Tail section guide rotor module and rotorcraft

Abstract

The present application relates to a tail-section flow-guiding rotor module and a rotorcraft. The tail-section flow-guiding rotor module includes a cowling, an electric machine component, a gravity heat pipe component, an air propeller, and a flow-guiding tail wing. An air inlet is provided at one end of the cowling. The gravity heat pipe component is disposed at the end of the cowling close to the air inlet. The electric machine component is disposed on the side of the gravity heat pipe component away from the air inlet. The gravity heat pipe component can dissipate heat from the stator of the electric machine component. The rotor of the electric machine component can drive the air propeller to rotate. A flow-guiding channel extending along the axial direction of the air propeller is provided between the air propeller and the rotor of the electric machine component. The flow-guiding tail wing is disposed at the end of the cowling away from the air inlet. One end of the flow-guiding tail wing is connected to the cowling, and an air outlet is provided at the other end. The air flow sequentially passes through the air inlet, the gravity heat pipe component, the flow-guiding channel, the flow-guiding tail wing, and the air outlet. The tail-section flow-guiding rotor module and the rotorcraft provided by the present application solve the problem that it is difficult for a rotorcraft to balance the heat dissipation efficiency of the electric machine and the flight stability of the rotorcraft.

Description

Technical Field

[0001] This application relates to the technical field of rotary-wing flight devices, and particularly to a tail-section flow-guiding rotary-wing module and a rotary-wing aircraft. Background Art

[0002] As the uses of rotary-wing aircraft (including flying cars and drones) are increasing, the requirements for rotary-wing aircraft are also getting higher. For example, the load-carrying demand of rotary-wing aircraft is constantly increasing, and correspondingly, the power of the motor will also become larger. Thus, the heat generated by the motor will also double. Therefore, the heat dissipation of the motor is particularly important.

[0003] In order to improve the heat dissipation efficiency, in the prior art, the heat dissipation of the motor is generally carried out by the wind generated by the air propeller. In this way, although the heat dissipation efficiency can be improved to a certain extent, with such a setting, the air propeller needs to be arranged in front of the motor, that is, the overall setting position of the air propeller is relatively forward. At this time, it will cause the center of gravity of the entire rotary-wing module to be too forward, thereby affecting the flight stability of the rotary-wing aircraft. Summary of the Invention

[0004] Based on this, it is necessary to provide a tail-section flow-guiding rotary-wing module and a rotary-wing aircraft to solve the problem that the existing rotary-wing aircraft is difficult to balance the heat dissipation efficiency of the motor and the flight stability of the rotary-wing aircraft.

[0005] The tail-section flow-guiding rotary-wing module provided by this application includes a wind cover, a motor component, a gravity heat pipe component, an air propeller, and a flow-guiding tail wing. One end of the wind cover is provided with an air inlet. The gravity heat pipe component is arranged at one end of the wind cover close to the air inlet. The motor component is arranged on the side of the gravity heat pipe component away from the air inlet. The gravity heat pipe component can dissipate heat from the stator of the motor component. The air propeller is sleeved outside the rotor of the motor component so that the rotor of the motor component can drive the air propeller to rotate. And a flow-guiding channel extending along the axial direction of the air propeller is arranged between the air propeller and the rotor of the motor component. The flow-guiding tail wing is arranged at the end of the wind cover away from the air inlet. One end of the flow-guiding tail wing is connected to the wind cover, and the other end is provided with an air outlet. The air flow can sequentially pass through the air inlet, the gravity heat pipe component, the flow-guiding channel, the flow-guiding tail wing, and the air outlet.

[0006] In one embodiment, the distance A between the air propeller and the air outlet, and the distance B between the air propeller and the air inlet satisfy 0.8 ≤ A / B ≤ 1.2.

[0007] In one embodiment, A / B = 1.

[0008] In one embodiment, the cavity region between the wind hood and the motor component is defined as the first channel, and the cavity region between the wind hood and the guide vane is defined as the second channel. The flow area of the guide channel is smaller than the flow area of the first channel near the guide channel end, and the flow area of the guide channel is smaller than the flow area of the second channel near the guide channel end.

[0009] In one embodiment, along the direction from the motor component to the guide vane, the flow area of the second channel shows a decreasing trend.

[0010] In one embodiment, the tail-section guide vane type rotor module further includes a power fan. The power fan is arranged in the guide channel and fixedly sleeved on the outer periphery of the rotor of the motor component, so that the rotor of the motor component can drive the power fan to rotate, and the guide channel can generate an air flow flowing from the gravity heat pipe component to the guide vane.

[0011] In one embodiment, the guide vane includes a plurality of vanes arranged around the axis of the wind hood. Each vane extends along the axial direction of the wind hood, and adjacent vanes are arranged at intervals to form a guide groove.

[0012] In one embodiment, tooth-shaped protrusions are provided at the air outlet. One end of the tooth-shaped protrusion is connected to the guide vane, and the other end extends along the axial direction of the air paddle. Along the direction from the air inlet to the air outlet, the cross-sectional area of the tooth-shaped protrusion shows a decreasing trend, and a plurality of tooth-shaped protrusions are arranged circumferentially around the air outlet.

