Cooling device of aircraft oil-cooled motor

Abstract

The utility model provides a cooling device of an aircraft oil cooling motor, and belongs to the technical field of motor cooling. According to the utility model, the oil inlet pipeline and the oil return pipeline are respectively connected to the oil inlet and the oil outlet of the aircraft main reduction AC generator and are communicated with the oil tank, and the oil inlet pump in the oil inlet pipeline and the oil return pump in the oil return pipeline are driven by the variable frequency motor; the flow of the oil inlet pump and the flow of the oil return pump can be dynamically adjusted along with the calorific value of the aircraft main reduction alternating-current generator, heat dissipation is conducted through the radiator in the oil return pipeline, heat balance is achieved, and resource waste is avoided while the cooling effect is maintained. The pressure of cooling oil entering the aircraft main reduction alternating-current generator is adjusted through the overflow valve, variable-frequency suction of the oil inlet pump and the oil return pump is matched, the liquid level of the cooling oil in the aircraft main reduction alternating-current generator is maintained, meanwhile, the cooling oil is prevented from overflowing, flow balance is achieved, and the operation safety of an aircraft is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of motor cooling, in particular to a cooling device for an aircraft oil-cooled motor. Background Art

[0002] As a means of transportation operating in the airspace, aircraft have the advantages of high speed and not occupying ground resources. For example, airplanes, which belong to the type of aircraft, are currently the fastest public transportation tools and have become the first choice for people to travel long distances. They are widely used. Therefore, it is very necessary for the industry to improve the performance of aircraft.

[0003] As an important component of the aircraft power system, the generator can convert the mechanical energy generated by fuel combustion into the electrical energy required for the operation of the power system. Therefore, improving the performance of the generator has become a focus of industry research. At present, since a large amount of electrical energy is consumed during the operation of the aircraft, it is necessary to ensure the normal operation of the generator to ensure navigation safety. The existing aircraft main reduction AC generator is mainly cooled by oil cooling. The aircraft main reduction AC generator is equipped with an oil cooling pipeline and an oil inlet and an oil outlet connected to the oil cooling pipeline. The external oil cooling system is connected to the oil cooling pipeline of the generator through the inlet oil and the oil outlet, which quickly takes away the heat generated during the operation of the generator to ensure the continuous normal operation of the generator. Existing oil cooling pipelines are usually only equipped with a constant-flow oil pump, which realizes the supply and return of cooling oil through the oil pump. That is, although the cooling demand of the generator can be met during the cooling process, the operation of the generator is not constant power during actual use, and its temperature growth value will further increase with the extension of the running time. The oil cooling pipeline equipped with a constant-flow oil pump will have the problem of excessive cooling in the initial stage, resulting in waste of resources, and insufficient cooling will appear in the later stage, affecting the performance of the generator and further affecting the safety of the aircraft. Summary of the invention

[0004] In view of the above-mentioned problems existing in the prior art, the present invention aims to provide a cooling device for an oil-cooled motor of an aircraft, in which an oil pump with a variable frequency motor is arranged in both the oil inlet pipeline and the oil return pipeline, so that the flow rate of the oil pump can be adjusted in real time according to the heat generated by the generator, and the flow rate balance of the cooling oil in the oil inlet pipeline and the oil return pipeline can be controlled to adapt to the use requirements of the constantly changing heat generation when the generator is working, and the flow balance and thermal balance are maintained, which can not only avoid the problem of waste of resources caused by excessive cooling, but also ensure the cooling effect of the generator and ensure the safe operation of the aircraft.

