Propeller clamps, propeller assemblies, power units and drones

Abstract

Embodiments of the present invention provide a propeller clamp, a propeller assembly, a power unit and an unmanned aerial vehicle, and relate to the technical field of unmanned aerial vehicles. The propeller clamp includes a base, a mounting structure and a limiting structure. The mounting structure is arranged around the rotation axis of the base, and can be rotatably connected to the blades. The limiting structure is connected to the base or the mounting structure, and can abut the blades when the blades are retracted to limit the center of gravity of the blades from crossing the rotation axis of the base. It can be ensured that even when the blades are in the retracted state, their center of gravity still does not cross the rotation axis of the base. Therefore, after starting the propeller assembly, the blades will be smoothly unfolded under the action of centrifugal force, avoiding equipment failure caused by the inability to unfold the blades. The propeller assembly, the power unit and the unmanned aerial vehicle provided in the embodiments of the present application all include the propeller clamp provided in the embodiments of the present application, and therefore also have the advantage of being able to prevent the blades from being unable to unfold normally.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to a propeller clamp, a propeller assembly, a power device and a unmanned aerial vehicle. Background Art

[0002] In the existing field of drones, there are propeller assemblies with foldable blades. When the propeller stops, the blades can rotate around the rotation axis at the root toward the rotation axis of the propeller assembly, thereby folding. When the propeller assembly is started, the blades will unfold under the action of centrifugal force to provide power. However, the blades of the propeller assembly of the prior art sometimes fail to unfold, causing the propeller to be unbalanced and unable to fly. In severe cases, the aircraft may explode due to excessive vibration. Summary of the invention

[0003] The objects of the present invention include, for example, providing a propeller clamp, a propeller assembly, a power device and an unmanned aerial vehicle, which can better ensure that the blades can be normally unfolded.

[0004] The embodiments of the present invention can be implemented as follows:

[0005] In a first aspect, an embodiment of the present application provides a propeller clamp, comprising:

[0006] A base, the base can be drivingly connected to the output shaft of the driving assembly so that the base can rotate along with the output shaft;

[0007] At least two mounting structures are disposed on the base, the at least two mounting structures are disposed around a rotation axis of the base, and the mounting structures can be rotatably connected to the blades so that the blades can rotate relative to the mounting structures to be deployed or retracted;

[0008] The limiting structure is connected to the base and / or the mounting structure, and the limiting structure can abut the blade when the blade is folded to limit the center of gravity of the blade from crossing the rotation axis of the base.

[0009] In an optional embodiment, each mounting structure includes two mounting plates spaced apart in the circumferential direction of the base and a pin disposed between the two mounting plates, and the pin can be rotatably connected to the root of the blade.

[0010] In an optional embodiment, the two mounting plates are parallel to each other and are parallel to the rotation axis of the base.

[0011] In an optional embodiment, each mounting structure is connected to a limiting structure, which includes a first limiting member, wherein both ends of the first limiting member are respectively connected to the edge of the two mounting plates on a side away from the driving assembly, and the first limiting member can abut the blades when the blades are retracted to limit the center of gravity of the blades from crossing the axis of the output shaft.

[0012] In an optional embodiment, the limiting structure also includes a second limiting member, both ends of which are respectively connected to the edge of one side of the two mounting plates close to the driving assembly, and the second limiting member and the first limiting member are spaced apart in the extension direction of the rotation axis of the base, and the second limiting member can limit the expansion angle of the blades when the blades are expanded.

[0013] In an optional embodiment, the first position-limiting member and the second position-limiting member are plate-shaped, and the first position-limiting member, the second position-limiting member and the two mounting plates together form an installation space to accommodate the root of the blade.

[0014] In an optional embodiment, the installation space is an open box-like structure, and the opening of the box-like structure is away from the rotation axis of the base.

[0015] In an optional embodiment, the distance between the outer edge of the first limit member and the rotation axis of the base is smaller than the distance between the outer edges of the two mounting plates and the rotation axis of the base, so that a gap is formed on the side of the box-like structure away from the drive assembly, and the paddle can rotate into the gap and abut against the first limit member.

