Heat dissipation system and flight structure

Abstract

The invention discloses a heat dissipation system and a flight structure, the heat dissipation system comprises a rotor wing, a flight electric drive assembly, a machine arm and a heat dissipation structure, the flight electric drive assembly is located below the rotor wing and is used for driving the rotor wing to rotate; the vehicle arms are connected with the flying electric drive assembly; the heat dissipation structures are installed on the flying electric drive assemblies or the vehicle arms, the heat dissipation structures are located below the rotor wings, and heat exchange can be conducted between the flying electric drive assemblies and the heat dissipation structures; the rotor wing is provided with a heat dissipation structure, the heat dissipation structure is provided with a heat dissipation extension area, the heat dissipation extension area extends along the rotation path of the rotor wing and extends in the direction from the propeller root to the propeller tip of the rotor wing, and downwash airflow of the rotor wing passes through the heat dissipation extension area. According to the heat dissipation system, effective heat dissipation of the flight electric drive assembly can be achieved through downwash airflow of the rotor wings, the structure of the heat dissipation system is greatly simplified, the number of parts is small, the heat dissipation effect is good, the mass of the heat dissipation system is effectively reduced, and cost is saved.

Description

Technical Field

[0001] The present invention relates to the technical field of flight components, and in particular to a heat dissipation system and a flight structure. Background Art

[0002] At present, some flying structures, such as the electric drive heat dissipation structure of flying vehicles, are usually composed of rotors, flying electric drive assemblies, electric drive external heat dissipation systems, and aircraft arms, among which the electric drive external heat dissipation system includes structures such as kettles, water pumps, flying radiators, cooling pipe assemblies, and antifreeze flowing between the structures. During operation, the waste heat generated by the flying electric drive assembly is dissipated through the antifreeze circulating between the water pump, the kettle, and the cooling pipe assembly to the flying radiator. However, the electric drive external heat dissipation system used in this heat dissipation method has a complex structure, a large number of parts, poor heat dissipation effect, heavy weight, and high cost. Summary of the invention

[0003] The main purpose of the present invention is to propose a heat dissipation system and a flight structure, aiming to solve the problems in the prior art that the electric drive external heat dissipation system of the flight structure is complex in structure, has a large number of parts, has poor heat dissipation effect, is heavy in weight and has high cost.

[0004] To achieve the above object, the present invention provides a heat dissipation system, which comprises:

[0005] Rotor;

[0006] A flight electric drive assembly, the flight electric drive assembly is located below the rotor and is used to drive the rotor to rotate;

[0007] A machine arm, the machine arm being connected to the flight electric drive assembly;

[0008] A heat dissipation structure, wherein the heat dissipation structure is installed on the flight electric drive assembly or the aircraft arm, and the heat dissipation structure is located below the rotor. The flight electric drive assembly can exchange heat with the heat dissipation structure; the heat dissipation structure has a heat dissipation extension area, and the heat dissipation extension area extends along the rotation path of the rotor and extends from the blade root to the blade tip of the rotor. The downwash airflow of the rotor passes through the heat dissipation extension area.

[0009] Optionally, the heat dissipation structure includes:

[0010] A mounting seat, the mounting seat being mounted on the flight electric drive assembly or the aircraft arm;

[0011] An oil cooler is installed on the mounting seat, the oil cooler and the flight electric drive assembly are interconnected to form a circulating oil circuit, and the oil cooler has the heat dissipation extension area.

[0012] Optionally, the heat dissipation structure also includes an oil supply pipe and an oil return pipe, the oil outlet end of the flight electric drive assembly is connected to the oil inlet of the oil cooler through the oil supply pipe, and the oil inlet end of the flight electric drive assembly is connected to the oil outlet of the oil cooler through the oil return pipe, so as to form the circulating oil circuit between the oil cooler and the flight electric drive assembly.

[0013] Optionally, the oil cooler includes a plurality of cooling fins, the plurality of cooling fins form the cooling extension zone, the plurality of cooling fins are distributed sequentially along the direction from the blade root to the blade tip of the rotor, each cooling fin extends along the rotation path of the rotor, and an oil passage connecting the oil inlet and the oil outlet is formed in each cooling fin.

[0014] Optionally, any two adjacent heat dissipation fins are spaced apart to form a heat dissipation channel extending along the rotation path of the rotor.

[0015] Optionally, each of the heat dissipation fins is arranged vertically.

