Propeller hub structure, rotor wing and flight equipment

Abstract

The invention relates to a propeller hub structure, a rotor wing and flight equipment. The propeller hub structure comprises a mounting seat, a plurality of propeller blades and a plurality of propeller blades, wherein a plurality of open mounting cavities are radially formed in the mounting seat; the multiple paddle clamps are used for being connected with the paddles correspondingly, and one end of each paddle clamp is arranged in the corresponding mounting cavity and rotationally connected to the mounting base; the plurality of elastic energy storage elements are respectively arranged in the corresponding mounting cavities, and the single elastic energy storage element is respectively connected to the mounting seat and the corresponding paddle clamp along the axial direction; wherein the elastic energy storage element drives the static paddle clamp to be twisted to the folding position from the unfolding position through the pre-tightening force, and the rotating paddle clamp overcomes the pre-tightening force of the elastic energy storage element and rotates to the unfolding position. According to the scheme provided by the invention, the structure is simple and reliable, the folding and unfolding of the paddle can be quickly realized without manual operation, and the operation speed can be completed within a few seconds; and electric control and extra energy supply are not needed, the overall design structure of the rotor wings is simplified, and the overall portability of the aircraft is improved conveniently.

Description

Technical Field

[0001] The present application relates to the field of aircraft technology, and in particular to a hub structure, a rotor and a flight device. Background Art

[0002] The rotor (also known as propeller) is an essential power component of an aircraft. When the aircraft is parked, in order to reduce the storage space, the rotor blades generally need to be folded and retracted. In the related art, in order to achieve the folding of the blades, there are two commonly used folding methods, one is electric folding and the other is manual folding.

[0003] Among them, the electric folding method is to install a control module on the rotor. The control module generally includes a controller, a motor, and a mechanical locking mechanism for realizing the folding function. When the controller receives a folding command, the motor drives the mechanical locking mechanism to fold and lock the blades. The manual folding method requires the operator to climb up to achieve the folding of the blades.

[0004] However, the electric folding method has the risk of difficult mechanical design, high design cost, heavy weight, and reduced reliability due to complex mechanism. The manual folding method has the risk of cumbersome operation, low efficiency, and the risk of operators falling when climbing high. Summary of the invention

[0005] In order to solve or partially solve the problems existing in the related art, the present application provides a hub structure, a rotor and a flight device, which can quickly realize the folding and unfolding of the blades, and has a simple structure, is reliable and lightweight.

[0006] A first aspect of the present application provides a hub structure, comprising:

[0007] The mounting seat has a plurality of open mounting cavities radially formed therein;

[0008] A plurality of propeller clips, each used to connect a propeller blade, wherein one end of each propeller clip is disposed in the corresponding mounting cavity and is rotatably connected to the mounting seat;

[0009] A plurality of elastic energy storage elements are respectively arranged in the corresponding mounting cavities, and a single elastic energy storage element is respectively connected to the mounting seat and the corresponding propeller clamp along the axial direction;

[0010] The elastic energy storage element drives the stationary paddle clamp to twist from the unfolded position to the folded position through the preload force, and the rotating paddle clamp overcomes the preload force of the elastic energy storage element and rotates back to the unfolded position.

[0011] In some embodiments, the elastic energy storage element is a torsion spring, a tension spring, a compression spring, a coil spring or a spring.

[0012] In some embodiments, the paddle clamp is provided with a first mounting hole, and the mounting seat is provided with a second mounting hole, the first mounting hole and the second mounting hole are respectively located on both sides of the elastic energy storage element, one end of the elastic energy storage element is passed through the first mounting hole, and the other opposite end of the elastic energy storage element is passed through the second mounting hole.

[0013] In some embodiments, the hub structure further includes a plurality of guide shafts, a single guide shaft is axially disposed in the corresponding mounting cavity and is rotationally connected to the mounting seat, and the propeller clamp sleeve is connected to the corresponding guide shaft.

[0014] In some embodiments, the elastic energy storage element is sleeved on the guide shaft and is spaced apart from an outer peripheral wall of the guide shaft.

[0015] In some embodiments, the mounting seat includes a base and an upper seat that are arranged opposite to each other, and the base and the upper seat are relatively assembled to form at least one mounting cavity; the guide shaft is rotatably connected to the base and the upper seat.

