Aircraft power system heat dissipation system, method, equipment and medium

Abstract

The invention provides an aircraft power system heat dissipation system, method, device and medium, and relates to the field of heat dissipation, and the method comprises the steps that a heat dissipation working medium is pressurized through a pump set, the heat dissipation working medium flows into a heat source to absorb heat, a heating working medium is obtained, and a cold source is adjusted; in the taxiing stage of the aircraft, the heating working medium passes through a first-stage cooling area of the cold source and is subjected to low-wind-speed convection heat dissipation, and a preliminary cooling working medium is obtained; in the take-off or maneuvering stage of the airplane, the heating working medium passes through a second-stage cooling area of the cold source and is subjected to high-wind-speed convection heat dissipation, and a deep cooling working medium is obtained; and the primary cooling working medium or the deep cooling working medium serves as a new heat dissipation working medium and enters the pump set again after passing through the liquid storage device, and circulating heat dissipation is achieved. By accurately regulating and controlling the liquid flow and temperature and meeting the heat dissipation requirement of the power system, the heat dissipation requirement of the power system under different flight working conditions is met, stable operation of the power system under all working conditions is achieved, and the service life of the power system is prolonged.

Description

Technical Field

[0001] This invention relates to the field of heat dissipation technology, specifically to a system, method, equipment, and medium for heat dissipation in an aircraft power system. Background Technology

[0002] The propulsion system is a core component of an aircraft, providing necessary power support for all stages of flight, including takeoff, cruise, and landing.

[0003] Aircraft need to accelerate from a standstill to sufficient speed for takeoff in a short period. This requires the propulsion system to output extremely high power, with motors running at high speed and controllers making frequent adjustments to precisely control the power output. This high-power operation for a short time generates a large amount of heat in the motors and controllers; if heat cannot be dissipated effectively and promptly, the equipment temperature will rise rapidly.

[0004] During high-speed maneuvers, the power system operates under continuous high load, generating a significant amount of heat. Moreover, due to the extended duration of cruising maneuvers, the continuous accumulation of heat places even greater demands on the cooling system.

[0005] During taxiing, the propulsion system needs to make precise power adjustments based on the aircraft's descent speed and attitude to ensure a smooth landing. This process generates relatively less heat compared to takeoff and high-speed cruise phases.

[0006] The heat generated by the propulsion system varies greatly at different stages of flight, and the rate of heat generation changes rapidly with changes in flight conditions. Most existing heat dissipation technologies are unable to dynamically adjust to these real-time changing heat dissipation requirements, resulting in insufficient heat dissipation in some stages and excessive heat dissipation in others. Summary of the Invention

[0007] This invention addresses the problems existing in the prior art by providing a system, method, equipment, and medium for heat dissipation of aircraft power systems, thereby meeting the heat dissipation requirements of power systems under different flight conditions.

[0008] To achieve the above objectives, the technical solution adopted by the present invention is as follows:

[0009] A system for cooling an aircraft power system, comprising: Pump units are used to pressurize the heat dissipation medium; The measuring device includes a flow sensor and a pressure sensor. The flow sensor is located at the input end of the pump set, and the pressure sensor is located at the output end of the pump set. It is used to measure the flow rate and pressure of the heat dissipation medium after pressurization. The motor and motor controller flow channel are connected to the output end of the pump set and to the input end of the heat source to provide a flow path for the heat dissipation working fluid. A heat source is used to dissipate heat; the heat dissipation medium absorbs heat at the heat source and transforms into a heating medium. The cold source includes a staged cooling module, which is set in the working fluid flow path between the cold source and the heat source, and is used to stage-cool the heated working fluid. The reservoir, located at the inlet of the pump unit, is used to provide inlet pressure and stabilize the pump unit.

[0010] In some embodiments, the graded cooling module includes a first-stage cooling region and a second-stage cooling region; Both the first-stage cooling zone and the second-stage cooling zone are equipped with heat exchangers, adjustable air duct cross-sectional areas, and variable frequency fans.

[0011] In some embodiments, the heat exchanger includes a core, which is integrally brazed from baffles, fins and seals; The fins are arranged in a forward or oblique direction, and adjacent rows of fins are staggered and interleaved in the horizontal or vertical direction.

[0012] This invention proposes a method for heat dissipation in an aircraft power system, and applies it to a system for heat dissipation in an aircraft power system. The heat dissipation medium is pressurized by a pump unit, and then flows to the heat source to absorb heat, thus obtaining a heated medium, and the cold source is adjusted. During the aircraft taxiing phase, the heating working fluid passes through the first-stage cooling zone of the cold source and dissipates heat through low-speed convection to obtain a preliminary cooling working fluid. During the takeoff or maneuver phase of the aircraft, the heating working fluid passes through the second-stage cooling zone of the cold source and dissipates heat through high-speed convection to obtain a deeply cooling working fluid. The initial cooling medium or the deep cooling medium is used as a new heat dissipation medium and then enters the pump group again after passing through the liquid receiver to circulate and dissipate heat.

