Tail section flow guide type rotor wing module and rotor wing type aircraft

Abstract

The invention relates to a tail section flow guide type rotor module and a rotor type aircraft, the tail section flow guide type rotor module comprises a fan cover, a motor part, a gravity heat pipe fitting, an air paddle and a flow guide empennage, one end of the fan cover is provided with an air inlet, the gravity heat pipe fitting is arranged at the end, close to the air inlet, of the fan cover, and the motor part is arranged on the side, away from the air inlet, of the gravity heat pipe fitting; the gravity heat pipe fitting can dissipate heat of a stator of the motor part, a rotor of the motor part can drive the air paddle to rotate, and a flow guide channel extending in the axial direction of the air paddle is arranged between the air paddle and the rotor of the motor part. One end of the flow guide tail fin is communicated with the fan cover, the other end of the flow guide tail fin is provided with an air outlet, and airflow sequentially penetrates through the air inlet, the gravity heat pipe fitting, the flow guide channel, the flow guide tail fin and the air outlet. According to the tail section diversion type rotor wing module and the rotor wing type aircraft, the problem that the rotor wing type aircraft is difficult to consider the heat dissipation efficiency of the motor and the flight stability of the rotor wing type aircraft at the same time is solved.

Description

Technical Field

[0001] The present application relates to the technical field of rotary-wing flight devices, and in particular to a tail-section flow-guiding rotor module and a rotary-wing aircraft. Background Art

[0002] As the uses of rotorcraft (including flying cars and drones) increase, the requirements for rotorcraft are also getting higher and higher. For example, the load demand of rotorcraft is constantly increasing, and the corresponding motor power will also become larger and larger. In this way, 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 through the wind generated by the air propeller. Although this can improve the heat dissipation efficiency 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, the center of gravity of the entire rotor module will be too forward, thereby affecting the flight stability of the rotorcraft. Summary of the invention

[0004] Based on this, it is necessary to provide a tail-section guide rotor module and a rotorcraft 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.

[0005] The tail section guide rotor module provided by the present application includes a wind hood, a motor component, a gravity heat pipe component, an air paddle and a guide tail wing. An air inlet is provided at one end of the wind hood, the gravity heat pipe component is arranged at the end of the wind hood 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 to the stator of the motor component, the air paddle is sleeved on the outer side of the rotor of the motor component so that the rotor of the motor component can drive the air paddle to rotate, and a guide channel extending along the axis of the air paddle is provided between the air paddle and the rotor of the motor component; the guide tail wing is provided at the end of the wind hood away from the air inlet, one end of the guide tail wing is connected to the wind hood, and the other end is provided with an air outlet, and the airflow can pass through the air inlet, the gravity heat pipe component, the guide channel, the guide tail wing and the air outlet in sequence.

[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 of the embodiments, the cavity area of ​​the wind hood located between the motor component and the gravity heat pipe component is defined as the first channel, and the cavity area of ​​the wind hood located between the motor component and the guide tail is defined as the second channel. The flow area of ​​the guide channel is smaller than the flow area of ​​the first channel near one end of the guide channel, and the flow area of ​​the guide channel is smaller than the flow area of ​​the second channel near one end of the guide channel.

[0009] In one of the embodiments, the flow area of ​​the second channel tends to decrease along the direction from the motor component to the guide tail.

[0010] In one of the embodiments, the tail section guide rotor module also includes a power fan, which is arranged in the guide channel and fixedly mounted on the outer peripheral side 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 airflow flowing from the gravity heat pipe to the guide tail.

[0011] In one embodiment, the guide tail includes a plurality of fins arranged around the axis of the wind shield, each fin extends along the axial direction of the wind shield, and adjacent fins are arranged at intervals to form a guide groove.

[0012] In one of the embodiments, a tooth-like protrusion is provided at the air outlet, one end of the tooth-like protrusion is connected to the guide tail wing, and the other end extends along the axial direction of the air propeller. Along the direction from the air inlet to the air outlet, the cross-sectional area of ​​the tooth-like protrusion tends to decrease, and multiple tooth-like protrusions are arranged along the circumference of the air outlet.