[0016] In some embodiments, the paddle clamp includes an upper paddle clamp and a lower paddle clamp, the upper paddle clamp and the lower paddle clamp are used to be arranged opposite to each other to clamp the paddle blade, the upper paddle clamp is arranged close to the upper seat, and the lower paddle clamp is arranged close to the base;

[0017] One end of the elastic energy storage element is connected to the upper paddle clamp, and the other end of the elastic energy storage element is connected to the base; or one end of the elastic energy storage element is connected to the lower paddle clamp, and the other end of the elastic energy storage element is connected to the upper seat.

[0018] In some embodiments, the hub structure further includes a limit stopper, which is disposed in a receiving cavity of the mounting seat and is located between the propeller clamp and the mounting seat.

[0019] A second aspect of the present application provides a rotor, which includes a plurality of blades and a hub structure in any of the above-mentioned embodiments, wherein each of the blades is connected to a corresponding blade clamp.

[0020] A third aspect of the present application provides a flying device, which includes the rotor in any of the above-mentioned embodiments.

[0021] The technical solution provided by this application may have the following beneficial effects:

[0022] The hub structure of the present application is simple and reliable. It can quickly fold and unfold the blades without manual operation, and the operation can be completed within a few seconds. It does not require electric control and additional energy supply, which simplifies the overall design structure of the rotor and facilitates improving the overall lightness of the aircraft.

[0023] It should be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The above and other objects, features and advantages of the present application will become more apparent by describing in more detail exemplary embodiments of the present application in conjunction with the accompanying drawings, wherein the same reference numerals generally represent the same components in the exemplary embodiments of the present application.

[0025] Figure 1 is an exploded schematic diagram of a hub structure shown in an embodiment of the present application;

[0026] Figure 2 yes Figure 1 A schematic diagram of a folded state of the hub structure shown;

[0027] Figure 3 yes Figure 2 A schematic diagram of a folded state of the hub structure shown in another perspective;

[0028] Figure 4 yes Figure 1 A schematic diagram of the unfolded state of the hub structure shown;

[0029] Figure 5 yes Figure 4 A schematic diagram of the hub structure in an unfolded state from another perspective shown;

[0030] Figure 6 yes Figure 1 A schematic structural diagram of a mounting seat of a hub structure shown;

[0031] Figure 7 yes Figure 6 A schematic diagram of the structure of the upper seat in the mounting seat shown;

[0032] Figure 8 yes Figure 1 A schematic diagram of the structure of the propeller clamp of the propeller hub structure shown;

[0033] Fig. 9 yes Figure 1 A schematic structural diagram of the elastic energy storage element in the hub structure shown.

[0034] Reference numerals:

[0035] Mounting seat 100; base 110; upper seat 120; fastener 130; connecting hole 131; combined bearing 140; fixing hole 141; positioning member 150; positioning hole 151; mounting cavity 101; second mounting hole 102; weight reduction hole 103;

[0036] Paddle clamp 200; upper paddle clamp 210; lower paddle clamp 220; accommodating cavity 201; first mounting hole 202; limiting through hole 203;

[0037] Elastic energy storage element 300; fixing portion 310; elastic portion 320;

[0038] Guide shaft 400; limit stop block 500. DETAILED DESCRIPTION

[0039] The embodiments of the present application will be described in more detail below with reference to the accompanying drawings. Although the embodiments of the present application are shown in the accompanying drawings, it should be understood that the present application can be implemented in various forms and should not be limited by the embodiments described herein. On the contrary, these embodiments are provided to make the present application more thorough and complete, and to fully convey the scope of the present application to those skilled in the art.

[0040] The terms used in this application are for the purpose of describing specific embodiments only and are not intended to limit this application. The singular forms of "a", "said" and "the" used in this application and the appended claims are also intended to include plural forms unless the context clearly indicates other meanings. It should also be understood that the term "and / or" used herein refers to and includes any or all possible combinations of one or more associated listed items.

[0041] It should be understood that although the terms "first", "second", "third", etc. may be used in this application to describe various information, this information should not be limited to these terms. These terms are only used to distinguish the same type of information from each other. For example, without departing from the scope of this application, the first information may also be referred to as the second information, and similarly, the second information may also be referred to as the first information. Thus, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of this application, the meaning of "multiple" is two or more, unless otherwise clearly and specifically defined.