[0013] In some embodiments, the process of obtaining a preliminary cooling working fluid by passing through the first-stage cooling zone of the cold source and dissipating heat through low-speed convection during the aircraft taxiing phase includes: During the aircraft taxiing phase, the heated working fluid passes through the first-stage cooling zone of the cold source; The temperature of the heating medium, the preset initial cooling target temperature, and the low wind speed range are obtained. In the first-stage cooling zone, the cross-sectional area of ​​the adjustable air duct and the power of the variable frequency fan are set according to the low wind speed range; When the temperature of the heating medium reaches the initial cooling target temperature, the cross-sectional area of ​​the adjustable air duct and the power of the variable frequency fan are locked to maintain the low wind speed convection heat dissipation state until the initial cooling medium is obtained.

[0014] In some embodiments, the process of obtaining a deeply cooled working fluid by high-speed convection cooling in the second-stage cooling zone of the cold source during aircraft takeoff or maneuvering includes: During aircraft takeoff or maneuvering, the heated working fluid passes through the second-stage cooling zone of the cold source; Obtain the preset target temperature for deep cooling and the high wind speed range; In the second-stage cooling zone, the cross-sectional area of ​​the adjustable air duct and the power of the variable frequency fan are set according to the high wind speed range; When the temperature of the heating medium reaches the target temperature for deep cooling, the cross-sectional area of ​​the adjustable air duct and the power of the variable frequency fan are locked to maintain the high-speed convection heat dissipation state until the deep cooling medium is obtained.

[0015] In some embodiments, the process of re-entering the pump unit after passing through the reservoir with the initial cooling medium or the deep cooling medium as a new heat dissipation medium includes: The system pressure is obtained through a pressure sensor; When the system pressure is higher than the pressure of the pre-charged gas in the reservoir, the heat dissipation medium enters the gas bladder of the reservoir until the gas pressure rises to the same level as the system pressure. Then the heat dissipation medium stops entering and the remaining heat dissipation medium enters the pump unit. When the system pressure is lower than the pressure of the pre-charged gas in the reservoir, the medium in the reservoir's bladder replenishes the system until the system pressure is the same as the gas pressure. At this point, the replenishment of the medium in the reservoir's bladder stops, and the medium and heat dissipation medium in the bladder are combined and enter the pump unit.

[0016] In some embodiments, the process of adjusting the cold source is to adjust the fin spacing parameter of the heat exchanger in the cold source; Maximizing the heat exchange efficiency of the heat exchanger is the first objective function. In the formula, For heat exchange efficiency, It is the first constant. This refers to the fin spacing; Minimizing the flow resistance of the heat exchanger is the second objective function. In the formula, For dynamic resistance, It is the second constant; Different weight coefficients are assigned to the first objective function and the second objective function, and the optimal parameter combination for fin spacing is obtained by solving the problem using a genetic algorithm.

[0017] This invention proposes a computer device, comprising: At least one processor; and a memory storing a computer program executable on the processor, wherein the processor executes the steps of the method for cooling an aircraft power system when executing the program.

[0018] The present invention provides a computer-readable storage medium storing a computer program, which, when executed by a processor, performs the steps of the method for cooling an aircraft power system.

[0019] Compared with the prior art, the present invention has the following beneficial effects: This invention proposes a system, method, equipment, and medium for heat dissipation in an aircraft power system. The method includes: pressurizing a heat dissipation medium using a pump set; the heat dissipation medium flows to a heat source to absorb heat, obtaining a heated medium; and adjusting a cold source. During the aircraft taxiing phase, the heated medium passes through a first-stage cooling zone of the cold source and dissipates heat through low-speed convection, obtaining a preliminary cooling medium. During the aircraft takeoff or maneuvering phase, the heated medium passes through a second-stage cooling zone of the cold source and dissipates heat through high-speed convection, obtaining a deep cooling medium. The preliminary cooling medium or the deep cooling medium is then used as a new heat dissipation medium, passing through a reservoir and re-entering the pump set for cyclic heat dissipation.

[0020] This invention precisely controls the liquid flow rate and temperature to meet the heat dissipation requirements of the power system under different flight conditions, achieving stable operation of the power system under all operating conditions. It effectively solves the heat dissipation problem, reduces the thermal stress generated by the motor and controller due to high temperature, reduces fatigue damage to components, and thus extends the overall service life of the power system. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other embodiments can be obtained based on these drawings without creative effort.

[0022] Figure 1 This invention provides a system architecture diagram for heat dissipation in an aircraft power system.

[0023] Figure 2 A flowchart of a method for heat dissipation in an aircraft power system provided by the present invention.

[0024] Figure 3 A schematic diagram of the structure of an embodiment of the computer device provided by the present invention.

[0025] Figure 4This is a schematic diagram of an embodiment of the computer-readable storage medium provided by the present invention.

[0026] Figure 5 A heat exchanger diagram for a heat dissipation system of an aircraft power system provided by the present invention.

[0027] Figure 6 A core diagram of a heat exchanger for a heat dissipation system of an aircraft power system provided by the present invention.

[0028] Figure 7 A diagram of a liquid reservoir for cooling an aircraft power system provided by the present invention.

