of the coolant system before entering the high-power electronic device 7;

[0058] Step S2, detecting the return liquid temperature of the coolant system after heat exchange with the high-power electronic device 7;

[0059] Step S3, comparing the detected return liquid temperature with the set target liquid supply temperature;

[0060] Step S4: Based on the comparison result, adjust the operating parameters of the coolant system.

[0061] The control method of the present invention is a control method for a thermal management system with low energy consumption and wide temperature range. The target liquid supply temperature can be set according to the flight stage, the temperature of the electronic equipment (flight control feedback), and the temperature and humidity at the equipment, and compared with the current liquid supply temperature fed back by the temperature sensor, to achieve dynamic PI adjustment of the bypass valve, flow proportional control valve, and pump component frequency, thereby achieving the target liquid supply temperature and ensuring that the temperature of high-power electronic equipment is within the normal range and operates reliably.

[0062] like Figure 2 As shown, in this embodiment, the control method includes the following steps:

[0063] Calculate the dew point temperature based on the ambient temperature and humidity of the equipment;

[0064] Get the temperature of high-power electronic equipment;

[0065] Determine the flight phase;

[0066] Based on the calculated dew point temperature, the temperature of the high-power electronic device 7 and the flight stage, the target liquid supply temperature of the coolant system before entering the high-power electronic device 7 is set. After the target liquid supply temperature is set, the return liquid temperature is detected and the return liquid temperature is obtained through the temperature sensor. That is, the controller first calculates the dew point temperature according to the ambient temperature and humidity of the equipment, and sets the target liquid supply temperature in combination with the flight stage and the temperature of the electronic device (flight control feedback), and then judges the feedback result of the return liquid temperature sensor T1;

[0067] Then compare the return liquid temperature with the target set temperature;

[0068] Based on the comparison results, adjust the operating parameters of the refrigerant system, including:

[0069] Step S41, when the return liquid temperature is less than or equal to the target supply liquid temperature, adjusting the flow rate of the brine involved in heat exchange in the brine system to increase the return liquid temperature;

[0070] Specifically, adjusting the flow rate of the refrigerant involved in heat exchange in the refrigerant system to increase the return liquid temperature includes:

[0071] Determine whether the bypass valve 5 is fully open; it should be noted that the bypass valve 5 is fully open means that the flow rate of the brine entering the radiator 9 after the bypass valve 5 is 0, which indicates that the bypass valve 5 is in the fully open state;

[0072] When the bypass valve 5 is fully opened, it indicates that all the refrigerant has not passed through the radiator 9 for heat dissipation, and it is impossible to adjust the flow rate of the refrigerant flow path 1 corresponding to the radiator to achieve temperature adjustment. Therefore, the temperature can only be adjusted by the flow ratio regulating valve 6 before entering the bypass valve 5. Specifically, the flow ratio regulating valve 6 can be controlled to perform dynamic adjustment to increase the return liquid temperature until the standard value requirement is met; it should be noted that the dynamic adjustment refers to the flow ratio regulating valve 6 being continuously adjusted according to the temperature requirement to achieve the opening position of the required temperature;

[0073] When the bypass valve 5 is not fully opened, that is, there is still coolant entering the radiator 9 for heat dissipation and cooling, in order to increase the return liquid temperature, the actuator can be adjusted to control the bypass valve 5 to be fully opened, and then the return liquid temperature and the target supply liquid temperature can be compared. Then, corresponding control adjustments are made according to the comparison results.

[0074] Step S42, when the return liquid temperature is greater than the target supply liquid temperature, it indicates that the temperature control effect on the high-power electronic device 7 is insufficient and the coolant temperature needs to be further reduced; the coolant flow rate participating in heat exchange in the coolant system needs to be adjusted to reduce the return liquid temperature.

