Vertical power module heat dissipation device, vertical power module and aircraft

Abstract

The utility model provides a vertical power module heat dissipation device, a vertical power module and an aircraft, and belongs to the technical field of aircrafts, and the heat dissipation device comprises a heat exchanger fairing and a heat exchanger; the heat exchanger fairing is in a streamline shape with two sharp ends and a wide middle, the two ends of the heat exchanger fairing are fixedly arranged on the power arm body, and heat exchanger heat dissipation openings are formed in the top of the heat exchanger fairing and located below the forward-rotating propeller and the reverse-rotating propeller. Driving motor modules of the forward-rotating propellers and the reverse-rotating propellers are located in the heat exchanger fairing, and heat exchanger heat dissipation channels are formed between the inner side wall of the heat exchanger fairing and the two sides of the top of the power arm body; the heat exchanger is arranged in the heat exchanger fairing, and heat dissipation fins of the heat exchanger are arranged at heat dissipation openings of the heat exchanger; and a hot liquid inlet and a cold liquid outlet of the heat exchanger are respectively connected with a cooling liquid outlet pipe and a cooling liquid inlet pipe of the driving motor module. The problem that in the prior art, a heat dissipation structure is arranged outside a power arm, and flight resistance is caused to cruise flight of an aircraft can be solved.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, and more specifically, to a vertical lift power module heat dissipation device, a vertical lift power module and an aircraft. Background Art

[0002] EVTOL (Electric Vertical Take-Off and Landing) is a new type of aircraft that stems from the demand for efficient, convenient, green and clean urban air transportation. Traditional helicopters have problems such as high noise, high cost and complex operation. EVTOL combines electric technology and uses electric drive to reduce noise and operation and maintenance costs. With its vertical take-off and landing capabilities, it does not require a dedicated runway and can take off and land in confined spaces. It integrates technologies from multiple fields such as aviation, electrical and intelligent control, providing new solutions for urban air travel, logistics, emergency rescue and other scenarios, and has a wide range of application scenarios.

[0003] Because large EVs are powered by high-power electric motors, they are not suitable for natural heat dissipation. Therefore, the main cooling solutions currently available are air cooling and liquid cooling. Air cooling typically involves designing cooling fins on the motor, which remove heat through propellers or installing additional cooling fans. Liquid cooling is more direct and efficient, as the coolant directly contacts the areas with the highest heat generation, transferring the heat through cooling pipes to a heat exchanger for heat dissipation.

[0004] The typical cooling method currently used in vertical take-off power modules involves exposing cooling fins or fans to the outside of the power arm, using airflow through the fins or introduced by the fans to achieve heat exchange. This cooling method creates a certain amount of flight resistance during cruising flight and has low heat exchange efficiency. Utility Model Content

[0005] In view of the above problems, the purpose of the present invention is to provide a vertical power module heat dissipation device, a vertical power module and an aircraft, so as to solve the problem in the prior art that the heat dissipation fins or the heat dissipation fan need to be exposed to the outside of the power arm to achieve the purpose of heat exchange by using the air flow through the fins or the air flow introduced by the heat dissipation fan, which will cause certain flight resistance when the aircraft is cruising and the heat exchange efficiency is low.

[0006] The utility model provides a vertical power module heat dissipation device, comprising a heat exchanger fairing and a heat exchanger; wherein,

[0007] The heat exchanger fairing is in a streamlined shape with pointed ends and a wide middle. Both ends of the heat exchanger fairing are fixed to the power arm body. A heat exchanger heat dissipation port is provided at the top of the heat exchanger fairing, below the forward-rotating propeller and the reverse-rotating propeller. The drive motor modules of the forward-rotating propeller and the reverse-rotating propeller are both located inside the heat exchanger fairing. A heat exchanger heat dissipation channel is formed between the inner side wall of the heat exchanger fairing and both sides of the top of the power arm body.