[0029] Among them, 1. partition; 2. fins; 3. seal. Detailed Implementation

[0030] The present invention will be further described below with reference to the accompanying drawings. The following embodiments are only used to more clearly illustrate the technical solutions of the present invention and should not be construed as limiting the scope of protection of the present invention. It should be noted that the following detailed descriptions are exemplary and intended to provide further explanation of this application.

[0031] It should be noted that all uses of "first" and "second" in the embodiments of the present invention are for the purpose of distinguishing two entities or parameters with the same name but different names. It is clear that "first" and "second" are only for the convenience of expression and should not be construed as limiting the embodiments of the present invention. Subsequent embodiments will not explain this in detail.

[0032] This invention proposes a system for cooling an aircraft power system; please refer to [link / reference]. Figure 1 and Figure 7 ,include: Pump units are used to pressurize the heat dissipation medium; The measuring device includes a flow sensor and a pressure sensor. The flow sensor is located at the input end of the pump set, and the pressure sensor is located at the output end of the pump set. It is used to measure the flow rate and pressure of the heat dissipation medium after pressurization. The motor and motor controller flow channel are connected to the output end of the pump set and to the input end of the heat source to provide a flow path for the heat dissipation working fluid. A heat source is used to dissipate heat; the heat dissipation medium absorbs heat at the heat source and transforms into a heating medium. The cold source includes a staged cooling module, which is set in the working fluid flow path between the cold source and the heat source, and is used to stage-cool the heated working fluid. The reservoir, located at the inlet of the pump unit, is used to provide inlet pressure and stabilize the pump unit.

[0033] The pump unit is closely connected to the measuring device. The flow sensor is located at the pump unit's input end, and the pressure sensor is located at the output end. This connection allows for real-time and accurate monitoring of the flow rate and pressure of the heat dissipation medium before and after pressurization. The pump unit's output end is connected to the motor and motor controller's flow path, and then to the heat source input end, forming a smooth flow path for the heat dissipation medium. This ensures that the medium can smoothly reach the heat source to absorb heat, achieving efficient heat transfer.

[0034] The heat source and cold source are connected through a working fluid flow path, and the cold source is equipped with a staged cooling module, which allows the heated working fluid to gradually cool down as it flows through the cold source, thereby improving cooling efficiency and avoiding the impact on the system caused by a sudden drop in temperature.

[0035] The liquid receiver is located at the pump inlet and directly connected to the pump unit. It provides a stable inlet pressure, acting as a pressure stabilizer to prevent pressure fluctuations from affecting pump performance and the normal operation of the entire system. All components form a complete, efficient, and stable heat dissipation system, effectively ensuring the smooth progress of the heat dissipation process.

[0036] The sensor is mainly used to detect information such as pressure, flow rate, and water temperature. Based on the pressure sensor requirements, a standard pressure sensor device, model FMTKSG, was selected.

[0037] Based on the flow sensor requirements, a standard flow sensor device, model ZQ-01, was selected. The ZQ-01 flow sensor features impact resistance, high strength, corrosion resistance, compact structure, high accuracy, and light weight.

[0038] Based on the sensor requirements, a type T thermocouple was selected for temperature measurement. It offers good linearity, a large thermoelectric potential, high sensitivity, near-linear temperature readings, and good reproducibility. It can quickly and accurately sense temperature changes and output corresponding signals. The temperature range for measurement is -50 to 420℃, and the interface is a standard threaded connection, allowing for quick connection to a circuit.

[0039] In some embodiments, please refer to Figure 5 The graded cooling module includes a first-level cooling area and a second-level cooling area; Both the first-stage cooling zone and the second-stage cooling zone are equipped with heat exchangers, adjustable air duct cross-sectional areas, and variable frequency fans.

[0040] like Figure 5The heat exchanger shown is an air-cooled heat exchanger model. The inlet cross-sectional length is 190mm and the cross-sectional width is 140mm. The ambient temperature is 40℃. When the UAV is in a maneuvering state, the inlet airflow of the heat exchanger is 2202.48m3 / h, the inlet temperature of the hot fluid is 60℃, the outlet temperature is 49℃, and the heat exchange capacity is 6.8kW, which can meet the heat dissipation requirement of 6.3kW. When the UAV is in a gliding state, the inlet airflow of the heat exchanger decreases to 1627.92m3 / h, the inlet temperature of the hot fluid is 57℃, the outlet temperature is 49℃, and the heat exchange capacity is 5.7kW, which can meet the heat dissipation requirement of 4.5kW.

[0041] Both the first-stage and second-stage cooling zones are equipped with heat exchangers, which are connected by a working fluid flow path to form a parallel cooling structure. Depending on the operating conditions, the heated working fluid flows into the heat exchanger in the first-stage cooling zone for initial heat exchange with the cooling medium, achieving initial cooling; or it flows into the heat exchanger in the second-stage cooling zone for deep cooling, precisely controlling the degree of cooling of the working fluid to meet different heat dissipation requirements.

[0042] The adjustable air duct's cross-sectional area is matched with the variable frequency fan and connected around the heat exchanger. The variable frequency fan can adjust its speed and change the air volume according to the actual heat dissipation situation; the adjustable air duct can adjust its cross-sectional area according to the air volume demand, optimizing the airflow path and air volume distribution.