[0075] Specifically, adjusting the flow rate of the refrigerant involved in heat exchange in the refrigerant system to reduce the return liquid temperature includes:

[0076] Determine whether the flow ratio regulating valve 6 is fully closed (i.e., the brine flows entirely to the rear cabin radiator 8); when the flow ratio regulating valve 6 is fully closed, the brine flow in the brine bypass flow path 3 is 0, and the brine passes entirely through the rear cabin heat exchanger 8 for heat exchange;

[0077] (1) When the flow ratio regulating valve 6 is fully closed, it indicates that the brine has all passed through the heat exchanger 8 of the rear cabin. In order to adjust the temperature again, it is necessary to control from other aspects, for example, to control the frequency of the pump component 4 to perform dynamic PI adjustment of the component frequency (adjust the brine flow so that the return liquid temperature and the supply liquid temperature meet the requirements);

[0078] As an optional embodiment of the present invention, after the frequency of the control pump assembly 4 is dynamically adjusted, the following further comprises:

[0079] Determine whether the frequency of pump assembly 4 is the maximum;

[0080] When the frequency of the pump assembly 4 is not the maximum, the comparison between the return liquid temperature and the target supply liquid temperature is continued;

[0081] When the frequency of the pump assembly 4 is at the maximum, the bypass valve 5 is controlled to be dynamically adjusted to adjust the flow rate of the radiator flow path and its bypass flow path. The greater the flow rate of the radiator flow path, the lower the coolant supply temperature at T3 and T4. Specifically, it includes:

[0082] Obtain a new return liquid temperature (actual supply liquid temperature) again;

[0083] Compare the obtained new return liquid temperature with the target supply liquid temperature;

[0084] When the new return liquid temperature = the target supply liquid temperature, the adjustment is ended and the control under this setting ends;

[0085] When the new return liquid temperature is not equal to the target supply liquid temperature, the return liquid temperature and the target supply liquid temperature are compared, and this cycle is repeated three times. If the actual supply liquid temperature still does not meet the requirements, the system controller will feedback the abnormal status to the flight control system.

[0086] (2) When the flow ratio regulating valve 6 is not fully closed, first, the flow ratio regulating valve 6 is controlled to be fully closed (in order to reduce the return liquid temperature) so that all the refrigerant can be regulated by heat exchange in the rear cabin heat exchanger 8, and then return to continue comparing the return liquid temperature with the target supply liquid temperature.

[0087] In order to ensure that the whole machine meets the performance requirements, it is necessary to ensure that multiple high-power electronic equipment such as the electric hydraulic pump controller, power transformer rectifier, electric fan controller, etc. are in a reasonable temperature range, and the various components of the system should be able to work together to achieve full automatic control; due to the high temperature at the equipment, in order to ensure reliable operation, during the cooling process, condensation water should not be generated at the equipment to affect normal operation; In order to solve the above problems, such as Figure 3 As shown, the present invention provides a thermal management system for executing the above control method, including a coolant system and a ram air system; wherein:

[0088] The coolant system is connected to the rear cabin heat exchanger 8 and is connected to the high-power electronic equipment 7;

[0089] After the ram air system exchanges heat with the radiator 9 , it is connected to the high-power electronic device 7 .

[0090] It should be noted here that the refrigerant system of the present invention utilizes the aircraft rear cabin heat exchanger 8 to supply the temperature-regulated refrigerant, and the refrigerant contacts the high-power electronic equipment 7 to achieve temperature control of the high-power electronic equipment 7; the ram air system is blown to the high-power electronic equipment 7 after heat exchange through the radiator 9 to achieve a two-way cooling effect; of course, the refrigerant system and the ram air system can be used separately, or they can be used simultaneously when any temperature control requirement cannot be met, so as to achieve the maximum temperature control effect.

[0091] The thermal management system of the present invention shares the ram air channel with the aircraft environmental control system. During the operation of the thermal management system, it is necessary not to affect the environmental control system's control of the cabin environment. In addition, the ram air temperature range is relatively wide, and the system needs to meet the equipment cooling requirements under all temperature conditions.