[0042] In the related art, the folding of the rotor blades generally needs to be completed by complex electric equipment. While the complex equipment adds additional weight to the aircraft, its complex structure will also affect the overall design of the aircraft. Conventional mechanical folding structures generally require manual folding and unfolding of the blades, which has low operating efficiency and poses operational risks.

[0043] In response to the above problems, the embodiments of the present application provide a hub structure, a rotor and a flight device, which can quickly realize the folding and unfolding of the blades, and have a simple, reliable and lightweight structure.

[0044] The following is combined with Figures 1 to 9 The technical solution of the embodiment of the present application is described in detail.

[0045] In some embodiments, the rotor of the present application is applied to an aircraft. The aircraft may be a manned aircraft or a drone. The rotor includes a hub structure and blades connected to the hub structure. The number of blades is adjusted according to actual needs. For example, the blades may be 2 to 4, such as 2, 3, 4, etc. Optionally, the aircraft may include one or more rotors, and the number and installation position of the rotors may be arranged according to the actual structure of the aircraft. The rotor of the present application includes the hub structure in any of the following embodiments.

[0046] See also Figures 1 to 6 The hub structure in one embodiment of the present application includes a mounting seat 100, a plurality of blade clips 200 and a plurality of elastic energy storage elements 300. The mounting seat 100 is provided with a plurality of open mounting cavities 101 in the radial direction; the plurality of blade clips 200 are respectively used to connect blades (not shown in the figure), one end of a single blade clip 200 is arranged in the corresponding mounting cavity 101, and is rotatably connected to the mounting seat 100; the plurality of elastic energy storage elements 300 are respectively arranged in the corresponding mounting cavities 101, one end of a single elastic energy storage element 300 is axially connected to the blade clip 200, and the other end is connected to the mounting seat 100; the elastic energy storage element 300 drives the stationary blade clip 200 to twist from the unfolded position to the folded position through the preload force, and the rotating blade clip 200 overcomes the preload force of the elastic energy storage element 300 and rotates back to the unfolded position.

[0047] Specifically, the mounting seat 100 is also used to connect a driving device such as a motor to drive the blades to rotate. The mounting seat 100 can be an integrally formed component, or it can be an assembled component composed of multiple subcomponents. The number of mounting cavities 101 can be opened according to the actual number of paddle clips 200. For example, the number of mounting cavities 101 can be greater than or equal to the number of paddle clips 200. The mounting cavities 101 can be interconnected or not interconnected, or some of the mounting cavities 101 can be interconnected, and there is no limitation here.

[0048] Among them, at least part of the structure of a single paddle clamp 200 is located in the mounting cavity 101 of the mounting seat 100. In order to avoid mutual interference, a paddle clamp 200 can be arranged in a mounting cavity 101, and a single paddle clamp 200 is used to connect a paddle blade. In this embodiment, one end of the paddle clamp 200 can be indirectly rotatably connected to the mounting seat 100 in the mounting cavity 101, and the elastic energy storage element 300 can drive the paddle clamp 200 through the preload force (such as torque) in its natural state, so that the paddle clamp 200 rotates relative to the mounting seat 100, and then drives the corresponding paddle blade to fold or unfold. The other end of the paddle clamp 200 can extend radially outside the mounting cavity 101 for connecting the corresponding paddle. That is, the paddle clamp 200 is not directly connected to the mounting seat 100. Through the implementation of the preload force of the elastic energy storage element 300, the paddle clamp 200 can be folded by changing its position relative to the mounting seat 100 by rotation; and then the preload force of the elastic energy storage element 300 is overcome by centrifugal force, so that the paddle clamp 200 can be unfolded relative to the mounting seat 100. In other words, the paddle clamp 200 has a corresponding folding position and unfolding position relative to the mounting seat 100, and the paddle clamp 200 twists and turns between the folding position and the unfolding position according to the change in the force of the elastic energy storage element 300. It can be understood that the number of paddle clamps 200 can be 2, 3, 4, etc., and the number of paddle clamps 200 is set according to the number of blades.