[0043] In some embodiments, please refer to Figure 6 The heat exchanger includes a core, which is integrally brazed from a partition plate 1, fins 2 and a sealing strip 3; The fins 2 are arranged in a forward or oblique direction, and adjacent rows of fins 2 are staggered and interleaved in the horizontal or vertical direction.

[0044] During operation, the motor and motor controller release a large amount of heat. The heat carried by the working medium is transferred to the surface of the heat exchanger and the heat dissipation fins 2 through the heat exchanger. By drawing in ambient air to exchange heat with the heat exchanger, the heat generated during the operation of the motor and motor controller is removed, the temperature of the medium in the heat exchanger is reduced and flows out of the heat exchanger to enter the heat exchange cycle, ensuring that the motor and motor controller work stably and maintain the optimal cooling temperature.

[0045] Among the many types of air-cooled heat exchangers, plate heat exchangers, evolved from traditional shell-and-tube heat exchangers, are currently the most efficient and compact heat exchange devices. Plate-fin heat exchangers consist of the following components: Figure 6 As shown, the core is integrally brazed from components such as partition plate 1, fins 2, and seals 3. The core is the core of the plate-fin heat exchanger, and selecting appropriate heat dissipation core components can better meet its performance requirements.

[0046] like Figure 6The diagram shows a forward-arranged fin 2. Depending on the specific requirements, heat exchangers with a 30° oblique fin arrangement 2 can be manufactured. By arranging the fins 2 at a 30° angle, with adjacent rows of fins 2 staggered, turbulent flow of cooling air is created within the flow channel. This breaks up the air boundary layer adhesion and improves the convective heat transfer coefficient between the air and the fins 2. Simultaneously, the oblique staggered design reduces eddy current losses within the airflow channel.

[0047] The fins 2 are arranged either upright or obliquely, with adjacent rows of fins 2 staggered in the horizontal or vertical direction. This staggered arrangement increases the contact area and contact time between the working fluid and the fins 2, allowing for more efficient heat transfer between them. Simultaneously, this connection method improves the flow state of the working fluid within the heat exchanger, reduces dead zones, and allows the working fluid to flow more smoothly through the entire core, thus increasing heat exchange efficiency.

[0048] This invention proposes a method for heat dissipation in an aircraft power system, and applies it to a system for heat dissipation in an aircraft power system. Please refer to [link / reference]. Figure 2 , The heat dissipation medium is pressurized by a pump unit, and then flows to the heat source to absorb heat, thus obtaining a heated medium, and the cold source is adjusted. During the aircraft taxiing phase, the heating working fluid passes through the first-stage cooling zone of the cold source and dissipates heat through low-speed convection to obtain a preliminary cooling working fluid. During the takeoff or maneuver phase of the aircraft, the heating working fluid passes through the second-stage cooling zone of the cold source and dissipates heat through high-speed convection to obtain a deeply cooling working fluid. The initial cooling medium or the deep cooling medium is used as a new heat dissipation medium and then enters the pump group again after passing through the liquid receiver to circulate and dissipate heat.

[0049] The pump unit pressurizes the cooling medium to provide sufficient pressure for smooth flow within the system. The pressurized medium then flows into the heat source, typically a component on the aircraft that generates significant heat. The cooling medium absorbs heat at the heat source, increasing its temperature and becoming a warming medium. Simultaneously, the system adjusts the operating status of the cooling source according to different phases of aircraft operation.

[0050] When the aircraft is taxiing, its flight speed is relatively slow, and the amount of heat generated is relatively small. At this time, the heating medium enters the first-stage cooling zone of the cold source, where heat is dissipated through low-speed convection. At low wind speeds (1-5 m / s), the heat exchange between the air and the heating medium is relatively gentle, which can meet the relatively low heat dissipation requirements at this time, allowing the heating medium to achieve initial cooling and become the initial cooling medium.

[0051] During takeoff or maneuvering, the increased flight speed leads to a significant increase in heat generated by components such as the engine. The heated medium enters the second-stage cooling zone of the cold source, where high-speed (5-20 m / s) convection cooling is employed. High air speed accelerates airflow, enhancing the heat exchange efficiency between the air and the heated medium, resulting in deep cooling of the medium, transforming it into a deep-cooling medium.

[0052] The initial cooling medium or the deep cooling medium, acting as the new heat dissipation medium, first flows into the receiver. The receiver serves to stabilize the system pressure and provide inlet pressure for the pump unit. Afterward, the new heat dissipation medium re-enters the pump unit, starting a new cycle of heat dissipation.

[0053] To address the varying heat dissipation requirements of the power system during takeoff (11kW peak), maneuvering (6.3kW continuous), and taxiing (4.5kW continuous), an intelligent cooling strategy integrating adaptive wind speed adjustment and dual-mode water pump speed regulation is implemented. The core mechanism dynamically adjusts the cooling airflow speed according to the operating conditions, coupled with automatic switching of the circulating pump's follow-up mode. This achieves precise matching between heat dissipation capacity and the system's real-time heat dissipation and working fluid temperature, ensuring efficient heat dissipation under high heat dissipation conditions while achieving energy saving and consumption reduction under low heat dissipation conditions, thus completing precise, stepped cooling across all operating conditions.