[0092] As an optional embodiment of the present invention, Figure 3 As shown, the refrigerant system includes a refrigerant flow path 1, a refrigerant branch 2, a refrigerant bypass flow path 3, a bypass valve 5, a pump assembly 4, a flow ratio regulating valve 6, and a temperature sensor 10; wherein:

[0093] The coolant flow path 1 is connected in series with a high-power electronic device 7, a rear cabin heat exchanger 8 and a radiator 9 in sequence;

[0094] One end of the coolant branch 2 is connected to the coolant flow path 1 between the radiator 9 and the rear cabin heat exchanger 8 through the bypass valve 5, and the other end is connected to the coolant flow path 1 between the radiator 9 and the high-power electronic device 7;

[0095] The pump assembly 4 is arranged on the coolant flow path 1 between the bypass valve 5 and the rear cabin heat exchanger 8;

[0096] The coolant bypass flow path 3 is arranged on the coolant flow path 1 between the inlet and outlet of the rear cabin heat exchanger 8;

[0097] The flow ratio regulating valve 6 is arranged on the secondary coolant bypass flow path 3;

[0098] The temperature sensors 10 are respectively arranged on the coolant flow path 1 at both sides of the inlet and outlet of the high-power electronic device 7 and the inlet side of the pump assembly 4 .

[0099] Furthermore, a temperature sensor 10 is also provided on the outlet side of the radiator 9 .

[0100] The temperature sensor 10 located at the inlet side of the high-power electronic device 7 is T4; the temperature sensor 10 located at the inlet side of the pump assembly 4 is T2; the temperature sensor 10 located at the outlet side of the high-power electronic device 7 is T2, and the temperature sensor 10 located at the outlet side of the radiator 9 is T3.

[0101] The thermal management system of the present invention can meet the equipment cooling requirements under a wide temperature range by relying only on the refrigerant. In addition, the rear cabin heat exchanger 8 is preferentially used to use the circulating air for cooling. If the heat dissipation of the rear cabin heat exchanger cannot meet the requirements, the radiator 9 is used to use the ram air for further heat dissipation, and the excess cold of the circulating air can be recycled to reduce the system power consumption.

[0102] The thermal management system of the present invention can meet the cooling demand without phase change refrigeration equipment, greatly reducing energy consumption, and can meet the cooling demand under all temperature conditions; on the basis of meeting the cooling demand of high-power electronic equipment such as electric hydraulic pump controllers, electric fan controllers, and power transformer rectifiers, it can realize fully automatic dynamic adjustment according to the target liquid supply temperature. Equipped with ambient temperature and humidity detection equipment, the system can calculate the dew point temperature and automatically control the liquid supply temperature range, thereby avoiding the generation of condensed water from the equipment and greatly improving the system reliability. The system can automatically control the priority of the heat exchanger based on the feedback results of the detection element, thereby reducing the impact of the operation of the thermal management system on the performance of the environmental control system.

[0103] The present invention provides an aircraft, comprising the above-mentioned thermal management system.

[0104] The thermal management system is a low-energy, wide-temperature thermal management system, mainly including a pump assembly 4, a bypass valve 5, a one-way valve 11, a radiator 9, a rear cabin heat exchanger 8, a flow ratio regulating valve 6, a temperature sensor 10, a coolant flow path 1, a coolant branch 2, a coolant bypass flow path 3, a coolant, installation accessories, etc. Among them, the pump assembly 4 provides liquid supply pressure to drive the coolant flow, and has functions such as pressurization, backflow prevention, safety pressure relief, coolant filtration, and pressure stabilization to ensure the normal circulation of the coolant; the bypass valve 5 has three working modes: fully open, fully closed, and adjustable, which can control the flow of the coolant in the radiator 9 and the bypass, so as to ensure that the coolant supply temperature is within a certain range; the one-way valve 11 is used to prevent the bypass liquid from flowing back into the radiator 9. When liquid leaks from the radiator 9, the liquid can be prevented from entering the radiator 9; the radiator 9 is used for heat exchange between the refrigerant and the ram air, releasing the heat of the refrigerant; the rear cabin heat exchanger 8 is used for heat exchange between the refrigerant and the circulating air, releasing the heat of the refrigerant, realizing the utilization of the excess cooling capacity of the circulating air and reducing the power consumption of the whole machine; the flow ratio regulating valve 6 is used to accurately adjust the refrigerant flow; the temperature sensor 10 is used to regularly detect the refrigerant temperature.

