Aero high-speed generator heat dissipation system and control method

Abstract

The application belongs to the technical field of aviation system, and discloses an aviation high-speed generator heat dissipation system and a control method, wherein a fuel pump is arranged on a main oil pipeline, and a radiator is arranged on a secondary oil pipeline; a pressure-bearing heat exchanger is connected with an oil tank through the main oil pipeline and the secondary oil pipeline respectively; the pressure-bearing heat exchanger is further connected with a turbine engine through a conveying pipeline; the pressure-bearing heat exchanger comprises a heat pipe and is connected with a high-speed generator through the heat pipe; the fuel pump is used for pumping out fuel in the oil tank and delivering the fuel to the pressure-bearing heat exchanger through the main oil pipeline; the pressure-bearing heat exchanger is used for exchanging heat between the fuel in the main oil pipeline and the high-speed generator, delivering a first part of the fuel after heat exchange to the turbine engine through the conveying pipeline, and delivering a second part of the fuel after heat exchange back to the oil tank through the secondary oil pipeline. The application can reduce the weight of the heat dissipation system, is more convenient for being carried by a UAV, and can also operate the heat dissipation function when the turbine engine is stopped.

Description

Technical Field

[0001] This application relates to the field of aviation system technology, and in particular to a heat dissipation system and control method for a high-speed aviation generator. Background Technology

[0002] Existing motors typically dissipate heat through natural convection, forced air cooling, water cooling, oil cooling, and hydrogen cooling. For high-power-density motors, natural convection is insufficient to meet their cooling requirements, making forced air cooling, water cooling, or oil cooling the preferred methods. Forced air cooling generally involves installing a cooling fan at the motor end, either coaxial with the motor shaft or driven separately, to exhaust air and dissipate heat from the motor's interior. Water or oil cooling involves installing water or oil cooling jackets on the outside or end of the motor housing. The flow of oil or water through these jackets removes heat from the housing and ends. Hydrogen cooling involves installing hydrogen cooling pipes around the motor windings and housing, using high-pressure flowing hydrogen to carry away heat.

[0003] However, forced air cooling achieves heat dissipation through air convection, resulting in low heat dissipation power and efficiency. Furthermore, the irregular shape of the internal flow channels of the motor leads to high airflow resistance, further worsening its heat dissipation efficiency. Oil and water cooling methods require additional cooling media (oil and water) and external circulation equipment, which is heavy. Hydrogen cooling requires bulky hydrogen storage and pressurization equipment, and also has high requirements for system sealing. For small aircraft such as drones, their payload capacity is small and space is extremely limited. Whether it is oil-cooled, water-cooled, or hydrogen-cooled, the accompanying cooling equipment is very large and heavy, making it difficult to install on drones. Summary of the Invention

[0004] This application provides a heat dissipation system and control method for a high-speed generator for aircraft, which can reduce the weight of the heat dissipation system, make it easier to carry on UAVs, and enable the heat dissipation function to operate even when the turbine engine is shut down.

[0005] In a first aspect, embodiments of this application provide a cooling system for an aircraft high-speed generator, including a main oil pipeline, an auxiliary oil pipeline, a delivery pipeline, a turbine engine, a high-speed generator, and a pressurized heat exchanger;

[0006] A fuel pump is installed on the main fuel line, and a radiator is installed on the auxiliary fuel line;

[0007] The pressure heat exchanger is connected to the oil tank via a main oil pipeline and a secondary oil pipeline, respectively.

[0008] The pressurized heat exchanger is also connected to the turbine engine via pipelines;

[0009] The pressure heat exchanger includes heat pipes and is connected to a high-speed generator via the heat pipes;

[0010] The fuel pump is used to extract fuel from the fuel tank and deliver it to the pressurized heat exchanger through the main fuel line.

[0011] The pressurized heat exchanger is used to exchange heat between the fuel in the main oil pipeline and the high-speed generator, and to transfer the first part of the fuel after heat exchange to the turbine engine through the delivery pipeline; and to transfer the second part of the fuel after heat exchange back to the fuel tank through the auxiliary oil pipeline.