[0016] Optionally, the oil cooler also includes a first oil collecting cylinder and a second oil collecting cylinder, the first oil collecting cylinder and the second oil collecting cylinder are installed on the mounting seat, the first oil collecting cylinder is provided with the oil inlet, the second oil collecting cylinder is provided with the oil outlet, the two ends of each of the heat dissipating fins are respectively connected to the first oil collecting cylinder and the second oil collecting cylinder, and the oil passage connects the first oil collecting cylinder and the second oil collecting cylinder.

[0017] Optionally, the oil inlet is connected to the oil delivery pipe through an oil inlet pipe, and the oil outlet is connected to the oil return pipe through an oil outlet pipe.

[0018] Optionally, the heat dissipation extension area is fan-shaped, semi-annular or annular.

[0019] Optionally, the rotation path of the rotor forms a rotation zone, and the rotation zone covers at least a portion of the heat dissipation extension zone.

[0020] Optionally, the rotating area fully covers the heat dissipation extension area.

[0021] Optionally, the heat dissipation structure is installed on the windward side of the flight electric drive assembly or the windward side of the aircraft arm.

[0022] The present invention further proposes a flight structure, which includes a flight body and the heat dissipation system as described above, and the aircraft arm is connected to the flight body.

[0023] Optionally, the flying structure is a flying vehicle, and the flying subject is a body of the flying vehicle.

[0024] During the operation of the heat dissipation system of the present invention, the flight electric drive assembly drives the rotor to rotate, and the rotor can generate downwash airflow when rotating. The flight electric drive assembly transfers the generated heat to the heat dissipation structure. Since the heat dissipation structure has a heat dissipation extension area, and the heat dissipation extension area extends along the rotation path of the rotor, it is convenient for the downwash airflow generated by the rotor when rotating to pass through the heat dissipation extension area, realize air cooling, play a good heat dissipation role, and improve the heat dissipation effect. In addition, the heat dissipation extension area extends from the blade root to the blade tip of the rotor, increasing the heat dissipation area and further improving the heat dissipation effect.

[0025] The heat dissipation system of the present invention only requires setting a heat dissipation extension zone on the heat dissipation structure so that the heat dissipation extension zone extends along the rotation path of the rotor and extends in the direction from the blade root to the blade tip of the rotor. The downwash airflow of the rotor can be used to achieve effective heat dissipation of the flight electric drive assembly, which greatly simplifies the structure of the heat dissipation system, reduces the number of parts and components, and has good heat dissipation effect. It also effectively reduces the weight of the heat dissipation system and saves costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0027] Figure 1 A schematic side view of a heat dissipation system according to an embodiment of the present invention;

[0028] Figure 2 A schematic top view of a heat dissipation system according to an embodiment of the present invention;

[0029] Figure 3 This is a schematic structural diagram of a heat dissipation system according to an embodiment of the present invention, in which the rotor, flight electric drive assembly and aircraft arm are omitted.

[0030] Description of Figure Numbers:

[0031]

[0032]

[0033] The realization of the purpose, functional features and advantages of the present invention will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0034] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0035] It should be noted that if the embodiments of the present invention involve directional indications (such as up, down, left, right, front, back, etc.), the directional indications are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0036] In addition, if there are descriptions involving "first", "second", etc. in the embodiments of the present invention, the descriptions of "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or suggesting their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In addition, the technical solutions between the various embodiments can be combined with each other, but they must be based on the ability of ordinary technicians in the field to implement them. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such a combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0037] The present invention provides a heat dissipation system 100 .

[0038] like Figures 1 to 3 As shown, in one embodiment, the heat dissipation system 100 includes a rotor 10, a flight electric drive assembly 20, an arm 30 and a heat dissipation structure 40, wherein the flight electric drive assembly 20 is located below the rotor 10 and is used to drive the rotor 10 to rotate, the arm 30 is connected to the flight electric drive assembly 20, the heat dissipation structure 40 is installed on the flight electric drive assembly 20 or the arm 30, the heat dissipation structure 40 is located below the rotor 10, and the flight electric drive assembly 20 can exchange heat with the heat dissipation structure 40; the heat dissipation structure 40 has a heat dissipation extension area 43, the heat dissipation extension area 43 extends along the rotation path of the rotor 10, and extends from the root to the tip of the rotor 10, and the downwash airflow of the rotor 10 passes through the heat dissipation extension area 43.