[0013] In one of the embodiments, the gravity heat pipe 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 close to the air inlet, and the evaporation part is arranged at one end of the gravity heat pipe close to the motor part; the condensation part and the liquid storage part are arranged opposite to each other along the radial direction of the wind cover, and when the axial direction of the air propeller is horizontally arranged, the condensation part is located above the liquid storage part; the tail section guide rotor module also includes a liquid absorption core, and the two ends of the liquid absorption core are respectively connected to the liquid storage part and the evaporation part.

[0014] In one of the embodiments, the gravity heat pipe also includes a guide portion, which connects the air inlet and the condensation portion so that the air flow can enter the condensation portion through the guide portion, and the flow area of ​​the guide portion tends to increase along the direction from the air inlet to the condensation portion.

[0015] In one of the embodiments, the stator of the motor component is hollowed out and constitutes the evaporation portion of the gravity heat pipe component.

[0016] The present application also provides a rotorcraft, which includes the tail-section guide rotor module described in any one of the above embodiments.

[0017] Compared with the prior art, the present application provides a tail section flow-guiding rotor module and a rotorcraft, wherein the wind shield serves as the outer shell of the entire tail section flow-guiding rotor module, and an air inlet is provided at one end thereof for introducing cooling airflow. The gravity heat pipe is installed in the wind shield near the air inlet, and utilizes its efficient heat conduction characteristics to quickly absorb the heat generated by the motor. The motor is located behind the gravity heat pipe, and its stator is in close contact with the gravity heat pipe through heat conduction, thereby realizing rapid heat transfer.

[0018] The air propeller sleeve is arranged on the outside of the motor rotor and rotates with the rotor. A guide channel extending along the axial direction is designed between the air propeller and the motor rotor. The function of this channel is to guide the airflow from the gravity heat pipe to the guide tail wing to form a continuous cooling airflow path.

[0019] The guide tail is installed at the tail end of the wind hood, one end of which is connected to the inside of the wind hood and the other end is provided with an air outlet. When the motor drives the air propeller to rotate, a strong airflow is generated. This airflow first enters the wind hood through the air inlet, then passes through the gravity heat pipe, taking away the heat it absorbs. Then, the airflow passes through the guide channel and finally is discharged through the guide tail and the air outlet.

[0020] The key to this design is the selection of gravity heat pipes. Gravity heat pipes use the principle of phase change to achieve efficient heat transfer under low temperature difference conditions, greatly improving heat dissipation efficiency. At the same time, the diversion tail is arranged at the tail, which effectively balances the center of gravity distribution of the entire module and improves flight stability. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the conventional technology, the drawings required for use in the embodiments or the conventional technology descriptions are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0022] Figure 1 A schematic diagram of the structure of a tail section flow-guiding rotor module according to an embodiment of the present application; Figure 2 A cross-sectional view of a tail section flow-guiding rotor module according to an embodiment of the present application; Figure 3 A schematic diagram of the partial structure of a tail section guide rotor module according to an embodiment of the present application; Figure 4 A partial cross-sectional view of a tail section guide rotor module according to another embodiment of the present application.

[0023] 1. The axial direction of the present invention is as follows: 100, wind hood; 110, air inlet; 120, first channel; 130, guide channel; 140, boost channel; 150, second channel; 160, rotating shaft hole; 200, guide tail; 210, air outlet; 220, wing; 230, guide groove; 300, motor component; 310, rotor; 320, stator; 400, gravity heat pipe component; 410, evaporation part; 420, condensation part; 430, conduit; 440, guide part; 500, air paddle; 600, power fan; 610, first blade; 620, second blade; 700, toothed protrusion; 800, liquid storage part; 810, liquid absorption core; 900, diversion protrusion. DETAILED DESCRIPTION

[0024] As the uses of rotorcraft (including flying cars and drones) increase, the requirements for rotorcraft are also getting higher and higher. For example, the load demand of rotorcraft is constantly increasing, and the corresponding motor power will also become larger and larger. In this way, the heat generated by the motor will also double. Therefore, the heat dissipation of the motor is particularly important.

[0025] In order to improve the heat dissipation efficiency, in the prior art, the heat dissipation of the motor is generally carried out through the wind generated by the air propeller. Although this can improve the heat dissipation efficiency 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, the center of gravity of the entire rotor module will be too forward, thereby affecting the flight stability of the rotorcraft.