[0008] The heat exchanger is arranged inside the heat exchanger fairing, and the heat dissipation fins of the heat exchanger are arranged at the heat dissipation port of the heat exchanger;

[0009] The hot liquid inlet and the cold liquid outlet of the heat exchanger are respectively connected to the coolant outlet pipe and the coolant inlet pipe of the drive motor module through the coolant conduit;

[0010] The coolant conduit and the coolant outlet pipe of the drive motor module and the coolant inlet pipe of the drive motor module are both connected through a sleeve-type pipe joint.

[0011] In addition, a preferred solution is that the middle part of the heat exchanger fairing is located between the forward-rotating propeller and the reverse-rotating propeller; the heat exchanger heat dissipation port is arranged in the middle part of the heat exchanger fairing; through holes for the forward-rotating propeller and the reverse-rotating propeller to pass through are respectively provided at the top of both ends of the heat exchanger fairing; the forward-rotating propeller and the reverse-rotating propeller are located above the top of the heat exchanger fairing.

[0012] In addition, a preferred solution is that the heat exchanger fairing is fixedly mounted on the power arm body through a heat exchanger fairing mounting bracket; wherein, the bottom end of the heat exchanger fairing mounting bracket is fixed on the reinforcing rib of the power arm body; and the inner side wall of the heat exchanger fairing is detachably fixedly mounted on the upper part of the heat exchanger fairing mounting bracket.

[0013] In addition, a preferred solution is that the heat exchanger heat dissipation port includes a first heat exchanger heat dissipation port arranged directly below the forward-rotating propeller and a second heat exchanger heat dissipation port arranged directly below the counter-rotating propeller.

[0014] In addition, a preferred solution is that the heat exchanger is fixed to the top of the power arm body through a heat exchanger mounting bracket; the bottom end of the heat exchanger mounting bracket is fixed to the top of the power arm body, and the heat exchanger is detachably fixed to the top of the heat exchanger mounting bracket.

[0015] In addition, a preferred solution is that the driving motor module of the forward-rotating propeller is fixed on the top of the power arm body; and / or the driving motor module of the reverse-rotating propeller is fixed on the top of the power arm body.

[0016] In addition, a preferred solution is that the bottom end of the forward-rotating propeller and the bottom end of the counter-rotating propeller are both mounted on the drive motor module through a propeller mounting base.

[0017] In addition, a preferred solution is that a power arm inspection port is provided on the power arm body; and a power arm inspection port cover is provided at the power arm inspection port.

[0018] The present utility model also provides an aircraft vertical take-off power module, comprising a vertical take-off power module body, on which the vertical take-off power module heat dissipation device as described above is arranged.

[0019] The utility model also provides an electric vertical take-off and landing aircraft, comprising an aircraft body, a vertical take-off power module being arranged on the aircraft body, and the vertical take-off power module heat dissipation device as described above being arranged on the vertical take-off power module.

[0020] From the above technical solutions, it can be seen that the vertical lift power module heat dissipation device, vertical lift power module and aircraft provided by the present invention, through the structural design of the heat exchanger fairing and the heat exchanger, the heat exchanger is arranged inside the heat exchanger fairing, and the heat exchanger's heat dissipation fins are arranged at the heat exchanger heat dissipation port of the heat exchanger fairing, so that the heat dissipation fins do not protrude from the surface of the power arm body, and the heat exchanger fairing is a streamlined shape with pointed ends and wide in the middle, which can effectively reduce the resistance of the aircraft during cruising flight; combined with the aerodynamic layout characteristics of the electric vertical take-off and landing aircraft, the heat exchanger heat dissipation port is arranged below the propeller, and the cold air flow generated by the rotation of the propeller during vertical take-off and landing phases flows through the heat exchanger's heat dissipation fins for heat dissipation, and the hot air after heat exchange is discharged from the outside of the power arm through the heat exchanger heat dissipation channel formed between the inner side wall of the heat exchanger fairing and the top two sides of the power arm body, thereby achieving the purpose of heat dissipation and ensuring the heat exchange efficiency of the heat exchanger during the vertical take-off and landing phase. In summary, the present invention has the advantages of high heat exchange efficiency, low cruising resistance, and light structural weight. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] By referring to the following description in conjunction with the accompanying drawings, and with a more comprehensive understanding of the present invention, other objects and results of the present invention will become more clear and easy to understand.