[0013] In one embodiment, the gravity heat pipe component includes an evaporation part, a condensation part, and a liquid storage part. The condensation part is arranged at one end of the gravity heat pipe component close to the air inlet, and the evaporation part is arranged at one end of the gravity heat pipe component close to the motor component; the condensation part and the liquid storage part are arranged opposite to each other along the radial direction of the wind hood. When the axial direction of the air paddle is horizontally arranged, the condensation part is located above the liquid storage part; the tail-section guide vane type rotor module further includes a liquid absorption core, and both ends of the liquid absorption core are respectively communicated with the liquid storage part and the evaporation part.

[0014] In one embodiment, the gravity heat pipe component further includes a guide part, and the guide part is communicated with the air inlet and the condensation part, so that the air flow can enter the condensation part through the guide part. Moreover, along the direction from the air inlet to the condensation part, the flow area of the guide part shows an increasing trend.

[0015] In one embodiment, the stator of the motor component is provided with a hollow and constitutes the evaporation part of the gravity heat pipe component.

[0016] This application also provides a rotorcraft, and the rotorcraft includes the tail-section guide vane type rotor module described in any one of the above embodiments.

[0017] Compared with the prior art, for the tail-section flow-guiding rotor module and the rotorcraft provided by the present application, the cowling serves as the outer shell of the entire tail-section flow-guiding rotor module, and one end thereof is provided with an air inlet for introducing cooling air flow. The gravity heat pipe component is installed inside the cowling near the air inlet, and by utilizing its high-efficiency heat conduction characteristic, it quickly absorbs the heat generated by the motor. The motor component is located behind the gravity heat pipe component, and its stator is in close contact with the gravity heat pipe component through heat conduction to achieve rapid heat transfer.

[0018] The air propeller sleeve is sleeved outside the rotor of the motor component and rotates together with the rotor. A flow-guiding channel extending axially is designed between the air propeller and the rotor of the motor component. The function of this channel is to guide the air flow from the gravity heat pipe component to the flow-guiding tail wing to form a continuous cooling air flow path.

[0019] The flow-guiding tail wing is installed at the tail end of the cowling, with one end communicating with the inside of the cowling and the other end provided with an air outlet. When the motor drives the air propeller to rotate, a strong air flow will be generated. This air flow first enters the cowling through the air inlet, then passes through the gravity heat pipe component to take away the heat it absorbs. Then, the air flow passes through the flow-guiding channel and finally is discharged through the flow-guiding tail wing and the air outlet.

[0020] The key to this design lies in the selection of the gravity heat pipe component. The gravity heat pipe utilizes the phase change principle and can achieve high-efficiency heat transfer under low temperature difference conditions, greatly improving the heat dissipation efficiency. At the same time, arranging the flow-guiding tail wing at the tail effectively balances the center of gravity distribution of the entire module and improves flight stability. Description of the Drawings

[0021] In order to more clearly illustrate the technical solutions in the embodiments of the present application or in the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the following-described drawings are only some embodiments of the present application. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0022] Figure 1 It is a schematic structural diagram of the tail-section flow-guiding rotor module according to an embodiment provided by the present application;

[0023] Figure 2 It is a cross-sectional view of the tail-section flow-guiding rotor module according to an embodiment provided by the present application;

[0024] Figure 3 It is a schematic partial structural diagram of the tail-section flow-guiding rotor module according to an embodiment provided by the present application;

[0025] Figure 4 It is a partial cross-sectional view of the tail-section flow-guiding rotor module according to another embodiment provided by the present application.

[0026] Reference numerals: 100, air shroud; 110, air inlet; 120, first channel; 130, diversion channel; 140, pressurization channel; 150, second channel; 160, rotary shaft hole; 200, diversion fin; 210, air outlet; 220, fin; 230, diversion groove; 300, motor component; 310, rotor; 320, stator; 400, gravity heat pipe component; 410, evaporation part; 420, condensation part; 430, conduit; 440, diversion part; 500, air paddle; 600, power fan; 610, first blade; 620, second blade; 700, serrated protrusion; 800, liquid storage part; 810, liquid absorption core; 900, diversion protrusion. Detailed implementation mode

[0027] As the uses of rotorcraft (including flying cars and drones) are increasing, the requirements for rotorcraft are also getting higher and higher. For example, the load demand of rotorcraft is constantly increasing, and the power of the corresponding motor will also become larger and larger. Thus, the heat generated by the motor will also double. Therefore, the heat dissipation of the motor is particularly important.

[0028] In order to improve the heat dissipation efficiency, in the prior art, the heat dissipation of the motor is generally carried out by the wind generated by the air paddle. In this way, although the heat dissipation efficiency can be improved to a certain extent, with such a setting, the air paddle needs to be arranged in front of the motor, that is, the overall setting position of the air paddle is relatively forward. At this time, the center of gravity of the entire rotor module will be too forward, thus affecting the flight stability of the rotorcraft.