[0039] It should be noted that the heat dissipation system 100 of the present invention can be applied to a flight structure, such as a flight vehicle or other flight structure with a rotor 10. The rotor 10, the flight electric drive assembly 20 and the arm 30 are the basic structures of the flight structure, and the existing technology can be used. The flight electric drive assembly 20 and the heat dissipation structure 40 are both located below the rotor 10, and the heat dissipation structure 40 is installed on the flight electric drive assembly or the arm 30, and the structural design is reasonable and compact.

[0040] During operation, the flight electric drive assembly 20 drives the rotor 10 to rotate, and the rotor 10 can generate downwash airflow when rotating. The flight electric drive assembly 20 transfers the generated heat to the heat dissipation structure 40. Since the heat dissipation structure 40 has a heat dissipation extension area 43, and the heat dissipation extension area 43 extends along the rotation path of the rotor 10, it is convenient for the downwash airflow generated by the rotor 10 when rotating to pass through the heat dissipation extension area 43, so as to achieve air cooling, play a good heat dissipation role, and improve the heat dissipation effect. In addition, the heat dissipation extension area 43 extends from the blade root to the blade tip of the rotor 10, which increases the heat dissipation area and further improves the heat dissipation effect.

[0041] The heat dissipation system 100 of this embodiment only sets a heat dissipation extension area 43 on the heat dissipation structure 40, so that the heat dissipation extension area 43 extends along the rotation path of the rotor 10 and extends from the root to the tip of the rotor 10. The downwash airflow of the rotor 10 can be used to achieve effective heat dissipation of the flight electric drive assembly 20, which greatly simplifies the structure of the heat dissipation system 100, reduces the number of parts, and has a good heat dissipation effect. It also effectively reduces the weight of the heat dissipation system 100 and saves costs.

[0042] The heat dissipation structure 40 includes a mounting seat 41 and an oil cooler 42, wherein the mounting seat 41 is installed on the flight electric drive assembly 20 or the arm 30; the oil cooler 42 is installed on the mounting seat 41, and the oil cooler 42 and the flight electric drive assembly 20 are interconnected to form a circulating oil circuit, and the oil cooler 42 has a heat dissipation extension area 43.

[0043] The installation position of the heat dissipation structure 40 can be flexibly selected. In one embodiment, the oil cooler 42 is installed on the flight electric drive assembly 20 through the mounting seat 41. In another embodiment, the oil cooler 42 is installed on the aircraft arm 30 through the mounting seat 41, which is convenient for assembly. The oil cooler 42 forms a circulating oil circuit with the flight electric drive assembly 20, and the oil cooler 42 has a heat dissipation extension area 43, so that the heat generated by the flight electric drive assembly 20 can be transferred to its cooling oil, and conducted to the oil cooler 42 through the flow of its cooling oil. After heat dissipation in the heat dissipation extension area 43, it becomes low-temperature cooling oil and enters the flight electric drive assembly 20 to continue working, and absorbs the heat generated by the flight electric drive assembly 20 and then conducts it to the oil cooler 42 for heat dissipation. In this cycle, continuous heat dissipation of the flight electric drive assembly 20 is achieved, and the heat dissipation effect is improved.

[0044] In one embodiment, the heat dissipation structure 40 also includes an oil supply pipe 44 and an oil return pipe 45. The oil outlet end of the flight electric drive assembly 20 is connected to the oil inlet of the oil cooler 42 through the oil supply pipe 44, and the oil inlet end of the flight electric drive assembly 20 is connected to the oil outlet of the oil cooler 42 through the oil return pipe 45, so as to form a circulating oil circuit between the oil cooler 42 and the flight electric drive assembly 20.

[0045] The oil cooler 42 is connected to the oil outlet and oil inlet of the flight electric drive assembly 20 through the oil delivery pipe 44 and the oil return pipe 45, respectively, so that a circulating oil circuit is formed between the oil cooler 42 and the flight electric drive assembly 20, thereby realizing heat dissipation of the flight electric drive assembly 20, and the structure is simple and easy to assemble. In one embodiment, the oil cooler 42 includes a plurality of heat dissipation fins 421, and the plurality of heat dissipation fins 421 form a heat dissipation extension area 43, and the plurality of heat dissipation fins 421 are distributed in sequence from the root of the rotor 10 to the tip of the rotor, and each heat dissipation fin 421 extends along the rotation path of the rotor 10, and each heat dissipation fin 421 forms an oil passage connecting the oil inlet and the oil outlet.