[0022] Figure 1 This is a schematic diagram of the external structure of the heat dissipation device for a vertical power module according to an embodiment of the present utility model;

[0023] Figure 2 This is a schematic diagram of the internal structure of the heat dissipation device for a vertical lift power module according to an embodiment of the present utility model;

[0024] Figure 3This is a schematic diagram of the heat dissipation device for a vertical lift power module according to an embodiment of the present invention;

[0025] Figure 4 This is a side internal schematic diagram of a heat dissipation device for a vertical power module according to an embodiment of the present invention;

[0026] Figure 5 The figure is a heat dissipation flow chart of an aircraft vertical take-off power module using an embodiment of the present utility model.

[0027] In the accompanying drawings, 1-heat exchanger fairing, 111-first heat exchanger heat dissipation port, 112-second heat exchanger heat dissipation port, 12-heat exchanger fairing mounting bracket, 2-heat exchanger, 21-heating fins, 22-heat exchanger mounting bracket, 3-power arm body, 31-reinforcement ribs, 32-power arm inspection cover, 41-forward-rotating propeller, 42-reverse-rotating propeller, 5-propeller mounting base, 6-drive motor module, 7-heat exchanger heat dissipation channel, 8-coolant duct.

[0028] The same reference numerals throughout the drawings indicate similar or corresponding features or functions. DETAILED DESCRIPTION

[0029] In the following description, for purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of one or more embodiments. However, it will be apparent that these embodiments may be practiced without these specific details.

[0030] In response to the above-mentioned existing technologies, it is necessary to expose the cooling fins or cooling fans to the outside of the power arm to achieve the purpose of heat exchange by using the air flow passing through the fins or using the air flow introduced by the cooling fan, which will cause certain flight resistance when the aircraft is cruising and the heat exchange efficiency is low. A vertical power module heat dissipation device, a vertical power module and an aircraft are proposed.

[0031] The specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0032] In order to illustrate the vertical lift power module heat dissipation device, vertical lift power module and aircraft provided by the present invention, Figure 1 The external structure of the heat dissipation device for a vertical power module according to an embodiment of the present utility model is shown; Figure 2 The internal structure of the heat dissipation device for a vertical power module according to an embodiment of the present utility model is shown; Figure 3 The schematic structure of the heat dissipation device for a vertical power module according to an embodiment of the present utility model is shown; Figure 4 The figure shows the lateral internal structure of the heat dissipation device of the vertical power module according to an embodiment of the present utility model; Figure 5 The heat dissipation process of the aircraft vertical take-off power module using the embodiment of the utility model is shown.

[0033] like Figures 1 to 4 As shown together, the vertical power module heat dissipation device provided by the present invention includes a heat exchanger fairing 1 and a heat exchanger 2; wherein,

[0034] The heat exchanger fairing 1 has a streamlined shape with pointed ends and a wide center. Both ends of the heat exchanger fairing 1 are fixed to the power arm body 3. A heat exchanger heat dissipation port is provided at the top of the heat exchanger fairing 1, below the forward-rotating propeller 41 and the reverse-rotating propeller 42. The drive motor modules 6 of the forward-rotating propeller 41 and the reverse-rotating propeller 42 are both located inside the heat exchanger fairing 1. A heat exchanger heat dissipation channel 7 is formed between the inner side wall of the heat exchanger fairing 1 and the two sides of the top of the power arm body 3.

[0035] The heat exchanger 2 is arranged inside the heat exchanger fairing 1, and the heat dissipation fins 21 of the heat exchanger 2 are arranged at the heat dissipation port of the heat exchanger;

[0036] The hot liquid inlet and cold liquid outlet of the heat exchanger 2 are connected to the coolant outlet pipe and coolant inlet pipe of the drive motor module 6 respectively through the coolant conduit 8;

[0037] The coolant conduit 8 and the coolant outlet pipe of the drive motor module 6 and the coolant conduit 8 and the coolant inlet pipe of the drive motor module 6 are both connected through a sleeve-type pipe joint.