[0049] It can be understood that the directions of different paddle clips 200 when twisted can be different or the same, and each paddle clip 200 has its own corresponding folding position and its own corresponding unfolding position. When all paddle clips 200 are rotated to the corresponding folding position, the angle between two adjacent paddle clips 200 has a corresponding folding angle. When all paddle clips 200 are rotated to the corresponding unfolding position, the angle between two adjacent paddle clips 200 has a corresponding unfolding angle. Obviously, the folding angle is smaller than the unfolding angle. For example, the folding angle can be 0° to 45°, and the unfolding angle can be 90° to 180°. According to the actual number of blades, the folding position and unfolding position of each blade change accordingly, and the folding angle and unfolding angle of two adjacent blades also change accordingly. For example, when the number of blades is 2, the folding angle can be 0°, and the unfolding angle can be 180°. In order to realize the folding of each paddle clip 200 to drive the blades to fold, the number of elastic energy storage elements 300 can match the number of paddle clips 200.

[0050] See also Figure 1 and Fig. 9In some embodiments, the elastic energy storage element 300 has a fixed portion 310 and an elastic portion 320, and the fixed portion 310 is used to connect the mounting seat 100 and the paddle clamp 200. The elastic portion 320 is elastic and has a preload force in a natural state to drive the paddle clamp 200 to twist or rotate relative to the mounting seat 100. In some specific embodiments, the elastic energy storage element 300 may be a torsion spring, a tension spring, a compression spring, a disc spring or a spring; wherein a plurality of elastic energy storage elements 300 may be the same or different. For example, when the elastic energy storage element 300 is a torsion spring, the fixed portion 310 of the torsion spring is the torsion pins corresponding to the two ends, and the elastic portion of the torsion spring is the spiral structure where the coil is located. For ease of explanation, see Figures 2 to 5 In the present application, the direction parallel to the blades can be regarded as radial, and the direction perpendicular or approximately perpendicular to the blades can be regarded as axial. Among them, when the rotor of the aircraft is in a stopped state, its blades need to be folded and gathered to reduce the storage space. In the hub structure of the present application, the elastic energy storage element 300 has a preload force in a natural state, and the preload force can twist the stationary propeller clamp 200 to a folded position, thereby driving the blades installed on the propeller clamp 200 to move synchronously to the folded position, thereby realizing the folding and gathering of the blades. When the rotor of the aircraft is deployed for use, as the blades rotate and the speed increases, the centrifugal force will overcome the preload force of the elastic energy storage element 300 itself, causing the propeller clamp 200 to twist to the deployed position as the blades rotate.

[0051] See also Figures 2 to 5 Taking the elastic energy storage element 300 as a torsion spring as an example, when one of the torsion pins is connected to the paddle clamp 200 and the other torsion pin is connected to the mounting seat 100, the preload force of the torsion spring in the natural state will drive the paddle clamp 200 to twist from the deployed position to the folded position. When the paddle clamp rotates, the centrifugal force overcomes the preload force and the paddle clamp can be rotated back from the folded position to the deployed position. Of course, according to the above operating principle, the elastic energy storage element 300 is not limited to a torsion spring, but can also be other elastic structures that can store energy and preload force in the natural state.

[0052] The hub structure of the present application is simple and reliable. It can quickly fold and unfold the blades without manual operation, and the operation can be completed within a few seconds. It does not require electric control and additional energy supply, which simplifies the overall design structure of the rotor and facilitates improving the overall lightness of the aircraft.

[0053] See also Figure 3 and Figure 4In order to make the propeller clip 200 twist more stably, in some embodiments, the propeller hub structure further includes a plurality of guide shafts 400, a single guide shaft 400 is axially arranged in the corresponding mounting cavity 101 and is rotatably connected to the mounting seat 100, and the propeller clip 200 is sleeved and connected to the corresponding guide shaft 400. Specifically, the guide shaft 400 can be rotatably connected to the mounting seat 100 through the combined bearing 140, the propeller clip 200 is fixedly sleeved on the outer peripheral wall of the guide shaft 400, the propeller clip 200 can be rotatably connected to the mounting seat 100 through the rotating guide shaft 400, and the propeller clip 200 rotates with the rotation of the guide shaft 400, so that the propeller clip 200 rotates to the folded position or rotates back to the unfolded position more stably with the guide shaft 400.