[0054] In some embodiments, the process of obtaining a preliminary cooling working fluid by passing through the first-stage cooling zone of the cold source and dissipating heat through low-speed convection during the aircraft taxiing phase includes: During the aircraft taxiing phase, the heated working fluid passes through the first-stage cooling zone of the cold source; The temperature of the heating medium, the preset initial cooling target temperature, and the low wind speed range are obtained. In the first-stage cooling zone, the cross-sectional area of ​​the adjustable air duct and the power of the variable frequency fan are set according to the low wind speed range; When the temperature of the heating medium reaches the initial cooling target temperature, the cross-sectional area of ​​the adjustable air duct and the power of the variable frequency fan are locked to maintain the low wind speed convection heat dissipation state until the initial cooling medium is obtained.

[0055] Low heat dissipation mode (coasting phase): The system switches to the energy-saving cooling level, reduces the incoming airflow velocity, and reduces the power consumption of the air path; when the temperature decreases, the speed is appropriately reduced. Under the premise of ensuring the working fluid temperature is stable, the power consumption of the pump group is reduced to the maximum extent to meet the continuous low heat dissipation demand of 4.5kW.

[0056] During the aircraft taxiing phase, the heated working fluid, having absorbed heat from the heat source, is guided into the first-stage cooling zone of the cold source. At this time, the system quickly acquires the current temperature of the heated working fluid and simultaneously determines the preset initial cooling target temperature and low wind speed range. The initial cooling target temperature is set based on the safe operating temperature range of each component during aircraft taxiing, while the low wind speed range is determined based on extensive experiments and practical operating experience.

[0057] Within the first-stage cooling zone, the cross-sectional area of ​​the adjustable air duct and the power of the variable frequency fan are set according to the determined low air velocity range. The adjustable air duct adjusts the airflow by changing the cross-sectional area, while the variable frequency fan controls the air velocity by adjusting its power, enabling convection cooling between the air and the heated working fluid.

[0058] During the heat dissipation process, the system continuously monitors the temperature of the heating medium. When the temperature of the heating medium gradually decreases and reaches the initial cooling target temperature, the system immediately locks the cross-sectional area of ​​the adjustable air duct and the power of the variable frequency fan. This ensures that the low-speed convection heat dissipation state is maintained stably until the heating medium is completely transformed into the initial cooling medium.

[0059] For example, assuming the temperature of the working fluid during aircraft taxiing is 80℃, the preset initial cooling target temperature is 50℃, and the low wind speed range is set at 2-3 m / s. The system adjusts the adjustable duct cross-sectional area and the variable frequency fan power according to this range. When the working fluid temperature drops to 50℃, the current setting is locked, ultimately obtaining a working fluid with an initial cooling temperature of 50℃.

[0060] In some embodiments, the process of obtaining a deeply cooled working fluid by high-speed convection cooling in the second-stage cooling zone of the cold source during aircraft takeoff or maneuvering includes: During aircraft takeoff or maneuvering, the heated working fluid passes through the second-stage cooling zone of the cold source; Obtain the preset target temperature for deep cooling and the high wind speed range; In the second-stage cooling zone, the cross-sectional area of ​​the adjustable air duct and the power of the variable frequency fan are set according to the high wind speed range; When the temperature of the heating medium reaches the target temperature for deep cooling, the cross-sectional area of ​​the adjustable air duct and the power of the variable frequency fan are locked to maintain the high-speed convection heat dissipation state until the deep cooling medium is obtained.

[0061] High heat dissipation conditions (takeoff / maneuvering phase): The system triggers the full-load cooling stage, providing strong convection heat exchange conditions for the heat exchanger with maximum wind speed; the circulating pump starts in follow-up mode, and collects the working fluid temperature data in real time through the temperature sensor. The pump speed is dynamically adjusted according to the working fluid temperature. With high PWM output, the high-temperature working fluid flows quickly through the heat exchanger to complete efficient cooling, ensuring that the inlet and outlet temperatures of the motor and controller are strictly controlled within the limits, meeting the high heat dissipation requirements of 11kW peak and 6.3kW continuous operation.

[0062] During takeoff or maneuvering, the heated working fluid, having absorbed a significant amount of heat from the heat source, is guided into the secondary cooling zone of the cold source. The system acquires preset target deep cooling temperatures and high airflow ranges. The target deep cooling temperature is set based on the upper temperature limit at which the aircraft's components can operate safely and stably during this phase, ensuring that once the working fluid temperature is reduced to this range, excessively high temperatures will not affect component performance. Within the high airflow range, the heat exchange efficiency between the air and the heated working fluid reaches its optimal level, rapidly removing heat without causing system instability or excessive energy consumption due to excessive wind speed.

[0063] During the heat dissipation process, the system continuously and closely monitors the temperature of the heating medium. Once the temperature of the heating medium reaches the target temperature for deep cooling, the cross-sectional area of ​​the adjustable air duct and the power of the variable frequency fan are locked to maintain the current high-speed convection cooling state until the heating medium is completely transformed into a deep cooling medium.