[0029] Therefore, in order to solve the problem that the existing rotorcraft is difficult to balance the heat dissipation efficiency of the motor and the flight stability of the rotorcraft, the present application provides a tail-section diversion type rotor module.

[0030] Please refer to Figures 1-4 , the tail-section diversion type rotor module includes an air shroud 100, a motor component 300, a gravity heat pipe component 400, an air paddle 500 and a diversion fin 200. An air inlet 110 is provided at one end of the air shroud 100. The gravity heat pipe component 400 is arranged at one end of the air shroud 100 close to the air inlet 110. The motor component 300 is arranged on the side of the gravity heat pipe component 400 away from the air inlet 110. The gravity heat pipe component 400 can dissipate heat from the stator 320 of the motor component 300. The air paddle 500 is sleeved outside the rotor 310 of the motor component 300 so that the rotor 310 of the motor component 300 can drive the air paddle 500 to rotate. And a diversion channel 130 extending along the axial direction of the air paddle 500 is provided between the air paddle 500 and the rotor 310 of the motor component 300.

[0031] Among them, the air shroud 100 refers to a housing structure for covering components such as the motor component 300, the gravity heat pipe component 400, and the mounting bracket, and can be specifically implemented using a lightweight and high-strength material such as carbon fiber composite material.

[0032] Among them, the gravity heat pipe component 400 refers to a device that uses the principles of gravity and phase change for heat transfer, and can be specifically implemented using a sealed pipeline structure filled with a working medium inside.

[0033] It should be noted that the air shroud 100 is divided into two parts by the air paddle 500, and the air paddle 500 is rotationally matched with the air shroud 100, rather than driving the air shroud 100 to rotate synchronously. Specifically, the air paddle 500 includes a rotating ring arranged on the inner side and in a circular ring shape, and a plurality of blades arranged on the outer peripheral side of the rotating ring. The rotating ring and the air shroud 100 are in a relative rotation relationship, and a flow guiding channel 130 is provided between the rotating ring and the rotor 310.

[0034] Furthermore, it should be noted that the rotating ring of the air paddle 500 and the rotor 310 of the motor component 300 are fixedly connected through connecting columns. The adjacent connecting columns are arranged at intervals to form a flow guiding gap, and a plurality of flow guiding gaps constitute the flow guiding channel 130.

[0035] Therefore, it can be understood that the rotor 310 of the motor component 300, the air paddle 500, and the rotating ring rotate synchronously, and structures such as the stator 320 of the motor component 300, the gravity heat pipe component 400, and the air shroud 100 are fixed and do not rotate.

[0036] The flow guiding tail wing 200 is arranged at one end of the air shroud 100 away from the air inlet 110. One end of the flow guiding tail wing 200 is connected to the air shroud 100, and the other end is provided with an air outlet 210. Airflow can sequentially pass through the air inlet 110, the gravity heat pipe component 400, the flow guiding channel 130, the flow guiding tail wing 200, and the air outlet 210.

[0037] Among them, the flow guiding tail wing 200 refers to a structure located at the tail of the air shroud 100 for guiding airflow, and can be specifically implemented using a plurality of wing pieces 220 extending along the axial direction.

[0038] The core innovation point of this application lies in integrating the heat dissipation system into the tail of the tail section flow guiding rotor module. Through the synergistic effect of the gravity heat pipe component 400, the flow guiding channel 130, and the flow guiding tail wing 200, the unity of effective motor heat dissipation and center of gravity optimization is achieved. This design not only solves the problem of the center of gravity moving forward caused by traditional heat dissipation solutions, but also improves the overall heat dissipation efficiency.

[0039] The working principle of this application can be described in detail as follows:

[0040] The wind cover 100 serves as the outer shell of the entire tail-section ducted rotor module. One end of it is provided with an air inlet 110 for introducing cooling air flow. The gravity heat pipe component 400 is installed inside the wind cover 100 near the air inlet 110. Utilizing its high-efficient heat conduction characteristics, it quickly absorbs the heat generated by the motor. The motor component 300 is located behind the gravity heat pipe component 400, and its stator 320 is in close contact with the gravity heat pipe component 400 through heat conduction to achieve rapid heat transfer.

[0041] The air propeller 500 is sleeved outside the rotor 310 of the motor component 300 and rotates together with the rotor 310. Between the air propeller 500 and the rotor 310 of the motor component 300, an axially extending air guiding channel 130 is designed. The function of this channel is to guide the air flow from the gravity heat pipe component 400 to the guiding tail fin 200, forming a continuous cooling air flow path.

[0042] The guiding tail fin 200 is installed at the tail end of the wind cover 100. One end is in communication with the inside of the wind cover 100, and the other end is provided with an air outlet 210. When the motor drives the air propeller 500 to rotate, a strong air flow will be generated. This air flow first enters the wind cover 100 through the air inlet 110, then passes through the gravity heat pipe component 400, taking away the heat it absorbs. Then, the air flow passes through the air guiding channel 130, and finally is discharged through the guiding tail fin 200 and the air outlet 210.