[0054] In order to more stably guide the elastic energy storage element 300 to release the preload, see Figure 3 and Figure 4 In some embodiments, the elastic energy storage element 300 is sleeved on the guide shaft 400 and is spaced apart from the outer peripheral wall of the guide shaft 400. That is to say, the elastic energy storage element 300 and the paddle clamp 200 can be coaxially arranged through the guide shaft 400, and the guide shaft 400 can prevent the elastic energy storage element 300 from excessively twisting and deforming during the rebound and pulling process, while the elastic energy storage element 300 can stably apply force to guide the paddle clamp 200 to rotate to a specified position along the guide shaft 400. It can be understood that there is a gap between the elastic energy storage element 300 and the outer peripheral wall of the guide shaft 400, that is, the elastic energy storage element 300 does not rotate with the guide shaft 400, but is fixedly connected to the paddle clamp 200 and the mounting seat 100, thereby continuously applying pre-tightening force to the paddle clamp 200.

[0055] In order to prevent the paddle clamp 200 from colliding with the mounting base 100 after rotation, see Figures 1 to 4In some embodiments, the propeller hub structure further includes a limit stopper 500, which is disposed in the mounting cavity 101 of the mounting seat 100 and is located between the propeller clip 200 and the mounting seat 100. In some specific embodiments, the limit stopper 500 can be installed on the side of the mounting seat 100 close to the propeller clip 200, and the limit stopper 500 is isolated and blocked between the propeller clip 200 and the mounting seat 100 to prevent the propeller clip 200 from colliding with the cavity wall of the mounting cavity 101 when it rotates to the folded position, thereby improving the structural life of the propeller clip 200 and the mounting seat 100. Optionally, the limit stopper 500 can be screwed or bonded to the cavity wall. In some embodiments, the number of limit stops 500 connected to the cavity wall on one side can be one or more. For example, there can be multiple limit stops 500, and each limit stopper 500 is arranged on the cavity wall at intervals. While isolating the propeller clip 200 from the cavity wall, it can also reduce weight and produce a shock-absorbing effect through the interval distribution. Furthermore, by adjusting the thickness of the limit stopper 500, the folding position of the paddle clip 200 can be changed. That is, the thicker the limit stopper 500 is, the farther the paddle clip 200 is from the cavity wall, so that the angle between two adjacent paddle blades after folding is larger; the thinner the limit stopper 500 is, the smaller the distance between the paddle clip 200 and the cavity wall is, so that the angle between two adjacent paddle blades after folding is smaller, and the two adjacent paddle blades can be folded closer together, further reducing the storage space of the paddle blades. By adjusting the thickness of the limit stopper 500, the paddle clip 200 is prevented from being excessively twisted, thereby preventing the two adjacent paddle clips 200 from crossing and colliding with each other after folding.

[0056] In order to further simplify the hub structure, see Figure 1 , Figure 6 to Figure 7 In some embodiments, the mounting base 100 includes a base 110 and an upper base 120 that are arranged opposite to each other, and the base 110 and the upper base 120 are relatively assembled to form at least one mounting cavity 101. For ease of explanation, the base 110 refers to a component close to the fuselage of the aircraft, and the upper base 120 refers to a component far away from the fuselage of the aircraft. In some embodiments, the mounting base 100 also includes a plurality of fasteners 130, and the base 110 and the upper base 120 are respectively provided with a plurality of relatively connected connecting holes 131, and a single fastener 130 is provided with a corresponding connecting hole 131 to connect and assemble the base 110 and the upper base 120. Optionally, the fastener 130 can be, for example, a screw connection.

[0057] In some embodiments, the guide shaft 400 is rotatably connected to the base 110 and the upper seat 120. That is, one end of the guide shaft 400 is rotatably connected to the base 110, and the other end is rotatably connected to the upper seat 120. For example, the base 110 and the upper seat 120 may both have corresponding fixing holes 141, and each fixing hole 141 is provided with a combined bearing 140, so that the two ends of the guide shaft 400 are rotatably connected to the base 110 and the upper seat 120 respectively through the combined bearing 140.

[0058] In order to more reliably realize the folding and unfolding of the paddle clip 200, see Figures 1 to 4 In some embodiments, the paddle clip 200 includes an upper paddle clip 210 and a lower paddle clip 220, the upper paddle clip 210 and the lower paddle clip 220 are used to be arranged opposite to each other to clamp the paddle blade, the upper paddle clip 210 is arranged close to the upper seat, and the lower paddle clip is arranged close to the base; one end of the elastic energy storage element is connected to the upper paddle clip 210, and the other end of the elastic energy storage element 300 is connected to the base 110; or one end of the elastic energy storage element is connected to the lower paddle clip 220, and the other end of the elastic energy storage element 300 is connected to the upper seat 120. By connecting one end of the elastic energy storage element 300 to the paddle clip 200 and the other end to the mounting seat 100, one end of the elastic energy storage element 300 can fold and retract the paddle clip 200 in a static state through a pre-tightening force.