[0046] like Figures 1 to 3 As shown, the heat dissipation extension area 43 can be formed by a plurality of heat dissipation fins 421, and each heat dissipation fin 421 can be conducted to dissipate the heat in the oil cooler 42, thereby improving the heat dissipation efficiency and heat dissipation effect. Further, the plurality of heat dissipation fins 421 are sequentially distributed along the direction from the root to the tip of the rotor 10, and each heat dissipation fin 421 extends along the rotation path of the rotor 10, so that each heat dissipation fin 421 can make full use of the downwash airflow of the rotor 10 to achieve air cooling and heat dissipation, further improve the heat dissipation efficiency and heat dissipation effect, and improve the heat dissipation uniformity. Furthermore, an oil passage is formed in each heat dissipation fin 421, and both ends of each oil passage are connected to the oil inlet and the oil outlet, so that the cooling oil entering the oil cooler 42 can be divided into a plurality of branches and pass through a plurality of different oil passages, respectively, so that each heat dissipation fin 421 can fully dissipate the cooling oil in its oil passage, thereby greatly improving the heat dissipation efficiency, heat dissipation effect and heat dissipation uniformity of the oil cooler 42.

[0047] In one embodiment, any two adjacent heat dissipation fins 421 are spaced apart to form a heat dissipation channel 422 extending along the rotation path of the rotor 10. Multiple heat dissipation fins 421 are spaced apart in sequence along the direction from the blade root to the blade tip of the rotor 10, so that a heat dissipation channel 422 is formed between any two adjacent heat dissipation fins 421, which is conducive to the heat dissipation from the heat dissipation channel 422, and avoids the situation where the two heat dissipation fins 421 abut against each other and interfere with each other, which is not conducive to heat dissipation. Moreover, the heat dissipation channel 422 extends along the rotation path of the rotor 10, so as to make full use of the downwash airflow of the rotor 10 for heat dissipation. In a preferred embodiment, multiple heat dissipation fins 421 are spaced apart evenly along the direction from the blade root to the blade tip of the rotor 10, so as to further improve the heat dissipation uniformity of the oil cooler 42.

[0048] In one embodiment, each heat dissipation fin 421 is arranged vertically to improve the compactness of the structure. Compared with the heat dissipation fin 421 arranged horizontally or in other directions, the heat dissipation fin 421 is arranged vertically to reduce the space occupied in the direction from the root to the tip of the rotor 10, so that a large number of heat dissipation fins 421 can be arranged under the rotor 10, thereby improving the heat dissipation efficiency and heat dissipation effect.

[0049] In one embodiment, the oil cooler 42 also includes a first oil collecting cylinder 423 and a second oil collecting cylinder 424, which are installed on the mounting base 41, the first oil collecting cylinder 423 is provided with an oil inlet, and the second oil collecting cylinder 424 is provided with an oil outlet, and both ends of each heat dissipating fin 421 are respectively connected to the first oil collecting cylinder 423 and the second oil collecting cylinder 424, and the oil passage connects the first oil collecting cylinder 423 and the second oil collecting cylinder 424.

[0050] like Figure 3 As shown, the two ends of the oil cooler 42 are provided with a first oil collecting barrel 423 and a second oil collecting barrel 424, respectively. By providing the first oil collecting barrel 423, it is convenient to collect the cooling oil sent into the first oil collecting barrel 423 through the oil inlet by the oil delivery pipe 44, and divide it into multiple branches and distribute it to multiple oil passages for heat dissipation, thereby realizing the centralized distribution of the cooling oil, avoiding the situation where the cooling oil is concentrated in some oil passages while other oil passages are not oiled, and improving the adequacy and uniformity of heat dissipation. The cooling oil after heat dissipation through multiple oil passages is uniformly collected by the second oil collecting barrel 424 and then sent back to the flight drive assembly from the return oil pipe 45 through the oil outlet, thereby realizing the smooth circulation of the circulating oil circuit.

[0051] In one embodiment, the oil inlet is connected to the oil delivery pipe 44 through an oil inlet pipe 425, and the oil outlet is connected to the oil return pipe 45 through an oil outlet pipe 426, so that the circulating oil circuit assembly is realized by connecting the pipelines to each other, which is simple, convenient and easy to assemble. Specifically, the oil inlet pipe 425 and the oil delivery pipe 44, the oil delivery pipe 44 and the flight electric drive assembly 20, the oil outlet pipe 426 and the oil return pipe 45, and the oil return pipe 45 and the flight electric drive assembly 20 are all connected by a clamp 50, which is simple and convenient.