[0016] In an optional embodiment, a side of the first limit member close to the base is connected to the base, and a side of the second limit member close to the base is connected to the base.

[0017] In an optional embodiment, a first transition surface is formed at a connection between the first limit member and the base, and a second transition surface is formed at a connection between the second limit member and the base. The first transition surface and the second transition surface are smooth curved surfaces.

[0018] In an optional embodiment, when the blade abuts against the first stopper, the blade forms a first angle with the unfolding plane, and the angle range of the first angle is 20° to 80°;

[0019] When the blade abuts against the second limit member, the blade forms a second angle with the unfolding plane, and the angle range of the second angle is 3° to 10°.

[0020] In an optional embodiment, a pin hole is provided on the mounting plate, and the pin shaft can pass through the root of the blade and can be detachably inserted into the pin holes of the two mounting plates.

[0021] In an optional embodiment, the oar clamp further includes an elastic member, which is disposed between the two mounting plates and is used to provide a folding force to the oar blades.

[0022] In an optional embodiment, the mounting structure further includes a mounting shaft disposed between the two mounting plates, the elastic member is a torsion spring, the torsion spring is sleeved on the mounting shaft, and one of the elastic arms of the torsion spring can abut against the blade to provide a retracting force to the blade.

[0023] In an optional embodiment, the mounting axis is parallel to the pin axis and is spaced apart from each other.

[0024] In an optional embodiment, each mounting structure is connected to a limiting structure, which includes a first limiting member arranged on the edge of the two mounting plates away from the driving assembly and a second limiting member arranged on the edge of the two mounting plates close to the driving assembly, and the other elastic arm of the torsion spring can abut the second limiting member.

[0025] In an optional embodiment, the distance between the mounting shaft and the first limit member is greater than the distance between the pin shaft and the first limit member; the distance between the mounting shaft and the rotation axis of the base is less than the distance between the pin shaft and the rotation axis of the base.

[0026] In an optional embodiment, the base includes a cylindrical first connecting portion and a second connecting portion arranged circumferentially of the first connecting portion; the first connecting portion is sleeved on the output shaft of the driving assembly and can rotate with the output shaft, and the second connecting portion is connected to two mounting plates at one end away from the first connecting portion.

[0027] In an optional embodiment, an end of the first connection portion away from the driving assembly is aligned with an end of the second connection portion away from the driving assembly, and an end of the first connection portion close to the driving assembly protrudes out of an end of the second connection portion close to the driving assembly.

[0028] In an optional embodiment, each mounting structure is connected to a limiting structure, and the limiting structure includes a first limiting member arranged on an edge of the two mounting plates away from the driving assembly and a second limiting member arranged on an edge of the two mounting plates close to the driving assembly;

[0029] The dimension of the mounting plate along the rotation axis direction of the base is larger than the dimension of the second connection part along the rotation axis direction of the base, the first limiter protrudes from the surface of the second connection part, and the second limiter protrudes from the surface of the other end of the second connection part.

[0030] In an optional embodiment, there are two mounting structures, and the two mounting structures are symmetrical with respect to the center of the rotation axis of the base.

[0031] In an optional embodiment, a connecting hole matching with the output shaft is provided in the middle of the base.

[0032] In an optional embodiment, the limiting structure is connected to the base and the mounting structure.

[0033] In an optional embodiment, the base, the limiting structure and the mounting plate of the mounting structure are integrally formed.

[0034] In a second aspect, an embodiment of the present application provides a propeller assembly, comprising at least two blades and a propeller clamp provided in the first aspect, wherein the at least two blades are rotationally connected to a mounting structure of the propeller clamp in a one-to-one correspondence.

[0035] In a third aspect, an embodiment of the present application provides a power device for use in an aircraft, the power device comprising a drive assembly and a propeller assembly provided in the second aspect above, the output shaft of the drive assembly being transmission-connected to a base of a propeller clamp.

[0036] In a fourth aspect, an embodiment of the present application provides a drone, comprising the power device provided in the third aspect above.

