Blade structure and power assembly for trans-medium rotorcraft

Abstract

The present invention belongs to the fields of structural design and power propulsion technology of cross-medium aircraft, and provides a blade structure and power assembly for cross-medium rotorcraft. The blade structure includes a shaft, an inner blade, a duct wall and an outer blade. The duct wall is coaxially arranged with the shaft, the inner side of the inner blade is fixedly connected to the shaft, the inner blade extends radially between the shaft and the duct wall, the inner side of the outer blade is attached to the outer side of the duct wall, the outer side of the outer blade is suspended, and one of the outer blade and the inner blade is fixedly connected to the duct wall. Among them, the blade of the outer blade is longer in radial dimension than the blade of the inner blade, and the change of the spiral curvature of the blade surface is smaller; when the inner blade rotates synchronously with the shaft, the outer blade can selectively rotate synchronously with the shaft through the duct wall. The present invention can selectively rotate or not rotate the outer blade according to the heat dissipation inside the aircraft, taking into account the power consumption control and internal heat dissipation requirements when the aircraft is working underwater.

Description

Technical Field

[0001] The present invention relates to the field of structural design and power propulsion technology for a trans-medium aircraft, and in particular to a blade structure and a power assembly for a trans-medium rotorcraft. 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 blade structure and a power assembly for a cross-medium rotorcraft.

[0006] On the one hand, the present invention provides a blade structure for a cross-medium rotorcraft, the blade structure comprising a shaft, an inner blade, a duct wall and an outer blade. The duct wall is coaxially arranged with the shaft, the inner side of the inner blade is fixedly connected to the shaft, the inner blade radially extends between the shaft and the duct wall, the inner side of the outer blade is attached to the outer side of the duct wall, the outer side of the outer blade is suspended in the air, and one of the outer blade and the inner blade is fixedly connected to the duct wall. Among them, 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; when the inner blade rotates synchronously with the shaft, the outer blade can selectively rotate synchronously with the shaft through the duct wall.

[0007] In some embodiments, the outer side of the inner blade is suspended, and the inner side of the outer blade is fixedly connected to the outer side of the duct wall. At least one coupling mechanism is provided on the inner side of the duct wall, and each coupling mechanism is attached to the shaft avoiding the inner blade. A clutch connection is provided between at least one of the coupling mechanisms and the shaft, and the clutch connection is configured to revocably connect the shaft and the coupling mechanism, thereby reversibly coupling the shaft to the outer blade. A bearing is provided between at least one of the coupling mechanisms and the shaft, and the outer blade and the duct wall are supported by the shaft through the bearing.

[0008] Preferably, the coupling mechanism is configured to include a bracket and a support ring, the support ring is sleeved on the outer side of the shaft and is coaxially arranged with the shaft, and the bracket extends radially inward from the inner side of the duct wall and is connected to the support ring. The clutch connection is configured to revocably connect the shaft and the support ring. The bearing is arranged between the shaft and the support ring, the inner side of the bearing is coupled to the shaft, and the outer side of the bearing is coupled to the support ring.

[0009] In other embodiments, the outer side of the inner blade is fixedly connected to the inner side of the duct wall. The outer side of the duct wall is sleeved with a coupling mechanism, and the inner side of the outer blade is fixedly connected to the coupling mechanism. A clutch connection is provided between the coupling mechanism and the duct wall, and the clutch connection is configured to revocably connect the duct wall to the coupling mechanism, and then reversibly couple the outer blade to the shaft. A bearing is also provided between the coupling mechanism and the duct wall, and the outer blade is supported by the duct wall through the bearing.

[0010] Preferably, the coupling mechanism is configured as a support ring, the support ring is sleeved on the outer side of the duct wall and is coaxially arranged with the shaft, the inner side of the outer blade is fixedly connected to the support ring, the bearing is arranged between the duct wall and the support ring, the inner side of the bearing is coupled to the duct wall, and the outer side of the bearing is coupled to the support ring.

[0011] Preferably, the clutch connector has a telescopic portion, and a groove structure is provided on the inner side of the support ring; when the telescopic portion is controlled to move into the groove structure, the outer blade is coupled to the shaft. When the telescopic portion is controlled to move out of the groove structure, the outer blade is decoupled from the shaft.