[0043] The key to this design lies in the selection of the gravity heat pipe component 400. The gravity heat pipe utilizes the phase change principle and can achieve high-efficient heat transfer under low temperature difference conditions, greatly improving the heat dissipation efficiency. At the same time, arranging the guiding tail fin 200 at the tail effectively balances the center of gravity distribution of the entire module and improves the flight stability.

[0044] It should be noted that in one embodiment, the rotary shaft hole 160 can be set at one end of the wind cover 100 near the air inlet 110, but it is not limited to this. In other embodiments, the rotary shaft hole 160 can also be set at one end of the wind cover 100 near the guiding tail fin 200.

[0045] In one embodiment, the distance A between the air propeller 500 and the air outlet 210, and the distance B between the air propeller 500 and the air inlet 110 satisfy 0.8 ≤ A / B ≤ 1.2.

[0046] This design can optimize the positional relationship between the air propeller 500 and the air inlet 110 and the air outlet 210, thereby improving the overall performance of the rotor module. Specifically, by controlling the distance ratio between the air propeller 500 and the air inlet 110 and the air outlet 210, while ensuring the heat dissipation effect, the air flow path can be optimized and the working efficiency of the rotor module can be improved.

[0047] Furthermore, when the ratio of A / B is between 0.8 and 1.2, an optimal position configuration can be achieved between the air paddle 500, the air inlet 110, and the air outlet 210. This ratio range is obtained through a large number of experiments and calculations and can maintain good performance under different working conditions.

[0048] As a preferred embodiment, the value of A / B can be set to 1. This means that the distance from the air paddle 500 to the air inlet 110 is equal to the distance to the air outlet 210. This configuration can make the airflow form the most uniform flow inside the tail-section guiding rotor module, further reducing eddy currents and airflow resistance. This configuration can not only optimize the airflow path but also make the center of gravity of the rotor module more centered, which is beneficial to the stability of the rotorcraft.

[0049] In one embodiment, as Figure 2 shown, the cavity area of the wind hood 100 located between the motor component 300 and the gravity heat pipe component 400 is defined as the first channel 120, and the cavity area of the wind hood 100 located between the motor component 300 and the guiding tail fin 200 is defined as the second channel 150. The flow area of the guiding channel 130 is smaller than the flow area of the first channel 120 at the end close to the guiding channel 130, and the flow area of the guiding channel 130 is smaller than the flow area of the second channel 150 at the end close to the guiding channel 130.

[0050] The purpose of this design is to further optimize the airflow path and efficiency. By reasonably designing the flow areas of each channel, better airflow control and guiding effects can be achieved. Specifically, the flow area of the guiding channel 130 is smaller than the flow areas of the first channel 120 and the second channel 150 at the ends close to the guiding channel 130. This design can generate a certain pressure difference, prompting the airflow to pass through the guiding channel 130 more concentratedly.

[0051] The working principle of this design is as follows: When the air paddle 500 rotates, airflow will be generated in the first channel 120 and the second channel 150. Due to the smaller flow area of the guiding channel 130, the airflow will accelerate when passing through the guiding channel 130. This acceleration effect can increase the kinetic energy of the airflow, thereby enhancing the heat dissipation effect. At the same time, since the flow area of the guiding channel 130 is smaller than the flow areas of the first channel 120 and the second channel 150, a local low-pressure area will be formed at the entrance of the guiding channel 130, which helps to suck more airflow into the guiding channel 130, further enhancing the flow efficiency of the airflow.

[0052] In addition, this design can also optimize the flow path of the air current. The air current first passes through the first channel 120 to cool the gravity heat pipe component 400. Then, when the air current passes through the diversion channel 130, it accelerates, which can not only enhance the cooling effect on the motor component 300, but also improve the working efficiency of the air paddle 500. Finally, the air current passes through the second channel 150 and the diversion fin 200 to further dissipate heat and provide additional thrust.

[0053] Furthermore, in one embodiment, as Figure 2 shown, along the direction from the motor component 300 to the diversion fin 200, the flow area of the second channel 150 shows a decreasing trend.

[0054] This design can further optimize the flow path of the air current and improve the overall heat dissipation efficiency. Specifically, by making the flow area of the second channel 150 gradually decrease along the air current direction, a constricted flow channel structure can be naturally formed without adding additional components.

[0055] This constricted flow channel structure has the following advantages:

[0056] Firstly, it can accelerate the flow speed of the air current. According to Bernoulli's principle, during the fluid flow process, when the flow area decreases, the fluid speed will increase accordingly. Therefore, the gradual decrease in the flow area of the second channel 150 can make the air current speed gradually increase when passing through this area, thus improving the flow efficiency of the air current.

[0057] Secondly, the accelerated air current can more effectively carry away heat. The high-speed flowing air current has a stronger heat exchange capacity and can carry away the heat generated by the motor component 300 more quickly, further improving the heat dissipation efficiency.

