Power assembly and cross-medium rotorcraft containing the same

Abstract

The present invention belongs to the technical field of structural design and power propulsion of a trans-medium aircraft, and provides a power assembly and a trans-medium rotorcraft including the same. The power assembly includes a blade structure and a guide frame. The blade structure includes a duct wall, a shaft, an inner blade and an outer blade, and the blade of the outer blade is longer in radial dimension and has a smaller change in blade surface spiral curvature than the blade of the inner blade. The guide frame is coaxially arranged with the blade structure and the blade structure is rotatably arranged on the inner side of the guide frame; the guide frame includes a front control panel, a rear control panel and a structural wall. When the aircraft is working underwater, the front control panel and the rear control panel are both in a closed state to isolate the outer blade from the water, and the power is provided by the inner blade; when the aircraft is working in the air, the front control panel and the rear control panel are both in an open state, and the power is provided by the outer blade. The present invention reduces the workload and repeated design of the aircraft by using the same set of blades and motors.

Description

Technical Field

[0001] The present invention relates to the field of structural design and power propulsion technology of a trans-medium aircraft, and in particular to a trans-medium rotorcraft and a power component therein. Background Art

[0002] Rotorcraft are increasingly being used due to their low cost, low security requirements, strong maneuverability, low safety risk factor and high reusability. They are not only widely used in the civilian field, but also have broad prospects in the military field. In recent years, the development of rotorcraft, especially rotorcraft UAV technology, has been centered on improving the versatility and large-scale of the aircraft, and expanding the working field and environment, requiring the ability to work in multiple environments and wide fields, such as cross-media performance.

[0003] In cross-medium motion, water and air have different factors such as density, viscosity, and thermal conductivity. The blades in the air rotate fast and have low torque, which results in less air resistance, less motor power, and less heat. The blades in the water rotate slowly and have high torque, which results in greater motor power and heat. This makes the rotor structure originally designed for single-medium motion less adaptable to complex environments, ultimately leading to structural function failure and even equipment damage.

[0004] Most of the existing classic cross-medium aircraft rotors are designed with two sets of propellers with different functions to work in the air and underwater respectively. The two sets of structures are independent of each other, and the motors and blades are designed differently, and the aircraft attitude is controlled by the rudder structure. First, the use of multiple sets of different motors and blades and the separate waterproof design for the aerial working part increase the design difficulty of the equipment and the maintenance and repair costs of the equipment in the later stage. Secondly, multiple sets of different motors and blades increase the control difficulty of the equipment. Third, there are a lot of non-working loads on the equipment after the medium crossing is completed. When the aircraft is working in the water, the air rotor and motor are completely non-working, and this part of the weight increases the workload, and vice versa. Fourth, compared with the water propeller, the air propeller is larger in size and occupies more space. The external form generally used is more prone to damage; the larger and more prominent structural design will destroy the overall streamline of the equipment and increase the movement resistance. Fifth, compared with the air, the movement resistance of the equipment in the water is greater, and the motor heats up more strongly, but in order to ensure waterproofness, the equipment needs to meet the sealing requirements, so it is difficult to dissipate heat in the water. Summary of the invention

[0005] In order to solve the above technical problems, the present invention provides a power assembly and a trans-medium rotorcraft including the same.

[0006] In the first aspect, the present invention provides a power assembly for a cross-medium rotorcraft, comprising a blade structure and a guide frame. The blade structure comprises a duct wall, a shaft, an inner blade and an outer blade, the shaft is coaxially arranged with the duct wall, the inner side of the inner blade is fixedly connected to the shaft, the outer side of the inner blade is fixedly connected to the inner side of the duct wall, the inner side of the outer blade is fixedly connected to the outer side of the duct wall, and the blade of the outer blade is longer in radial dimension and has a smaller change in blade surface spiral curvature than the blade of the inner blade. The guide frame is coaxially arranged with the blade structure and the blade structure is rotatably arranged on the inner side of the guide frame; the guide frame comprises a front control plate, a rear control plate and a structural wall surface, the front control plate and the rear control plate are respectively configured as annular plates that can be opened and closed, the structural wall surface is respectively connected to the outer edge of the front control plate and the outer edge of the rear control plate in the front-to-back direction and forms a circumferentially closed cylinder, and the inner edge of the front control plate and the inner edge of the rear control plate are respectively sealed and connected to the outer side of the duct wall. When the trans-medium rotorcraft is working underwater, the front control panel and the rear control panel are both in a closed state to isolate the outer blades from the water, and the power is provided by the inner blades; when the trans-medium rotorcraft is working in the air, the front control panel and the rear control panel are both in an open state, and the power is provided by the outer blades. Further, the power assembly also includes a blade motor, which is coupled to the shaft, and a motor support portion is provided in the middle of the rear side of the guide frame, and the motor support portion is used to install the blade motor.