[0012] Furthermore, a first controllable valve is provided on the delivery pipeline; the first controllable valve is used to control the flow rate of the first portion of fuel in the delivery pipeline; the delivery pipeline is also provided with a first oil temperature sensor and a first flow sensor between the first controllable valve and the turbine generator, respectively used to obtain the first fuel temperature and the first fuel flow rate value of the first portion of fuel.

[0013] Furthermore, a second controllable valve is installed in the auxiliary oil pipeline between the pressurized heat exchanger and the radiator;

[0014] The second controllable valve is used to control the flow rate of the second portion of fuel in the auxiliary oil pipeline;

[0015] The auxiliary oil pipeline is also equipped with a second oil temperature sensor and a second flow sensor between the second controllable valve and the radiator, which are used to obtain the second fuel oil temperature and the second fuel flow value of the second part of the fuel, respectively.

[0016] Furthermore, a third oil temperature sensor is installed in the main oil pipeline between the fuel pump and the fuel tank;

[0017] The third oil temperature sensor is used to obtain the third fuel oil temperature in the main oil pipeline;

[0018] The main oil pipeline is also equipped with a third flow sensor and a pressure sensor between the fuel pump and the pressure heat exchanger, which are used to obtain the third fuel flow rate and fuel pressure value in the main oil pipeline, respectively.

[0019] Furthermore, the pressure heat exchanger includes an exchanger, an oil inlet, a first oil outlet, a second oil outlet, a collector, and multiple heat pipes; the oil inlet is connected to the main oil pipeline, the first oil outlet is connected to the delivery pipeline, and the second oil outlet is connected to the auxiliary oil pipeline.

[0020] Each heat pipe is welded to the collector, and the collector and the exchanger are connected by screws;

[0021] The collector is used to collect the heat from each heat pipe and transfer it to the heat exchanger;

[0022] The heat exchanger is used to exchange the heat collected by the collector with the fuel entering from the inlet.

[0023] Furthermore, the exchanger includes an interconnected top cover and a base, the base including annular heat dissipation fins and an oil baffle;

[0024] The oil inlet, the first oil outlet, and the second oil outlet are all located on the top cover;

[0025] The oil stop is used to isolate the oil inlet from the first and second oil outlets.

[0026] Secondly, embodiments of this application provide a heat dissipation control method for an aircraft high-speed generator, applied to an aircraft high-speed generator heat dissipation system as described in any of the above embodiments, comprising:

[0027] In response to a fuel supply command, the fuel pump is activated; the fuel supply command includes a target fuel pressure value.

[0028] Determine whether the difference between the fuel pressure value and the target fuel pressure value is within the preset error range;

[0029] If not, the fuel pump power is adjusted based on the target fuel pressure value.

[0030] Furthermore, the control method also includes:

[0031] Obtain the generator temperature of the high-speed generator;

[0032] Determine whether the generator temperature or the first fuel oil temperature is greater than a first preset threshold and continue for a preset duration;

[0033] If so, the second valve opening is obtained based on the generator temperature, the first fuel oil temperature, and the preset opening coefficient.

[0034] Turn on the radiator and activate the second controllable valve on the auxiliary oil pipeline based on the opening degree of the second valve.

[0035] Furthermore, the control method also includes:

[0036] Determine whether the temperature of the third fuel is greater than the second preset threshold.

[0037] If so, the second valve opening of the second controllable valve is controlled to be 100%; otherwise, the second valve opening of the second controllable valve is calculated based on the generator temperature, the first fuel temperature, and the preset opening calculation coefficient.

[0038] Furthermore, the control method also includes:

[0039] If the generator temperature is detected to be greater than the first preset threshold, then determine whether the first fuel flow rate value is 0;

[0040] If so, the second valve opening of the second controllable valve is set to 100%, and the radiator is turned on.

[0041] Furthermore, the fuel supply command also includes a target fuel supply flow rate or a target controllable valve opening degree; the control method also includes:

[0042] The first controllable valve is adjusted based on the target oil supply flow rate or the target controllable valve opening.