[0058] Thirdly, this design can reduce the turbulence and eddy current phenomena of the air current. Through the gradually constricted channel, the air current can flow more smoothly, reducing the turbulence generated by the sudden change in cross-section, thereby reducing the energy loss.

[0059] In addition, this design can also improve the thrust efficiency of the tail-section diversion rotor module to a certain extent. The accelerated air current has higher kinetic energy when leaving the diversion fin 200, which can generate a greater reaction force, thereby improving the thrust efficiency of the rotor.

[0060] In specific implementation, the flow area of the second channel 150 can be gradually reduced in various ways. For example, it can be achieved through the contour design of the inner wall of the air shroud 100, such that the inner wall of the air shroud 100 gradually contracts inward from the motor component 300 to the guiding tail fin 200. Another way is to arrange some flow guiding structures in the second channel 150, such as spiral flow guiding vanes, which can gradually reduce the effective flow area of the channel while guiding the airflow.

[0061] However, it is not limited to this. In other embodiments, along the direction from the motor component 300 to the guiding tail fin 200, the flow area of the second channel 150 can also remain unchanged.

[0062] Furthermore, in one embodiment, as Figure 3 shown, the tail section flow guiding rotor module further includes a power fan 600. The power fan 600 is arranged in the flow guiding channel 130 and fixedly sleeved on the outer peripheral side of the rotor 310 of the motor component 300, so that the rotor 310 of the motor component 300 can drive the power fan 600 to rotate, and the flow guiding channel 130 can generate an airflow flowing from the gravity heat pipe component 400 to the guiding tail fin 200.

[0063] By adding the power fan 600 in the flow guiding channel 130, not only the flow efficiency of the airflow is improved, but also the heat dissipation capacity of the entire tail section flow guiding rotor module is enhanced. Since the power fan 600 and the rotor 310 of the motor component 300 are coaxially arranged, no additional driving mechanism is added, maintaining the simplicity of the structure. This improvement enables the rotor module to still maintain a good heat dissipation effect during high-power operation, providing the possibility for the performance improvement of the rotorcraft.

[0064] Specifically, in one embodiment, the power fan 600 includes a first fan blade group and a second fan blade group. The first fan blade group is arranged at one end of the flow guiding channel 130 close to the gravity heat pipe component 400, and the first fan blade group includes a plurality of first blades 610 arranged at intervals along the circumferential direction of the flow guiding channel 130; the second fan blade group is arranged at one end of the flow guiding channel 130 far from the gravity heat pipe component 400, and the second fan blade group includes a plurality of second blades 620 arranged at intervals along the circumferential direction of the flow guiding channel 130; the first fan blade group and the second fan blade group are arranged at intervals along the axial direction of the air paddle 500.

[0065] It should be noted that the shape of the first blade 610 can be various shapes such as straight plate shape, arc shape or bent shape, etc., which are not listed one by one here.

[0066] Similarly, the shape of the second blade 620 can be various shapes such as straight plate shape, arc shape or bent shape, etc., which are not listed one by one here.

[0067] In one embodiment, the tail-section flow-guiding rotor module further includes a flow-dividing protrusion 900. The flow-dividing protrusion 900 is disposed on the side of the motor component 300 close to the air inlet 110 and protrudes towards the direction close to the air inlet 110, so that the air flow can be guided to the flow-guiding channel 130 through the flow-dividing protrusion 900.

[0068] Compared with the prior art, the solution of the present application realizes the effective guidance and utilization of the air flow by adding the flow-dividing protrusion 900, and avoids the disordered diffusion and waste of the air flow. At the same time, since the setting of the flow-dividing protrusion 900 does not significantly increase the weight and volume of the tail-section flow-guiding rotor module, it will not have an obvious impact on the center of gravity and flight performance of the aircraft. This design improves the heat dissipation efficiency while maintaining the compactness and light-weight characteristics of the tail-section flow-guiding rotor module.

[0069] In one embodiment, as Figure 2 shown, the flow-guiding tail fin 200 includes a plurality of fins 220 arranged around the axis of the air shroud 100. Each fin 220 extends along the axial direction of the air shroud 100, and adjacent fins 220 are spaced apart to form a flow-guiding groove 230.

[0070] It should be noted that the air shroud 100 and the air propeller 500 are coaxially arranged, and the axis of the air shroud 100 and the axis of the air propeller 500 are the same axis.

[0071] Specifically, the number of the fins 220 can be one, two, three, four or more (the number > 4), etc., which will not be enumerated one by one here.

[0072] The technical solution proposed by the present application can effectively guide the air flow to flow along a specific direction by arranging a plurality of fins 220 and flow-guiding grooves 230 on the flow-guiding tail fin 200, thereby improving the flow-guiding effect. This design can not only enhance the directivity of the air flow, but also reduce the generation of eddy currents, further improving the overall efficiency of the rotor module.