[0105] The thermal management system can set the target liquid supply temperature according to the flight stage, the temperature of the electronic equipment (flight control feedback), and the temperature and humidity at the equipment, and compare the current return liquid temperature fed back by the temperature sensor with the standard return liquid temperature under the operating conditions, thereby realizing dynamic PI adjustment of the bypass valve, flow proportional control valve, and pump component frequency, thereby achieving the target liquid supply temperature and ensuring that the temperature of high-power electronic equipment is within the normal range and operates reliably.

[0106] The system does not require phase change refrigeration equipment and can meet the equipment cooling requirements under a wide temperature range by relying only on the refrigerant. In addition, the rear cabin heat exchanger is used to cool the equipment using circulating air first. If the heat dissipation of the rear cabin heat exchanger cannot meet the demand, the radiator is used to further dissipate heat using ram air, which can recycle the excess cooling capacity of the circulating air to reduce system power consumption.

[0107] like Figure 2 As shown, the high-temperature coolant liquid after heat exchange with the high-power electronic device 7 is detected by T1 in the temperature sensor 10, and then enters the rear cabin heat exchanger 8 and its coolant bypass flow path 3 (flow ratio regulating valve 6 flow path) for pre-cooling to become a normal temperature coolant, and then enters the pump component 4 for pressure increase after being detected by T2 in the temperature sensor 10. The low-temperature coolant at the outlet of the pump component 4 flows into the coolant branch 2 and the radiator 9 for further cooling under the regulation of the bypass valve 5, ensuring that the low-temperature coolant liquid at T4 meets the temperature requirement, and then cools the high-power electronic device 7. It should be noted that the whole machine thermal management system gives priority to using the rear cabin radiator 8 for cooling. If the heat dissipation of the rear cabin radiator 8 cannot meet the demand, the radiator after the bypass valve is used for further heat dissipation.

[0108] In general, when this technology is applied, detailed tests should be conducted on the automatic control effects under different refrigeration conditions and system operating states to ensure that the system can operate efficiently and stably under different conditions. For example, the standard value should be set according to the experimental test results under each condition to ensure a better cooling effect.

[0109] The system and control method can realize fully automatic control of a thermal management system with low energy consumption and wide temperature range, meet the cooling and reliability requirements of high-power electronic equipment, and reduce the impact of the system operation on cabin environment control.

[0110] First of all, it should be explained here that “inward” refers to the direction toward the center of the accommodating space, and “outward” refers to the direction away from the center of the accommodating space.

[0111] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate directions or positional relationships based on the attached Figure 1 The orientation or positional relationship shown is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0112] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0113] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0114] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, a first feature being "above", "above" or "above" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below", "below" or "below" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0115] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0116] The above is only a specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art can easily think of changes or substitutions within the technical scope disclosed by the present invention, which should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims

1. A control method, characterized in that: The method is implemented by applying a thermal management system, wherein the thermal management system includes a coolant system; the coolant system is connected to a rear cabin heat exchanger and is connected to a high-power electronic device; the method includes the following steps: Set the target supply temperature of the coolant system before entering the high-power electronic equipment; Detect the return liquid temperature of the coolant system after heat exchange with high-power electronic equipment; Compare the detected return liquid temperature with the set target liquid supply temperature; Based on the comparison results, the operating parameters of the refrigerant system are adjusted.