[0043] In summary, compared with the prior art, the beneficial effects of the technical solution provided in this application include at least the following:

[0044] This application provides a high-speed generator cooling system for aircraft. First, it uses the onboard fuel of the UAV as the cooling medium, eliminating the need for additional cooling media and reducing the overall weight of the cooling system. Second, it utilizes the main oil pipeline supplying fuel to the turbine engine as the same pipeline supplying fuel to the cooling system, achieving partial oil circuit sharing, high integration, further reducing the weight of the cooling system and making it easier for the UAV to carry. Furthermore, the fuel, after heat exchange, can be considered preheated, resulting in higher combustion efficiency during use. Moreover, even when the turbine engine is shut down, i.e., when there is no flow in the delivery pipeline, the cooling system structure can still achieve the cooling function of the high-speed generator through the main and auxiliary oil pipelines. Attached Figure Description

[0045] Figure 1 This is a structural diagram of a high-speed generator cooling system for an aircraft, provided as an exemplary embodiment of this application.

[0046] Figure 2 An overall structural diagram of a pressure heat exchanger provided for an exemplary embodiment of this application.

[0047] Figure 3 This is a schematic diagram of the structure of a solar collector and heat pipe provided for an exemplary embodiment of this application.

[0048] Figure 4 This is an overall structural diagram of a switch provided for an exemplary embodiment of this application.

[0049] Figure 5 An exploded view of the top cover and base provided for an exemplary embodiment of this application.

[0050] Figure 6 A flowchart illustrating a heat dissipation control method for an aircraft high-speed generator, provided as an exemplary embodiment of this application. Detailed Implementation

[0051] The technical solutions in the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments.

[0052] Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without inventive effort are within the scope of protection of this application.

[0053] Please see Figure 1 This application provides a cooling system for an aircraft high-speed generator, including a main oil pipeline, a secondary oil pipeline, a delivery pipeline, a turbine engine, a high-speed generator, and a pressurized heat exchanger.

[0054] The main fuel line is equipped with a fuel pump, and the auxiliary fuel line is equipped with a radiator.

[0055] The pressure heat exchanger is connected to the oil tank via the main oil pipeline and the auxiliary oil pipeline.

[0056] The pressurized heat exchanger is also connected to the turbine engine via pipelines.

[0057] The pressure heat exchanger includes heat pipes and is connected to a high-speed generator via the heat pipes.

[0058] The fuel pump is used to extract fuel from the fuel tank and deliver it to the pressurized heat exchanger via the main fuel line.

[0059] The pressurized heat exchanger is used to exchange heat between the fuel in the main oil pipeline and the high-speed generator, and to transfer the first part of the fuel after heat exchange to the turbine engine through the delivery pipeline; and to transfer the second part of the fuel after heat exchange back to the fuel tank through the auxiliary oil pipeline.

[0060] Specifically, the heat dissipation system of this application is divided into two flow paths: a main oil circuit and a secondary oil circuit.

[0061] Please see Figure 1 The main fuel line begins at the fuel tank. Fuel flows from the tank, is pressurized by the fuel pump, and then flows through the main line to the pressurized heat exchanger. The main fuel line is divided into engine-side and fuel tank-side, with the pressurized heat exchanger as the dividing point. The section from the fuel tank to the pressurized heat exchanger is the fuel tank-side main fuel line, and the section from the pressurized heat exchanger to the engine-side is the engine-side main fuel line. The fuel tank-side main fuel line is implemented through the main fuel pipeline, while the engine-side main fuel line is implemented through the delivery pipeline. The auxiliary fuel line is implemented through the auxiliary fuel pipeline.

[0062] The fuel flow in the main fuel line is as follows: fuel tank → fuel pump → main fuel line → pressure sensor, and then enters the pressurized heat exchanger. After heat exchange in the pressurized heat exchanger, the fuel is divided into two paths: one path enters the turbocharger engine, and the other path enters the auxiliary fuel line, where it is cooled by the radiator and then returns to the fuel tank.

[0063] The above-described high-speed generator cooling system for aircraft provides several advantages. First, it uses the onboard fuel of the UAV as the cooling medium, eliminating the need for additional cooling media and reducing the overall weight of the cooling system. Second, it utilizes the main oil pipeline supplying fuel to the turbine engine as the same pipeline supplying fuel to the cooling system, achieving partial oil circuit sharing, high integration, further reducing the weight of the cooling system, and making it easier for the UAV to carry. Furthermore, the fuel, after heat exchange, can be considered preheated, resulting in higher combustion efficiency during use. Moreover, even when the turbine engine is shut down, i.e., when there is no flow in the delivery pipeline, the cooling system structure can still achieve the cooling function of the high-speed generator through the main and auxiliary oil pipelines.