[0073] Specifically, the flow-guiding tail fin 200 includes a plurality of fins 220, which are evenly distributed around the axis of the air shroud 100. Each fin 220 extends along the axial direction of the air shroud 100 to form a continuous flow-guiding surface. There is a gap between adjacent fins 220, and these gaps form the flow-guiding grooves 230. This structural design divides the air flow into multiple strands when passing through the flow-guiding tail fin 200, and each strand of air flow is guided to flow along a specific path.

[0074] Further, in one embodiment, as Figure 1 and Figure 2As shown, a toothed protrusion 700 is provided at the air outlet 210. One end of the toothed protrusion 700 is connected to the guiding tail wing 200, and the other end extends along the axial direction of the air paddle 500. Along the direction from the air inlet 110 to the air outlet 210, the cross-sectional area of the toothed protrusion 700 shows a decreasing trend, and multiple toothed protrusions 700 are arranged along the circumference of the air outlet 210.

[0075] This design is mainly to further optimize the guiding effect of the air flow. By setting the toothed protrusion 700 at the air outlet 210, the flowing direction of the air flow can be better guided, the degree of air flow disorder can be reduced, and the directivity of the air flow can be improved. The design with the decreasing cross-sectional area of the toothed protrusion 700 can gradually contract the air flow, increase the air flow speed, and thus improve the thrust efficiency. The design with multiple toothed protrusions 700 arranged along the circumference of the air outlet 210 can evenly guide the air flow in the entire area of the air outlet 210.

[0076] Specifically, there are various implementation ways for the design of the toothed protrusion 700. For example, the toothed protrusion 700 can be multiple triangular structures arranged at equal intervals, or can be structures in the shape of a trapezoid or a curve. The number of the toothed protrusions 700 can be adjusted according to the size of the air outlet 210 and the specific application scenario to ensure sufficient guiding effect without excessive increasing of resistance.

[0077] A coordinated working system is formed among the toothed protrusion 700, the guiding tail wing 200 and the air paddle 500. The guiding tail wing 200 guides the air flow into the air outlet 210, and the toothed protrusion 700 further optimizes the outlet characteristics of the air flow. This design not only improves the directivity of the air flow, but also may reduce the formation of the wake vortex to a certain extent, thus improving the efficiency of the entire rotor module. And, the toothed protrusion 700 can also reduce the noise generated by the air flow to a certain extent.

[0078] In one embodiment, as Figure 4 shown, the gravity heat pipe component 400 includes an evaporation part 410, a condensation part 420 and a liquid storage part 800. The condensation part 420 is arranged at one end of the gravity heat pipe component 400 close to the air inlet 110, and the evaporation part 410 is arranged at one end of the gravity heat pipe component 400 close to the motor component 300; the condensation part 420 and the liquid storage part 800 are arranged oppositely along the radial direction of the wind cover 100. When the axial direction of the air paddle 500 is horizontally arranged, the condensation part 420 is located above the liquid storage part 800; the tail section guiding type rotor module further includes a liquid absorption core 810, and both ends of the liquid absorption core 810 are respectively communicated with the liquid storage part 800 and the evaporation part 410.

[0079] Through the special design of the gravity heat pipe component 400, the heat dissipation efficiency is further improved. Specifically, the evaporation part 410 of the gravity heat pipe component 400 is close to the motor component 300 and can directly absorb the heat generated by the motor component 300. The condensation part 420 is arranged at a position close to the air inlet 110, and the entering cold air can be fully utilized for heat dissipation. The liquid storage part 800 and the condensation part 420 are arranged opposite to each other radially. When the air paddle 500 is horizontal, the condensation part 420 is above. This layout utilizes the gravity effect to make the condensed liquid flow back to the liquid storage part 800 naturally.

[0080] The setting of the wick 810 further enhances the circulation efficiency of the heat pipe. The wick 810 connects the liquid storage part 800 and the evaporation part 410, and transports the cooling liquid in the liquid storage part 800 to the evaporation part 410 through capillary action, ensuring a continuous supply of coolant to the evaporation part 410. This design enables the heat pipe to maintain a good heat dissipation effect in various postures.

[0081] This design has significant advantages compared with traditional heat dissipation structures. Traditional heat dissipation usually relies on direct air cooling, with low efficiency and being easily affected by the flight posture. The gravity heat pipe structure of this application utilizes the phase change principle, has higher heat dissipation efficiency and is not restricted by the flight posture. At the same time, the design of the flow guide part 440 ensures that the cold air can effectively reach the condensation part 420, further improving the heat dissipation efficiency.

[0082] Furthermore, in one embodiment, the evaporation part 410 and the condensation part 420 are connected through a conduit 430, and a flow splitting protrusion 900 is fixedly sleeved outside the conduit 430.

[0083] With this setting, a certain distance can be provided between the evaporation part 410 and the condensation part 420, greatly enhancing the layout flexibility of the gravity heat pipe component 400.