[0064] For example, when an aircraft takes off, the temperature of the heating medium reaches 120°C, the preset target temperature for deep cooling is 30°C, and the high wind speed range is set at 12-15 m / s. The system adjusts the settings accordingly, and locks the parameters when the medium temperature drops to 30°C, ultimately obtaining the deep cooling medium.

[0065] In some embodiments, please refer to Figure 7 The process of using the initial cooling medium or the deep cooling medium as a new heat dissipation medium to re-enter the pump unit after passing through the liquid receiver includes: The system pressure is obtained through a pressure sensor; When the system pressure is higher than the pressure of the pre-charged gas in the reservoir, the heat dissipation medium enters the gas bladder of the reservoir until the gas pressure rises to the same level as the system pressure. Then the heat dissipation medium stops entering and the remaining heat dissipation medium enters the pump unit. When the system pressure is lower than the pressure of the pre-charged gas in the reservoir, the medium in the reservoir's bladder replenishes the system until the system pressure is the same as the gas pressure. At this point, the replenishment of the medium in the reservoir's bladder stops, and the medium and heat dissipation medium in the bladder are combined and enter the pump unit.

[0066] When the system pressure is higher than the pressure of the pre-charged gas in the reservoir, it means that the system pressure is relatively high. At this time, the heat dissipation medium will enter the reservoir's gas chamber under the influence of the pressure difference. As the heat dissipation medium continues to flow in, the gas chamber gradually expands, compressing the pre-charged gas inside, and the gas pressure also increases. When the gas pressure rises to the same level as the system pressure, the pressure difference disappears, and the heat dissipation medium stops entering the gas chamber. The remaining heat dissipation medium in the system will then directly enter the pump unit, waiting for the next cycle of heat dissipation.

[0067] Conversely, when the system pressure is lower than the pressure of the pre-charged gas in the reservoir, it indicates insufficient system pressure. At this time, the reservoir's gas bladder contracts under the internal gas pressure, releasing the stored medium, typically water, into the system to increase the pressure. As the medium is continuously added, the system pressure gradually rises, stopping when it equals the gas pressure. Subsequently, the liquid, now containing the medium from the gas bladder and the original heat dissipation medium, enters the pump unit to continue participating in the heat dissipation cycle.

[0068] For example, assuming the initial system pressure is 3 MPa and the pre-charge gas pressure in the reservoir is 2 MPa, if the system pressure is higher than the pre-charge gas pressure, the heat dissipation medium enters the gas bag until the gas pressure rises to 3 MPa and stops; if the system pressure becomes 1.5 MPa, which is lower than the pre-charge gas pressure, the medium in the gas bag replenishes the system until the system pressure rises to 2 MPa, after which the fusion medium enters the pump unit.

[0069] As a pressure-stabilizing element in the system, the receiver first needs to provide the inlet pressure of the circulating pump to ensure that the pump operates within its normal pressure range. Secondly, the receiver can absorb pressure fluctuations in the system, ensuring smooth operation and preventing vibration. Finally, when system operating conditions change, it compensates for changes in the volume of the working fluid due to temperature variations and maintains pressure stability. Considering its main functions and the requirement for a long system lifespan, a diaphragm-type receiver is adopted.

[0070] When the reservoir is used in the system, because the system pressure is higher than the pre-charge gas pressure, some working medium will enter the bladder (or the tank for diaphragm systems) until a new equilibrium is reached. When the system pressure rises again and exceeds the pre-charge gas pressure, some medium will again enter the bladder, compressing the gas between the bladder and the tank. The compressed gas pressure increases until it matches the system pressure, at which point medium entry stops. Conversely, when the system pressure drops and the system medium pressure falls below the gas pressure between the bladder and the tank, water in the bladder will be forced out by the gas and added to the system, causing the system pressure to rise until the system working medium pressure equals the gas pressure between the bladder and the tank. At this point, water in the bladder will no longer be added to the system, maintaining a dynamic equilibrium. The reservoir is like... Figure 7 As shown.

[0071] Based on the system's operating temperature range and that of key components, the initial selection of the working fluid as either a 50% ethylene glycol aqueous solution or a perfluorocyclic ether is made. The system filling pressure for both working fluids is 1 bar. A comparison of the working fluid parameters is shown in Table 1 below.

[0072] Table 1 Comparison and Analysis of Working Fluid Parameters

[0073] In some embodiments, the process of adjusting the cold source is to adjust the fin spacing parameter of the heat exchanger 2 in the cold source; Maximizing the heat exchange efficiency of the heat exchanger is the first objective function. In the formula, For heat exchange efficiency, It is the first constant. The spacing between fins 2; Minimizing the flow resistance of the heat exchanger is the second objective function. In the formula, For dynamic resistance, It is the second constant; Different weight coefficients are assigned to the first objective function and the second objective function, and the optimal parameter combination for the fin spacing is obtained by solving the problem using a genetic algorithm.