[0052] like Figure 2 and Figure 3 As shown, in one embodiment, the heat dissipation extension area 43 is fan-shaped. The fan-shaped heat dissipation extension area 43 has a high compact structure while achieving effective heat dissipation, and has the advantages of small space occupation and light weight.

[0053] In another embodiment, the heat dissipation extension area 43 is semi-annular. Compared with the fan-shaped heat dissipation extension area 43, the semi-annular heat dissipation extension area 43 can increase its heat dissipation area and improve the heat dissipation effect.

[0054] In other embodiments, the heat dissipation extension zone 43 is in the shape of a ring, that is, the heat dissipation extension zone 43 can form a ring-shaped structure connected head to tail, covering the entire rotation path of the rotor 10, so as to maximize the use of the downwash airflow of the rotor 10 and achieve maximum heat dissipation efficiency, heat dissipation effect and heat dissipation uniformity.

[0055] In addition, the heat dissipation extension area 43, which is configured to be fan-shaped, semi-circular or circular, has a high degree of matching with the appearance of the flight electric drive assembly 20 and has the advantage of beautiful appearance.

[0056] The shape of the heat dissipation extension area 43 of the present invention can be flexibly set according to actual conditions, and it is only necessary to use the downwash airflow of the rotor 10 in a better way to dissipate heat. The present invention does not limit the shape of the heat dissipation extension area 43.

[0057] In one embodiment, the rotation path of the rotor 10 forms a rotation zone, and the rotation zone covers at least part of the heat dissipation extension zone 43. That is, the vertical projection of the rotation zone overlaps with the vertical projection of at least part of the heat dissipation extension zone 43, and at least part of the heat dissipation extension zone 43 is located directly below the rotation zone, and the distance between the two is relatively close. The downwash airflow of the rotor 10 can be directly blown to the heat dissipation extension zone 43, with small flow resistance, improving the air cooling effect, and further improving the utilization of the downwash airflow of the rotor 10 by the heat dissipation structure 40.

[0058] Furthermore, the rotating zone fully covers the heat dissipation extension zone 43, that is, the vertical projection of the heat dissipation extension zone 43 completely overlaps with the vertical projection of the rotating zone, and the entire heat dissipation extension zone 43 is located directly below the rotating zone, which can directly and fully utilize the downwash airflow of the rotor 10, thereby greatly improving the heat dissipation effect of the heat dissipation structure 40.

[0059] It should be noted that the heat dissipation structure 40 can flexibly adjust its installation position according to actual needs, and can be installed on the flight electric drive assembly 20 or the aircraft arm 30. The mounting seat 41 of the heat dissipation structure 40 can be fixed to the flight electric drive assembly 20 or the aircraft arm 30 by screwing, welding, riveting, etc. The heat dissipation structure 40 in the heat dissipation system 100 of the present invention can be directly installed on the flight electric drive assembly 20, or installed on the aircraft arm 30 near the flight electric drive assembly 20, with a reasonable layout, a high degree of integration, improved structural compactness, and reduced space occupancy.

[0060] In one embodiment, the heat dissipation structure 40 is installed on the windward side of the flight electric drive assembly 20, so as to fully utilize the downwash airflow of the rotor 10, and the structural design is reasonable. In another embodiment, the heat dissipation structure 40 is installed on the windward side of the arm 30, which can also fully utilize the downwash airflow of the rotor 10, and the structural design is reasonable.

[0061] It should be noted that, compared with the existing electric drive external cooling system 100, the cooling system 100 of the present invention reduces parts such as water pumps, kettles, cooling pipe assemblies, saves about 40% of development costs, and reduces weight by more than 77%, which has obvious advantages.

[0062] The present invention further proposes a flying structure, which includes a flying body and the above-mentioned heat dissipation system 100, and the arm 30 is connected to the flying body. The flying structure can be a flying vehicle or other flying structure with a rotor 10, such as a drone. The specific structure of the heat dissipation system 100 in the flying structure refers to the above-mentioned embodiment. Since the present flying structure adopts all the technical solutions of all the above-mentioned embodiments, it has at least all the beneficial effects brought by the technical solutions of the above-mentioned embodiments, which will not be repeated here one by one.