[0084] Even further, in one embodiment, the gravity heat pipe component 400 further includes a flow guide part 440. The flow guide part 440 connects the air inlet 110 and the condensation part 420 so that the air flow can enter the condensation part 420 through the flow guide part 440. And, along the direction from the air inlet 110 to the condensation part 420, the flow area of the flow guide part 440 shows an increasing trend.

[0085] The flow guide part 440 connects the air inlet 110 and the condensation part 420, enabling the cold air to directly enter the condensation part 420. More importantly, the flow area of the flow guide part 440 gradually increases along the air flow direction. This design can reduce the air flow speed and extend the contact time between the cold air and the condensation part 420, thereby improving the heat exchange efficiency.

[0086] Specifically, in one embodiment, the flow guide part 440 directly connects the air inlet 110 and the condensation part 420.

[0087] In another embodiment, as Figure 2 shown, the liquid storage part 800 and the air inlet 110 are arranged at intervals, so that the condensation part 420, the liquid storage part 800, and the inner wall of the first housing enclose a pressurization channel 140, and the pressurization channel 140 can be communicated through the condensation part 420 and the air outlet 210.

[0088] Specifically, the liquid storage part 800 and the air inlet 110 are arranged at intervals, so that the condensation part 420, the liquid storage part 800, and the inner wall of the air hood 100 jointly enclose a pressurization channel 140. This pressurization channel 140 is communicated through the condensation part 420 and the air outlet 210, thus creating an optimized air flow path. When the air flow enters through the air inlet 110, part of the air flow will enter this pressurization channel 140. Due to the special design of the channel, the air flow will generate a certain pressure increase when passing through, and this pressure increase helps to improve the flow rate and heat exchange efficiency of the air flow.

[0089] In one embodiment, as Figure 4 shown, the stator 320 of the motor component 300 is hollowed out and constitutes the evaporation part 410 of the gravity heat pipe component 400.

[0090] This design can effectively improve the heat dissipation efficiency of the motor component 300. Specifically, the stator 320 of the motor component 300 is hollowed out and constitutes the evaporation part 410 of the gravity heat pipe component 400, which can enable the working medium to directly absorb the heat generated by the stator 320 of the motor component 300.

[0091] The advantage of this design is that it utilizes the high-efficiency heat transfer characteristics of the gravity heat pipe component 400 to closely combine the heat dissipation of the motor component 300 with the working process of the gravity heat pipe component 400. The hollowed-out stator 320 as the evaporation part 410 can quickly absorb the heat generated by the stator 320, and transfer the heat to the working medium rapidly. In this way, not only can the high-efficiency heat dissipation of the motor component 300 be realized. Moreover, the layout of the gravity heat pipe component 400 can be optimized, the volume required for the gravity heat pipe component 400 can be reduced, and further the volume of the tail-section guide vane rotor module can be made more compact.

[0092] However, it is not limited to this. In other embodiments, the gravity heat pipe component 400 can also be attached to the heating surface of the stator 320 of the motor component 300 to dissipate heat from the stator 320 of the motor component 300.

[0093] This application also provides a rotorcraft, which includes the tail-section guide vane rotor module described in any one of the above embodiments.

[0094] The technical features of the above-described embodiments can be combined arbitrarily. For the sake of brevity of description, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, it should be considered as falling within the scope described in this specification.

[0095] The above-described embodiments merely represent several implementation manners of the present application. The description thereof is relatively specific and detailed, but it should not be construed as a limitation to the scope of the patent application. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present application, several modifications and improvements can still be made, and these all belong to the protection scope of the present application. Therefore, the patent protection scope of the present application shall be subject to the appended claims.

[0096] In the description of the present application, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present application.

[0097] In addition, the terms "first" and "second" are only used for descriptive purposes and should not be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one of such features. In the description of the present application, "a plurality of" means at least two, such as two, three, etc., unless otherwise specifically and clearly defined.

[0098] In the present application, unless otherwise clearly specified and defined, the terms "install", "connect", "connection", "fix", etc. should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or integrated; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and it may be the internal communication of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific circumstances.

[0099] In this application, unless otherwise clearly specified and defined, the first feature being "on" or "under" the second feature 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. Moreover, the first feature being "above", "over" and "on top of" the second feature may mean that the first feature is directly above or obliquely above the second feature, or simply indicates that the first feature has a higher horizontal height than the second feature. The first feature being "under", "below" and "beneath" the second feature may mean that the first feature is directly below or obliquely below the second feature, or simply indicates that the first feature has a lower horizontal height than the second feature.

[0100] It should be noted that when an element is referred to as being "fixed to" or "disposed on" another element, it can be directly on the other element or there may also be an intermediate element. When an element is considered to be "connected to" another element, it can be directly connected to the other element or there may be an intermediate element at the same time. The terms "vertical", "horizontal", "upper", "lower", "left", "right" and similar expressions used herein are for illustrative purposes only and do not represent the only implementation.

[0101] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by those skilled in the technical field to which this application belongs. The terms used herein in the specification of this application are only for the purpose of describing specific implementations and are not intended to limit this application. The term "and / or" used herein includes any and all combinations of one or more of the related listed items.