[0007] Furthermore, the front control panel and the rear control panel are respectively constructed to include a plurality of sub-panels, each sub-panel including a fixed panel and a movable panel, the fixed panel is fixed, and the movable panel can be controlled to fold around the fixed panel so that each sub-panel is in an open state or a closed state; when the front control panel or the rear control panel is in a closed state, all the sub-panels of the front control panel or the rear control panel are in a closed state; when the front control panel or the rear control panel is in an open state, at least one sub-panel of the front control panel or the rear control panel is in an open state.

[0008] In some embodiments, when the sub-plate is closed, the movable plate is flush with the front and rear surfaces of the fixed plate; when the sub-plate is open, the movable plate is folded backward relative to the fixed plate until the plate surface of the movable plate is parallel to the airflow direction.

[0009] In some embodiments, when the sub-plate is in a closed state, the front and rear surfaces of the movable plate are flush with the fixed plate; when the sub-plate is in an open state, the plate surface of the movable plate is neither perpendicular nor parallel to the airflow direction.

[0010] Furthermore, the inner edges of the front control plate and the rear control plate are sealed and connected to the outer side of the duct wall by at least one of a bearing water seal, a combined water seal, an outer ring seal, a double end face seal and a gas seal.

[0011] Preferably, the guide frame is provided with an air inlet and an air outlet connected to the cavity defined between the guide frame and the duct wall, and the air inlet and the air outlet are used to provide a heat dissipation channel for the cooling airflow for cooling other equipment in the trans-medium rotorcraft. When the trans-medium rotorcraft is working underwater, the rotating outer blades provide power for the flow of the airflow entering the cavity defined between the guide frame and the duct wall, so that the airflow before cooling flows into the interior of the guide frame through the air inlet and exchanges heat with the duct wall, and the airflow after cooling flows out of the guide frame from the air outlet.

[0012] Preferably, the air inlet is arranged on the structural wall surface located at the front side of the blade structure, and the air outlet is arranged on the structural wall surface located at the rear side of the blade structure.

[0013] Preferably, the air inlet and the air outlet are both configured as openings with adjustable openings, and the air inlet is provided with a drainage fan.

[0014] In a second aspect, the present invention further provides a cross-medium rotor aircraft including a power assembly according to the first aspect, wherein the front side of the blade structure is arranged in an upward direction corresponding to the fuselage of the cross-medium rotor aircraft, and the rear side of the blade structure is arranged in a downward direction corresponding to the fuselage of the cross-medium rotor aircraft.

[0015] The features and advantages of the present invention include: by using the same set of blades and motors when working underwater and in the air, the working load and repeated design of the aircraft are reduced; by changing the direct contact area between the blades and different media, the flow field environment in which the blades work is improved, thereby avoiding damage to structures such as the blades; and by utilizing the closed channel design and the pressure difference on both sides when working in water, the internal heat dissipation efficiency of the aircraft is improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions in the embodiments of the present disclosure, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present disclosure. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0017] Figure 1 A three-dimensional schematic diagram of a blade structure of the present invention is shown;

[0018] Figure 2 A three-dimensional schematic diagram of a power assembly of the present invention is shown, wherein the first control panel and the second control panel are both in a fully opened state;

[0019] Figure 3 Shows Figure 2 A schematic front view of a power assembly in FIG.

[0020] Figure 4 Shows Figure 2 A bottom view schematic diagram of a power assembly in FIG.

[0021] Figure 5 Shows Figure 3 AA cross-sectional view of the power assembly in FIG.

[0022] Figure 6 A three-dimensional schematic diagram of a power assembly of the present invention is shown, wherein the first control panel and the second control panel are both in a fully closed state;

[0023] Figure 7 Shows Figure 6 A schematic front view of a power assembly in FIG.

[0024] Figure 8 An embodiment of the invention is shown Figure 7 BB cross-sectional view of the power assembly in FIG.

[0025] Fig. 9 Another embodiment is shown Figure 7 BB cross-sectional view of the power assembly in FIG.