[0038] Among them, the power arm in the present invention refers to a component that connects the power unit (such as a motor and a propeller, etc.) with the main structure of the aircraft.

[0039] It should be noted that the use of coolant for liquid cooling in the drive motor module 6 is prior art. Specifically, the heat dissipation structure of the coolant in the drive motor module 6 in the present invention is prior art. Coolant enters the drive motor module 6 through the coolant inlet pipe, cools the heat-generating area, and then flows out of the coolant outlet pipe. Coolant delivery is achieved by a mechanical gear pump driven by the rotation of the motor. Since this is prior art, the specific structure of this part will not be described in detail in the present invention.

[0040] The coolant is pumped to the heat exchanger 2 by a mechanical gear pump driven by the rotation of the motor in the drive motor module 6, cleverly linking the coolant flow rate with the motor speed. The faster the motor speed, the higher the power and the faster the coolant is pumped. Conversely, when the motor speed is slow or even stops, the coolant pumping speed can also be reduced.

[0041] The heat dissipation fins 21 on the top of the heat exchanger 2 are arranged at the heat dissipation port of the heat exchanger, and the heat dissipation fins 21 at the end are located in the heat dissipation channel 7 of the heat exchanger.

[0042] Through the structural design of the heat exchanger fairing 1 and the heat exchanger 2, the heat exchanger 2 is arranged inside the heat exchanger fairing 1, and the heat exchanger fins 21 of the heat exchanger 2 are arranged at the heat exchanger heat dissipation port of the heat exchanger fairing 1, so that the heat exchanger fins 21 do not protrude from the surface of the power arm body 3. The heat exchanger fairing 1 has a streamlined shape with pointed ends and wide center, which can effectively reduce the resistance of the aircraft during cruising flight. In combination with the aerodynamic layout characteristics of the electric vertical take-off and landing aircraft, the heat exchanger heat dissipation port is arranged below the propeller. The cold air generated by the rotation of the propeller during vertical take-off and landing phases flows through the heat exchanger fins 21 of the heat exchanger 2 to dissipate heat. The hot air after heat exchange is discharged to the outside of the power arm through the heat exchanger heat dissipation channel 7 formed between the inner side wall of the heat exchanger fairing 1 and the top two sides of the power arm body 3, thereby achieving the purpose of heat dissipation and ensuring the heat exchange efficiency of the heat exchanger during vertical take-off and landing. The utility model has the advantages of high heat exchange efficiency, low cruising resistance, and light structure weight.

[0043] As a preferred embodiment of the present invention, the middle part of the heat exchanger fairing 1 is located between the forward-rotating propeller 41 and the reverse-rotating propeller 42; the heat exchanger heat dissipation port is arranged in the middle part of the heat exchanger fairing 1; through holes for the forward-rotating propeller 41 and the reverse-rotating propeller 42 to pass through are respectively provided at the top of both ends of the heat exchanger fairing 1; the forward-rotating propeller 41 and the reverse-rotating propeller 42 are located above the top of the heat exchanger fairing 1.

[0044] Specifically, the middle part of the heat exchanger fairing 1 is located between the forward-rotating propeller 41 and the reverse-rotating propeller 42, and the heat exchanger heat dissipation port is arranged in the middle part of the heat exchanger fairing 1, which has a better heat dissipation effect on the heat exchanger 2. By respectively providing through holes for the forward-rotating propeller 41 and the reverse-rotating propeller 42 to pass through at the top of both ends of the heat exchanger fairing 1, it is convenient to position the forward-rotating propeller 41 and the reverse-rotating propeller 42 above the top of the heat exchanger fairing 1 without affecting the normal operation of the forward-rotating propeller 41 and the reverse-rotating propeller 42.