[0012] On the other hand, the present invention also provides a power assembly, which includes a guide frame, a blade motor and the blade structure of the first aspect. The guide frame is coaxially arranged with the blade structure and is located outside the blade structure. The guide frame includes a front control panel, a rear control panel and a structural wall. The front control panel and the rear control panel are respectively configured as annular plates that can be opened and closed. The structural wall is respectively connected to the outer edge of the front control panel and the outer edge of the rear control panel in the front-to-back direction to form a circumferentially closed cylinder. The inner edge of the front control panel and the inner edge of the rear control panel are respectively sealed and connected to the outer side of the duct wall. The blade motor is installed in the middle of the rear side of the guide frame, and the blade motor is coupled to the shaft. 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.

[0013] 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.

[0014] 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 airflow for cooling other equipment in the trans-medium rotorcraft. When the trans-medium rotorcraft is working underwater, the clutch connection can be selectively controlled to move so that the outer blades are coupled to the shaft, and the outer blades rotate synchronously with the shaft, and the 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.

[0015] 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, and both the air inlet and the air outlet are constructed as openings with adjustable openings.

[0016] The features and advantages of the present invention include: when working underwater and in the air, the same set of blades and motors are used, which reduces the working load and repeated design of the aircraft; by changing the direct contact area between the blades and different media, the flow field environment of the blades is improved, and damage to the blades and other structures is avoided. When working underwater, the outer blades can be selectively rotated or not according to the heat dissipation inside the aircraft, taking into account the power consumption control during underwater work and the heat dissipation requirements of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] 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 creative work.

[0018] Figure 1 A perspective schematic diagram showing a blade structure according to an exemplary embodiment of the present invention;

[0019] Figure 2 Shows Figure 1 AA cross-sectional view of the blade structure, wherein the clutch connector connects the shaft to the duct wall;

[0020] Figure 3 Shows Figure 1 AA cross-sectional view of the blade structure in FIG. 1 , wherein the clutch connector causes the shaft and the duct wall to be in a disconnected state;

[0021] Figure 4 Another embodiment of the blade structure is shown in FIG. Figure 1 The cross-sectional view in the same direction as AA in the figure shows that the clutch connector makes the duct wall and the outer blade connected.

[0022] Figure 5 Another embodiment of the blade structure is shown in FIG. Figure 1 A schematic cross-sectional view with the same sectioning direction as AA, wherein the clutch connector makes the duct wall and the outer blade in a disconnected state;

[0023] 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 opened state;

[0024] Figure 7 Shows Figure 6 A schematic side view of a power assembly in FIG.

[0025] Figure 8 Shows Figure 7 A BB cross-sectional schematic diagram of a power assembly in which the clutch connector couples the outer blade to the shaft;

[0026] Fig. 9 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;

[0027] Fig.10 Shows Fig. 9A schematic side view of a power assembly in FIG.

[0028] Fig.11 Shows Fig.10 A CC cross-sectional view of the power assembly in FIG. 1 , wherein the clutch connector decouples the outer blade from the shaft;

[0029] Fig.12 Another embodiment is shown Fig.10 Schematic diagram of CC cross-section of the power assembly.

[0030] Description of reference numerals:

[0031] 10-blade structure, 12-inner blade, 13-bearing, 14-outer blade, 15-shaft, 16-duct wall, 17-clutch connector, 18-coupling mechanism, 182-support ring, 184-bracket;

[0032] 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;

[0033] 30-power assembly, 32-drainage fan, 36-sealing ring, 38-motor support part. DETAILED DESCRIPTION

[0034] 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.

[0035] 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.

[0036] refer to Figures 1 to 5The present invention provides a blade structure 10, which can be applied to a dual-purpose water and air rotorcraft. The blade structure 10 includes a shaft 15, an inner blade 12, a duct wall 16 and an outer blade 14. The shaft 15 and the duct wall 16 are coaxially arranged, the inner side of the inner blade 12 is fixedly connected to the shaft 15, the inner side of the outer blade 14 is attached to the outer side of the duct wall 16, the outer side of the outer blade 14 is suspended in the air, and one of the outer blade 14 and the inner blade 12 is fixedly connected to the duct wall 16. The number of the inner blade 12 and the outer blade 14 can be two, three or more, respectively. The blades of the inner blade 12 and the outer blade 14 are both spiral structures. The blade size of the outer blade 14 is longer in the radial direction, and the spiral curvature of the blade changes less, which meets the characteristics of the cross-medium rotorcraft that requires high speed and small torque when flying in the air. The inner blade 12 has a shorter blade in radial direction and a larger blade surface spiral arc, which is convenient for converting the blade rotation into a sufficiently large axial thrust when diving underwater, which meets the characteristics of the aircraft requiring low speed and high torque when diving underwater. According to the blade structure 10 of various embodiments provided by the present invention, when the inner blade 12 rotates synchronously with the shaft 15, the outer blade 14 can selectively rotate synchronously with the inner blade 12 through the duct wall 16.