[0026] Fig.10 A three-dimensional schematic diagram of a power assembly of the present invention is shown, wherein the first control panel is in a partially open state and the second control panel is in a fully open state;

[0027] Fig.11 Shows Fig.10 A schematic front view of a power assembly in FIG.

[0028] Fig.12 Shows Fig.11 Schematic diagram of CC cross-section of the power assembly.

[0029] Description of reference numerals:

[0030] 10-blade structure, 12-inner blade, 14-outer blade, 15-shaft, 16-duct wall;

[0031] 20- flow guide frame, 22- front control panel, 24- rear control panel, 26- structural wall, 262- air inlet, 264- air outlet, 28- sub-plate, 282- fixed plate, 284- movable plate;

[0032] 30-power assembly, 32-drainage fan, 36-sealing ring, 38-motor support part. DETAILED DESCRIPTION

[0033] The following will be combined with the drawings in the embodiments of the present disclosure to clearly and completely describe the technical solutions in the embodiments of the present disclosure. Obviously, the described embodiments are only part of the embodiments of the present disclosure, not all of the embodiments. Based on the embodiments in the present disclosure, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present disclosure.

[0034] In a far field environment, the direction of movement of the flow field fluid is from the front to the rear. When describing the present invention, "front" and "rear" are both referenced to the direction of movement of the fluid in the far field. When one or more components are described as being connected, linked, fixed, coupled, attached or otherwise interconnected, such interconnection may be a direct interconnection between the components, or may be an indirect interconnection, such as by using one or more intermediate components.

[0035] refer to Figure 1 The present invention provides an integrated blade structure 10, which can be applied to a dual-purpose water-air rotorcraft. The blade structure 10 includes a duct wall 16, a shaft 15, an inner blade 12 and an outer blade 14. The shaft 15 is coaxially arranged with the duct wall 16. The inner side of the inner blade 12 is fixedly connected to the shaft 15, the outer side of the inner blade 12 is fixedly connected to the inner side of the duct wall 16, the inner side of the outer blade 14 is fixedly connected to the outer side of the duct wall 16, and the outer side of the outer blade 14 is suspended. The shaft 15 is coupled to a blade motor (not shown in the figure). When the shaft 15 drives the inner blade 12 to rotate, the duct wall 16 and the outer blade 14 rotate synchronously with the inner blade 12.

[0036] The number of inner blades 12 and outer blades 14 can be two, three or more respectively. The blades of the inner blades 12 and the outer blades 14 are both spiral structures. The blades of the outer blades 14 are relatively long in radial direction, and the spiral curvature of the blades varies less, which is in line with the characteristics of high speed and small torque required when the cross-medium rotorcraft is flying in the air. The blades of the inner blades 12 are relatively short in radial direction, and the spiral curvature of the blade surface is relatively large, which is convenient for converting the rotation of the blades into a sufficiently large axial thrust when diving underwater, which is in line with the characteristics of low speed and large torque required when the aircraft is diving underwater.

[0037] refer to Figures 2 to 12 The present invention also provides a power assembly 30 for a cross-medium rotorcraft. The power assembly 30 includes a guide frame 20, an integrated blade structure 10 and a blade motor (not shown). The blade motor is coupled to the shaft 15, and a motor support portion 38 is provided in the middle of the rear side of the guide frame 20, and the motor support portion 38 is used to install the blade motor. The power assembly 30 can change the flow field environment where the blade is located by limiting the contact between the blade and different media on the basis of effectively utilizing a single blade structure and a blade motor, while additionally improving the internal heat dissipation environment of the aircraft, and ultimately improving the working efficiency of the equipment.

[0038] refer to Figure 2 The guide frame 20 is coaxially arranged with the shaft 15 of the blade structure 10, and the blade structure 10 is rotatably arranged on the inner side of the guide frame 20. The guide frame 20 includes a front control panel 22, a rear control panel 24 and a structural wall 26. The front control panel 22 and the rear control panel 24 are respectively configured as annular plates that can be opened and closed. The structural wall 26 is respectively connected to the outer edge of the front control panel 22 and the outer edge of the rear control panel 24 in the front-to-back direction and forms a circumferentially closed cylinder. The inner edge of the front control panel 22 and the inner edge of the rear control panel 24 are respectively sealed and connected to the outer side of the duct wall 16. Among them, the structural wall 26 can be made into an integrated structure with the body structure of other parts of the aircraft. The inner blade 12 of the blade structure 10 radially extends between the shaft 15 and the duct wall 16, and the outer blade 14 of the blade structure 10 radially extends between the duct wall 16 and the structural wall 26. Specifically, the front control panel 22 and the rear control panel 24 can be opened and closed by a motor (not a blade motor) or a hydraulic device configured inside the trans-medium aircraft. When the trans-medium rotorcraft is working underwater, both the front control panel 22 and the rear control panel 24 are in a closed state (refer to Figure 6 and Figure 7 ), the outer blades 14 are isolated from the water, and the power of the aircraft is provided by the inner blades 12. When the trans-medium rotor aircraft is working in the air, both the front control panel 22 and the rear control panel 24 are in the open state (refer to Figure 2 , Figure 3 , Fig.10 and Fig.11 ), the power of the aircraft is provided by the outer blades 14. Closing in the present invention refers to blocking the fluid path, and opening refers to passing the fluid path.