[0026] Therefore, in order to solve the problem that it is difficult for existing rotorcraft to take into account both the heat dissipation efficiency of the motor and the flight stability of the rotorcraft, the present application provides a tail-section guide rotor module.

[0027] See also Figure 1-Figure 4 The tail section flow-guiding rotor module includes a wind shield 100, a motor component 300, a gravity heat pipe component 400, an air paddle 500 and a flow-guiding tail wing 200. 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 on a side of the gravity heat pipe component 400 away from the air inlet 110. The gravity heat pipe component 400 can dissipate heat for the stator 320 of the motor component 300. The air paddle 500 is sleeved on the outer side 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. In addition, a flow-guiding 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.

[0028] The wind shield 100 refers to a shell structure for covering the motor component 300, the gravity heat pipe component 400, and components such as a mounting bracket, and can be made of a lightweight and high-strength material such as a carbon fiber composite material.

[0029] The gravity heat pipe 400 refers to a device that uses gravity and phase change principles to transfer heat, and can be specifically implemented by using a sealed pipeline structure filled with a working fluid.

[0030] It should be noted that the wind shield 100 is divided into two by the air propeller 500, and the air propeller 500 and the wind shield 100 rotate in coordination, rather than driving the wind shield 100 to rotate synchronously. Specifically, the air propeller 500 includes a rotating ring arranged on the inner side and in a circular shape and a plurality of blades arranged on the outer circumference of the rotating ring. The rotating ring and the wind shield 100 are in a relative rotation relationship, and a guide channel 130 is provided between the rotating ring and the rotor 310.

[0031] Further, it should be noted that the rotating ring of the air propeller 500 and the rotor 310 of the motor component 300 are fixedly connected via connecting columns, and adjacent connecting columns are spaced apart to form flow guide gaps, and a plurality of flow guide gaps constitute the flow guide channel 130 .

[0032] Therefore, it can be understood that the rotor 310, the air paddle 500 and the rotating ring of the motor component 300 rotate synchronously, and the stator 320, the gravity heat pipe component 400 and the wind cover 100 of the motor component 300 are fixed and do not rotate.

[0033] The guide tail 200 is arranged at one end of the wind hood 100 away from the air inlet 110. One end of the guide tail 200 is connected to the wind hood 100, and the other end is provided with an air outlet 210. The air flow can pass through the air inlet 110, the gravity heat pipe 400, the guide channel 130, the guide tail 200 and the air outlet 210 in sequence.

[0034] The guide tail 200 refers to a structure located at the rear of the wind shield 100 for guiding the airflow, and can be specifically implemented by using a plurality of fins 220 extending in the axial direction.

[0035] The core innovation of this application is to integrate the heat dissipation system into the tail of the tail section flow-guiding rotor module, and achieve the unity of effective heat dissipation of the motor and optimization of the center of gravity through the synergistic effect of the gravity heat pipe 400, the flow-guiding channel 130 and the flow-guiding tail 200. This design not only solves the problem of the center of gravity moving forward caused by the traditional heat dissipation solution, but also improves the overall heat dissipation efficiency.

[0036] The working principle of this application can be described in detail as follows: The wind shield 100 serves as the outer shell of the entire tail section flow-guiding rotor module, and an air inlet 110 is provided at one end thereof for introducing cooling airflow. The gravity heat pipe 400 is installed in the wind shield 100 near the air inlet 110, and utilizes its efficient heat conduction characteristics to quickly absorb the heat generated by the motor. The motor component 300 is located behind the gravity heat pipe 400, and its stator 320 is in close contact with the gravity heat pipe 400 through heat conduction, thereby realizing rapid heat transfer.

[0037] The air paddle 500 is sleeved on the outer side of the rotor 310 of the motor component 300 and rotates with the rotor 310. A flow guide channel 130 extending in the axial direction is designed between the air paddle 500 and the rotor 310 of the motor component 300. The function of this channel is to guide the airflow from the gravity heat pipe component 400 to the flow guide tail 200 to form a continuous cooling airflow path.