[0045] As a preferred solution of the present invention, the heat exchanger fairing 1 is fixedly mounted on the power arm body 3 through the heat exchanger fairing mounting bracket 12; wherein, the bottom end of the heat exchanger fairing mounting bracket 12 is fixed on the reinforcing rib 31 of the power arm body 3; the inner side wall of the heat exchanger fairing 1 is detachably fixedly mounted on the upper part of the heat exchanger fairing mounting bracket 12.

[0046] Specifically, reinforcing ribs 31 are provided along both sides of the top of the power arm body 3. The heat exchanger fairing mounting bracket 12 is preferably, but not limited to, fixed to the reinforcing ribs 31 by welding. The top of the power arm body 3 is a smooth curved surface, which forms a heat exchanger heat dissipation channel 7 between the curved surface formed by the inner sidewall of the heat exchanger fairing 1. The inner sidewall of the heat exchanger fairing 1 is preferably, but not limited to, detachably fixed to the heat exchanger fairing mounting bracket 12 by detachable fasteners such as bolts, facilitating installation and removal.

[0047] As a preferred solution of the present invention, the heat exchanger heat dissipation port includes a first heat exchanger heat dissipation port 111 arranged directly below the forward-rotating propeller 41 and a second heat exchanger heat dissipation port 112 arranged directly below the reverse-rotating propeller 42 .

[0048] Specifically, heat exchanger vents are provided below the forward-rotating propeller 41 and the counter-rotating propeller 42, respectively, and a heat exchanger 2 is installed corresponding to each heat exchanger vent. That is, each propeller has two drive motor modules 6, and a heat exchanger 2 is provided for each drive motor module of the forward-rotating propeller 41 and the counter-rotating propeller 42. The provision of two heat exchanger vents corresponding to the two heat exchangers 2 improves heat exchange and heat dissipation. Of course, the drive motor modules of the forward-rotating propeller 41 and the counter-rotating propeller 42 can also share a single heat exchanger 2, and this is not particularly limited in the present invention.

[0049] As a preferred solution of the present invention, the heat exchanger 2 is fixed to the top of the power arm body 3 through the heat exchanger mounting bracket 22; the bottom end of the heat exchanger mounting bracket 22 is fixed to the top of the power arm body 3, and the heat exchanger 2 is detachably fixed to the top of the heat exchanger mounting bracket 22.

[0050] Specifically, the heat exchanger mounting bracket 22 is preferably but not limited to being fixed to the top of the power arm body 3 by welding, and the heat exchanger 2 is preferably but not limited to being detachably fixed to the top of the heat exchanger mounting bracket 22 by detachable parts such as bolts, so as to facilitate disassembly and maintenance of the heat exchanger 2.

[0051] As a preferred solution of the present invention, the driving motor module 6 of the forward-rotating propeller 41 is fixed on the top of the power arm body 3; and / or the driving motor module 6 of the reverse-rotating propeller 42 is fixed on the top of the power arm body 3.

[0052] Specifically, the driving motor modules 6 of the forward-rotating propellers 41 and the reverse-rotating propellers 42 are preferably, but not limited to, fixed to the top of the power arm body 3 by means of bolts or the like, so as to facilitate the disassembly and replacement of components.

[0053] As a preferred solution of the present invention, the bottom ends of the forward-rotating propeller 41 and the reverse-rotating propeller 42 are both mounted on the drive motor module 6 via the propeller mounting base 5 .

[0054] The propeller mounting base 5 facilitates the installation of the forward and reverse rotating propellers on the corresponding drive motor modules 6 .

[0055] As a preferred solution of the present invention, a power arm maintenance port is provided on the power arm body 3; a power arm maintenance port cover 32 is provided at the power arm maintenance port to facilitate maintenance work inside the power arm body 3.