[0039] Specifically, the inner edge of the front control plate 22 and the inner edge of the rear control plate 24 can be sealed to the outer side of the duct wall 16 by at least one of a bearing water seal, a combined water seal, an outer ring seal, a double end seal and a gas seal. Fig. 9 The inner edge of the front control plate 22 and the inner edge of the rear control plate 24 are sealed to the outer side of the duct wall 16 via a sealing ring 36 .

[0040] The outer side of the structural wall 26 is in communication with the airflow of other equipment inside the cross-medium rotorcraft. The guide frame 20 is provided with an air inlet and an air outlet that are in communication with the cavity defined between the guide frame 20 and the duct wall 16. The air inlet and the air outlet are used to provide a heat dissipation channel for the hotter airflow generated by other equipment in the cross-medium rotorcraft. When the cross-medium rotorcraft is operating underwater, the rotating outer blades 14 provide power for the flow of the airflow entering the cavity defined between the guide frame 20 and the duct wall 16, so that the airflow before cooling flows into the interior of the guide frame 20 through the air inlet and exchanges heat with the duct wall 16, and the airflow after cooling flows out of the guide frame 20 from the air outlet. Preferably, reference Figure 8 The structural wall surface 26 located at the front side of the blade structure 10 is provided with an air inlet 262, and the structural wall surface 26 located at the rear side of the blade structure 10 is provided with an air outlet 264. When the cross-medium aircraft is working underwater, the airflow outside the structural wall surface 26 flows into the interior of the guide frame 20 through the air inlet 262 and exchanges heat with the duct wall 16, and then returns to the outside of the structural wall surface 26 through the air outlet 264.

[0041] More specifically, by designing the direction of the heat dissipation channel on the outside of the structural wall 26, the airflow passes through the equipment or devices with high heat generation in other structures of the aircraft, such as batteries and other motor structures; after the air in the heat dissipation channel passes through the various heat generating devices, the hot air returns to the front side of the blade. Because the inner side of the duct wall 16 is liquid and connected to the external environment, the hot airflow exchanges heat and cools down with the water by contacting the duct wall 16, achieving the design purpose of heat dissipation.

[0042] Preferably, the air inlet 262 and the air outlet 264 are each configured as two, and the two air inlets 262 and the two air outlets 264 are symmetrically arranged on both sides of the structural wall 26. More preferably, each air inlet 262 and air outlet 264 is configured as an opening with an adjustable opening, so as to achieve controllable heat dissipation efficiency and prevent water from entering the interior of the aircraft after the closed channel fails and water enters. Preferably, the air inlet 262 is also provided with a drainage fan 32, which can increase the flow rate of the heat dissipation airflow and achieve controllable heat dissipation efficiency.

[0043] Further, the cross-sectional areas of the front control panel 22 and the rear control panel 24 are equal, and the front control panel 22 and the rear control panel 24 are respectively configured to include a plurality of sub-panels 28, and the sum of the areas of the plurality of sub-panels 28 is equivalent to the cross-sectional area of ​​the front control panel 22 or the rear control panel 24. Figure 2 , the front control panel 22 is used as an example for explanation. Each sub-panel 28 includes a fixed panel 282 and a movable panel 284. The fixed panel 282 is fixed relative to the duct wall 16 and the structural wall surface 26, and the movable panel 284 can be controlled to fold around the fixed panel 282 to make each sub-panel 28 open or closed. Figure 6 and Figure 7When the front control panel 22 or the rear control panel 24 is in the closed state, all the sub-panels 28 of the front control panel 22 or the rear control panel 24 are in the closed state. Figure 2 , Figure 3 , Fig.10 and Fig.11 , when the front control panel 22 or the rear control panel 24 is in an open state, at least one sub-panel 28 of the front control panel 22 or the rear control panel 24 is in an open state. In some embodiments, reference Figure 5 , the sub-plate 28 may be configured to include a fixed plate 282 located in the middle and two movable plates 284 connected to both sides of the fixed plate 282. In other embodiments, the sub-plate 28 may be configured to include a fixed plate 282 and a movable plate 284 connected to a single side of the fixed plate 282. More specifically, when the front control panel 22 is in an open state, the air flow channel between adjacent sub-plates 28 is roughly fan-shaped. The area configuration between the fixed plate 282 and the movable plate 284 needs to satisfy that the area proportion of the movable plate 284 is as large as possible, so that when the sub-plate is in an open state, the conduction area of ​​the flow field is as large as possible, reducing the resistance of air flight.