2. The method according to claim 1, characterized in that The setting of the target liquid supply temperature of the coolant system before entering the high-power electronic equipment includes: Calculate the dew point temperature based on ambient temperature and humidity; Get the temperature of high-power electronic equipment; Determine the flight phase; Based on the calculated dew point temperature, the temperature of the power electronics, and the flight phase, a target supply temperature of the coolant system before entering the power electronics is set.

3. The method according to claim 1, characterized in that The adjusting the operating parameters of the secondary coolant system based on the comparison result includes: When the return liquid temperature is ≤ the target supply liquid temperature, the flow rate of the brine participating in the heat exchange in the brine system is adjusted to increase the return liquid temperature; When the return liquid temperature is greater than the target supply liquid temperature, the flow rate of the refrigerant participating in the heat exchange in the refrigerant system is adjusted to reduce the return liquid temperature.

4. The method according to claim 3, characterized in that The method of adjusting the flow rate of the brine involved in heat exchange in the brine system to increase the return liquid temperature includes: Determine whether the bypass valve is fully open; When the bypass valve is fully open, the flow ratio regulating valve is controlled to perform dynamic regulation; When the bypass valve is not fully opened, the bypass valve is controlled to be fully opened, and the comparison between the return liquid temperature and the target supply liquid temperature is continued.

5. The method according to claim 3, characterized in that: The method of adjusting the flow rate of the refrigerant participating in heat exchange in the refrigerant system to reduce the return liquid temperature includes: Determine whether the flow ratio regulating valve is fully closed; When the flow ratio regulating valve is fully closed, the frequency of the control pump assembly is dynamically adjusted; When the flow ratio regulating valve is not fully closed, the flow ratio regulating valve is controlled to be fully closed, and the return liquid temperature is returned to continue to compare the target liquid supply temperature.

6. The method according to claim 5, characterized in that After the frequency of the control pump assembly is dynamically adjusted, the method further includes: Determine whether the pump component frequency is the maximum; When the pump assembly frequency is not the maximum, return to continue to compare the return liquid temperature with the target supply liquid temperature; When the pump assembly frequency is at a maximum, the bypass valve is controlled to be dynamically adjusted.

7. The method according to claim 6, characterized in that When the pump assembly frequency is at the maximum, the bypass valve is controlled to perform dynamic adjustment, including: Obtain a new liquid return temperature again; Compare the obtained new return liquid temperature with the target supply liquid temperature; When the new return liquid temperature = target supply liquid temperature, the adjustment is ended; When the new return liquid temperature is not equal to the target supply liquid temperature, the process returns to continue comparing the return liquid temperature with the target supply liquid temperature.

8. A thermal management system, characterized in that: Used to execute the control method as claimed in any one of claims 1 to 7, comprising a coolant system and a ram air system; wherein: The coolant system is connected to the rear cabin heat exchanger and is connected to the high-power electronic equipment; After the ram air system exchanges heat with the radiator, it is connected to a high-power electronic device.

9. The thermal management system according to claim 8, characterized in that: The brine system includes a brine flow path, a brine branch, a brine bypass flow path, a bypass valve, a pump assembly, a flow ratio regulating valve, and a temperature sensor; wherein: The coolant flow path is connected in series with the high-power electronic equipment, the rear cabin heat exchanger and the radiator in sequence; One end of the coolant branch is connected to the coolant flow path between the radiator and the rear cabin heat exchanger through the bypass valve, and the other end is connected to the coolant flow path between the radiator and the high-power electronic equipment; The pump assembly is arranged on the coolant flow path between the bypass valve and the rear cabin heat exchanger; The brine bypass flow path is arranged on the brine flow path between the inlet and outlet of the rear cabin heat exchanger; The flow ratio regulating valve is arranged on the coolant bypass flow path; The temperature sensors are respectively arranged on the coolant flow path at both sides of the inlet and outlet of the high-power electronic device and on the inlet side of the pump component.

10. An aircraft, characterized in that: Comprising a thermal management system as claimed in any one of claims 8-9.

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