[0038] The guide tail 200 is installed at the rear end of the wind shield 100, one end of which is connected to the inside of the wind shield 100, and the other end is provided with an air outlet 210. When the motor drives the air propeller 500 to rotate, a strong airflow is generated. This airflow first enters the wind shield 100 through the air inlet 110, and then passes through the gravity heat pipe 400 to take away the heat absorbed by it. Then, the airflow passes through the guide channel 130, and finally is discharged through the guide tail 200 and the air outlet 210.

[0039] The key to this design is the selection of gravity heat pipe 400. The gravity heat pipe uses the phase change principle to achieve efficient heat transfer under low temperature difference conditions, greatly improving the heat dissipation efficiency. At the same time, the guide tail 200 is arranged at the tail, which effectively balances the center of gravity distribution of the entire module and improves flight stability.

[0040] It should be noted that, in one embodiment, the rotating shaft hole 160 can be disposed at one end of the wind shield 100 close to the air inlet 110 , but is not limited thereto. In other embodiments, the rotating shaft hole 160 can also be disposed at one end of the wind shield 100 close to the guide tail 200 .

[0041] In one embodiment, 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.

[0042] 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, the flow path of the airflow can be optimized while ensuring the heat dissipation effect, thereby improving the working efficiency of the rotor module.

[0043] Furthermore, when the ratio of A / B is between 0.8 and 1.2, the optimal position configuration between the air propeller 500 and the air inlet 110 and the air outlet 210 can be achieved. This ratio range is obtained through a large number of experiments and calculations, and can maintain good performance under different working conditions.

[0044] As a preferred embodiment, the value of A / B can be set to 1. This means that the distance from the air propeller 500 to the air inlet 110 is equal to the distance from the air propeller 500 to the air outlet 210. This configuration can make the airflow form the most uniform flow inside the tail section guide rotor module, further reducing vortices 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.

[0045] In one embodiment, if Figure 2 As 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 guide tail 200 is defined as the second channel 150. The flow area of ​​the guide channel 130 is smaller than the flow area of ​​the first channel 120 near 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 near one end of the guide channel 130.

[0046] The purpose of this design is to further optimize the flow path and efficiency of the airflow. By reasonably designing the flow area of ​​each channel, better airflow control and guiding effects can be achieved. Specifically, the flow area of ​​the guide channel 130 is smaller than the flow area of ​​the first channel 120 and the second channel 150 near one end of the guide channel 130. This design can generate a certain pressure difference, which promotes the airflow to pass through the guide channel 130 more concentratedly.

[0047] The working principle of this design is as follows: when the air paddle 500 rotates, airflow is generated in the first channel 120 and the second channel 150. Since the flow area of ​​the guide channel 130 is small, the airflow is accelerated when passing through the guide 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 guide channel 130 is smaller than the flow area of ​​the first channel 120 and the second channel 150, a local low-pressure area is formed at the entrance of the guide channel 130, which helps to draw more airflow into the guide channel 130, further enhancing the flow efficiency of the airflow.

[0048] In addition, this design can also optimize the flow path of the airflow. The airflow first passes through the first channel 120 to cool the gravity heat pipe 400. Then, the airflow is accelerated when passing through the guide channel 130, which can not only enhance the cooling effect on the motor 300, but also improve the working efficiency of the air propeller 500. Finally, the airflow passes through the second channel 150 and the guide tail 200 to further dissipate heat and provide additional thrust.

[0049] Further, in one embodiment, if Figure 2 As shown, along the direction from the motor component 300 to the guide tail 200, the flow area of ​​the second channel 150 tends to decrease.

[0050] This design can further optimize the flow path of the airflow and improve the overall heat dissipation efficiency. Specifically, by gradually reducing the flow area of ​​the second channel 150 along the airflow direction, a contracted flow channel structure can be naturally formed without adding additional components.

[0051] This constricted flow channel structure has the following advantages: First, it can accelerate the flow speed of the airflow. According to Bernoulli's principle, during the flow of fluid, when the flow area decreases, the fluid speed will increase accordingly. Therefore, the gradual reduction of the flow area of ​​the second channel 150 can gradually increase the speed of the airflow when passing through the area, thereby improving the flow efficiency of the airflow.

[0052] Secondly, the accelerated airflow can more effectively remove heat. The high-speed airflow has a stronger heat exchange capacity and can more quickly remove the heat generated by the motor component 300, further improving the heat dissipation efficiency.