[0044] The present invention drives the opening and closing of each sub-panel 28 by a motor (not a blade motor) configured inside the trans-medium rotorcraft to realize the opening and closing of the front control panel 22 and the rear control panel 24. When the sub-panel 28 is in a closed state, the movable panel 284 is flush with the front and rear surfaces of the fixed panel 282; when the sub-panel 28 is in an open state, the movable panel 284 is folded backward relative to the fixed panel 282. In some embodiments, when the sub-panel 28 is in an open state, the plate surface of the movable panel 284 is parallel to the airflow direction. In other embodiments, when the sub-panel 28 is in an open state, the plate surface of the movable panel 284 is neither perpendicular nor parallel to the airflow direction.

[0045] When all sub-panels 28 are closed, the front control panel 22, the rear control panel 24, the duct wall 16 and the structural wall 26 can form a closed channel, and the outer blades 14 are located in the closed channel. Each sub-panel 28 on the front control panel 22 and the rear control panel 24 can be independently controlled to form a partial opening or flow limiting of the closed channel, thereby achieving control of the aircraft such as attitude adjustment, steering, speed change, etc. When the front control panel 22 and the rear control panel 24 are both in an open state, the opening and closing configuration of each sub-panel 28 of the front control panel 22 is not necessarily completely consistent with the opening and closing configuration of each sub-panel of the rear control panel 24. For example, refer to Figures 10 to 12 Each sub-plate 28 can be independently controlled to tilt in the same direction, which guides the airflow blown out of the propeller. The difference in flow fields on the left and right sides produces a left-right pressure difference, which causes the overall structure to be subjected to lateral force, thereby realizing the control of the movement posture of the aircraft.

[0046] On the other hand, the present invention also provides a cross-medium multi-rotor aircraft including the aforementioned power assembly 30. The front side of the blade structure 10 is arranged in the upward direction corresponding to the fuselage of the cross-medium rotor aircraft, and the rear side of the blade structure 10 is arranged in the downward direction corresponding to the fuselage of the cross-medium rotor aircraft. When the aircraft is working in the water, the front control panel 22 and the rear control panel 24 are completely closed, and there is no water in the sealed channel; the closed surfaces of the front and rear control panels and the blade structure 10 form a small underwater ducted propeller structure; the blade motor is adjusted to use low speed and high torque for underwater work. When the aircraft is working in the air, for example, the front control panel 22 and the rear control panel 24 are fully opened, the blade structure 10 and the overall structure of the aircraft form a large ducted propeller structure; the outer blade 14 provides lift in full size, giving full play to the structural advantages of the ducted propeller; at this time, the blade motor uses high speed and small torque to work in the air.

[0047] The blade structure and power assembly provided by the present invention have the following advantages:

[0048] 1) By using the same set of blades and motors, the workload and repeated design of the cross-medium rotorcraft are reduced;

[0049] 2) By changing the direct contact area between the blades and different media, the flow field environment of the blades is improved, thus avoiding damage to the blades and other structures;

[0050] 3) The design incorporates the design of ducted propellers and has certain characteristics and advantages of ducted propellers;

[0051] 4) Using the closed channel design and the pressure difference on both sides when working in water, the internal heat dissipation efficiency of the aircraft can be improved;

[0052] 5) Independently control each sub-board on the front and rear control panels to achieve control of the aircraft's motion posture.

[0053] Overall, the present invention reduces the disadvantages of traditional solutions and reduces the modification of other existing mature structures of the aircraft. It improves the adaptability of the aircraft to the cross-media motion environment, increases system stability, is more convenient and safe, and reduces work costs overall.

