Aircraft

Abstract

The utility model provides an aircraft, and relates to the technical field of aircrafts. The aircraft comprises a nacelle, the nacelle is provided with a first cavity, the first cavity is provided with a first opening and a second opening, and the first opening and the second opening communicate with the interior and the exterior of the first cavity; the electric engine comprises a power motor, a radiator and a fan, the radiator is used for dissipating heat of the power motor, the power motor and the nacelle are arranged at intervals, and the radiator is provided with an air duct communicating with the interior of the first cavity through the first opening; the fan is used for sucking air entering the first cavity from the second opening into the air duct and blowing the air to the side, facing the fan, of the power motor. Therefore, the internal temperature of the power motor can be controlled within an allowable range, and the working performance of the power motor is ensured.

Description

Technical Field

[0001] The present application relates to the field of aircraft technology, and in particular to an aircraft. Background Art

[0002] An electric vertical take-off and landing (eVTOL) vehicle includes an electric propulsion system, which includes a propeller and an electric motor. The electric motor includes a power motor, which is connected to the propeller and drives the propeller. During operation, the power motor generates heat that accumulates over time, gradually increasing its internal temperature and reducing its performance. Utility Model Content

[0003] The present application aims to provide an aircraft that can control the internal temperature of a power motor within an allowable range to ensure the working performance of the power motor.

[0004] An embodiment of the present application provides an aircraft, comprising:

[0005] The nacelle has a first cavity, the first cavity has a first opening and a second opening, and the first opening and the second opening both communicate with the interior and the exterior of the first cavity;

[0006] An electric engine includes a power motor, a radiator and a fan. The radiator is used to dissipate heat from the power motor. The power motor is arranged at intervals from the nacelle. The radiator has an air duct connected to the interior of the first cavity through a first opening. The fan is used to suck air entering the first cavity from the second opening into the air duct and blow it to the side of the power motor facing the fan.

[0007] The heat generated during the operation of the power motor is transferred to the radiator, preventing heat from continuously accumulating inside the power motor, controlling the temperature inside the power motor within an allowable range, and ensuring the operating performance of the power motor. The fan blows air from the first cavity toward the air duct of the radiator. The radiator and the air exchange heat, transferring the heat to the air. The air then removes the heat from the radiator, cooling the radiator and ensuring that the heat generated by the power motor is continuously transferred to the radiator.

[0008] Air outside the nacelle enters the first cavity through the second opening. Driven by the fan, the air inside the first cavity enters the air duct to cool the radiator, removing heat from the radiator and ensuring that the radiator effectively dissipates heat for the power motor. Furthermore, the lower temperature of the air outside the nacelle effectively dissipates heat from the radiator, helping to improve the radiator's heat dissipation capacity.

[0009] In some possible implementations, the first cavity includes a plurality of opening groups, the plurality of opening groups are arranged at intervals along the axial direction of the fan, and each opening group includes a plurality of second openings arranged at intervals along the circumferential direction of the fan.

[0010] In some possible implementations, the nacelle further has a second cavity separated from the first cavity, the second cavity has a communication opening, and the communication opening connects the interior and the exterior of the second cavity.

[0011] In some possible implementations, the nacelle further has a second cavity, and the nacelle includes a partition member, which separates the first cavity from the second cavity, and the distance between a side of the partition member close to the radiator and the radiator gradually decreases in a direction from the outside of the nacelle to the inside;

[0012] At least one second opening is adjacent to the partition member.

[0013] In some possible implementations, the power motor is located outside the nacelle and is arranged side by side with the nacelle along the axial direction of the fan.

[0014] In some possible implementations, the nacelle further includes a third cavity, the third cavity being located on a side of the first cavity facing the power motor, the first opening communicating with the first cavity and the third cavity, the third cavity having a third opening communicating with the interior and exterior of the third cavity, and at least a portion of a rotor of the power motor being located within the third cavity through the third opening;

[0015] The fan is used to draw the air in the first cavity into the third cavity through the air channel.

[0016] In some possible implementations, the rotor and the inner wall of the third cavity form an exhaust channel, and the exhaust channel is used to discharge the air in the third cavity to the outside of the third cavity; and / or,

[0017] The third cavity further has a fourth opening, which is located between the third opening and the first cavity. The fourth opening is used to discharge the air in the third cavity to the outside of the third cavity.

[0018] In some possible implementations, the fan has an air inlet side and an air outlet side along its axial direction, the power motor is located on the air outlet side of the fan, and the radiator is located on the air inlet side of the fan; the electric engine further includes: a wind shielding structure, the wind shielding structure being disposed around the outer periphery of the fan, and the wind shielding structure, the radiator, and the fan forming an air inlet channel, the air inlet channel being in communication with an air duct of the radiator;

[0019] The fan is used to suck the air in the first cavity through the air duct and the air inlet channel and blow it out from the air outlet side to the side of the power motor facing the fan.

[0020] In some possible implementations, the wind shielding structure and the heat sink are located inside the first cavity through the first opening; a portion of the fan blades is located inside the first cavity, and another portion of the fan blades is located outside the first cavity.

[0021] In some possible implementations, the power motor is located outside the nacelle and arranged side by side with the nacelle along the axial direction of the fan;

[0022] Along the axial direction of the fan, the minimum distance between the nacelle and the power motor is greater than the maximum distance between the fan blades and the power motor.

[0023] In some possible implementations, along the axial direction of the fan, the radiator is located below the fan, and the power motor is located above the fan;

[0024] A first air outlet channel is formed between the fan and the power motor.

[0025] In some possible implementations, along the axial direction of the fan, part of the outer peripheral side of the fan is located in the space surrounded by the wind protection structure, and part of the outer peripheral side of the fan is located outside the wind protection structure, so that part of the outer peripheral side of the fan forms a second air outlet channel.

[0026] In some possible implementations, the fan includes blades, and along the axial direction of the fan, part of the outer peripheral side of the blades is located within the space enclosed by the wind shielding structure, and part of the outer peripheral side of the blades is located outside the wind shielding structure;

[0027] The height of the fan blade within the wind protection structure is greater than or equal to a first height and less than or equal to a second height. The first height is one-third of the maximum height of the fan blade along the axial direction of the fan, and the second height is two-thirds of the maximum height of the fan blade along the axial direction of the fan.

[0028] In some possible implementations, the power motor has a liquid cooling channel, the outlet of the liquid cooling channel is connected to the inlet of the radiator, and the outlet of the radiator is connected to the inlet of the liquid cooling channel, and the liquid cooling channel and the radiator are used to form a cooling medium circuit;

[0029] The electric engine also includes: a liquid pump, which is fixed to the housing of the power motor, the outlet end of the liquid pump is connected to the inlet end of the liquid cooling channel, the inlet end of the liquid pump is connected to the outlet end of the radiator, and the liquid pump is used to make the cooling medium flow in the cooling medium circuit.