[0063] In a preferred embodiment, the flying structure is a flying vehicle, and the flying main body is the body of the flying vehicle. It can be understood that the end of the arm 30 in the heat dissipation system 100 away from the flying electric drive assembly 20 can be connected to the body of the flying vehicle to achieve the assembly of the heat dissipation system 100 and the body. By applying the heat dissipation system 100 to the flying vehicle, the heat generated by the flying electric drive assembly in the flying car is fully and effectively dissipated, and the total weight of the flying vehicle is reduced and the cost is reduced.

[0064] The above are only preferred embodiments of the present invention, and are not intended to limit the patent scope of the present invention. All equivalent structural changes made using the contents of the present invention's specification and drawings, or directly / indirectly applied in other related technical fields, are included in the patent protection scope of the present invention.

Claims

1. A heat dissipation system, characterized in that: The heat dissipation system comprises: Rotor; A flight electric drive assembly, the flight electric drive assembly is located below the rotor and is used to drive the rotor to rotate; A machine arm, the machine arm being connected to the flight electric drive assembly; A heat dissipation structure, wherein the heat dissipation structure is installed on the flight electric drive assembly or the aircraft arm, and the heat dissipation structure is located below the rotor. The flight electric drive assembly can exchange heat with the heat dissipation structure; the heat dissipation structure has a heat dissipation extension area, and the heat dissipation extension area extends along the rotation path of the rotor and extends from the blade root to the blade tip of the rotor. The downwash airflow of the rotor passes through the heat dissipation extension area.

2. The heat dissipation system according to claim 1, characterized in that: The heat dissipation structure comprises: A mounting seat, the mounting seat being mounted on the flight electric drive assembly or the aircraft arm; An oil cooler is installed on the mounting seat, the oil cooler and the flight electric drive assembly are interconnected to form a circulating oil circuit, and the oil cooler has the heat dissipation extension area.

3. The heat dissipation system according to claim 2, characterized in that: The heat dissipation structure also includes an oil supply pipe and an oil return pipe. The oil outlet end of the flight electric drive assembly is connected to the oil inlet of the oil cooler through the oil supply pipe, and the oil inlet end of the flight electric drive assembly is connected to the oil outlet of the oil cooler through the oil return pipe, so as to form the circulating oil circuit between the oil cooler and the flight electric drive assembly.

4. The heat dissipation system according to claim 2, characterized in that: The oil cooler includes a plurality of cooling fins, which form the cooling extension zone. The plurality of cooling fins are sequentially distributed along the direction from the blade root to the blade tip of the rotor. Each cooling fin extends along the rotation path of the rotor, and an oil passage connecting the oil inlet and the oil outlet is formed in each cooling fin.

5. The heat dissipation system according to claim 4, characterized in that: Any two adjacent heat dissipation fins are spaced apart to form a heat dissipation channel extending along the rotation path of the rotor.

6. The heat dissipation system according to claim 4, characterized in that: Each of the heat dissipation fins is arranged vertically.

7. The heat dissipation system according to claim 4, characterized in that: The oil cooler also includes a first oil collecting cylinder and a second oil collecting cylinder, the first oil collecting cylinder and the second oil collecting cylinder are installed on the mounting seat, the first oil collecting cylinder is provided with the oil inlet, the second oil collecting cylinder is provided with the oil outlet, both ends of each of the heat dissipating fins are respectively connected to the first oil collecting cylinder and the second oil collecting cylinder, and the oil passage connects the first oil collecting cylinder and the second oil collecting cylinder.

8. The heat dissipation system according to claim 3, characterized in that: The oil inlet is communicated with the oil delivery pipe through an oil inlet pipe, and the oil outlet is communicated with the oil return pipe through an oil outlet pipe.

9. The heat dissipation system according to any one of claims 1 to 8, characterized in that: The heat dissipation extension area is fan-shaped, semi-annular or circular.

10. The heat dissipation system according to any one of claims 1 to 8, characterized in that: The rotation path of the rotor forms a rotation zone, and the rotation zone covers at least a portion of the heat dissipation extension zone.

11. The heat dissipation system according to claim 10, characterized in that: The rotating area fully covers the heat dissipation extension area.

12. The heat dissipation system according to any one of claims 1 to 8, characterized in that: The heat dissipation structure is installed on the windward side of the flight electric drive assembly or the windward side of the aircraft arm.

13. A flying structure, characterized in that: The flight structure comprises a flight body and a heat dissipation system as claimed in any one of claims 1 to 12, and the aircraft arm is connected to the flight body.

14. The flying structure according to claim 13, characterized in that The flying structure is a flying vehicle, and the flying subject is a body of the flying vehicle.

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