[0005] The specific technical solutions are as follows:

[0006] A cooling device for an aircraft oil-cooled motor, connected to an oil inlet and an oil outlet of an aircraft main reduction alternator, has the following characteristics, including:

[0007] An oil tank, wherein cooling oil is stored;

[0008] An oil inlet pipeline is arranged between the oil tank and the oil inlet, and comprises an oil inlet pump, an oil suction filter and an oil outlet filter. The inlet and outlet of the oil inlet pump are respectively connected with the outlet of the oil suction filter and the inlet of the oil outlet filter, the inlet of the oil suction filter is connected with the oil tank, and the outlet of the oil outlet filter is connected with the oil inlet;

[0009] An oil return pipeline is arranged between the oil outlet and the oil tank, and includes an oil return pump, a radiator and an oil return filter. The inlet of the oil return pump is connected to the oil outlet, the outlet of the oil return pump is connected to the inlet of the radiator, the outlet of the radiator is connected to the inlet of the oil return filter, and the outlet of the oil return filter is connected to the oil tank;

[0010] A relief valve is arranged between the oil inlet pipeline and the oil return pipeline, and the inlet of the relief valve is connected between the outlet of the oil filter and the oil inlet, and the outlet of the relief valve is connected between the outlet of the oil return pump and the radiator; and,

[0011] The oil inlet pump and the oil return pump both include a variable frequency motor and an oil pump, and the output shaft of the variable frequency motor is dynamically connected to the pump shaft of the oil pump.

[0012] In the above-mentioned cooling device for an aircraft oil-cooled motor, the filter apertures of the oil suction filter, the oil outlet filter and the oil return filter are different, and the filter aperture of the oil suction filter is the largest, and the filter aperture of the oil outlet filter is the smallest.

[0013] In the above-mentioned cooling device for an aircraft oil-cooled motor, the radiator includes a plurality of groups of air coolers, and the plurality of groups of air coolers are arranged in series.

[0014] The above-mentioned cooling device for an aircraft oil-cooled motor also includes a temperature sensor. Temperature sensors are provided on both the oil inlet pipeline and the oil return pipeline. The temperature sensor in the oil inlet pipeline is provided at the oil inlet, and the temperature sensor in the oil return pipeline is provided at the oil outlet.

[0015] The above-mentioned cooling device for an aircraft oil-cooled motor also includes a pressure sensor. Pressure sensors are provided on both the oil inlet pipeline and the oil return pipeline. The pressure sensor in the oil inlet pipeline is provided at the oil inlet, and the pressure sensor in the oil return pipeline is provided at the oil outlet.

[0016] The above-mentioned cooling device for an aircraft oil-cooled motor further includes a flow meter, which is arranged in the oil inlet pipeline and located between the inlet of the overflow valve and the oil inlet.

[0017] The above-mentioned cooling device for an aircraft oil-cooled motor further includes a one-way valve and a shut-off valve, and the one-way valve and the shut-off valve are both provided in the oil inlet pipeline and the oil return pipeline.

[0018] The above-mentioned cooling device for an aircraft oil-cooled motor further includes a liquid level sensor and a liquid level gauge, and the liquid level sensor and the liquid level gauge are both arranged on the oil tank.

[0019] The cooling device for an aircraft oil-cooled motor mentioned above further includes an air filter, which is arranged at the air vent of the oil tank.

[0020] In the cooling device for an aircraft oil-cooled motor, an extended sampling pipeline is provided on the oil tank and communicated with the oil tank, and a sampling valve is provided on the sampling pipeline.

[0021] The positive effects of the above technical solution are:

[0022] The cooling device of the above-mentioned aircraft oil-cooled motor connects an oil inlet pipeline with an oil inlet pump and an oil return pipeline with an oil return pump to the oil inlet and oil outlet of the aircraft main reduction AC generator respectively, and the oil inlet pump and the oil return pump are both driven by a variable frequency motor, so that the flow rates in the oil inlet pump and the oil return pump can be dynamically adjusted following the heat generation of the aircraft main reduction AC generator, so that the operation of the cooling device will not cause the problem of waste of resources due to excessive flow, and can also avoid the problem of poor cooling effect due to excessive flow, thereby maintaining thermal balance. At the same time, an overflow valve is provided between the oil inlet pipeline and the oil return pipeline, and the pressure of the cooling oil entering the aircraft main reduction AC generator is limited by the overflow valve to avoid damage to the aircraft main reduction AC generator, and the flow balance with the oil inlet pump is maintained in combination with the action of the return oil pump, thereby better ensuring the operation safety of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 The present invention is a structural diagram of an embodiment of a cooling device for an aircraft oil-cooled motor according to the present invention.