[0059] In order to make the overall structure of the hub structure more centralized, in some embodiments, an accommodating chamber 201 is formed between the upper paddle clamp 210 and the lower paddle clamp 220, and a single elastic energy storage element 300 is disposed in the accommodating chamber 201; one end of the elastic energy storage element 300 is connected to the upper paddle clamp 210 or the upper seat 120, and the other end of the elastic energy storage element 300 is connected to the lower paddle clamp 220 or the base 110. In other words, the upper paddle clamp 210 and the upper seat 120 are both located on one side of the elastic energy storage element 300, and the lower paddle clamp 220 and the base 110 are both located on the other side opposite to the elastic energy storage element 300, so that the upper paddle clamp 210, the upper seat 120, the elastic energy storage element 300, the lower paddle clamp 220 and the base 110 are all coaxially arranged along the axial direction of the guide shaft 400 from top to bottom, so that the hub structure is more streamlined and reliable, and the elastic energy storage element 300 can release the preload more stably to stably drive the paddle clamp 200 to twist along the axial direction. Optionally, there may be a gap between the upper paddle clip 210 and the upper seat 120, and there may be a gap between the lower paddle clip 220 and the base 110, so as to prevent the paddle clip 200 from rubbing against the mounting seat 100 when rotating. In some embodiments, the upper paddle clip 210 and the lower paddle clip 220 may be an integrally formed structure or a detachable structure.

[0060] To facilitate assembly of the blade clamp and guide shaft, see Figures 1 to 7 In some embodiments, the upper paddle clamp 210 and the lower paddle clamp 200 have coaxially arranged limiting through holes 203 , and the guide shaft 400 is passed through the limiting through holes 203 to be rotatably connected to the base 110 and the upper seat 120 of the mounting seat 100 .

[0061] In order to make the elastic energy storage element 300 more reliably drive the blade clamp 200 to rotate along the mounting seat 100, see Figure 1 , Figure 7 and Figure 8In some embodiments, the paddle clip 200 is provided with a first mounting hole 202, the mounting seat 100 is provided with a second mounting hole 102, the first mounting hole 202 and the second mounting hole 101 are respectively located on both sides of the elastic energy storage element 300, one end of the elastic energy storage element 300 is passed through the first mounting hole 202, and the other opposite end of the elastic energy storage element 300 is passed through the second mounting hole 102. In other words, the first mounting hole 202 and the second mounting hole 101 do not need to be simultaneously provided on the same side of the elastic energy storage element 300. In a specific embodiment, the upper paddle clip 210 is provided with a first mounting hole 202, the base 110 is provided with a second mounting hole 102, one end of the elastic energy storage element 300 is passed through the first mounting hole 202 of the upper paddle clip 210, and the other end is passed through the second mounting hole 102 of the base 110. Alternatively, the lower paddle clamp 220 is provided with a first mounting hole 202, the upper seat 120 is provided with a second mounting hole 102, one end of the elastic energy storage element 300 is passed through the first mounting hole 202 of the lower paddle clamp 220, and the other end is passed through the second mounting hole 102 of the upper seat 120. For example, when the elastic energy storage element 300 is a torsion spring, the two ends of the elastic energy storage element 300 are the two torsion feet of the torsion spring, and the two torsion feet are respectively passed through the first mounting hole 202 and the second mounting hole 102 on the corresponding side. Optionally, in order to facilitate stabilizing the stress state of the elastic energy storage element, the first mounting hole 202 and the second mounting hole 101 can both be blind holes, thereby providing support for the release of the preload force of the elastic energy storage element. By connecting and fixing the fixed part of the elastic energy storage element to different components respectively, the paddle clamp can be twisted by the preload force based on the mounting seat as a fulcrum.

[0062] It should be noted that each oar clip 200 has a first mounting hole 202, and the number of the second mounting holes 102 of the mounting base 100 is at least equal to the sum of the numbers of the first mounting holes 202 of each oar clip 200. Of course, in order to facilitate the adjustment of the position of the elastic energy storage element, the number of the first mounting holes 202 of a single oar clip 200 is not limited.