[0074] Through coupled analysis of fluid and thermal simulations, the optimal parameter combination for the spacing of fins 2 was determined. This spacing maximizes the arrangement of heat exchange fins 2 and baffles 1 within a space of 215×140×150mm, increasing the heat exchange area by 15% compared to the original equidistant design. At the same time, it takes into account the flow characteristics of the working fluid and air, avoiding the problems of a sudden increase in flow resistance due to too small a spacing and the waste of heat exchange area due to too large a spacing, ensuring that the thermal edge flow resistance is controlled within the design range of 3.82~3.86kPa and the air flow resistance is controlled within the design range of 1.34~1.42kPa.

[0075] By comprehensively considering the heat exchange efficiency and flow resistance of the heat exchanger, the optimal balance between the two can be found, thereby significantly improving the overall performance of the heat exchanger, reducing the energy consumption of the aircraft, improving the stability and reliability of the aircraft's heat dissipation system, and ensuring that the aircraft can operate safely and efficiently under various operating conditions.

[0076] Based on the same inventive concept, according to another aspect of the present invention, such as Figure 3 As shown, an embodiment of the present invention also provides a computer device 30, which includes a processor 310 and a memory 320. The memory 320 stores a computer program 321 that can be run on the processor. When the processor 310 executes the program, it performs the steps of the method described above.

[0077] Based on the same inventive concept, according to another aspect of the present invention, such as Figure 4 As shown, embodiments of the present invention also provide a computer-readable storage medium 40, which stores a computer program 410 that, when executed by a processor, performs the methods described above.

[0078] Embodiments of the present invention may also include a corresponding computer device. The computer device includes a memory, at least one processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes any of the methods described above when executing the program.

[0079] The memory, as a non-volatile computer-readable storage medium, can be used to store non-volatile software programs, non-volatile computer-executable programs, and modules, such as program instructions / modules in the embodiments of this application. The processor executes various functional applications and data processing of the device by running the non-volatile software programs, instructions, and modules stored in the memory, thereby implementing the above-described method.

[0080] The memory may include a program storage area and a data storage area. The program storage area may store the operating system and applications required for at least one function; the data storage area may store data created based on the use of the device. Furthermore, the memory may include high-speed random access memory and non-volatile memory, such as at least one disk storage device, flash memory device, or other non-volatile solid-state storage device. In embodiments, the memory may optionally include memory remotely located relative to the processor, which can be connected to the local module via a network. Examples of such networks include, but are not limited to, the Internet, corporate intranets, local area networks, mobile communication networks, and combinations thereof.

[0081] Finally, it should be noted that those skilled in the art will understand that all or part of the processes in the above embodiments can be implemented by a computer program instructing related hardware. The program can be stored in a computer-readable storage medium, and when executed, it can include the processes of the embodiments of the methods described above. The storage medium for the program can be a magnetic disk, optical disk, read-only memory (ROM), or random access memory (RAM), etc. The above computer program embodiments can achieve the same or similar effects as any of the corresponding foregoing method embodiments.

[0082] Those skilled in the art will also understand that the various exemplary logic blocks, modules, circuits, and algorithm steps described in conjunction with the disclosure herein can be implemented as electronic hardware, computer software, or a combination of both. To clearly illustrate this interchangeability between hardware and software, the functionality of various illustrative components, blocks, modules, circuits, and steps has been generally described. Whether this functionality is implemented as software or as hardware depends on the specific application and the design constraints imposed on the system as a whole. Those skilled in the art can implement the functionality in various ways for each specific application, but such implementation decisions should not be construed as departing from the scope of the embodiments disclosed herein.

[0083] The above are exemplary embodiments disclosed in this invention. However, it should be noted that various changes and modifications can be made without departing from the scope of the embodiments of this invention as defined by the claims. The functions, steps, and / or actions of the methods according to the disclosed embodiments described herein do not need to be performed in any particular order. The sequence numbers of the disclosed embodiments of this invention are for descriptive purposes only and do not represent the superiority or inferiority of the embodiments. Furthermore, although the elements disclosed in the embodiments of this invention may be described or claimed individually, they may be understood as multiple unless explicitly limited to a singular number.

[0084] It should be understood that, as used herein, the singular form “a” is intended to include the plural form as well, unless the context clearly supports an exception. It should also be understood that, as used herein, “and / or” refers to any and all possible combinations of one or more of the associated listed items.

[0085] Those skilled in the art should understand that the discussion of any of the above embodiments is merely exemplary and is not intended to imply that the scope of the invention (including the claims) is limited to these examples. Within the framework of the invention, technical features of the above embodiments or different embodiments can be combined, and many other variations of different aspects of the invention exist, which are not provided in the details for the sake of brevity. Therefore, any omissions, modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the invention should be included within the protection scope of the invention.

Claims

1. A system for cooling an aircraft power system, characterized in that, include: Pump units are used to pressurize the heat dissipation medium; The measuring device includes a flow sensor and a pressure sensor. The flow sensor is located at the input end of the pump set, and the pressure sensor is located at the output end of the pump set. It is used to measure the flow rate and pressure of the heat dissipation medium after pressurization. The motor and motor controller flow channel are connected to the output end of the pump set and to the input end of the heat source to provide a flow path for the heat dissipation working fluid. A heat source is used to dissipate heat; the heat dissipation medium absorbs heat at the heat source and transforms into a heating medium. The cold source includes a staged cooling module, which is set in the working fluid flow path between the cold source and the heat source, and is used to stage-cool the heated working fluid. The reservoir, located at the inlet of the pump unit, is used to provide inlet pressure and stabilize the pump unit.