[0053] Thirdly, this design can reduce the turbulence and eddy current of the airflow. Through the gradually narrowing channel, the airflow can flow more smoothly, reducing the turbulence caused by the sudden change of cross section, thereby reducing energy loss.

[0054] In addition, this design can also improve the thrust efficiency of the tail section guide rotor module to a certain extent. The accelerated airflow has higher kinetic energy when leaving the guide tail 200, which can generate a greater reaction force, thereby improving the thrust efficiency of the rotor.

[0055] In specific implementation, the flow area of ​​the second channel 150 can be gradually reduced in a variety of ways. For example, it can be achieved by designing the contour of the inner wall of the wind shield 100 so that the inner wall of the wind shield 100 gradually shrinks inward from the motor component 300 to the guide tail 200. Another way is to set some guide structures in the second channel 150, such as spiral guide vanes, which can gradually reduce the effective flow area of ​​the channel while guiding the airflow.

[0056] However, the present invention is not limited thereto. In other embodiments, the flow area of ​​the second channel 150 may remain unchanged along the direction from the motor component 300 to the guide fin 200 .

[0057] Furthermore, in one embodiment, if Figure 3 As shown, the tail section guide rotor module also includes a power fan 600, which is arranged in the guide channel 130 and fixedly mounted 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 enable the guide channel 130 to generate an airflow flowing from the gravity heat pipe 400 to the guide tail 200.

[0058] By adding the power fan 600 in the guide channel 130, not only the flow efficiency of the airflow is improved, but also the heat dissipation capacity of the entire tail section guide rotor module is enhanced. Since the power fan 600 and the rotor 310 of the motor 300 are coaxially arranged, no additional drive mechanism is added, and the simplicity of the structure is maintained. This improvement enables the rotor module to maintain a good heat dissipation effect when operating at high power, providing a possibility for improving the performance of the rotorcraft.

[0059] Specifically, in one embodiment, the power fan 600 includes a first blade group and a second blade group, the first blade group is arranged at one end of the guide channel 130 close to the gravity heat pipe 400, and the first blade group includes a plurality of first blades 610 arranged circumferentially at intervals along the guide channel 130; the second blade group is arranged at one end of the guide channel 130 away from the gravity heat pipe 400, and the second blade group includes a plurality of second blades 620 arranged circumferentially at intervals along the guide channel 130; the first blade group and the second blade group are arranged axially at intervals along the air paddle 500.

[0060] It should be noted that the shape of the first blade 610 can be a straight plate, an arc shape, a curved shape, or other shapes, which are not listed here one by one.

[0061] Similarly, the shape of the second blade 620 can be a straight plate, an arc shape, a bent shape, or other shapes, which are not listed here one by one.

[0062] In one embodiment, the tail section flow-guiding rotor module also includes a diverter protrusion 900, which is covered on a side of the motor component 300 close to the air inlet 110 and protrudes toward the direction close to the air inlet 110, so that the airflow can be guided to the guide channel 130 through the diverter protrusion 900.

[0063] Compared with the prior art, the solution of the present application achieves effective guidance and utilization of airflow by adding the diverter protrusion 900, avoiding disorderly diffusion and waste of airflow. At the same time, since the provision of the diverter protrusion 900 will not significantly increase the weight and volume of the tail section flow-guiding rotor module, it will not have a significant impact on the center of gravity and flight performance of the aircraft. This design improves the heat dissipation efficiency while maintaining the compactness and lightweight characteristics of the tail section flow-guiding rotor module.

[0064] In one embodiment, if Figure 2 As shown, the guide tail 200 includes a plurality of fins 220 arranged around the axis of the wind shield 100 , each fin 220 extends axially along the wind shield 100 , and adjacent fins 220 are arranged at intervals to form a guide groove 230 .

[0065] It should be noted that the wind shield 100 and the air propeller 500 are coaxially arranged, and the axis of the wind shield 100 and the axis of the air propeller 500 are the same axis.

[0066] Specifically, the number of the fins 220 may be one, two, three, four, or more (the number is greater than 4), etc., which are not listed here one by one.