[0063] In some embodiments, in order to facilitate assembly of the structure, the mounting base 100 further includes at least one positioning member 150, and the base 110 and the upper base 120 are respectively provided with at least one positioning hole 151 that is relatively connected, and a single positioning member 150 is inserted into two corresponding positioning holes 151. Optionally, the positioning member 150 can be a positioning pin.

[0064] In order to further improve the portability of the hub structure, in some embodiments, the mounting seat 100 is further provided with a weight-reducing hole 103. For example, one or more weight-reducing holes 103 may be respectively provided in the base 110 and / or the upper seat 120. By removing redundant structures, the weight of the mounting seat 100 is reduced, thereby improving the portability of the hub structure.

[0065] In some embodiments, the guide shaft 400 may be a hollow shaft. When the guide shaft 400 is a hollow structure, the weight of the hub structure can be further reduced. Of course, in order to improve the structural strength, the guide shaft 400 may also be a solid shaft.

[0066] In some embodiments, the peripheral wall of the guide shaft 400 may be a stepped structure. That is, in order to keep a distance between the guide shaft 400 and the elastic energy storage element 300, in some embodiments, the diameter of the shaft corresponding to the guide shaft 400 and the elastic energy storage element 300 is smaller than the diameter of the shaft in other parts. By reducing the diameter of part of the shaft, weight reduction can be achieved while keeping a distance from the elastic energy storage element 300 sleeved on the peripheral wall.

[0067] The following will introduce the hub structure of the present application in conjunction with specific examples. The number of blades is two for example, and the actual number of blades is not limited here. In this embodiment, it is assumed that the angle between the two blades when folded is 0°, and the angle when unfolded is 180°. Therefore, the blade clamp 200 has corresponding folded positions and unfolded positions.

[0068] In order to improve the stability of the hub structure, the mounting seat 100 is provided with two mounting cavities 101 symmetrically along the radial direction. The mounting seat 100 includes an upper seat 120 and a base 110, and the upper seat 120 and the base 110 can be screwed and disassembled by fasteners 130. Each mounting cavity 101 is provided with a paddle clamp 200, an elastic energy storage element 300 and a guide shaft 400. Among them, each paddle clamp 200 can include an upper paddle clamp 210 and a lower paddle clamp 220, and the upper paddle clamp 210 and the lower paddle clamp 220 can be relatively assembled to clamp a paddle blade. The upper paddle clamp 210 and the lower paddle clamp 220 are both provided with mounting through holes for being sleeved on the guide shaft 400. The upper paddle clip 210 or the lower paddle clip 220 is provided with a first mounting hole 202, the base 110 or the upper seat 120 is provided with a second mounting hole 102, the base 110 and the upper seat 120 are provided with a fixing hole 141, and a combined bearing 140 is arranged in the fixing hole 141. In addition, a limit stopper 500 is installed on the cavity wall of each mounting cavity 101 to prevent the paddle clip 200 from colliding.

[0069] Taking the elastic energy storage element 300 as a torsion spring as an example, when assembling the hub structure, in each installation cavity 101, one end of the corresponding guide shaft 400 is passed through the combined bearing 140 of the base 110, and the lower paddle clamp 220 is sleeved on the guide shaft 400, so that the lower paddle clamp 220 and the guide shaft 400 are closely matched. Then the torsion spring is sleeved on the guide shaft 400, and one of the twist pins is inserted into the first installation hole 202 of the lower paddle clamp 220. Then the upper paddle clamp 210 is sleeved on the guide shaft 400. Finally, the upper seat 120 is assembled with the base 110, and the other twist pin of the torsion spring is passed through the second installation hole 102 of the upper seat 120, and the upper seat 120 and the base 110 can be assembled through the fastener 130 to obtain an assembled hub structure.

[0070] When assembling the rotor, the end of the blade can be inserted between the upper blade clamp 210 and the lower blade clamp 220. The rotor is then connected to the driving device of the aircraft through the mounting seat 100.

[0071] The following will introduce the process of folding and unfolding the rotor blades.