[0037] The beneficial effects of the embodiments of the present invention include, for example:

[0038] The propeller clamp of the embodiment of the present application includes a base, a mounting structure and a limiting structure. The base can be connected to the output shaft of the drive assembly in a transmission manner so that the base rotates with the output shaft; the mounting structure is arranged around the rotation axis of the base and can be rotatably connected to the blades so that the blades can rotate relative to the mounting structure to unfold or fold; the limiting structure is connected to the base and / or the mounting structure, and the limiting structure can abut the blades when the blades are folded to limit the center of gravity of the blades from crossing the rotation axis of the base. If the center of gravity of the blades crosses the rotation axis, after the propeller assembly is quickly started, the centrifugal force will cause the blades to have a tendency to rotate in the direction away from the unfolding, resulting in failure to unfold. Through the propeller clamp of the present application, it can be ensured that even when the blades are folded, their center of gravity will not cross the rotation axis of the base. Therefore, after starting the propeller assembly, the blades will be smoothly unfolded under the action of centrifugal force, avoiding equipment failure caused by the inability to unfold the blades.

[0039] The propeller assembly, power device and drone provided in the embodiments of the present application all include the propeller clamp provided in the embodiments of the present application, and therefore also have the advantage of being able to prevent the propeller blades from being unable to unfold normally. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for use in the embodiments are briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present invention and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without creative work.

[0041] Figure 1 It is a schematic diagram of a propeller assembly in the prior art with the blades deployed;

[0042] Figure 2 It is a schematic diagram of a blade of a propeller assembly in the prior art in a retracted state;

[0043] Figure 3 This is a schematic diagram of a power device in an embodiment of the present application when the blades are deployed;

[0044] Figure 4 This is a schematic diagram of a power device in an embodiment of the present application when the blades are retracted;

[0045] Figure 5 This is an exploded view of a power device in one embodiment of the present application;

[0046] Figure 6 This is a schematic diagram of the assembly of a propeller assembly in one embodiment of the present application;

[0047] Figure 7 A cross-sectional view of a propeller assembly in one embodiment of the present application;

[0048] Figure 8 This is a schematic diagram of a paddle clamp in one embodiment of the present application (the pin shaft and the mounting shaft are omitted).

[0049] Icons: 1'-blade; 2'-propeller clamp; 010-power device; 100-propeller assembly; 110-propeller clamp; 120-base; 121-first connecting part; 122-connecting hole; 123-second connecting part; 124-pressing sheet; 130-mounting structure; 131-mounting plate; 132-pin hole; 133-pin shaft; 134-mounting hole; 135-mounting shaft; 140-elastic member; 150-limiting structure; 152-first limiting member; 154-second limiting member; 160-propeller blade; 200-driving assembly; 210-driving member; 220-propeller seat. DETAILED DESCRIPTION

[0050] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0051] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0052] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0053] In the description of the present invention, it should be noted that if the terms "upper", "lower", "inside", "outside", etc. appear to indicate an orientation or position relationship, they are based on the orientation or position relationship shown in the accompanying drawings, or are the orientation or position relationship in which the product of the invention is usually placed when used. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0054] In addition, the terms “first”, “second”, etc., if used, are merely used to distinguish between the descriptions and should not be understood as indicating or implying relative importance.

[0055] It should be noted that, in the absence of conflict, the features in the embodiments of the present invention may be combined with each other.

[0056] Figure 1 It is a schematic diagram of a propeller assembly in the prior art with the blades 1' deployed; Figure 2 FIG. 1 is a schematic diagram of a propeller blade 1' in a retracted state in the prior art. Figure 1 and Figure 2 As shown, the blade clamp 2' of the existing propeller assembly is hinged to the blade 1'. When the propeller assembly stops rotating and the blade 1' is above the rotation axis, the blade 1' can be folded in the direction of the rotation axis of the propeller assembly, thereby being retracted to prevent the blade 1' from colliding with the ground or other obstacles. When the propeller assembly rotates, the blade 1' will unfold under the action of centrifugal force. However, the existing foldable propeller assembly may fail to unfold, such as Figure 2 As shown, since the center of gravity of the blade 1' located above the rotation axis has passed the rotation axis of the propeller assembly after the blade 1' is folded, when the propeller assembly is quickly started, the centrifugal force will not cause the blade 1' to unfold, but will cause it to continue to rotate toward the side where the other blade 1' is located. When the blade 1' fails to unfold, the center of gravity of the propeller assembly deviates from the rotation axis and causes imbalance, which is prone to produce violent vibrations, which not only makes it impossible to fly, but also causes serious accidents such as explosions.