[0030] In some possible implementations, the electric engine further includes a drive motor, which is drivingly connected to the fan, and the drive motor serves as a pump motor of the liquid pump, and is also used to drive the fan to rotate; or,

[0031] The electric engine also includes a drive motor and a liquid pump motor. The drive motor is connected to the fan transmission. The drive motor is also used to drive the fan to rotate. The liquid pump motor serves as a pump motor for the liquid pump.

[0032] In some possible implementations, the aircraft further includes a propeller, which is disposed on a side of the power motor away from the radiator and is transmission-connected to the power motor, and the power motor is used to drive the propeller to rotate;

[0033] The radiator and fan are located on the side of the power motor away from the propeller. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, a brief introduction will be given below to the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative labor.

[0035] Figure 1 A schematic diagram of the three-dimensional structure of an aircraft provided in an embodiment of the present application;

[0036] Figure 2 A schematic diagram of the architecture of an electric propulsion device provided in an embodiment of the present application;

[0037] Figure 3 A schematic top view of a radiator provided in an embodiment of the present application;

[0038] Figure 4 A schematic front view of an electric engine provided in an embodiment of the present application;

[0039] Figure 5 for Figure 4 A schematic diagram of the electric motor architecture is shown;

[0040] Figure 6 for Figure 4 A schematic diagram of the three-dimensional structure of the fan and the wind protection structure;

[0041] Figure 7 for Figure 4 A front view schematic diagram of the cooperation between the fan and the wind protection structure;

[0042] Figure 8 for Figure 4 Schematic diagram of the three-dimensional structure of the fan;

[0043] Figure 9 for Figure 8 A schematic front view of the fan shown;

[0044] Figure 10 for Figure 4 The schematic diagram of the structure of the electric engine and the nacelle shown;

[0045] Figure 11 for Figure 10 Schematic diagram of the internal structure of the nacelle;

[0046] Figure 12 A schematic structural diagram of another nacelle provided in an embodiment of the present application;

[0047] Figure 13 for Figure 10 A schematic diagram of the electric engine and the nacelle shown;

[0048] Figure 14 A schematic structural diagram of another nacelle and electric engine provided in an embodiment of the present application.

[0049] Description of reference numerals:

[0050] 11. Fuselage; 12. Wings; 13. Tail; 14. Arms;

[0051] 15. Nacelle; 151. First cavity; 152. Second cavity; 153. Partitioning member; 154. First opening; 155. Second opening; 156. Connecting opening; 157. Third cavity; 158. Third opening; 159. Fourth opening; 160. Annular partition;

[0052] 20. Electric propulsion device; 20a. Fixed electric propulsion device; 20b. Tilting electric propulsion device; 21. Electric engine; 22. Propeller;

[0053] 100, power motor; 110, stator; 111, stator bracket; 112, stator winding; 120, rotor; 121, rotor housing; 122, magnet;

[0054] 200, radiator; 210, air duct;

[0055] 300, fan; 310, fan blade; 320, hub;

[0056] 400, wind protection structure; 410, wind protection ring;

[0057] 500, drive motor;

[0058] 600, liquid supply pipe; 700, liquid return pipe; 800, motor controller. DETAILED DESCRIPTION

[0059] To make the purpose, technical solutions, and advantages of the embodiments of this application more clear, the technical solutions in the embodiments of this application will be clearly and completely described below in conjunction with the drawings in the embodiments of this application. Obviously, the described embodiments are part of the embodiments of this application, not all of the embodiments. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this application.

[0060] It should be noted that the terms "first" and "second" are used for descriptive purposes only and should not be understood to indicate or imply relative importance or implicitly specify the number of the technical features indicated. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include at least one of such features. In the description of this application, "plurality" means at least two, for example, two, three, etc., unless otherwise specifically defined.

[0061] In this application, unless otherwise specified or limited, the terms "mounted," "connected," and "fixed" should be understood broadly. For example, they can refer to fixed connections, detachable connections, or integration; direct connections, indirect connections through an intermediate medium, or internal connections between two components or interactions between two components, unless otherwise specified. Those skilled in the art will understand the specific meanings of these terms in this application based on the specific circumstances.

[0062] In this application, unless otherwise expressly specified or limited, when a first feature is "above" or "below" a second feature, it may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Furthermore, when a first feature is "above," "above," or "above" a second feature, it may mean that the first feature is directly above or diagonally above the second feature, or simply means that the first feature is at a higher level than the second feature. When a first feature is "below," "below," or "below" a second feature, it may mean that the first feature is directly below or diagonally below the second feature, or simply means that the first feature is at a lower level than the second feature.

[0063] In the above description, the reference terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine different embodiments or examples described in this specification and features of different embodiments or examples without contradiction.

[0064] At present, when an aircraft is in operation, the power motor generates a large amount of heat. In related technologies, a radiator is used to dissipate heat from the motor. For example, the heat generated by the power motor flows into the radiator, and then the heat of the radiator is taken away by the flow of external air, forming a cooling effect. However, when the radiator uses external air flow to dissipate heat, the heat dissipation efficiency is low.

[0065] For this purpose, a fan is often set up to blow air to the radiator to achieve the purpose of dissipating heat from the radiator. Among them, when the fan and the radiator are arranged, the fan is arranged above the radiator, and the fan blows air downward to dissipate heat from the radiator. In the related field, in order to improve the heat dissipation performance of the radiator, the volume of the radiator and the fan is increased or the distance between the power motor and the fan is increased. However, the increase in the volume of the radiator and the fan and the increase in the distance between the power motor and the fan often lead to an increase in the volume of the equipment, but the electric engine of the aircraft is relatively small, and the space for arranging the radiator and the fan is often small. It is impossible to arrange the large-volume radiator and fan in the related field, and it is impossible to increase the distance between the power motor and the fan.

[0066] It is understandable that many high-power, heat-generating motion devices, such as the drive motors of new energy vehicles and the engines of fuel vehicles, generate a lot of heat during operation, so they are usually equipped with a cooling system (radiator and fan). The airflow generated by the fan blows through the radiator, thereby taking away the heat generated by the motion devices. For motors and engines such as automobiles, the heat dissipation is relatively spacious because of the structural layout and there are no rigid quality requirements. Therefore, in order to meet the heat dissipation requirements, there will not be too much research and development on the size of the radiator and the fan, and usually the front end of the radiator will not be very tight and have too much obstruction. In order to meet the weight and layout space requirements, the current electric vertical take-off and landing aircraft usually require the design of products to be small and precise, and to ensure the achievement of performance. In this way, the air inlet of the radiator will be blocked by the motor and pump. This type of layout will inevitably cause new problems that do not occur in other industries, such as uneven distribution of the air intake, which can seriously cause a large amount of heat backflow in the middle area of ​​the radiator.