[0056] like Figure 5 As shown, the vertical lift power module heat dissipation device of the present invention is used to dissipate heat from the vertical lift power module, including the following steps:

[0057] Step S1: When the aircraft is preparing for vertical takeoff or vertical landing, the carrier aircraft sends a start command to the drive motor module 6 of the forward-rotating propeller 41 and the reverse-rotating propeller 42;

[0058] In step S2, the drive motor module 6 of the forward-rotating propeller 41 and the reverse-rotating propeller 42 starts to operate according to the start-up instruction, thereby driving the forward-rotating propeller 41 and the reverse-rotating propeller 42 to rotate. When the drive motor module 6 is operating, the motor drives the gear pump inside the drive motor module 6 to rotate, thereby pumping coolant to cool the drive motor module 6.

[0059] Step S3: Inside the driving motor module 6, the coolant with a higher temperature after cooling enters the heat exchanger 2 through the coolant conduit 8, and after heat exchange in the heat exchanger 2, circulates back to the coolant inlet pipe of the driving motor module 6 through the coolant conduit 8;

[0060] In step S4 , the forward-rotating propeller 41 and the reverse-rotating propeller 42 rotate to generate a downward airflow, which takes away the heat generated by the heat exchanger 2 exchanging heat with the coolant of the drive motor module 6 through the heat exchanger heat dissipation port and discharges it from the heat exchanger heat dissipation channel 7 .

[0061] It should be noted that the forward-rotating propeller 41 and the reverse-rotating propeller 42 each correspond to a respective driving motor module 6 .

[0062] The aircraft vertical take-off power module provided by the present invention comprises a vertical take-off power module body, on which the vertical take-off power module heat dissipation device as described above is provided.

[0063] Among them, the vertical power module body refers to the power structure including the power arm and propeller, etc. This is the existing technology and will not be described in detail.

[0064] The electric vertical take-off and landing aircraft provided by the present invention includes an aircraft body, a vertical take-off power module is arranged on the aircraft body, and the vertical take-off power module heat dissipation device of the present invention as described above is arranged on the vertical take-off power module.

[0065] The installation process of the vertical lift power module heat dissipation device provided by the utility model on the aircraft body is as follows:

[0066] First, assemble the motor mounting base of the drive motor module 6 on the reinforcing rib 31 of the power arm body 3, and then install the corresponding propeller mounting base 5, drive motor module 6, heat exchanger fairing mounting bracket 12, and heat exchanger mounting bracket 22 in sequence, then install the heat exchanger 2, connect the coolant conduit 8, connect the heat exchanger fairing 1 and the heat exchanger fairing mounting bracket 12 with bolts, and finally install the forward-rotating propeller 41 and the reverse-rotating propeller 42.

[0067] It can be seen from the above specific embodiments that the vertical lift power module heat dissipation device, vertical lift power module and aircraft provided by the present invention, through the structural design of the heat exchanger fairing and the heat exchanger, the heat exchanger is arranged inside the heat exchanger fairing, and the heat exchanger's heat dissipation fins are arranged at the heat exchanger heat dissipation port of the heat exchanger fairing, so that the heat dissipation fins do not protrude from the surface of the power arm body, and the heat exchanger fairing is a streamlined shape with pointed ends and wide in the middle, which can effectively reduce the resistance of the aircraft during cruising flight; combined with the aerodynamic layout characteristics of the electric vertical take-off and landing aircraft, the heat exchanger heat dissipation port is arranged below the propeller, and the cold air flow generated by the rotation of the propeller during vertical take-off and landing phases flows through the heat exchanger's heat dissipation fins for heat dissipation, and the hot air after heat exchange is discharged from the outside of the power arm through the heat exchanger heat dissipation channel formed between the inner side wall of the heat exchanger fairing and the top two sides of the power arm body, thereby achieving the purpose of heat dissipation and ensuring the heat exchange efficiency of the heat exchanger during the vertical take-off and landing phase. In summary, the present invention has the advantages of high heat exchange efficiency, low cruising resistance, and light structural weight.