[0037] In some embodiments, the outer side of the inner blade 12 is suspended, and the inner side of the outer blade 14 is fixedly connected to the outer side of the duct wall 16. The inner side of the duct wall 16 is provided with a plurality of (at least one) coupling mechanisms 18, and each coupling mechanism 18 is attached to the shaft 15 avoiding the inner blade 12. Among the plurality of coupling mechanisms 18, a clutch connection 17 is provided between at least one of the coupling mechanisms 18 and the shaft 15, and the clutch connection 17 is configured to revocably connect the shaft 15 and the coupling mechanism 18, thereby reversibly coupling the shaft 15 to the outer blade 14. Among the plurality of coupling mechanisms 18, a bearing 13 is provided between at least one of the coupling mechanisms 18 and the shaft 15, and the outer blade 14 and the duct wall 16 can obtain support from the shaft 15 through the bearing 13. When the clutch connection 17 places the shaft 15 and the coupling mechanism 18 in an unconnected state, the outer blades 14 and the duct wall 16 cannot rotate synchronously with the rotation of the shaft 15 , that is, the outer blades 14 do not rotate synchronously with the inner blades 12 .

[0038] Optionally, the coupling mechanism 18 is configured as two, and the two coupling mechanisms 18 avoid the inner blade 12 and are attached to the shaft 15 at an axial interval. Figure 2 and Figure 3 , the two coupling mechanisms 18 may be respectively arranged at the front end and the rear end of the shaft 15. Alternatively, the two coupling mechanisms 18 may be arranged at intervals along the shaft 15 on the same side of the inner blade 12, for example, on the front side or on the rear side). For example, referring to Figure 2 and Figure 3, the clutch connection 17 is configured as at least one, the bearing 13 is configured as one, the clutch connection 17 is arranged at the coupling mechanism 18 at the front end, and the bearing 13 is arranged at the coupling mechanism 18 at the rear end. Alternatively, the clutch connection 17 is arranged at the coupling mechanism 18 at the rear end, and the bearing 13 is arranged at the coupling mechanism 18 at the front end. Optionally, the clutch connection 17 is configured as three, and the three clutch connections 17 are arranged along the circumference of the shaft 15, which is conducive to strengthening the torque transmission between the shaft 15 and the outer blades 14. Alternatively, the clutch connecting members 17 are constructed as six and the bearings 13 are constructed as two, wherein three clutch connecting members 17 and one bearing 13 are arranged at the coupling mechanism 18 at the front end, and another three clutch connecting members 17 and one bearing 13 are arranged at the coupling mechanism 18 at the rear end, that is, three clutch connecting members 17 and one bearing 13 are arranged at each coupling mechanism 18, and the three clutch connecting members 17 arranged circumferentially along the shaft 15 are arranged axially with the bearings 13.

[0039] Optionally, the coupling mechanism 18 is configured as one, and one coupling mechanism 18 is attached to the shaft 15 avoiding the inner blade 12. The clutch connection 17 is configured as three, and the bearing 13 is configured as one, and the three clutch connections 17 and the bearing 13 are all arranged at the same coupling mechanism 18.

[0040] Specifically and by way of example, reference is made to Figure 2 and Figure 3 The coupling mechanism 18 is configured to include a support ring 182 and a bracket 184. The support ring 182 is sleeved on the outer side of the shaft 15 and is coaxially arranged with the shaft 15. The bracket 184 extends radially inward from the inner side of the duct wall 16 and is connected to the support ring 182. The clutch connection 17 is arranged at the front end of the coupling mechanism 18. The clutch connection 17 is configured to have a retractable part (such as a pin). The inner side of the front end support ring 182 is provided with a groove structure that can engage with the retractable part of the clutch connection 17, so that the clutch connection 17 can be controlled to move and revocably connect the shaft 15 and the support ring 182, and then the shaft 15 can be reversibly coupled to the outer blade 14. The bearing 13 is arranged at the rear end of the coupling mechanism 18. Specifically, the bearing 13 is arranged between the shaft 15 and the support ring 182. The inner side of the bearing 13 is coupled to the shaft 15, and the outer side of the bearing 13 is coupled to the support ring 182. More specifically, a radial clearance is provided between the support ring 182 of each coupling mechanism 18 and the shaft 15, thereby providing a space for the bearing 13, or preventing the support ring 182 and the shaft 15 from generating friction loss due to relative rotation after the support ring 182 is disconnected from the clutch connector 17. Optionally, the bracket 184 of each coupling mechanism 18 is integrally formed with the support ring 182. Optionally, the bracket 184 of each coupling mechanism 18 is configured in multiple, for example, three or four.