[0064] Please see Figure 1 In some embodiments, a first controllable valve is provided on the delivery pipeline; the first controllable valve is used to control the flow rate of a first portion of fuel in the delivery pipeline; the delivery pipeline is also provided with a first oil temperature sensor and a first flow sensor between the first controllable valve and the turbine generator, respectively used to obtain the first fuel oil temperature and the first fuel flow rate value of the first portion of fuel.

[0065] The auxiliary oil pipeline is also equipped with a second controllable valve between the pressure heat exchanger and the radiator.

[0066] The second controllable valve is used to control the flow rate of the second portion of fuel in the auxiliary fuel pipeline.

[0067] The auxiliary oil pipeline is also equipped with a second oil temperature sensor and a second flow sensor between the second controllable valve and the radiator, which are used to obtain the second fuel oil temperature and the second fuel flow value of the second part of the fuel, respectively.

[0068] A third oil temperature sensor is installed in the main oil pipeline between the fuel pump and the fuel tank.

[0069] The third oil temperature sensor is used to obtain the third fuel oil temperature in the main oil pipeline.

[0070] The main oil pipeline is also equipped with a third flow sensor and a pressure sensor between the fuel pump and the pressure heat exchanger, which are used to obtain the third fuel flow rate and fuel pressure value in the main oil pipeline, respectively.

[0071] Please see Figure 1 The first controllable valve is controllable valve 1, the second controllable valve is controllable valve 2, the first flow sensor is flow sensor 1, the second flow sensor is flow sensor 2, the third flow sensor is flow sensor 3, the first oil temperature sensor is oil temperature sensor 1, the second oil temperature sensor is oil temperature sensor 2, and the third oil temperature sensor is oil temperature sensor 3.

[0072] The above embodiment is equipped with flow sensors, controllable valves and oil temperature sensors on the three pipelines respectively, which facilitates real-time monitoring of the heat dissipation operation of the heat dissipation system, and can promptly detect abnormalities in various structures within the system and make precise adjustments.

[0073] Please see Figure 2 and Figure 3 In some embodiments, the pressure heat exchanger includes an exchanger, an oil inlet, a first oil outlet, a second oil outlet, a collector, and multiple heat pipes; the oil inlet is connected to the main oil pipeline, the first oil outlet is connected to the delivery pipeline, and the second oil outlet is connected to the auxiliary oil pipeline; each heat pipe is welded to the collector, and the collector and the exchanger are connected by screws.

[0074] The collector is used to collect the heat from each heat pipe and transfer it to the heat exchanger.

[0075] The heat exchanger is used to exchange the heat collected by the collector with the fuel entering from the inlet.

[0076] Among them, the first oil outlet is Figure 2 The main oil outlet and the second oil outlet are... Figure 2 The secondary oil line outlet.

[0077] After the fuel in the main oil pipeline undergoes heat exchange in the exchanger, the first part of the fuel flows to the delivery pipeline through the first outlet, and the second part of the fuel flows to the auxiliary oil pipeline through the second outlet.

[0078] Specifically, please see Figure 3 The collector is used to remove heat from the generator. It can be made of copper, which has a high thermal conductivity, and is equipped with a heat pipe bent at a 90-degree angle at the bottom. The heat pipe and collector are brazed together. The other end of the heat pipe is inserted into the bottom of the winding or into the motor housing. Heat is transferred from inside the motor to the collector via the heat pipe. The collector and exchanger have matching screw holes for installation, and the gaps between them can be filled with thermally conductive materials such as silicone grease.

[0079] In practice, the number of heat pipes can be determined based on the actual number of motor slots or the motor's heat dissipation structure. The heat exchanger can also be equipped with various types and models of collectors.

[0080] Please see Figure 4 and Figure 5 In some embodiments, the exchanger includes an interconnected upper cover and a base, the base including annular heat dissipation fins and an oil baffle; the oil inlet, the first oil outlet and the second oil outlet are both located on the upper cover.

[0081] The oil stop is used to isolate the oil inlet from the first and second oil outlets.

[0082] The top cover features a hollow design and is made of lightweight aerospace-grade aluminum alloy, while the base is made of copper, which has a high thermal conductivity. The base also features annular heat dissipation fins and an oil baffle, both made of copper.