[0067] The technical solution proposed in this application can effectively guide the airflow to flow in a specific direction by providing a plurality of fins 220 and guide grooves 230 on the guide tail 200, thereby improving the guide effect. This design can not only enhance the directionality of the airflow, but also reduce the generation of vortices, further improving the overall efficiency of the rotor module.

[0068] Specifically, the guide tail 200 includes a plurality of fins 220, which are evenly distributed around the axis of the wind shield 100. Each fin 220 extends along the axial direction of the wind shield 100 to form a continuous guide surface. There are intervals between adjacent fins 220, and these intervals form guide grooves 230. This structural design allows the airflow to be divided into multiple streams when passing through the guide tail 200, and each stream of air is guided to flow along a specific path.

[0069] Further, in one embodiment, if Figure 1 and Figure 2 As shown, a tooth-like protrusion 700 is provided at the air outlet 210, one end of the tooth-like protrusion 700 is connected to the guide tail 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 tooth-like protrusion 700 tends to decrease, and multiple tooth-like protrusions 700 are arranged along the circumference of the air outlet 210.

[0070] This design is mainly to further optimize the guiding effect of the airflow. By providing the tooth-shaped protrusion 700 at the air outlet 210, the flow direction of the airflow can be better guided, the degree of turbulence of the airflow can be reduced, and the directionality of the airflow can be improved. The design of the cross-sectional area of ​​the tooth-shaped protrusion 700 showing a decreasing trend can gradually shrink the airflow, increase the airflow speed, and thus improve the thrust efficiency. The design of multiple tooth-shaped protrusions 700 arranged circumferentially along the air outlet 210 can evenly guide the airflow in the entire air outlet 210 area.

[0071] Specifically, the design of the tooth-shaped protrusions 700 can be implemented in a variety of ways. For example, the tooth-shaped protrusions 700 can be a plurality of triangular structures arranged at equal intervals, or a trapezoidal or curved structure. The number of tooth-shaped protrusions 700 can be adjusted according to the size of the air outlet 210 and the specific application scenario to ensure sufficient diversion effect without excessively increasing resistance.

[0072] The tooth-shaped protrusion 700 forms a coordinated system with the guide tail 200 and the air propeller 500. The guide tail 200 guides the airflow into the air outlet 210, and the tooth-shaped protrusion 700 further optimizes the outlet characteristics of the airflow. This design not only improves the directionality of the airflow, but also reduces the formation of the tail vortex to a certain extent, thereby improving the efficiency of the entire rotor module. In addition, the tooth-shaped protrusion 700 can also reduce the noise generated by the airflow to a certain extent.

[0073] In one embodiment, if Figure 4 As shown, the gravity heat pipe 400 includes 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 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, and 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 includes a liquid absorption core 810, and the two ends of the liquid absorption core 810 are respectively connected to the liquid storage section 800 and the evaporation section 410.

[0074] The present application further improves the heat dissipation efficiency through the special design of the gravity heat pipe 400. Specifically, the evaporation section 410 of the gravity heat pipe 400 is close to the motor component 300 and can directly absorb the heat generated by the motor component 300. The condensation section 420 is arranged at a position close to the air inlet 110, and can make full use of the incoming cold air for heat dissipation. The liquid storage section 800 and the condensation section 420 are arranged radially opposite to each other. When the air paddle 500 is horizontal, the condensation section 420 is at the top. This layout utilizes the effect of gravity to allow the condensed liquid to naturally flow back to the liquid storage section 800.

[0075] The provision of the liquid wick 810 further enhances the circulation efficiency of the heat pipe. The liquid 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 that the evaporation part 410 has a continuous supply of cooling liquid. This design enables the heat pipe to maintain a good heat dissipation effect in various postures.

[0076] This design has significant advantages over traditional heat dissipation structures. Traditional heat dissipation usually relies on direct air cooling, which is inefficient and easily affected by flight posture. The gravity heat pipe structure of the present application utilizes the phase change principle, has higher heat dissipation efficiency, and is not restricted by flight posture. At the same time, the design of the guide portion 440 ensures that the cold air can effectively reach the condensation portion 420, further improving the heat dissipation efficiency.

[0077] Furthermore, in one embodiment, the evaporation portion 410 and the condensation portion 420 are connected via a conduit 430 , and a diversion protrusion 900 is fixedly sleeved on the outer side of the conduit 430 .