[0067] Therefore, in electric vertical take-off and landing aircraft, due to space and weight requirements, the volume of the radiator and fan cannot be increased, and the distance between the power motor and the fan cannot be increased, resulting in poor heat dissipation performance of the radiator.

[0068] In response to the above technical problems, an embodiment of the present application provides an aircraft in which, without increasing the volume of the radiator and fan or the distance between the power motor and the fan to improve the heat dissipation effect, a fan is arranged above the radiator. The fan can draw air from the nacelle below the radiator into the interior of the radiator and discharge it from above the radiator, forming an airflow path with downward inlet and upward outlet. Because the bottom of the radiator is not blocked, air can enter all areas of the radiator, and the air intake volume meets the requirements, thereby improving the heat dissipation performance of the radiator. In addition, the downward inlet and upward outlet airflow path can reduce the axial distance between the fan and the power motor, thereby reducing the axial length of the electric motor, thereby reducing the volume of the electric motor and facilitating the layout of the electric motor.

[0069] The aircraft provided in the embodiments of the present application may be an electric vertical take-off and landing (eVTOL) aircraft, or other types of aircraft.

[0070] Figure 1 This is a schematic diagram of the three-dimensional structure of an aircraft provided in an embodiment of the present application. Figure 1 The aircraft shown is for illustration only and does not constitute a limitation to the specific structure and shape of the aircraft.

[0071] like Figure 1 As shown, the aircraft includes a fuselage 11, wings 12, and a tail 13. The fuselage 11 is a symmetrical structure, and the remaining structure and shape of the fuselage 11 are not limited and can refer to the fuselage structure of existing aircraft. The wings 12 are fixedly connected to the fuselage 10. The structure of the wings 12 can also refer to the fixed wing structure of existing aircraft and will not be described in detail here. The tail 13 is provided at the tail of the fuselage 11. The tail 13 is integrally formed with the fuselage 11 or mechanically connected and has a symmetrical structure. The structure of the tail 13 can also refer to the tail structure of existing aircraft and will not be described in detail here.

[0072] It should be noted that, in some scenarios, the aircraft may also include a fuselage 11 and wings 12 , that is, the aircraft does not include a tail 13 .

[0073] like Figure 1 As shown, the aircraft further includes an electric propulsion device 20, which can be used to provide power for the aircraft. The number of the electric propulsion device 20 is one or more electric propulsion devices 20, for example Figure 1 As shown, the aircraft includes eight electric propulsion devices 20 .

[0074] The electric propulsion device 20 is arranged on the fuselage 11 and / or the wings 12 and / or the tail 13, for example Figure 1As shown, electric propulsion devices 20 are symmetrically provided on the wings 12 and the tail 13. Of course, in some scenarios, the electric propulsion devices 20 are provided on the fuselage 11, while the wings 12 and tail 13 are not provided with electric propulsion devices 20. In other scenarios, the electric propulsion devices 20 are provided on the wings 12, while the fuselage 11 and tail 13 are not provided with electric propulsion devices 20. In still other scenarios, the electric propulsion devices 20 are provided on the tail 13, while the fuselage 11 and wings 12 are not provided with electric propulsion devices 20.

[0075] Continue to see Figure 1 As shown, the aircraft further includes an arm 14 and a nacelle 15, both of which are fixedly connected to the electric propulsion device 20, so that the electric propulsion device 20 is disposed on the fuselage 11, the wing 12, or the tail 13. Of course, in some scenarios, the aircraft may also include either the arm 14 or the nacelle 15.

[0076] In some embodiments, as Figure 1 As shown, the electric propulsion device 20 is disposed on the wing 12 via the arm 14. In other embodiments, the electric propulsion device 20 may also be disposed on the wing 12 via a nacelle 15 (not shown in the figure).

[0077] In some embodiments, as Figure 1 As shown, the electric propulsion device 20 is disposed on the tail 13 via the nacelle 15. In other embodiments, the electric propulsion device 20 may also be disposed on the tail 13 via the machine arm 14 (not shown in the figure).

[0078] In some examples, the electric propulsion device 20 provided on the aircraft may include a fixed electric propulsion device 20 a (eg, a fixed rotor), which is fixedly connected to any one of the fuselage 11 , the wings 12 , and the tail 13 .

[0079] In some examples, the electric propulsion device 20 provided on the aircraft may include a tilting electric propulsion device 20b (e.g., a tilting rotor), and a tilting mechanism is provided between the tilting electric propulsion device 20b and any one of the fuselage 11, wings 12, and tail 13, and the tilting mechanism is used to adjust the tilt angle of the tilting electric propulsion device 20b.

[0080] In some examples, all electric propulsion devices 20 provided on the aircraft are fixed electric propulsion devices 20 a.

[0081] In other examples, all electric propulsion devices 20 provided on the aircraft are tilting electric propulsion devices 20b.

[0082] In some other examples, some of the electric propulsion devices 20 provided on the aircraft are fixed electric propulsion devices 20a, and some of the electric propulsion devices 20 are tilting electric propulsion devices 20b, for example. Figure 1As shown, four of the electric propulsion devices 20 are fixed electric propulsion devices 20a, and the remaining four electric propulsion devices 20 are tilting electric propulsion devices 20b. The fixed electric propulsion devices 20a are arranged on the outside of the tilting electric propulsion devices 20b.

[0083] In this embodiment, the electric propulsion device 20 is composed of a power battery (not shown), an electric motor 21, a propeller 22, and their accessories. The electric motor 21 is a system consisting of a power motor 100, a motor controller 800, cables, and their accessories, which converts electrical energy into mechanical energy. In actual implementation, the electric motor 21 can also be referred to as an electric propulsion system.

[0084] Among them, such as Figure 1 As shown, the electric engine 21 is arranged on the arm 14 or the nacelle 15, and the propeller 22 is arranged on one side of the electric engine 21. The electric engine 21 is transmission-connected to the propeller 22, and the electric engine 21 is used to drive the propeller 22 to rotate.

[0085] Figure 2 A schematic diagram of the architecture of an electric propulsion device provided in an embodiment of the present application.