[0083] Specifically, the annular heat exchange fins have a large contact area with the fuel, resulting in high heat exchange efficiency and thus improving the heat dissipation efficiency of the high-speed generator; while the fuel baffle is to prevent short circuits in the fuel circuit (fuel flows directly from the inlet to the outlet). After entering the pressurized heat exchanger, the fuel flows along the direction of the annular heat exchange fins and undergoes heat exchange, finally flowing out from the two outlets.

[0084] The internal structure of the pressure heat exchanger described in the above embodiments can improve the efficiency of heat collection from the high-speed generator and the contact area between the fuel and the exchanger, thereby improving the system's heat dissipation efficiency.

[0085] Please see Figure 6 Another embodiment of this application provides a heat dissipation control method for an aircraft high-speed generator, applied to a heat dissipation system for an aircraft high-speed generator as described in any of the above embodiments, comprising:

[0086] Step S1: In response to the fuel supply command, start the fuel pump; the fuel supply command includes the target fuel pressure value.

[0087] Step S2: Determine whether the difference between the fuel pressure value and the target fuel pressure value is within the preset error range.

[0088] Step S3: If not, adjust the power of the fuel pump based on the target fuel pressure value.

[0089] The cooling system for high-speed aircraft generators also includes a controller, and the aforementioned control methods are executed by the controller.

[0090] The controller is connected to the high-speed generator, fuel pump, first controllable valve, second controllable valve, first flow sensor, second flow sensor, third flow sensor, first oil temperature sensor, second oil temperature sensor, third oil temperature sensor, pressure sensor and radiator respectively; the controller also has a communication module that can communicate with the engine controller (ECU), receive fuel supply commands, start the fuel pump, deliver fuel to the main fuel line and build up pressure.

[0091] The controller uses the fuel pressure value sensed by the pressure sensor as the working pressure value of the fuel pump. If the difference between the fuel pressure value and the target fuel pressure value in the fuel supply command is greater than the preset error, the PID controller controls the fuel pump to operate to adjust the pressure until the difference between the fuel pressure value and the target fuel pressure value is less than or equal to the preset error.

[0092] In some embodiments, the control method further includes:

[0093] Obtain the generator temperature of the high-speed generator.

[0094] Determine whether the generator temperature or the first fuel oil temperature is greater than the first preset threshold and continue for a preset duration.

[0095] If so, the second valve opening is obtained based on the generator temperature, the first fuel temperature, and the preset opening coefficient.

[0096] Turn on the radiator and activate the second controllable valve on the auxiliary oil pipeline based on the opening degree of the second valve.

[0097] Specifically, a temperature sensor can also be installed in the high-speed generator and connected to the controller to obtain the generator temperature; or the controller can obtain the temperature by communicating with the ECU.

[0098] The first preset threshold includes the generator temperature threshold T. gen-th and the main oil circuit temperature threshold T fuel-th If the generator temperature exceeds the preset generator temperature threshold and the duration exceeds the preset time t... th If the temperature of the first fuel exceeds the preset main fuel circuit temperature threshold and the duration exceeds the preset time t, then an abnormal temperature is determined. th This also indicates an abnormal temperature. At this point, the second controllable valve is opened, and the radiator fan is started, with auxiliary cooling provided by the secondary oil circuit. The calculation method for the second valve opening of the second controllable valve is as follows:

[0099] N = max[(T) gen ―T gen―th )×K gen ,(T fuelturbine ―T fuelturbine―th )×K fuleturbine ]×100%

[0100] Where N is the second valve opening degree of the second controllable valve, expressed as a percentage; T gen and T fuelturbine These are the generator temperature and the first fuel oil temperature, respectively. T fuelturbine―th That is, the main oil circuit temperature threshold T fuel-th K gen and K fuelturbine The preset opening degree calculation coefficient stored in the controller is determined by the system's heat dissipation capacity and experimental results.

[0101] The above embodiment can promptly determine whether the current temperature of the high-speed generator is too high by real-time detection of the generator temperature and the first fuel temperature, thereby increasing the amount of fuel returned and starting the radiator to cool the second part of the fuel returned; ensuring that the temperature of the fuel as the cooling medium can carry out sufficient heat exchange, so as to improve the heat dissipation effect in the heat exchanger.