[0024] In the attached figure: 1. Aircraft main reduction AC generator; 11. Oil inlet; 12. Oil outlet; 2. Fuel tank; 21. Liquid level sensor; 22. Liquid level meter; 23. Air filter; 24. Sampling pipeline; 241. Sampling valve; 3. Oil inlet pipeline; 31. Oil inlet pump; 32. Oil suction filter; 33. Oil outlet filter; 34. Flow meter; 311. Frequency conversion motor; 312. Oil pump; 4. Oil return pipeline; 41. Oil return pump; 42. Radiator; 43. Oil return filter; 5. Overflow valve; 6. Temperature sensor; 7. Pressure sensor; 8. Check valve; 9. Shut-off valve. DETAILED DESCRIPTION

[0025] In order to make the technical means, creative features, objectives and effects of the present invention easy to understand, the following embodiments are combined with the attached Figure 1 The technical solution provided by the utility model is described in detail, but the following content is not intended to limit the utility model.

[0026] Figure 1 FIG. 1 is a structural diagram of an embodiment of a cooling device for an aircraft oil-cooled motor according to the utility model. Figure 1 As shown, the cooling device of the aircraft oil-cooled motor provided in this embodiment is used for oil cooling of the aircraft main reduction AC generator 1. At this time, the cooling device of the aircraft oil-cooled motor provided in this embodiment is connected to the oil inlet 11 and the oil outlet 12 of the aircraft main reduction AC generator 1 to realize the supply and reflux of cooling oil, thereby realizing the cooling of the aircraft main reduction AC generator 1.

[0027] Specifically, the cooling device for the aircraft oil-cooled motor provided in this embodiment includes an oil tank 2 , an oil inlet pipeline 3 , an oil return pipeline 4 and a relief valve 5 .

[0028] Specifically, the oil tank 2 stores cooling oil, which can provide cooling oil for the oil inlet pipeline 3 and serve as a collection container for the cooling oil in the oil return pipeline 4, thereby meeting the recycling demand of the cooling oil.

[0029] Specifically, the oil inlet pipeline 3 is arranged between the oil tank 2 and the oil inlet 11, and the cooling oil in the oil tank 2 is inputted from the oil inlet 11 into the aircraft main reduction AC generator 1 through the oil inlet pipeline 3 to realize cooling of the aircraft main reduction AC generator 1. In addition, the oil inlet pipeline 3 also includes an oil inlet pump 31, an oil suction filter 32 and an oil outlet filter 33, and the inlet and outlet of the oil inlet pump 31 are respectively connected with the outlet of the oil suction filter 32 and the inlet of the oil outlet filter 33, so that the cooling oil extracted by the oil inlet pump 31 can be first filtered through the oil suction filter 32 to avoid the impurities that may be contained in the cooling oil from interfering with or damaging the oil inlet pump 31, and the cooling oil extracted by the oil inlet pump 31 is filtered again through the oil outlet filter 33 before entering the oil inlet 11 of the aircraft main reduction AC generator 1, and the impurities entering the aircraft main reduction AC generator 1 are further reduced through multi-layer filtration, so as to realize the protection of the aircraft main reduction AC generator 1 and ensure its normal operation. In addition, the inlet of the oil suction filter 32 is connected to the oil tank 2, and the outlet of the oil outlet filter 33 is connected to the oil inlet 11, that is, when the oil inlet pump 31 draws cooling oil from the oil tank 2, it needs to be filtered through the oil suction filter 32, and the cooling oil discharged by the oil inlet pump 31 needs to be filtered again through the oil outlet filter 33 before entering the aircraft main reduction AC generator 1 through the oil inlet 11, ensuring that the impurity content in the cooling oil entering the aircraft main reduction AC generator 1 meets the use requirements, thereby extending the service life of the aircraft main reduction AC generator 1.