[0086] like Figure 2 As shown, the electric engine 21 includes a power motor 100 and a motor controller 800. The power motor 100 is transmission-connected to the propeller 22. The motor controller 800 is located inside the power motor 100. The motor controller 800 is electrically connected to the power motor 100. The motor controller 800 is used to control the power motor 100 to drive the propeller 22 to rotate.

[0087] like Figure 2 As shown, the power motor 100 includes a rotor 120 and a stator 110. The rotor 120 includes a rotor housing 121 and a magnet 122 connected to the inside of the rotor housing 121. The rotor housing 121 is used to be fixedly connected to the hub of the propeller 22. The stator 110 includes a stator winding 112 and a stator bracket 111. The stator winding 112 is connected to the outside of the stator bracket 111 and is located inside the rotor housing 121.

[0088] like Figure 2 As shown, the motor controller 800 is located inside the stator bracket 111. Furthermore, the motor controller 800 includes a power module, busbar capacitors, a drive board, and a main control board. It should be noted that, in addition to controlling the power motor 100 that drives the propeller 22, the motor controller 800 can also be used to control the drive motor 500 and / or the variable pitch motor and / or the liquid pump motor.

[0089] Figure 3 A schematic top view of a radiator provided in an embodiment of the present application.

[0090] During the operation of the power motor 100, heat will continuously accumulate inside the power motor 100, which will cause the temperature inside the power motor 100 to rise. In order to control the temperature inside the power motor 100 within the allowable range, as shown in FIG. Figure 2 As shown, the electric motor 21 further includes a radiator 200, which is located on a side of the power motor 100 away from the propeller 22. The radiator 200 has an air duct 210 (such as Figure 3 As shown), the air channel 210 is used for allowing air to pass through, thereby increasing the heat exchange area between the radiator 200 and the air and improving the heat dissipation capacity of the radiator 200.

[0091] The specific structure of the heat sink 200 is not limited herein. For example, the heat sink 200 includes an annular body and a plurality of heat dissipating fins. The plurality of heat dissipating fins are arranged radially and spaced apart within the annular body. Each heat dissipating fin is fixedly connected to the annular body at both ends, and the gap between two adjacent heat dissipating fins forms an air channel 210.

[0092] In order to take away the heat generated by the power motor 100, the power motor 100 has a liquid cooling channel (not shown in the figure), the inlet end of the liquid cooling channel is connected to the outlet end of the radiator 200, and the outlet end of the liquid cooling channel is connected to the inlet end of the radiator 200. The radiator 200 and the liquid cooling channel are used to form a cooling medium circuit for the flow of cooling medium.

[0093] The cooling medium may be a single coolant (eg, a water / ethylene glycol mixture, oil, etc.) or a mixture of multiple coolants.

[0094] The cooling medium in the liquid cooling channel absorbs the heat generated by the power motor 100 and changes from a low-temperature cooling medium to a high-temperature cooling medium. After the high-temperature cooling medium enters the radiator 200, it exchanges heat with the air through the radiator 200 and becomes a low-temperature cooling medium again. The low-temperature cooling medium then enters the liquid cooling channel. This cycle can promptly remove the heat from the power motor 100, keeping the temperature within the power motor 100 within the allowable range and ensuring the output power of the power motor 100.

[0095] It can be seen from this that the heat generated by the power motor 100 is transferred to the radiator 200 through the cooling medium, preventing the heat from continuously accumulating inside the power motor 100, controlling the temperature inside the power motor 100 within the allowable range, and ensuring the working performance of the power motor 100.

[0096] In order to make the cooling medium flow in the cooling medium circuit, the electric engine 21 also includes a liquid pump (not shown in the figure), the outlet end of the liquid pump is connected to the inlet end of the liquid cooling channel, and the inlet end of the liquid pump is connected to the outlet end of the radiator 200. The liquid pump is used to make the cooling medium flow in the cooling medium circuit.

[0097] Figure 4 This is a front view schematic diagram of an electric engine provided in an embodiment of the present application. Figure 5 for Figure 4 Schematic diagram of the electric motor architecture shown.

[0098] In order to improve the heat dissipation efficiency of the radiator 200, the electric motor 21 further includes a fan 300 and a wind shielding structure 400. The radiator 200, the fan 300 and the wind shielding structure 400 are all located on the side of the power motor 100 away from the propeller 22. Figure 4 The fan 300 has an air inlet side and an air outlet side. The power motor 100 is located on the air outlet side of the fan 300, and the radiator 200 is located on the air inlet side of the fan 300. The wind shielding structure 400 is arranged around the outer periphery of the fan 300, and the wind shielding structure 400, the radiator 200 and the fan 300 form an air inlet channel. The air inlet channel is connected to the air channel 210 of the radiator 200. The fan 300 is used to transfer the air on the side of the radiator 200 facing away from the fan 300 (such as Figure 5 The air (as indicated by the solid arrows in the middle) is sucked in through the air duct 210 and the air inlet channel and blown out from the air outlet side of the fan 300.

[0099] The fan 300 draws air from the side of the radiator 200 away from the fan 300 into the air duct 210. The air in the air duct 210 exchanges heat with the radiator 200, becoming hot air. The hot air then enters the air inlet channel and exits the air inlet channel from the outlet side of the fan 300, removing heat from the radiator 200 and cooling it, ensuring that the heat generated by the power motor 100 is continuously transferred to the radiator 200.

[0100] Given that the fan 300 blows air from the side of the radiator 200 facing away from the fan 300 through the air duct 210 and the air inlet channel to the air outlet side of the fan 300, forming a bottom-in, top-out airflow path, the axial distance between the fan 300 and the power motor 100 can be reduced, thereby reducing the axial length of the electric motor 21 and, in turn, reducing the volume of the electric motor 21, which is beneficial for the layout of the electric motor 21. In addition, the bottom-in, top-out airflow path and the unobstructed side of the radiator 200 facing away from the fan 300 ensure that air can also enter the central area of ​​the radiator 200, thereby increasing the air intake speed into the air duct 210 and thus improving the heat dissipation efficiency of the radiator 200.

[0101] In order to discharge the air in the air inlet duct, Figure 5 As shown, along the axial direction of the fan 300 (as Figure 5The heat sink 200 is located below the fan 300, and the power motor 100 is located above the fan 300. A first air outlet channel (as shown in the figure A1) is formed between the fan 300 and the power motor 100. The air in the air inlet channel is thrown out from the fan 300 along the axial direction of the fan 300 toward the upper end surface of the power motor 100 and discharged from the first air outlet channel (as shown in the figure A1). Figure 5 shown).

[0102] Figure 6 for Figure 4 Schematic diagram of the three-dimensional structure of the fan and wind protection structure, Figure 7 for Figure 4 Schematic diagram of the front view of the fan and wind protection structure.