[0102] In some embodiments, the control method further includes:

[0103] Determine whether the temperature of the third fuel is greater than the second preset threshold.

[0104] If so, the second valve opening of the second controllable valve is controlled to be 100%; otherwise, the second valve opening of the second controllable valve is calculated based on the generator temperature, the first fuel temperature, and the preset opening calculation coefficient.

[0105] The second preset threshold can be the main oil circuit temperature threshold T from the first preset threshold. fuel-th .

[0106] Specifically, when the third fuel oil temperature is greater than the second preset threshold, the fuel tank temperature is determined to be abnormal, and the second controllable valve is controlled to open to 100%. When it is lower than the second preset threshold, the opening degree of the second valve can be calculated according to the above calculation formula.

[0107] In some embodiments, the control method further includes:

[0108] If the generator temperature is detected to be greater than the first preset threshold, then determine whether the first fuel flow rate value is 0.

[0109] If so, the second valve opening of the second controllable valve is set to 100%, and the radiator is turned on.

[0110] Specifically, a first fuel flow rate of 0 indicates that the turbine engine is shut down. At this time, if the generator temperature is higher than the generator temperature threshold T... gen-th If the generator temperature is detected to be below the generator temperature threshold, the second controllable valve will be opened to 100% and the cooling fan will be turned on to ensure heat dissipation after the engine stops. If the generator temperature is detected to be below the generator temperature threshold, the second controllable valve will be closed.

[0111] Furthermore, the controller also has a fault detection function. When the fuel pump continuously maintains pressure, if it detects that the fuel pressure value drops rapidly until it falls below the pressure threshold P, it will detect the fault. th And the duration exceeds the time threshold T th If so, an alarm will be triggered via the communication module.

[0112] In some embodiments, the oil supply command further includes a target oil supply flow rate or a target controllable valve opening degree, and the control method further includes:

[0113] The first controllable valve is adjusted based on the target oil supply flow rate or the target controllable valve opening.

[0114] Specifically, when the fuel supply command provides a target fuel supply flow rate, the controller calculates the difference between the target fuel supply flow rate and the engine-side flow rate in the main fuel circuit, i.e., the first fuel flow rate value, and uses a PID controller to calculate the opening degree of the first controllable valve. When the fuel supply command provides the target controllable valve opening degree, the controller directly controls the first controllable valve to open according to the target controllable valve opening degree.

[0115] In summary, the cooling system and control method for a high-speed aircraft generator provided in this application have the following advantages:

[0116] 1. The cooling medium is fuel oil, so no additional cooling medium is needed, and the heated fuel oil has a higher combustion efficiency.

[0117] 2. The cooling circuit and fuel line are partially shared, resulting in high integration and further reducing the weight of the heat dissipation system.

[0118] 3. Using a pressure-bearing heat exchanger to maintain oil pressure effectively suppresses oil pressure fluctuations. At the same time, the fuel does not need to flow directly through the oil cooling circuit, resulting in a shorter path, lower fluid resistance, and higher heat dissipation efficiency.

[0119] 4. The fuel flow is controlled by a controllable valve, which has a fast response and high accuracy.

[0120] 5. The main and auxiliary oil circuits can be controlled separately for flow rate, resulting in higher heat dissipation efficiency.

[0121] 6. When the engine is stopped, fuel circulation and heat dissipation can be achieved through the auxiliary oil circuit.

[0122] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0123] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the invention patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.