[0041] Continue to refer Figure 2 and Figure 3 When the clutch connector 17 is controlled to move until its retractable portion enters the groove structure of the front support ring 182, the shaft 15 and the front support ring 182 are connected, and the outer blades 14, the duct wall 16 and the inner blades 12 can rotate synchronously with the rotation of the shaft 15. When the clutch connector 17 is controlled to move until its retractable portion leaves the groove structure of the front support ring 182, the shaft 15 and the front support ring 182 are disconnected, and the inner blades 12 can rotate synchronously with the rotation of the shaft 15, but the outer blades 14 and the duct wall 16 cannot rotate synchronously with the rotation of the shaft 15. Specifically, in these embodiments, the movement of the clutch connector 17 can be achieved by a control mechanism such as a telescopic cylinder, a telescopic electric push rod, etc., and such a control mechanism can be arranged on the shaft 15.

[0042] In other embodiments, the outer side of the inner blade 12 is fixedly connected to the inner side of the duct wall 16, the outer side of the duct wall 16 is sleeved with a coupling mechanism 18, and the inner side of the outer blade 14 is fixedly connected to the coupling mechanism 18. A clutch connection 17 is provided between the coupling mechanism 18 and the duct wall 16, and the clutch connection 17 is configured to revocably connect the duct wall 16 with the coupling mechanism 18, thereby reversibly coupling the outer blade 14 to the shaft 15. A bearing 13 is also provided between the coupling mechanism 18 and the duct wall 16, and the outer blade 14 is supported by the duct wall 16 through the bearing 13.

[0043] Specifically, refer to Figure 4 and Figure 5 The coupling mechanism 18 is configured as a support ring 182, which is sleeved on the outer side of the duct wall 16 and coaxially arranged with the shaft 15, and the inner side of the outer blade 14 is fixedly connected to the support ring 182. The bearing 13 is arranged between the duct wall 16 and the support ring 182, the inner side of the bearing 13 is coupled to the duct wall 16, and the outer side of the bearing 13 is coupled to the support ring 182. The clutch connection 17 is configured to have a retractable part (such as a pin), and the inner side of the support ring 182 is provided with a groove structure that can be engaged with the retractable part of the clutch connection 17, so that the clutch connection 17 can be controlled to move and revocably connect the duct wall 16 and the support ring 182, and then the shaft 15 can be reversibly coupled to the outer blade 14. More specifically, there is a radial gap between the support ring 182 and the duct wall 16. Optionally, the support ring 182 is integrally formed with the outer blade 14.

[0044] Continue to refer Figure 4 and Figure 5When the clutch connector 17 is controlled to move until its retractable portion enters the groove structure of the support ring 182, the duct wall 16 and the support ring 182 are connected, and the outer blades 14, the duct wall 16 and the inner blades 12 can all rotate synchronously with the rotation of the shaft 15. When the clutch connector 17 is controlled to move until its retractable portion leaves the groove structure of the support ring 182, the duct wall 16 and the support ring 182 are disconnected, and the inner blades 12 and the duct wall 16 can rotate synchronously with the rotation of the shaft 15, but the outer blades cannot rotate synchronously with the rotation of the shaft 15. Specifically, in these embodiments, the clutch connector 17 is configured as a pin shaft whose retractable portion automatically retracts and retracts in response to a signal after receiving a signal, and the energy storage component of the pin shaft is provided on the duct wall 16. Alternatively, the movement of the clutch connector 17 can be achieved by a control mechanism such as a telescopic cylinder, a telescopic electric push rod, etc. Such a control mechanism can be arranged on the duct wall 16 and powered by an energy storage device arranged on the duct wall 16.

[0045] refer to Figures 6 to 12 The present invention also provides a power assembly 30 for a trans-medium rotorcraft. The power assembly 30 includes a guide frame 20, a blade structure 10 and a blade motor (not shown). The rotor of 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 effectively utilize a single blade structure and a blade motor, and can select whether the outer blade 14 rotates synchronously with the shaft 15 in water according to needs. For example, when the aircraft has sufficient energy and needs to dissipate heat, the outer blade 14 can rotate synchronously with the shaft 15 to improve the internal heat dissipation environment of the aircraft, and ultimately improve the working efficiency of the equipment; when the aircraft does not need to dissipate heat or the energy is insufficient, the outer blade 14 can be decoupled from the shaft 15.