[0103] In order to further improve the exhaust efficiency of the airflow in the air inlet channel, in some possible implementations, Figure 6 and Figure 7 It can be seen that along the axial direction of the fan 300, part of the outer peripheral side of the fan 300 is located in the space surrounded by the wind protection structure 400, and part of the outer peripheral side of the fan 300 is located outside the wind protection structure 400, so that part of the outer peripheral side of the fan 300 forms a second air outlet channel (such as Figure 5 As shown in A2 in FIG, part of the air in the air inlet channel is thrown out from the side of the fan 300 and discharged from the second air outlet channel (as shown in FIG. Figure 5 shown).

[0104] For example, Figure 6 and Figure 7 As shown, the wind protection structure 400 includes a wind protection ring 410, which is arranged around the outer periphery of the fan 300 and is fixedly connected to the radiator 200. Figure 5 As shown, along the radial direction of the fan 300 (as Figure 5 In the Y direction), the wind shield 410 is spaced apart from the fan 300.

[0105] In order to prevent air flow from leaking from the installation gap between the wind shield and the radiator 200, the wind shield structure 400 also includes a seal (not shown in the figure), which is arranged between the wind shield ring 410 and the radiator 200 to seal the gap between the wind shield ring 410 and the radiator 200.

[0106] The sealing member is annular and is disposed around the fan 300. Furthermore, the sealing member is made of a flexible material, such as sponge. When the sealing member is made of sponge, the weight of the electric motor 21 can be reduced.

[0107] Figure 8 for Figure 4 Schematic diagram of the three-dimensional structure of the fan, Figure 9 for Figure 8A schematic front view of the fan is shown.

[0108] like Figure 8 and Figure 9 As shown, the fan 300 includes a hub 320 and a plurality of blades 310. The plurality of blades 310 are arranged around the hub 320. The plurality of blades 310 are arranged at intervals along the circumference of the fan 300. One end of each blade 310 is fixedly connected to the hub 320, and the other end of each blade 310 is a free end.

[0109] There is no limitation on the blade shape of the fan blade 310. Figure 8 and Figure 9 It can be seen that along the radial direction of the fan 300 , the direction of the fan blades 310 is designed to be a straight line from the inside to the outside, and the deflection angle of the fan blades 310 is designed to be a torsion.

[0110] In some embodiments, as Figure 8 As shown, the fan blades 310 and the hub 320 are an integrally formed structure, which can improve the manufacturing efficiency of the fan 300. In other embodiments, the fan blades 310 and the hub 320 can also be fixedly connected by means of threaded connection or the like.

[0111] In order to make the air on the side of the radiator 200 away from the fan 300 be sucked into the air duct 210 and the air inlet channel and discharged from the air outlet side, Figure 6 and Figure 7 It can be seen that along the axial direction of the fan 300 (such as Figure 7 In the middle Z direction), part of the outer circumference of blade 310 is located within the space enclosed by wind shield structure 400, and part of the outer circumference of blade 310 is located outside wind shield structure 400. In other words, along the axial direction of fan 300, part of blade 310 extends into the space enclosed by wind shield structure 400, or in other words, part of blade 310 is wrapped by wind shield structure 400.

[0112] Of course, along the axial direction of the fan 300, in addition to setting a part of the outer peripheral side of the fan blade 310 in the space enclosed by the wind protection structure 400 and the other part outside the wind protection structure 400, in some scenarios, along the axial direction of the fan 300, the outer peripheral side of the fan blade 310 can also be located in the space enclosed by the wind protection structure 400, that is, the fan blade 310 extends into the space enclosed by the wind protection structure 400.

[0113] There is no restriction on the height of blades 310 within wind shielding structure 400. For example, the height of blades 310 within wind shielding structure 400 is greater than or equal to a first height and less than or equal to a second height, where the first height is one-third of the maximum height of blades 310 along the axial direction of fan 300, and the second height is two-thirds of the maximum height of blades 310 along the axial direction of fan 300. Setting the height of blades 310 within wind shielding structure 400 between the first and second heights can increase the airflow discharged from the second air outlet channel and keep the airflow velocity within an allowable range, thereby further improving the airflow discharge efficiency.

[0114] In order to make the cooling medium flow into the interior of the liquid cooling channel, in some possible implementations, such as Figure 4 As shown, the electric engine 21 further includes a liquid supply pipe 600 and a liquid return pipe 700. The outlet of the liquid cooling channel is connected to the inlet of the radiator 200 via the liquid return pipe 700, and the outlet of the radiator 200 is connected to the inlet of the liquid cooling channel via the liquid supply pipe 600. The liquid cooling channel, the liquid return pipe 700, the radiator 200, and the liquid supply pipe 600 form a cooling medium circuit.

[0115] The liquid return pipe 700 can be directly or indirectly connected to the outlet end of the liquid cooling channel, and the liquid supply pipe 600 can be directly or indirectly connected to the inlet end of the liquid cooling channel.

[0116] To simplify the structure of the electric generator 21, in some possible implementations, the return pipe 700 is a rigid pipe, with its ends fixedly connected to the radiator 200 and the housing of the power motor 100, respectively. For example, the housing of the power motor 100 includes a motor rear cover fixedly connected to the stator bracket 111, and the return pipe 700 is fixedly connected to the motor rear cover. The supply pipe 600 is a rigid pipe, with its ends fixedly connected to the radiator 200 and the housing of the power motor 100, respectively. For example, the supply pipe 600 is fixedly connected to the motor rear cover.

[0117] It can be seen from this that the material of the return liquid pipe 700 and the supply liquid pipe 600 is rigid material, and the return liquid pipe 700 and the supply liquid pipe 600 also play a supporting role in function, so that the radiator 200 is fixed to the power motor 100, so there is no need to set up a fixed structure connecting the radiator 200 and the power motor 100, thereby increasing the use of the return liquid pipe 700 and the supply liquid pipe 600 and reducing the number of parts of the electric engine 21, thereby achieving the purpose of simplifying the structure of the electric engine 21.