[0030] Specifically, the oil return line 4 is arranged between the oil outlet 12 and the oil tank 2, that is, the cooling oil flowing out of the oil outlet 12 of the aircraft main reduction AC generator 1 will return to the oil tank 2 through the oil return line, so as to realize the recycling of the cooling oil. In addition, the oil return line 4 also includes an oil return pump 41, a radiator 42 and an oil return filter 43. At this time, the inlet of the oil return pump 41 is connected with the oil outlet 12, that is, the cooling oil in the aircraft main reduction AC generator 1 is extracted through the oil return pump 41, so as to ensure that the cooling oil can flow normally in the aircraft main reduction AC generator 1, and take away the heat generated during the operation of the aircraft main reduction AC generator 1 through heat exchange, and at the same time, the oil return line 4 has a suction capacity, which can not only ensure the liquid level of the cooling oil, but also prevent the cooling oil from overflowing from the aircraft main reduction AC generator 1, that is, the safety is improved while ensuring the cooling effect. Furthermore, the outlet of the return oil pump 41 is connected to the inlet of the radiator 42, so that the cooling oil extracted from the oil outlet 12 of the aircraft main reduction AC generator 1 by the return oil pump 41 needs to be cooled by the radiator 42 when returning to the oil tank 2, so that the temperature of the cooling oil with a higher temperature is reduced, which provides conditions for the subsequent heat exchange with the aircraft main reduction AC generator 1 as cooling oil with a lower temperature. In addition, the outlet of the radiator 42 is connected to the inlet of the return oil filter 43, and the outlet of the return oil filter 43 is connected to the oil tank 2, so that the cooling oil with a lower temperature flowing out of the radiator 42 will first be filtered by the return oil filter 43, and then the cooling oil filtered by the return oil filter 43 will be returned to the oil tank 2, that is, the impurities that may be generated by the cooling oil during the circulation process are filtered out by the return oil filter 43, ensuring that the cooling oil returned to the oil tank 2 can remain relatively clean, and the structural design is more reasonable.

[0031] Specifically, an overflow valve 5 is further provided between the oil inlet pipeline 3 and the oil return pipeline 4. At this time, the inlet of the overflow valve 5 is connected between the outlet of the oil outlet filter 33 and the oil inlet 11, and at the same time, the outlet of the overflow valve 5 is connected between the outlet of the return oil pump 41 and the radiator 42, so that when the amount of cooling oil extracted by the oil inlet pump 31 is too large and the pressure at the oil inlet 11 increases, the overflow valve 5 can be opened appropriately. By opening the overflow valve 5, part of the cooling oil extracted by the oil inlet pump 31 can flow directly into the oil return pipeline 4 through the pipeline where the overflow valve 5 is located, thereby reducing the pressure at the oil inlet 11, realizing the pressure regulation of the cooling oil entering the aircraft main reduction AC generator 1, avoiding the problem of excessive pressure affecting the aircraft main reduction AC generator 1, and having higher safety assurance. At the same time, the outlet of the overflow valve 5 is connected between the outlet of the return oil pump 41 and the radiator 42, so that the cooling oil passing through the overflow valve 5 will not affect the operation of the return oil pump 41, that is, the double unblocking of the return oil pump 41 and the overflow valve 5 is achieved to maintain the flow rate consistent with the oil feed pump 31, that is, the flow balance during the oil feed and oil return process is achieved.

[0032] More specifically, the oil inlet pump 31 and the oil return pump 41 both include a variable frequency motor 311 and an oil pump 312. At this time, the output shaft of the variable frequency motor 311 is dynamically connected to the pump shaft of the oil pump 312, so that the operation of the oil inlet pump 31 and the oil return pump 41 are both frequency-controlled, so that the flow rates in the oil inlet pump 31 and the oil return pump 41 can be dynamically adjusted following the heat generation of the aircraft's main reduction AC generator 1, so that the operation of the cooling device will not cause a problem of waste of resources due to excessive flow, and can also avoid the problem of poor cooling effect due to too small flow, thereby maintaining thermal balance.