[0046] refer to Figure 6 and Fig. 9 The guide frame 20 is coaxially arranged with 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 constructed 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 to form 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 extends radially between the shaft 15 and the duct wall 16, and the outer blade 14 of the blade structure 10 extends radially between the duct wall 16 and the structural wall 26. Specifically, the opening and closing of the front control panel 22 and the rear control panel 24 can be achieved by a motor (non-blade motor) or a hydraulic device configured inside the trans-medium rotorcraft.

[0047] For the power assembly 30, the following Figures 1 to 3 The blade structure 10 shown is used in conjunction with the guide frame 20 for exemplary purposes. Figure 4 and Figure 5 When the blade structure 10 shown is matched with the guide frame 20, their connection relationship and working principle are similar and will not be described in detail.

[0048] When the trans-medium rotorcraft is operating in the air, both the front control panel 22 and the rear control panel 24 are in an open state (refer to Figure 6 ), the power of the aircraft is provided by the outer blade 14. The opening described in the present invention refers to the opening of the fluid path. Accordingly, the clutch connector 17 is controlled to move until its retractable part enters the groove structure of the support ring 182, the shaft 15 is connected to the front support ring 182, and then the outer blade 14 is coupled to the shaft 15, and the outer blade 14 and the duct wall 16 can rotate synchronously with the rotation of the shaft 15.

[0049] 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 Fig. 9 ), the outer blades 14 are isolated from the water, and the power of the aircraft is provided by the inner blades 12. The closing described in the present invention refers to blocking the fluid path. Correspondingly, the connection state of the clutch connector 17 is exactly the same as the connection state when working in the air, or is completely opposite to the connection state when working in the air. In some embodiments, if the equipment inside the aircraft generates a large amount of heat and requires auxiliary heat dissipation (described in detail later), the clutch connector 17 can be controlled to move until the retractable part enters the groove structure of the support ring 182, thereby coupling the outer blades 14 to the shaft 15, and the outer blades 14 can rotate synchronously with the inner blades 12 in the flow channel of the heat dissipation airflow, thereby improving the heat dissipation efficiency of the airflow. In other embodiments, if there is no need for auxiliary heat dissipation, the clutch connector 17 can be controlled to move until the retractable part leaves the groove structure of the support ring 182, thereby releasing the connection between the shaft 15 and the front end support ring 182, and further releasing the coupling between the outer blade 14 and the shaft 15. The outer blade 14 does not rotate synchronously with the inner blade 12, which can reduce the power loss of the aircraft when working underwater and extend the flight time.

[0050] 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.12 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 .

[0051] The outer side of the structural wall 26 is in airflow communication with other equipment inside the trans-medium rotorcraft. Figures 6 to 12 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 and needs auxiliary heat dissipation, 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 under the action of the rotating outer blade 14.

[0052] 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 it is underwater, the inner side of the duct wall 16 is liquid and connected to the external environment. The hot airflow exchanges heat with the water by contacting the duct wall 16 to achieve the design purpose of heat dissipation.

[0053] 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.

[0054] 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 6 , 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. Fig. 9, when the front control panel 22 or the rear control panel 24 is in a closed state, all the sub-panels 28 of the front control panel 22 or the rear control panel 24 are in a closed state. 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, the sub-panel 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-panel 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-panels 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-panel is in an open state, the conduction area of ​​the flow field is as large as possible, reducing the resistance of air flight.

[0055] 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.

[0056] When all the sub-panels 28 are closed, the front control panel 22, the rear control panel 24, the duct wall 16 and the structural wall surface 26 can form a closed channel, and the outer blade 14 is 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, so as to achieve 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, each sub-panel 28 can be independently controlled to tilt in the same direction, so that it has a guiding effect on the airflow blown out of the propeller, and the difference in the flow field on the left and right sides produces a left and right pressure difference, so that the overall structure is subjected to lateral force, thereby realizing the control of the motion attitude of the aircraft.

[0057] The power assembly 30 provided by the present invention can be applied to a cross-medium rotorcraft. The front side of the blade structure 10 is arranged in the upward direction corresponding to the fuselage of the cross-medium rotorcraft, and the rear side of the blade structure 10 is arranged in the downward direction corresponding to the fuselage of the cross-medium rotorcraft. 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 front and rear control panel surfaces 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 clutch connector 17 is controlled to move so that the outer blade 14 is coupled to the shaft 15, and 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.