[0118] Exemplarily, the electric generator 21 may include multiple liquid supply pipes 600 and multiple liquid return pipes 700. The radiator 200 is fixedly connected to the power motor 100 via the multiple liquid supply pipes 600 and the multiple liquid return pipes 700, so that the radiator 200 and the power motor 100 are fixedly secured. In this case, the radiator 200 may include multiple outlets corresponding to the liquid supply pipes 600 and multiple inlet ports corresponding to the liquid return pipes 700. Each inlet port of the radiator 200 is connected to the outlet port of the liquid cooling channel via a corresponding liquid return pipe 700, and each outlet port of the radiator 200 is connected to the inlet port of the liquid pump via a corresponding liquid inlet pipe. For example, the electric generator 21 may include two liquid supply pipes 600 and two liquid return pipes 700. The two liquid supply pipes 600 and the two liquid return pipes 700 are evenly spaced along the circumference of the fan 300, so that the radiator 200 is fixed more firmly. The liquid supply pipes 600 and the liquid return pipes 700 can be alternately arranged along the circumference of the fan 300, so that the cooling medium can flow into the radiator 200 from two opposite positions on the radiator 200 and flow out of the radiator 200 from two opposite positions on the radiator 200, which is conducive to uniform heat dissipation of the radiator 200.

[0119] It should be noted that, in some embodiments, one of the return pipe 700 and the supply pipe 600 is a rigid pipe. In this case, one of the return pipe 700 and the supply pipe 600 serves as a supporting structure for fixing the radiator 200 to the power motor 100 .

[0120] In some possible implementations, such as Figure 4 As shown, the electric generator 21 also includes a drive motor 500, which is transmission-connected to the fan 300. The drive motor 500 serves as the pump motor for the liquid pump and is used to drive the fan 300. Specifically, the drive motor 500 includes an output shaft, one end of which is transmission-connected to the fan 300, and the other end of which is transmission-connected to the pump rotor of the liquid pump. As can be seen, the liquid pump and the fan 300 share a single motor. The drive motor 500, while serving as the power source for both the fan 300 and the liquid pump, eliminates the need for a separate fan motor to drive the fan 300, simplifying the structure of the electric generator 21.

[0121] Of course, in addition to utilizing the pump motor of the liquid pump, in other possible implementations, the electric motor 21 may include a liquid pump motor (not shown) and a drive motor 500. The liquid pump motor serves as the pump motor of the liquid pump, while the drive motor 500 is in transmission connection with the fan 300 and is used to drive the fan 300. In this case, the liquid pump and the fan 300 are each driven by a single motor.

[0122] Figure 10 for Figure 4The schematic diagram of the structure of the electric engine and the nacelle shown is as follows, Figure 11 for Figure 10 Schematic diagram of the internal structure of the nacelle.

[0123] like Figure 10 As shown, when the electric motor 21 is installed in the nacelle 15, the power motor 100 is located outside the nacelle 15 and arranged side by side with the nacelle 15 along the axial direction of the fan 300. At this time, the rotor 120 of the power motor 100 is located in front of the leading edge of the nacelle 15 and is rotatably coupled to the stator 110. The power motor 100 is located outside the nacelle 15 and arranged side by side with the nacelle 15 along the axial direction of the fan 300. At this time, the rotor 120 of the power motor 100 is located in front of the leading edge of the nacelle 15 and is rotatably coupled to the stator 110. The radiator 200 is close to the nacelle 15.

[0124] In order to ensure that the side of the radiator 200 away from the fan 300 has air, Figure 11 As shown, the nacelle 15 includes a first cavity 151 and a second cavity 152 separated from each other. The first cavity 151 is located between the power motor 100 and the second cavity 152. The first cavity 151 has a first opening 154 and a second opening 155. The first opening 154 and the second opening 155 both connect the inside and the outside of the first cavity 151. Figure 10 As shown, the air duct 210 of the radiator 200 of the electric engine 21 is connected to the first cavity 151 through the first opening 154, and the fan 300 of the electric engine 21 is used to suck in the air entering the first cavity 151 from the second opening 155 through the air duct 210 and blow it to the air outlet side of the fan 300, that is, blown between the nacelle 15 and the power motor 100.

[0125] As can be seen, the second opening 155 functions as the air inlet of the first cavity 151. Air outside the nacelle 15 enters the interior of the first cavity 151 through the second opening 155, resulting in air from outside the nacelle 15 flowing through the side of the heat sink 200 away from the fan 300. Under the action of the fan 300, the air in the first cavity 151 first enters the interior of the air duct 210, then enters the air inlet channel, and is discharged from the air outlet side of the fan 300. The air outside the nacelle 15 is at a lower temperature, so using this air to dissipate heat further improves the heat dissipation efficiency of the heat sink 200. Furthermore, using air from outside the nacelle 15 to dissipate heat from the heat sink 200 in a bottom-in, top-out manner prevents hot air absorbed from the heat sink 200 from blowing onto components within the second cavity 152, thereby preventing secondary thermal damage to these components.

[0126] The components in the second cavity 152 include batteries, sensors, controllers, etc. In addition, in order to dissipate heat for the components in the second cavity 152, as shown in FIG. Figure 11 As shown, the second cavity 152 also includes a connecting opening 156, which connects the inside and outside of the second cavity 152. The air outside the nacelle 15 enters the second cavity 152 through the connecting opening 156 to cool the device and keep the device in the second cavity 152 free of air.

[0127] In some embodiments, along the axial direction of the fan 300, the communication opening 156 is located on a side of the second cavity 152 away from the power motor 100, or in other words, the communication opening 156 is located at an end of the nacelle 15 away from the power motor 100. Of course, the communication opening 156 can also be provided at other locations on the nacelle 15.

[0128] Figure 12 A schematic structural diagram of another nacelle provided in an embodiment of the present application.

[0129] In order to drain the water in the first cavity 151, in some embodiments, as shown in FIG. Figure 11 As shown, the nacelle 15 includes a partition 153, which divides the interior of the nacelle 15 into a first cavity 151 and a second cavity 152, that is, the partition 153 separates the first cavity 151 from the second cavity 152. Figure 11 and Figure 12 As can be seen, the distance between the side of the partition 153 closest to the radiator 200 and the radiator 200 gradually decreases from the outside of the nacelle 15 inward, resulting in a tapered surface of the partition 153 facing the power motor 100 along the axial direction of the fan 300. At least one second opening 155 is located near the partition 153. Thus, water within the first cavity 151 flows from inside to outside along the tapered surface and exits the first cavity 151 through the second opening 155 near the partition 153.

[0130] To increase the speed at which water flows out of second opening 155 near barrier 153, as shown in the figure, the distance between the inner wall of second opening 155 near barrier 153 and the edge of barrier 153 in the axial direction of fan 300 is a predetermined distance, for example, zero. In other words, second opening 155 near barrier 153 also functions as a water outlet for first cavity 151.

[0131] In order to improve the air intake efficiency of the first cavity 151, in some possible implementations, the first cavity 151 includes a plurality of opening groups, such as Figure 11As shown, there are five opening groups. Of course, the number of opening groups may be less than or greater than five. Each opening group includes a plurality of second openings 155 spaced apart along the circumference of the fan 300. The plurality of opening groups are spaced apart along the axial direction of the fan 300. The opening group closest to the second cavity 152 of the plurality of opening groups is close to the partition 153. The second openings 155 of the opening group closest to the second cavity 152 are also used to drain water from the first cavity 151.