Claims

1. A heat dissipation system for a high-speed aircraft generator, characterized in that, It includes main oil pipelines, auxiliary oil pipelines, transmission pipelines, turbine engines, high-speed generators, and pressure heat exchangers; The main oil pipeline is equipped with a fuel pump, and the auxiliary oil pipeline is equipped with a radiator; The pressure-bearing heat exchanger is connected to the oil tank via the main oil pipeline and the auxiliary oil pipeline, respectively; The pressurized heat exchanger is also connected to the turbine engine via the delivery pipeline; The pressure-bearing heat exchanger includes heat pipes and is connected to the high-speed generator via the heat pipes; The fuel pump is used to extract fuel from the fuel tank and transfer it to the pressurized heat exchanger through the main fuel pipeline. The pressurized heat exchanger is used to exchange heat between the fuel in the main oil pipeline and the high-speed generator, and to transfer the first part of the fuel after heat exchange to the turbine engine through the delivery pipeline; and to transfer the second part of the fuel after heat exchange back to the fuel tank through the auxiliary oil pipeline. The pressure-bearing heat exchanger includes an exchanger, an oil inlet, a first oil outlet, a second oil outlet, a collector, and multiple heat pipes. The oil inlet is connected to the main oil pipeline, the first oil outlet is connected to the delivery pipeline, and the second oil outlet is connected to the auxiliary oil pipeline. Each heat pipe is welded to the collector, and the collector and the exchanger are connected by screws. The collector collects heat from each heat pipe and transfers it to the exchanger. The exchanger exchanges the heat collected by the collector with the fuel oil input from the oil inlet. The auxiliary oil pipeline is further provided with a second controllable valve between the pressure heat exchanger and the radiator; the second controllable valve is used to control the flow rate of the second portion of fuel in the auxiliary oil pipeline; the auxiliary oil pipeline is further provided with a second oil temperature sensor and a second flow sensor between the second controllable valve and the radiator, respectively used to obtain the second fuel oil temperature and the second fuel flow rate value of the second portion of fuel. The exchanger includes an interconnected upper cover and a base. The base includes annular heat dissipation fins and an oil baffle. The oil inlet, the first oil outlet, and the second oil outlet are all located on the upper cover. The oil baffle is used to isolate the oil inlet from the first oil outlet and the second oil outlet. The delivery pipeline is equipped with a first controllable valve; the first controllable valve is used to control the flow rate of the first portion of fuel in the delivery pipeline; the delivery pipeline is also equipped with a first oil temperature sensor and a first flow sensor between the first controllable valve and the turbine engine, respectively used to obtain the first fuel temperature and the first fuel flow rate value of the first portion of fuel. The high-speed generator cooling system also includes a controller; the controller is used to obtain the generator temperature of the high-speed generator; if the generator temperature is detected to be greater than a first preset threshold, it determines whether the first fuel flow value is 0; if so, it controls the second valve opening of the second controllable valve to 100% and turns on the radiator.

2. The heat dissipation system for a high-speed aircraft generator according to claim 1, characterized in that, A third oil temperature sensor is installed between the fuel pump and the fuel tank in the main oil pipeline; The third oil temperature sensor is used to obtain the third fuel oil temperature in the main oil pipeline; The main oil pipeline is further equipped with a third flow sensor and a pressure sensor between the fuel pump and the pressure heat exchanger, which are used to obtain the third fuel flow rate value and fuel pressure value in the main oil pipeline, respectively.

3. A method for controlling the heat dissipation of a high-speed aircraft generator, characterized in that, The system is applied to a high-speed aircraft generator cooling system as described in any one of claims 1-2, comprising: In response to a fuel supply command, the fuel pump is activated; the fuel supply command includes a target fuel pressure value. Determine whether the difference between the fuel pressure value and the target fuel pressure value is within the preset error range; If not, the power of the fuel pump is adjusted based on the target fuel pressure value; Obtain the generator temperature of the high-speed generator; Determine whether the generator temperature or the first fuel oil temperature is greater than a first preset threshold and continue for a preset duration; If so, the second valve opening is obtained based on the generator temperature, the first fuel temperature, and a preset opening coefficient. Turn on the radiator and activate the second controllable valve on the auxiliary oil pipeline based on the opening degree of the second valve; If the generator temperature is detected to be greater than the first preset threshold, then determine whether the first fuel flow rate value is 0; If so, the second valve opening of the second controllable valve is controlled to 100%, and the radiator is turned on.

4. The heat dissipation control method for high-speed aircraft generators according to claim 3, characterized in that, Also includes: Determine whether the temperature of the third fuel is greater than the second preset threshold. If so, then control the second valve opening of the second controllable valve to 100%; Otherwise, the second valve opening of the second controllable valve is calculated based on the generator temperature, the first fuel oil temperature, and the preset opening calculation coefficient.

5. The heat dissipation control method for high-speed aircraft generators according to claim 3, characterized in that, The oil supply command also includes a target oil supply flow rate or a target controllable valve opening; the method further includes: The first controllable valve is adjusted based on the target oil supply flow rate or the target controllable valve opening.

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