Claims

1. A tail section guide rotor module, characterized in that: The invention comprises a wind shield (100), a motor component (300), a gravity heat pipe component (400), an air paddle (500) and a guide tail (200), wherein an air inlet (110) is provided at one end of the wind shield (100), the gravity heat pipe component (400) is arranged at one end of the wind shield (100) close to the air inlet (110), the motor component (300) is arranged at a side of the gravity heat pipe component (400) away from the air inlet (110), and the gravity heat pipe component (400) is arranged at a side of the gravity heat pipe component (400) away from the air inlet (110). 00) can dissipate heat for the stator (320) of the motor component (300), the air paddle (500) is sleeved on the outside of the rotor (310) of the motor component (300), so that the rotor (310) of the motor component (300) can drive the air paddle (500) to rotate, and a guide channel (130) extending along the axial direction of the air paddle (500) is provided between the air paddle (500) and the rotor (310) of the motor component (300); The guide tail wing (200) is arranged at one end of the wind cover (100) away from the air inlet (110); one end of the guide tail wing (200) is connected to the wind cover (100), and the other end is provided with an air outlet (210); airflow can sequentially pass through the air inlet (110), the gravity heat pipe (400), the guide channel (130), the guide tail wing (200) and the air outlet (210).

2. The tail section guide rotor module according to claim 1, characterized in that: A distance A between the air propeller (500) and the air outlet (210), and a distance B between the air propeller (500) and the air inlet (110) satisfy 0.8≤A / B≤1.

2.

3. The tail section guide rotor module according to claim 2, characterized in that: A / B=1.

4. The tail section guide rotor module according to claim 1, characterized in that: A cavity area of ​​the wind hood (100) between the motor component (300) and the gravity heat pipe component (400) is defined as a first channel (120), and a cavity area of ​​the wind hood (100) between the motor component (300) and the guide tail wing (200) is defined as a second channel (150). The flow area of ​​the guide channel (130) is smaller than the flow area of ​​the first channel (120) close to one end of the guide channel (130), and the flow area of ​​the guide channel (130) is smaller than the flow area of ​​the second channel (150) close to one end of the guide channel (130).

5. The tail section guide rotor module according to claim 4, characterized in that: Along the direction from the motor component (300) to the guide tail (200), the flow area of ​​the second channel (150) tends to decrease.

6. The tail section guide rotor module according to claim 5, characterized in that: The invention also comprises a power fan (600), wherein the power fan (600) is arranged in the guide channel (130) and is fixedly sleeved on the outer peripheral side of the rotor (310) of the motor component (300), so that the rotor (310) of the motor component (300) can drive the power fan (600) to rotate, and the guide channel (130) can generate an airflow flowing along the gravity heat pipe component (400) to the guide tail wing (200).

7. The tail section guide rotor module according to claim 1, characterized in that: The guide tail (200) comprises a plurality of fins (220) arranged around the axis of the wind shield (100), each fin (220) extending axially along the wind shield (100), and adjacent fins (220) are arranged at intervals to form a guide groove (230).

8. The tail section guide rotor module according to claim 7, characterized in that: A tooth-shaped protrusion (700) is provided at the air outlet (210), one end of the tooth-shaped protrusion (700) is connected to the guide tail (200), and the other end extends along the axial direction of the air propeller (500), and along the direction from the air inlet (110) to the air outlet (210), the cross-sectional area of ​​the tooth-shaped protrusion (700) tends to decrease, and a plurality of tooth-shaped protrusions (700) are arranged along the circumference of the air outlet (210).

9. The tail section guide rotor module according to claim 1, characterized in that: The gravity heat pipe (400) comprises an evaporation section (410), a condensation section (420) and a liquid storage section (800); the condensation section (420) is arranged at one end of the gravity heat pipe (400) close to the air inlet (110), and the evaporation section (410) is arranged at one end of the gravity heat pipe (400) close to the motor device (300); the condensation section (420) and the liquid storage section (800) are arranged opposite to each other along the radial direction of the wind cover (100); when the axial direction of the air propeller (500) is horizontally arranged, the condensation section (420) is located above the liquid storage section (800); the tail section guide rotor module also comprises a liquid wick (810), and two ends of the liquid wick (810) are respectively connected to the liquid storage section (800) and the evaporation section (410).

10. The tail section guide rotor module according to claim 9, characterized in that: The gravity heat pipe (400) further includes a flow guide portion (440), wherein the flow guide portion (440) is connected to the air inlet (110) and the condensation portion (420) so that airflow can enter the condensation portion (420) through the flow guide portion (440), and the flow area of ​​the flow guide portion (440) tends to increase along the direction from the air inlet (110) to the condensation portion (420).

11. The tail section guide rotor module according to claim 9, characterized in that: The stator (320) of the motor component (300) is hollowed out and constitutes the evaporation portion (410) of the gravity heat pipe component (400).

12. A rotary-wing aircraft, characterized in that: It comprises a tail section guide rotor module as described in any one of claims 1 to 11.

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