2. The system for cooling an aircraft power system according to claim 1, characterized in that, The graded cooling module includes a first-level cooling area and a second-level cooling area; Both the first-stage cooling zone and the second-stage cooling zone are equipped with heat exchangers, adjustable air duct cross-sectional areas, and variable frequency fans.

3. The system for cooling an aircraft power system according to claim 2, characterized in that, The heat exchanger includes a core, which is integrally brazed from a partition (1), fins (2) and a seal (3); The fins (2) are arranged in a forward or oblique direction, and adjacent rows of fins (2) are staggered and interleaved in the horizontal or vertical direction.

4. A method for heat dissipation of an aircraft power system, applied in a system comprising heat dissipation of an aircraft power system as described in any one of claims 1-3, characterized in that, The heat dissipation medium is pressurized by a pump unit, and then flows to the heat source to absorb heat, thus obtaining a heated medium, and the cold source is adjusted. During the aircraft taxiing phase, the heating working fluid passes through the first-stage cooling zone of the cold source and dissipates heat through low-speed convection to obtain a preliminary cooling working fluid. During the takeoff or maneuver phase of the aircraft, the heating working fluid passes through the second-stage cooling zone of the cold source and dissipates heat through high-speed convection to obtain a deeply cooling working fluid. The initial cooling medium or the deep cooling medium is used as a new heat dissipation medium and then enters the pump group again after passing through the liquid receiver to circulate and dissipate heat.

5. A method for heat dissipation of an aircraft power system according to claim 4, characterized in that, During the aircraft taxiing phase, the process by which the heated working fluid dissipates heat through low-speed convection in the first-stage cooling zone of the cold source to obtain a pre-cooled working fluid includes: During the aircraft taxiing phase, the heated working fluid passes through the first-stage cooling zone of the cold source; The temperature of the heating medium, the preset initial cooling target temperature, and the low wind speed range are obtained. In the first-stage cooling zone, the cross-sectional area of ​​the adjustable air duct and the power of the variable frequency fan are set according to the low wind speed range; When the temperature of the heating medium reaches the initial cooling target temperature, the cross-sectional area of ​​the adjustable air duct and the power of the variable frequency fan are locked to maintain the low wind speed convection heat dissipation state until the initial cooling medium is obtained.

6. A method for heat dissipation of an aircraft power system according to claim 5, characterized in that, The process by which the heated working fluid dissipates heat through high-speed convection in the second-stage cooling zone of the cold source during aircraft takeoff or maneuvering to obtain a deeply cooled working fluid includes: During aircraft takeoff or maneuvering, the heated working fluid passes through the second-stage cooling zone of the cold source; Obtain the preset target temperature for deep cooling and the high wind speed range; In the second-stage cooling zone, the cross-sectional area of ​​the adjustable air duct and the power of the variable frequency fan are set according to the high wind speed range; When the temperature of the heating medium reaches the target temperature for deep cooling, the cross-sectional area of ​​the adjustable air duct and the power of the variable frequency fan are locked to maintain the high-speed convection heat dissipation state until the deep cooling medium is obtained.

7. A method for heat dissipation of an aircraft power system according to claim 4, characterized in that, The process of using the initial cooling medium or the deep cooling medium as a new heat dissipation medium to re-enter the pump unit after passing through the liquid receiver includes: The system pressure is obtained through a pressure sensor; When the system pressure is higher than the pressure of the pre-charged gas in the reservoir, the heat dissipation medium enters the gas bladder of the reservoir until the gas pressure rises to the same level as the system pressure. Then the heat dissipation medium stops entering and the remaining heat dissipation medium enters the pump unit. When the system pressure is lower than the pressure of the pre-charged gas in the reservoir, the medium in the reservoir's bladder replenishes the system until the system pressure is the same as the gas pressure. At this point, the replenishment of the medium in the reservoir's bladder stops, and the medium and heat dissipation medium in the bladder are combined and enter the pump unit.

8. A method for heat dissipation of an aircraft power system according to claim 4, characterized in that, The process of adjusting the cold source is to adjust the fin spacing parameter (2) of the heat exchanger in the cold source; Maximizing the heat exchange efficiency of the heat exchanger is the first objective function. In the formula, For heat exchange efficiency, It is the first constant. The spacing between the fins (2); Minimizing the flow resistance of the heat exchanger is the second objective function. In the formula, For dynamic resistance, It is the second constant; Different weight coefficients are assigned to the first objective function and the second objective function, and the optimal parameter combination of the fin (2) spacing is obtained by solving the problem through a genetic algorithm.

9. A computer device, comprising: At least one processor; And a memory storing a computer program executable on the processor, characterized in that the processor executes the program to perform the steps of a method for cooling an aircraft power system as described in any one of claims 4 to 8.

10. A computer-readable storage medium storing a computer program, characterized in that, When the computer program is executed by the processor, it performs the steps of a method for cooling an aircraft power system as described in any one of claims 4 to 8.

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