[0033] More specifically, the filter apertures of the oil suction filter 32, the oil outlet filter 33, and the oil return filter 43 are different, which can achieve graded filtration of impurities of different particle sizes, avoid the problem of low filtration efficiency caused by unified filtration, improve filtration efficiency, and ensure filtration effect. Preferably, the filter aperture of the oil suction filter 32 is set to the largest, and the filter aperture of the oil outlet filter 33 is set to the smallest, which can not only maintain the normal operation of the oil inlet pump 31, but also reduce the amount of impurities entering the aircraft main reduction AC generator 1, ensure the normal operation of the aircraft main reduction AC generator 1, and ensure that the impurities in the cooling oil flowing back to the oil tank 2 can also be further removed.

[0034] More specifically, the radiator 42 includes several groups of air coolers, that is, the radiator 42 is a structure in which multiple air coolers work together. At this time, several groups of air coolers are arranged in series, so that when the cooling oil with a higher temperature passes through the radiator 42 again, it will pass through multiple groups of air coolers for multi-stage heat exchange, which has a better cooling effect on the cooling oil. At the same time, the air cooler can make full use of air flow for heat exchange, which is not only simple in structure and easy to use, but also unaffected by the environment, can adapt to the aircraft operating environment, and has a more reasonable structural arrangement. It is worth pointing out that the motor of the air cooler also adopts a variable frequency motor 311, so that the operation of the air cooler can also be adjusted in real time according to the actual operating conditions of the aircraft main reduction AC generator 1, so that the total heat generated by the cooling device of the aircraft oil-cooled motor disclosed in this embodiment and the cooled aircraft main reduction AC generator 1 can be balanced with the heat dissipation of the radiator 42, maintaining thermal balance, and avoiding waste of resources while ensuring the heat dissipation effect, and the structural design is more reasonable.

[0035] More specifically, both the oil inlet line 3 and the oil return line 4 are provided with a temperature sensor 6. At this time, the temperature sensor 6 in the oil inlet line 3 is arranged near the oil inlet 11, which can effectively monitor the temperature of the cooling oil entering the aircraft main reduction AC generator 1, and ensure that the temperature of the cooling oil entering the aircraft main reduction AC generator 1 meets the use requirements. At the same time, the temperature sensor 6 in the oil return line 4 is arranged near the oil outlet 12 to monitor the temperature of the cooling oil flowing out of the aircraft main reduction AC generator 1, which facilitates the monitoring personnel to intuitively obtain the information on the cooling effect of the aircraft main reduction AC generator 1, and at the same time, it also provides data support for the subsequent frequency conversion control of the oil inlet pump 31, the oil return pump 41 and the air cooler.

[0036] More specifically, pressure sensors 7 are also provided on both the oil inlet line 3 and the oil return line 4, and the pressure sensor 7 in the oil inlet line 3 is provided near the oil inlet 11, which can effectively monitor the pressure of the cooling oil entering the aircraft main reduction AC generator 1, and ensure the safe operation of the aircraft main reduction AC generator 1. At the same time, the pressure sensor 7 in the oil return line 4 is provided near the oil outlet 12, which can effectively detect the pressure of the cooling oil extracted from the aircraft main reduction AC generator 1, thereby obtaining the flow of the cooling oil in the aircraft main reduction AC generator 1, judging whether the cooling process is smooth, and also providing conditions for the subsequent suction adjustment of the oil return pump 41 to maintain the liquid level of the cooling oil and prevent the cooling oil from overflowing, with higher safety assurance.

[0037] More specifically, a flow meter 34 is also provided in the oil inlet pipeline 3. At this time, the flow meter 34 is located between the inlet of the relief valve 5 and the oil inlet 11. The flow meter 34 can monitor the flow of the cooling oil flowing into the aircraft main reduction AC generator 1 in real time, which provides data reference for the monitoring personnel to adjust the relief valve 5, provides data support for achieving flow balance in the whole system, and the structural design is more reasonable.