[0054] The above are only several embodiments of the present disclosure. Those skilled in the art may make various changes or modifications to the embodiments of the present disclosure based on the contents disclosed in the application documents without departing from the spirit and scope of the present disclosure.

Claims

1. A power assembly for a trans-medium rotorcraft, characterized in that: The power assembly comprises: A blade structure, the blade structure comprising a duct wall, a shaft, an inner blade and an outer blade, the shaft being coaxially arranged with the duct wall, the inner side of the inner blade being fixedly connected to the shaft, the outer side of the inner blade being fixedly connected to the inner side surface of the duct wall, the inner side of the outer blade being fixedly connected to the outer side surface of the duct wall, the blade of the outer blade being longer in radial direction and having a smaller change in blade surface spiral curvature than the blade of the inner blade; and A guide frame, wherein the guide frame is coaxially arranged with the blade structure and the blade structure is rotatably arranged on the inner side of the guide frame; the guide frame comprises a front control plate, a rear control plate and a structural wall surface, wherein the front control plate and the rear control plate are respectively configured as openable and closable annular plates, wherein the structural wall surface is respectively connected to the outer edge of the front control plate and the outer edge of the rear control plate in the front-to-back direction to form a circumferentially closed cylinder, and the inner edge of the front control plate and the inner edge of the rear control plate are respectively sealed and connected to the outer side surface of the duct wall; When the trans-medium rotor aircraft is working underwater, the front control panel and the rear control panel are both in a closed state to isolate the outer blades from water, and power is provided by the inner blades; when the trans-medium rotor aircraft is working in the air, the front control panel and the rear control panel are both in an open state, and power is provided by the outer blades.

2. The power assembly according to claim 1, characterized in that: The front control panel and the rear control panel are respectively constructed to include a plurality of sub-panels, each of which includes a fixed panel and a movable panel, the fixed panel is fixed, and the movable panel can be controlled to fold around the fixed panel to make each sub-panel in an open state or a closed state; when the front control panel or the rear control panel is in a closed state, all the sub-panels of the front control panel or the rear control panel are in a closed state; when the front control panel or the rear control panel is in an open state, at least one sub-panel of the front control panel or the rear control panel is in an open state.

3. The power assembly according to claim 2, characterized in that: When the sub-plate is in a closed state, the movable plate is flush with the front and rear surfaces of the fixed plate; when the sub-plate is in an open state, the movable plate is folded backward relative to the fixed plate until the plate surface of the movable plate is parallel to the airflow direction.

4. The power assembly according to claim 2, characterized in that: When the sub-plate is in a closed state, the movable plate is flush with the front and rear surfaces of the fixed plate; when the sub-plate is in an open state, the plate surface of the movable plate is neither perpendicular nor parallel to the airflow direction.

5. The power assembly according to claim 1, characterized in that: The inner edges of the front control plate and the rear control plate are sealed and connected to the outer side surface of the duct wall by at least one of a bearing water seal, a combined water seal, an outer ring seal, a double end face seal and a gas seal.

6. The power assembly according to claim 1, characterized in that: The guide frame is provided with an air inlet and an air outlet which are connected to the cavity defined between the guide frame and the duct wall, and the air inlet and the air outlet are used to provide a heat dissipation channel for the cooling airflow for cooling other equipment in the trans-medium rotorcraft; When the cross-medium rotorcraft is operating underwater, the rotating outer blades provide power for the flow of air entering the defined cavity, so that the airflow before cooling flows into the interior of the guide frame through the air inlet and exchanges heat with the duct wall, and the airflow after cooling flows out of the guide frame from the air outlet.

7. The power assembly according to claim 6, characterized in that: The air inlet is arranged on the structural wall surface located at the front side of the blade structure, and the air outlet is arranged on the structural wall surface located at the rear side of the blade structure.

8. The power assembly according to claim 7, characterized in that: The air inlet and the air outlet are both configured as openings with adjustable openings, and the air inlet is provided with a drainage fan.

9. The power assembly according to claim 1, characterized in that: The power assembly also includes a blade motor, which is coupled to the shaft. A motor support portion is provided in the middle of the rear side of the guide frame, and the motor support portion is used to install the blade motor.

10. A trans-medium rotorcraft, characterized in that: The power assembly comprises the power assembly as described in any one of claims 1 to 9, wherein the front side of the blade structure is arranged in an upward direction corresponding to the fuselage of the cross-medium rotor aircraft, and the rear side of the blade structure is arranged in a downward direction corresponding to the fuselage of the cross-medium rotor aircraft.

Images