[0058] The blade structure and power assembly provided by the present invention have the following advantages:

[0059] 1) By using the same set of blades and motors, the workload and repeated design of the cross-medium rotorcraft are reduced;

[0060] 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;

[0061] 3) The design incorporates the design of ducted propellers and has certain characteristics and advantages of ducted propellers;

[0062] 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;

[0063] 5) The split blade structure design meets the dual needs of underwater heat dissipation and reduced power consumption to extend flight time;

[0064] 6) Independently control each sub-board on the front and rear control panels to achieve control of the aircraft's motion posture.

[0065] 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.

[0066] 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 blade structure for a cross-medium rotorcraft, characterized in that: The blade structure includes a shaft, an inner blade, a duct wall and an outer blade; The duct wall is coaxially arranged with the shaft, the inner side of the inner blade is fixedly connected to the shaft, the outer side of the inner blade is suspended, the inner blade radially extends between the shaft and the duct wall, the inner side of the outer blade is fixedly connected to the outer side of the duct wall, and the outer side of the outer blade is suspended; At least one set of brackets and support rings is provided on the inner side of the duct wall, and each set of brackets and support rings is attached to the shaft avoiding the inner blades; the support ring is sleeved on the outer side of the shaft and is coaxially arranged with the shaft, and the brackets extend radially inward from the inner side surface of the duct wall and are connected to the support rings; A clutch connection is provided between at least one of the support rings and the shaft, the clutch connection being configured to revocably couple the shaft to the support ring and thereby reversibly couple the shaft to the outer blade; A bearing is provided between the support ring and the shaft, the inner side of the bearing is coupled to the shaft, the outer side of the bearing is coupled to the support ring, and the outer blade and the duct wall are supported by the shaft through the bearing; Among them, the blades of the outer blades are longer in radial direction and have a smaller change in blade surface spiral curvature than the blades of the inner blades; when the inner blades rotate synchronously with the shaft, the outer blades can selectively rotate synchronously with the shaft through the duct wall.

2. A blade structure for a cross-medium rotorcraft, characterized in that: The blade structure comprises a shaft, an inner blade, a duct wall and an outer blade; The duct wall is coaxially arranged with the shaft, the inner side of the inner blade is fixedly connected to the shaft, the inner blade radially extends between the shaft and the duct wall, and the outer side of the inner blade is fixedly connected to the inner side surface of the duct wall; the outer side of the duct wall is sleeved with a support ring and the support ring is coaxially arranged with the shaft, the inner side of the outer blade is fixedly connected to the support ring, and the outer side of the outer blade is suspended; A clutch connection is provided between the support ring and the duct wall, the clutch connection being configured to revocably couple the duct wall to the support ring, thereby reversibly coupling the outer blade to the shaft; A bearing is further provided between the support ring and the duct wall, the inner side of the bearing is coupled to the duct wall, the outer side of the bearing is coupled to the support ring, and the outer blade is supported by the duct wall through the bearing; Among them, the blades of the outer blades are longer in radial direction and have a smaller change in blade surface spiral curvature than the blades of the inner blades; when the inner blades rotate synchronously with the shaft, the outer blades can selectively rotate synchronously with the shaft through the duct wall.

3. The blade structure according to claim 1 or 2, characterized in that: The clutch connector has a retractable portion, and the inner side of the support ring is provided with a groove structure; When the retractable portion is controlled to extend into the slot structure, the outer blade is coupled to the shaft; The outer blades are decoupled from the shaft upon controlled movement of the retractable portion out of the slot structure.

4. A power assembly for a trans-medium rotorcraft, characterized in that: The power assembly comprises a guide frame, a blade motor and a blade structure according to any one of claims 1 to 3; The guide frame is coaxially arranged with the blade structure and is located on the outside of the blade structure; the guide frame includes 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 openable and closable annular plates, 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; The blade motor is installed at the middle of the rear side of the guide frame, and the blade motor is coupled to the shaft; 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.

5. The power assembly according to claim 4, 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.

6. The power assembly according to claim 5, 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 trans-medium rotorcraft is operating underwater, the clutch connection can be selectively controlled to move so that the outer blades are coupled to the shaft, and the outer blades rotate synchronously with the shaft. The 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 a structural wall surface located at the front side of the blade structure, and the air outlet is arranged on a structural wall surface located at the rear side of the blade structure. Both the air inlet and the air outlet are configured as openings with adjustable openings.

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