[0038] More specifically, a one-way valve 8 and a shutoff valve 9 are provided in the oil inlet pipeline 3, and the one-way valve 8 prevents the cooling oil from flowing back, and the shutoff valve 9 controls the on-off of the oil inlet pipeline 3, so that it is convenient to disassemble and assemble the corresponding pipeline after the cut-off, ensuring that the pipeline disassembly and assembly process is not affected by the cooling oil in the pipeline, and the pipeline disassembly and assembly is more convenient. Similarly, a one-way valve 8 and a shutoff valve 9 are also provided in the oil return pipeline 4, and the one-way valve 8 prevents the cooling oil from flowing back, and the shutoff valve 9 controls the on-off of the oil return pipeline 4, and it is also convenient to disassemble and assemble the corresponding pipeline after the cut-off, ensuring that the pipeline disassembly and assembly process is not affected by the cooling oil in the pipeline, and the pipeline disassembly and assembly is more convenient.

[0039] More specifically, the oil tank 2 is also provided with a liquid level sensor 21 and a liquid level gauge 22. Both the liquid level sensor 21 and the liquid level gauge 22 are arranged on the oil tank 2. The storage amount of the cooling oil in the oil tank 2 is effectively monitored by the liquid level sensor 21 and the liquid level gauge 22, thereby providing monitoring conditions for ensuring the normal operation of the cooling circuit and providing higher safety assurance.

[0040] More specifically, the air filter 23 is disposed at the air vent of the oil tank 2. The air in and out of the oil tank 2 is filtered by the air filter 23, thereby preventing impurities in the air from entering the oil tank 2 and contaminating the cooling oil. The structural design is more reasonable.

[0041] More specifically, an extended sampling line 24 is provided in the middle of the oil tank 2. At this time, the sampling line 24 is connected to the oil tank 2, and a sampling valve 241 is provided on the sampling line 24. The sampling valve 241 is a shut-off valve, so that subsequent monitoring personnel can sample and detect the cooling oil in the oil tank 2 through the sampling line 24, which is more convenient to operate. At the same time, the sampling valve 241 is used to control the on-off of the sampling line 24, which is more convenient to control and also facilitates the disassembly and assembly of the sampling line. In addition, the sampling line provided in the middle of the oil tank can facilitate the sampling of the cooling oil in the middle of the oil tank, and the sampled cooling oil sample is more representative, avoiding the problem of inaccurate cooling oil samples collected due to the sampling position being too high or too low.

[0042] As a preferred embodiment, structures such as the temperature sensor 6, the pressure sensor 7, the flow meter 34, the liquid level sensor 21 and the liquid level meter 22 can be connected to external expansion equipment, providing conditions for realizing functions such as data printing and data storage.

[0043] The cooling device of the aircraft oil-cooled motor provided in this embodiment includes an oil tank 2, an oil inlet pipeline 3, an oil return pipeline 4 and a relief valve 5; the oil inlet pipeline 3 and the oil return pipeline 4 are respectively connected to the oil inlet port 11 and the oil outlet port 12 of the aircraft main reduction AC generator 1, and the oil inlet pipeline 3 and the oil return pipeline 4 are both connected to the oil tank 2, and the oil inlet pump 31 in the oil inlet pipeline 3 and the oil return pump 41 in the oil return pipeline 4 are both driven by the variable frequency motor 311, so that the flow rates of the oil inlet pump 31 and the oil return pump 41 can be dynamically adjusted according to the heat generation of the aircraft main reduction AC generator 1. The heat is dissipated through the radiator 42 in the return oil pipeline 4 to achieve thermal balance, thereby maintaining the cooling effect and avoiding waste of resources. In addition, the overflow valve 5 is arranged between the oil inlet pipeline 3 and the return oil pipeline 4. The pressure of the cooling oil entering the aircraft main reduction AC generator 1 is controlled by adjusting the overflow valve 5. In conjunction with the variable frequency suction of the oil inlet pump 31 and the return oil pump 41, the liquid level of the cooling oil in the aircraft main reduction AC generator 1 can be maintained to ensure the cooling effect, and the cooling oil can be prevented from overflowing, thereby maintaining the flow balance and better ensuring the safe operation of the aircraft.