[0078] Such an arrangement allows a certain distance between the evaporation portion 410 and the condensation portion 420 , which greatly enhances the layout flexibility of the gravity heat pipe 400 .

[0079] Furthermore, in one embodiment, the gravity heat pipe 400 also includes a guide portion 440, which connects the air inlet 110 and the condensation portion 420 so that the air flow can enter the condensation portion 420 through the guide portion 440, and the flow area of ​​the guide portion 440 tends to increase along the direction from the air inlet 110 to the condensation portion 420.

[0080] The guide portion 440 connects the air inlet 110 and the condensation portion 420, so that the cold air can directly enter the condensation portion 420. More importantly, the flow area of ​​the guide portion 440 gradually increases along the airflow direction. This design can reduce the airflow speed and prolong the contact time between the cold air and the condensation portion 420, thereby improving the heat exchange efficiency.

[0081] Specifically, in one embodiment, the air guide portion 440 is directly connected to the air inlet 110 and the condensation portion 420 .

[0082] In another embodiment, if Figure 2 As shown, the liquid storage section 800 and the air inlet 110 are spaced apart so that the condensation section 420 , the liquid storage section 800 , and the inner wall of the first shell form a boosting channel 140 , and the boosting channel 140 can be connected through the condensation section 420 and the air outlet 210 .

[0083] 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 wind cover 100 together form a boost channel 140. This boost channel 140 is connected through the condensation part 420 and the air outlet 210, thereby creating an optimized airflow path. When the airflow enters through the air inlet 110, part of the airflow will enter this boost channel 140. Due to the special design of the channel, the airflow will produce a certain pressure increase when passing through, and this pressure increase helps to improve the flow rate and heat exchange efficiency of the airflow.

[0084] In one embodiment, if Figure 4 As shown, the stator 320 of the motor component 300 is hollowed out and constitutes the evaporation portion 410 of the gravity heat pipe component 400 .

[0085] 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 portion 410 of the gravity heat pipe 400, so that the working fluid can directly absorb the heat generated by the stator 320 of the motor component 300.

[0086] The advantage of this design is that it utilizes the efficient heat transfer characteristics of the gravity heat pipe 400, and closely combines the heat dissipation of the motor component 300 with the working process of the gravity heat pipe 400. The stator 320 is hollowed out as an evaporation portion 410, which can quickly absorb the heat generated by the stator 320 and quickly transfer the heat to the working fluid. In this way, not only can efficient heat dissipation of the motor component 300 be achieved. In addition, the layout of the gravity heat pipe 400 can be optimized, and the volume required for the gravity heat pipe 400 can be reduced, thereby making the volume of the tail section guide rotor module more compact.

[0087] However, the invention is not limited thereto. In other embodiments, the gravity heat pipe 400 may 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 .

[0088] The present application also provides a rotorcraft, which includes the tail-section guide rotor module described in any one of the above embodiments.

[0089] The technical features of the above-described embodiments may be arbitrarily combined. To make the description concise, not all possible combinations of the technical features in the above-described embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0090] The above-described embodiments only express several implementation methods of the present application, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the scope of the patent application. It should be pointed out that, for a person of ordinary skill in the art, several variations and improvements can be made without departing from the concept of the present application, and these all belong to the protection scope of the present application. Therefore, the scope of patent protection of the present application shall be subject to the attached claims.

[0091] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0092] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying 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 the description of this application, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0093] In this application, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0094] In the present application, unless otherwise clearly specified and limited, a first feature being “above” or “below” a 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, a first feature being “above”, “above”, and “above” a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being “below”, “below”, and “below” a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0095] It should be noted that when an element is referred to as being "fixed to" or "disposed on" another element, it may be directly on the other element or there may be a central element. When an element is considered to be "connected to" another element, it may be directly connected to the other element or there may be a central element at the same time. The terms "vertical", "horizontal", "upper", "lower", "left", "right" and similar expressions used herein are for illustrative purposes only and are not intended to be the only implementation method.

[0096] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as those commonly understood by those skilled in the art to which this application belongs. The terms used herein in the specification of this application are only for the purpose of describing specific embodiments 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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