[0132] In order to reduce the axial distance between the nacelle 15 and the power motor 100, in some possible implementations, such as Figure 11 As shown, the wind shielding structure 400 and the radiator 200 of the electric engine 21 are located inside the first cavity 151 through the first opening 154 .

[0133] Of course, in addition to the wind shielding structure 400 and the radiator 200 being located in the first cavity 151 through the first opening 154, in some embodiments, a portion of the wind shielding structure 400 is located outside the first cavity 151, while another portion of the wind shielding structure 400 and the radiator 200 are located inside the first cavity 151 through the first opening 154. In other embodiments, the wind shielding structure 400 is located outside the first cavity 151, and the radiator 200 is located inside the first cavity 151 through the first opening 154. In still other embodiments, a portion of the wind shielding structure 400 and the radiator 200 are located outside the first cavity 151, while a portion of the radiator 200 is located inside the first cavity 151 through the first opening 154.

[0134] Figure 13 for Figure 10 Schematic diagram of the electric engine and nacelle shown.

[0135] In order to increase the airflow discharge speed, in some possible implementations, such as Figure 13 As shown, a portion of the fan blades 310 of the fan 300 is located inside the first cavity 151, and another portion of the fan blades 310 is located outside the first cavity 151. Along the axial direction of the fan 300, the minimum distance between the nacelle 15 and the power motor 100 is greater than the maximum distance between the fan blades 310 and the power motor 100. In this way, a first air outlet channel is formed between the fan 300 and the power motor 100, and a second air outlet channel is formed on part of the outer periphery of the fan 300.

[0136] like Figure 13As shown, when fan 300 rotates, air outside nacelle 15 enters first cavity 151 through second opening 155, then enters air duct 210 of radiator 200, and finally enters the air inlet channel, before being discharged from the outlet side of fan 300. The exhaust airflow comprises a first airflow and a second airflow, with the first airflow discharged from the second outlet channel and the second airflow discharged from the first outlet channel. This bidirectional discharge of the first and second airflows improves the smoothness of the airflow throughout the entire flow process, increases the flow rate, and enhances the heat dissipation efficiency of radiator 200.

[0137] Of course, in addition to locating a portion of the fan blade 310 inside the first cavity 151 and another portion outside the first cavity 151 , in some scenarios, the fan blade 310 can also be set inside the first cavity 151 .

[0138] In the above description, the power motor 100 is located inside the nacelle 15 . However, in some scenarios, at least a portion of the power motor 100 may also be located inside the nacelle 15 .

[0139] Figure 14 A schematic structural diagram of another nacelle and electric engine provided in an embodiment of the present application.

[0140] Figure 14 and Figure 13 The difference is that part of the power motor 100 is located inside the nacelle 15. Specifically, Figure 14 As shown, the nacelle 15 further includes a third cavity 157. The first cavity 151 is located between the second cavity 152 and the third cavity 157. The first opening 154 connects the first cavity 151 and the third cavity 157. The third cavity 157 has a third opening 158. The third opening 158 connects the inside and the outside of the third cavity 157. At least part of the power motor 100 is located inside the third cavity 157 through the third opening 158, for example. Figure 14 As shown, a portion of the power motor 100 is located inside the third cavity 157 through the third opening 158 . Part of the rotor 120 of the power motor 100 is located inside the third cavity 157 through the third opening 158 .

[0141] The fan 300 is used to draw air from the first cavity 151 through the air duct 210 and the air inlet channel and discharge it from the air outlet side of the fan 300 to the interior of the third cavity 157. The air in the air inlet channel can be discharged from the first air outlet channel and / or the second air outlet channel to the interior of the third cavity 157, for example Figure 14 As shown, the air in the air inlet channel is discharged from the first air outlet channel and the second air outlet channel to the interior of the third cavity 157.

[0142] In order to discharge the air in the third cavity 157 to the outside, in some embodiments, as Figure 14 As shown, the rotor 120 and the inner wall of the third cavity 157 form an exhaust channel (as shown in FIG. Figure 14 As shown in FIG. 15 , the exhaust passage connects the inside and outside of the third cavity 157 , and the exhaust passage is used to discharge the air in the third cavity 157 to the outside of the third cavity 157 .

[0143] In other embodiments, Figure 14 As shown, the third cavity 157 further has a fourth opening 159 , which is located between the third opening 158 and the first cavity 151 . The fourth opening 159 is used to discharge the air in the third cavity 157 to the outside of the third cavity 157 .

[0144] In order to further improve the efficiency of discharging air in the third cavity 157, there are multiple fourth openings 159, and the multiple fourth openings 159 can be arranged at intervals along the circumference of the fan 300, or the multiple fourth openings 159 can be divided into multiple exhaust groups, and the multiple exhaust groups are arranged at intervals along the axial direction of the fan 300, and each exhaust group has multiple fourth openings 159 arranged at intervals along the circumference of the fan 300.

[0145] In summary, the air in the third cavity 157 can be discharged to the outside of the third cavity 157 through the fourth opening 159 and / or the exhaust channel.

[0146] There is no limitation on how the third cavity 157 is formed. Figure 14 As shown, the nacelle 15 may include an annular partition 160 . The annular partition 160 is located inside the nacelle 15 . The annular partition 160 has a first opening 154 . The annular partition 160 separates the first cavity 151 from the third cavity 157 .

[0147] It should be noted that when the electric propulsion device 20 is installed on the arm 14, the arm 14 includes a first cavity 151 having a first opening 154 and a second opening 155. The relationship between the electric propulsion device 20 and the first cavity 151 can be referred to the above content and will not be repeated here.

[0148] In addition, in order to drain the water in the first cavity 151, the first cavity 151 includes a conical inner wall, and the distance between the side of the conical inner wall close to the radiator 200 and the radiator 200 gradually decreases from the outside of the arm 14 to the inside. The function of the conical inner wall is the same as that of the partition 153 in the above content.

[0149] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit them. Although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some or all of the technical features therein. These modifications or replacements do not deviate the essence of the corresponding technical solutions from the scope of the technical solutions of the embodiments of the present application.