[0044] The above are only preferred embodiments of the present invention, and do not limit the implementation mode and protection scope of the present invention. Those skilled in the art should be aware that all solutions obtained by equivalent substitutions and obvious changes made using the description and illustrations of the present invention should be included in the protection scope of the present invention.

Claims

1. A cooling device for an aircraft oil-cooled motor, connected to the oil inlet and oil outlet of an aircraft main reduction alternator, characterized in that: include: an oil tank, wherein cooling oil is stored in the oil tank; An oil inlet pipeline, the oil inlet pipeline is arranged between the oil tank and the oil inlet, the oil inlet pipeline comprises an oil inlet pump, an oil suction filter and an oil outlet filter, the inlet and outlet of the oil inlet pump are respectively connected with the outlet of the oil suction filter and the inlet of the oil outlet filter, the inlet of the oil suction filter is connected with the oil tank, and the outlet of the oil outlet filter is connected with the oil inlet; An oil return pipeline, the oil return pipeline is arranged between the oil outlet and the oil tank, the oil return pipeline comprises an oil return pump, a radiator and an oil return filter, the inlet of the oil return pump is communicated with the oil outlet, the outlet of the oil return pump is communicated with the inlet of the radiator, the outlet of the radiator is communicated with the inlet of the oil return filter, and the outlet of the oil return filter is communicated with the oil tank; A relief valve, wherein the relief valve is disposed between the oil inlet pipeline and the oil return pipeline, and the inlet of the relief valve is connected between the outlet of the oil outlet filter and the oil inlet, and the outlet of the relief valve is connected between the outlet of the oil return pump and the radiator; and, The oil feed pump and the oil return pump both include a variable frequency motor and an oil pump, and the output shaft of the variable frequency motor is dynamically connected to the pump shaft of the oil pump.

2. The cooling device for an aircraft oil-cooled motor according to claim 1, characterized in that: The filter apertures of the oil suction filter, the oil outlet filter and the oil return filter are different, and the filter aperture of the oil suction filter is the largest, and the filter aperture of the oil outlet filter is the smallest.

3. The cooling device for an aircraft oil-cooled motor according to claim 1, characterized in that: The radiator includes a plurality of groups of air coolers, and the plurality of groups of air coolers are arranged in series.

4. The cooling device for an aircraft oil-cooled motor according to claim 3, characterized in that: It also includes a temperature sensor. The oil inlet pipeline and the oil return pipeline are both provided with temperature sensors. Moreover, the temperature sensor in the oil inlet pipeline is provided at the oil inlet, and the temperature sensor in the oil return pipeline is provided at the oil outlet.

5. The cooling device for an aircraft oil-cooled motor according to claim 1, characterized in that: It also includes a pressure sensor, which is disposed on both the oil inlet pipeline and the oil return pipeline. The pressure sensor in the oil inlet pipeline is disposed at the oil inlet, and the pressure sensor in the oil return pipeline is disposed at the oil outlet.

6. The cooling device for an aircraft oil-cooled motor according to claim 1, characterized in that: It also includes a flow meter, which is arranged in the oil inlet pipeline and located between the inlet of the overflow valve and the oil inlet.

7. The cooling device for an aircraft oil-cooled motor according to claim 1, characterized in that: It also includes a one-way valve and a cut-off valve, and the one-way valve and the cut-off valve are both arranged in the oil inlet pipeline and the oil return pipeline.

8. The cooling device for an aircraft oil-cooled motor according to claim 1, characterized in that: It also includes a liquid level sensor and a liquid level meter, and the liquid level sensor and the liquid level meter are both arranged on the oil tank.

9. The cooling device for an aircraft oil-cooled motor according to claim 1, characterized in that: It also includes an air filter, which is arranged at the air vent of the oil tank.

10. The cooling device for an aircraft oil-cooled motor according to claim 1, characterized in that: The oil tank is provided with a sampling pipeline extending therefrom and communicating with the oil tank, and a sampling valve is provided on the sampling pipeline.

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