[0072] When the rotor stops operating, the blades are in a stationary state, and the blades and blade clamp 200 are initially in the deployed position. The torsion force of the torsion spring drives the blade clamp 200 to rotate relative to the mounting seat 100 following the guide shaft 400, thereby driving the blades on the blade clamp 200 to rotate together, and then twisting the blade clamp 200 and the blades from the deployed position to the folded position. The folding speed can be completed within a few seconds without manual assistance or electric equipment control.

[0073] When the rotor is started, the driving device drives the rotor to start rotating. As the speed increases, the centrifugal force increases, causing the blades to be thrown out. By overcoming the torsion of the torsion spring, the blades drive the blade clamp 200 to follow the guide shaft 400 and rotate from the folded position to the unfolded position.

[0074] Similarly, when the rotor stops again, the centrifugal force is not sufficient to overcome the torque, and the torsion spring drives the blade clamp 200 to quickly twist to the folded position again, thereby achieving the folding and retracting of the blades again.

[0075] Regarding the above-mentioned embodiment, its specific implementation method has been described in detail in the embodiment of the method, and will not be elaborated again here.

[0076] 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.

[0077] The embodiments of the present application have been described above, and the above description is exemplary, not exhaustive, and is not limited to the disclosed embodiments. Many modifications and changes will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments. The selection of terms used herein is intended to best explain the principles of the embodiments, practical applications, or improvements to the technology in the market, or to enable other persons of ordinary skill in the art to understand the embodiments disclosed herein.

Claims

1. A hub structure, It is characterized in that include: The mounting seat has a plurality of open mounting cavities radially formed therein; A plurality of propeller clips, each used to connect a propeller blade, wherein one end of each propeller clip is disposed in the corresponding mounting cavity and is rotatably connected to the mounting seat; A plurality of elastic energy storage elements are respectively arranged in the corresponding mounting cavities, and a single elastic energy storage element is respectively connected to the mounting seat and the corresponding propeller clamp along the axial direction; The elastic energy storage element drives the stationary paddle clamp to twist from the unfolded position to the folded position through the preload force, and the rotating paddle clamp overcomes the preload force of the elastic energy storage element and rotates back to the unfolded position.

2. The hub structure according to claim 1, Features: The elastic energy storage element is one of a torsion spring, a tension spring, a compression spring, a disc spring or a spring.

3. The hub structure according to claim 1, Features: The paddle clamp is provided with a first mounting hole, and the mounting seat is provided with a second mounting hole. The first mounting hole and the second mounting hole are respectively located on both sides of the elastic energy storage element. One end of the elastic energy storage element is passed through the first mounting hole, and the other opposite end of the elastic energy storage element is passed through the second mounting hole.

4. The hub structure according to claim 1, Features: The hub structure also includes a plurality of guide shafts, wherein a single guide shaft is axially disposed in the corresponding mounting cavity and is rotationally connected to the mounting seat, and the propeller clamp sleeve is connected to the corresponding guide shaft.

5. The hub structure according to claim 4, Features: The elastic energy storage element is sleeved on the guide shaft and is spaced apart from the outer peripheral wall of the guide shaft.

6. The hub structure according to claim 4 or 5, Features: The mounting seat comprises a base and an upper seat which are arranged opposite to each other. The base and the upper seat are relatively assembled to form at least one mounting cavity. The guide shaft is rotatably connected to the base and the upper seat.

7. The hub structure according to claim 6, Features: The paddle clamp comprises an upper paddle clamp and a lower paddle clamp, wherein the upper paddle clamp and the lower paddle clamp are used to be arranged opposite to each other to clamp the paddle blades, the upper paddle clamp is arranged close to the upper seat, and the lower paddle clamp is arranged close to the base; One end of the elastic energy storage element is connected to the upper paddle clamp, and the other end of the elastic energy storage element is connected to the base; or one end of the elastic energy storage element is connected to the lower paddle clamp, and the other end of the elastic energy storage element is connected to the upper seat.

8. The hub structure according to any one of claims 1 to 4, 6 and 7, Features: The hub structure further comprises a limit stopper, which is arranged in the accommodating cavity of the mounting seat and is located between the propeller clamp and the mounting seat.

9. A rotor, It is characterized in that The invention comprises a plurality of blades and a hub structure according to any one of claims 1 to 8, wherein each of the blades is connected to a corresponding blade clamp.

10. A flying device, It is characterized in that Comprising the rotor as described in claim 9.

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