Claims

1. An aircraft, characterized in that: include: A nacelle (15), the nacelle (15) having a first cavity (151), the first cavity (151) having a first opening (154) and a second opening (155), the first opening (154) and the second opening (155) both communicating with the interior and exterior of the first cavity (151); An electric engine (21) comprises a power motor (100), a radiator (200) and a fan (300), wherein the radiator (200) is used to dissipate heat from the power motor (100), the radiator (200) has an air duct (210) communicating with the interior of the first cavity (151) through the first opening (154), and the fan (300) is used to draw air entering the first cavity (151) from the second opening (155) into the air duct (210) and blow the air to the side of the power motor (100) facing the fan (300).

2. The aircraft according to claim 1, characterized in that The first cavity (151) includes a plurality of opening groups, the plurality of opening groups are arranged at intervals along the axial direction of the fan (300), and each of the opening groups includes a plurality of second openings (155) arranged at intervals along the circumferential direction of the fan (300).

3. The aircraft according to claim 1, characterized in that The nacelle (15) further comprises a second cavity (152) separated from the first cavity (151), wherein the second cavity (152) comprises a communication opening (156), and the communication opening (156) connects the inside and the outside of the second cavity (152).

4. The aircraft according to claim 1, characterized in that The nacelle (15) further has a second cavity (152), and the nacelle (15) includes a partition (153), wherein the partition (153) separates the first cavity (151) from the second cavity (152), and the distance between the side of the partition (153) close to the radiator (200) and the radiator (200) gradually decreases in a direction from the outside of the nacelle (15) to the inside; At least one of the second openings (155) is located adjacent to the partition member (153).

5. The aircraft according to claim 1, characterized in that The power motor (100) is located outside the nacelle (15) and is arranged side by side with the nacelle (15) along the axial direction of the fan (300).

6. The aircraft according to claim 1, characterized in that The nacelle (15) further comprises a third cavity (157), the third cavity (157) being located on a side of the first cavity (151) facing the power motor (100), the first opening (154) communicating with the first cavity (151) and the third cavity (157), the third cavity (157) having a third opening (158), the third opening (158) communicating with the interior and exterior of the third cavity (157), and at least a portion of the rotor (120) of the power motor (100) being located inside the third cavity (157) through the third opening (158); The fan (300) is used to draw the air in the first cavity (151) into the third cavity (157) through the air duct (210).

7. The aircraft according to claim 6, characterized in that The rotor (120) and the inner wall of the third cavity (157) form an exhaust channel, and the exhaust channel is used to discharge the air in the third cavity (157) to the outside of the third cavity (157); and / or, The third cavity (157) further has a fourth opening (159), which is located between the third opening (158) and the first cavity (151), and the fourth opening (159) is used to discharge the air in the third cavity (157) to the outside of the third cavity (157).

8. The aircraft according to any one of claims 1 to 7, characterized in that: Along the axial direction of the fan (300), the fan (300) has an air inlet side and an air outlet side, the power motor (100) is located on the air outlet side of the fan (300), and the radiator (200) is located on the air inlet side of the fan (300); the electric engine (21) further comprises: a wind shielding structure (400), the wind shielding structure (400) is arranged around the outer periphery of the fan (300), and the wind shielding structure (400), the radiator (200) and the fan (300) form an air inlet channel, and the air inlet channel is communicated with the air duct (210) of the radiator (200); The fan (300) is used to suck the air in the first cavity (151) through the air duct (210) and the air inlet channel and blow it out from the air outlet side to the side of the power motor (100) facing the fan (300).

9. The aircraft according to claim 8, characterized in that The wind protection structure (400) and the radiator (200) are located inside the first cavity (151) through the first opening (154); a portion of the fan blade (310) of the fan (300) is located inside the first cavity (151), and another portion of the fan blade (310) is located outside the first cavity (151).

10. The aircraft according to claim 9, characterized in that The power motor (100) is located outside the nacelle (15) and is arranged side by side with the nacelle (15) along the axial direction of the fan (300); Along the axial direction of the fan (300), the minimum distance between the nacelle (15) and the power motor (100) is greater than the maximum distance between the fan blades (310) and the power motor (100).

11. The aircraft according to claim 8, characterized in that Along the axial direction of the fan (300), the radiator (200) is located below the fan (300), and the power motor (100) is located above the fan (300); A first air outlet channel is formed between the fan (300) and the power motor (100).

12. The aircraft according to claim 8, characterized in that Along the axial direction of the fan (300), part of the outer peripheral side of the fan (300) is located in the space surrounded by the wind protection structure (400), and part of the outer peripheral side of the fan (300) is located outside the wind protection structure (400), so that part of the outer peripheral side of the fan (300) forms a second air outlet channel.

13. The aircraft according to claim 12, characterized in that The fan (300) includes a fan blade (310), and along the axial direction of the fan (300), part of the outer peripheral side of the fan blade (310) is located in the space surrounded by the wind protection structure (400), and part of the outer peripheral side of the fan blade (310) is located outside the wind protection structure (400); The height of the fan blade (310) located in the wind protection structure (400) is greater than or equal to a first height and less than or equal to a second height, the first height being one-third of the maximum height of the fan blade (310) along the axial direction of the fan (300), and the second height being two-thirds of the maximum height of the fan blade (310) along the axial direction of the fan (300).

14. The aircraft according to any one of claims 1 to 7, characterized in that: The power motor (100) has a liquid cooling channel, the outlet end of the liquid cooling channel is in communication with the inlet end of the radiator (200), the outlet end of the radiator (200) is in communication with the inlet end of the liquid cooling channel, and the liquid cooling channel and the radiator (200) are used to form a cooling medium circuit; The electric engine (21) further comprises: a liquid pump, the liquid pump being fixed to the housing of the power motor (100), the outlet end of the liquid pump being in communication with the inlet end of the liquid cooling channel, the inlet end of the liquid pump being in communication with the outlet end of the radiator (200), and the liquid pump being used to allow the cooling medium to flow in the cooling medium circuit.

15. The aircraft according to claim 14, characterized in that The electric engine (21) further comprises a drive motor (500), the drive motor (500) being transmission-connected to the fan (300), the drive motor (500) serving as a pump motor of the liquid pump, and the drive motor (500) also being used to drive the fan (300) to rotate; or, The electric engine (21) further comprises a drive motor (500) and a liquid pump motor. The drive motor (500) is transmission-connected to the fan (300) to drive the fan (300) to rotate, and the liquid pump motor serves as a pump motor of the liquid pump.

16. The aircraft according to any one of claims 1 to 7, characterized in that: The aircraft further comprises a propeller (22), the propeller (22) being arranged on a side of the power motor (100) away from the radiator (200) and being in transmission connection with the power motor (100), and the power motor (100) being used to drive the propeller (22) to rotate; The radiator (200) and the fan (300) are both located on a side of the power motor (100) away from the propeller (22).

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