[0068] The vertical lift power module heat dissipation device, vertical lift power module, and aircraft according to the present invention have been described above by way of example with reference to the accompanying drawings. However, those skilled in the art will appreciate that various improvements may be made to the vertical lift power module heat dissipation device, vertical lift power module, and aircraft described above without departing from the scope of the present invention. Therefore, the scope of protection of the present invention shall be determined by the appended claims.

Claims

1. A heat dissipation device for a vertical power module, characterized in that: It includes a heat exchanger fairing and a heat exchanger; wherein, The heat exchanger fairing is in a streamlined shape with pointed ends and a wide middle. Both ends of the heat exchanger fairing are fixed to the power arm body. A heat exchanger heat dissipation port is provided at the top of the heat exchanger fairing, below the forward-rotating propeller and the reverse-rotating propeller. The drive motor modules of the forward-rotating propeller and the reverse-rotating propeller are both located inside the heat exchanger fairing. A heat exchanger heat dissipation channel is formed between the inner side wall of the heat exchanger fairing and both sides of the top of the power arm body. The heat exchanger is arranged inside the heat exchanger fairing, and the heat dissipation fins of the heat exchanger are arranged at the heat dissipation port of the heat exchanger; The hot liquid inlet and the cold liquid outlet of the heat exchanger are respectively connected to the coolant outlet pipe and the coolant inlet pipe of the drive motor module through the coolant conduit; The coolant conduit and the coolant outlet pipe of the drive motor module and the coolant inlet pipe of the drive motor module are both connected through a sleeve-type pipe joint.

2. The heat dissipation device for the vertical power module according to claim 1, characterized in that: The middle portion of the heat exchanger fairing is located between the forward-rotating propeller and the counter-rotating propeller; The heat exchanger heat dissipation port is arranged in the middle of the heat exchanger fairing; Through holes for the forward-rotating propeller and the reverse-rotating propeller to pass through are respectively provided on the tops of both ends of the heat exchanger fairing; the forward-rotating propeller and the reverse-rotating propeller are located above the top of the heat exchanger fairing.

3. The heat dissipation device for the vertical power module according to claim 1, characterized in that: The heat exchanger fairing is fixedly mounted on the power arm body through a heat exchanger fairing mounting bracket; wherein, The bottom end of the heat exchanger fairing mounting bracket is fixed to the reinforcing rib of the power arm body; The inner side wall of the heat exchanger fairing is detachably fixedly mounted on the upper portion of the heat exchanger fairing mounting bracket.

4. The heat dissipation device for a vertical power module according to claim 1, characterized in that: The heat exchanger heat dissipation port includes a first heat exchanger heat dissipation port arranged directly below the forward-rotating propeller and a second heat exchanger heat dissipation port arranged directly below the reverse-rotating propeller.

5. The heat dissipation device for a vertical power module according to claim 1, characterized in that: The heat exchanger is fixed to the top of the power arm body through a heat exchanger mounting bracket; The bottom end of the heat exchanger mounting bracket is fixed to the top of the power arm body, and the heat exchanger is detachably fixed to the top of the heat exchanger mounting bracket.

6. The heat dissipation device for a vertical power module according to claim 1, characterized in that: The driving motor module of the forward-rotating propeller is fixed on the top of the power arm body; and / or, The driving motor module of the counter-rotating propeller is fixed on the top of the power arm body.

7. The heat dissipation device for the vertical power module according to claim 6, characterized in that: The bottom ends of the forward-rotating propeller and the reverse-rotating propeller are both mounted on the drive motor module via a propeller mounting base.

8. The heat dissipation device for a vertical power module according to claim 1, characterized in that: A power arm inspection port is provided on the power arm body; A power arm inspection port cover is provided at the power arm inspection port.

9. A vertical power module, comprising a vertical power module body, characterized in that: The vertical power module is provided with a vertical power module heat dissipation device as described in any one of claims 1 to 8.

10. An aircraft, comprising an aircraft body, on which a vertical lift power module is provided, characterized in that: The vertical power module is provided with a vertical power module heat dissipation device according to any one of claims 1 to 8.

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