[0057] In order to improve the deficiencies in the above-mentioned prior art, the embodiments of the present application provide a propeller clamp, a propeller assembly, a power device and a drone.

[0058] Figure 3 This is a schematic diagram of a power device 010 in an embodiment of the present application when the blades 160 are deployed; Figure 4 This is a schematic diagram of a power device 010 in an embodiment of the present application when the blades 160 are folded; Figure 5 This is an exploded view of a power device 010 in one embodiment of the present application. Please refer to Figures 3 to 5The power device 010 provided in the embodiment of the present application includes a driving assembly 200 and a propeller assembly 100 that is transmission-connected to the driving assembly 200. The driving assembly 200 is used to drive the propeller assembly 100 to rotate, and includes a driving member 210 and a propeller seat 220 that is transmission-connected to the driving member 210. The propeller seat 220 has an output shaft. When the driving member 210 drives the propeller seat 220 to rotate, the output shaft rotates around its own axis.

[0059] The propeller assembly 100 includes a propeller clamp 110 and at least two propeller blades 160. The propeller clamp 110 is sleeved on the output shaft of the drive assembly 200 and is pressed by a pressing sheet 124 to keep it fixed to the output shaft of the drive assembly 200. The propeller blades 160 are rotatably connected to the propeller clamp 110 and can be deployed and retracted by rotating relative to the propeller clamp 110. Figure 4 As shown, the blade clamp 110 of the embodiment of the present application has the function of limiting the position of the blade 160, so that the blade 160 will not rotate excessively when it is folded, causing the center of gravity of the blade 160 to cross the rotation axis of the propeller assembly 100. In the present application, the plane where the two blades 160 are unfolded to 180° is defined as the unfolding plane, at which the propeller assembly 100 has the largest windward surface. In the present embodiment, the blade 160 is folded to a first angle α with the unfolding plane at most. Of course, the first angle α does not exceed 90° to prevent the center of gravity of the blade 160 from exceeding the rotation axis of the propeller assembly 100. In the present embodiment, the blade 160 can also swing to the side where the drive assembly 200 is located at a second angle β to the extreme position relative to the unfolding plane. The rotation margin design of the second angle β can ensure that the blade 160 will not be immediately rigidly contacted by the blade clamp 110 and stop unfolding after rotating to the unfolding plane, but has a certain buffer space. It should be understood that the rotation axis of the propeller assembly 100, that is, the axis of the output shaft of the drive assembly 200, is colinear with the rotation axis of the propeller clamp 110 and the rotation axis of the base 120 described below.

[0060] Figure 6 This is a schematic diagram of the assembly of a propeller assembly 100 in one embodiment of the present application; Figure 7 This is a cross-sectional view of a propeller assembly 100 in one embodiment of the present application; Figure 8 This is a schematic diagram of an oar clamp 110 in an embodiment of the present application (the pin 133 and the mounting shaft 135 are omitted). Figures 5 to 8In the present embodiment, the blade clamp 110 of the propeller assembly 100 includes a base 120, at least two mounting structures 130 disposed on the base, and a limiting structure 150. The base 120 is used for driving connection with the output shaft of the driving assembly 200 so that the base 120 rotates with the output shaft. At least two mounting structures 130 are disposed around the rotation axis of the base 120, and the mounting structures 130 can be rotatably connected to the blades 160, so that at least two blades 160 are rotatably connected to the mounting structures 130 connected to the blade clamp 110 in a one-to-one correspondence, so that the blades 160 can rotate relative to the mounting structures 130 to be unfolded or folded. The limiting structure 150 is connected to the base 120 and / or the mounting structure 130, and the limiting structure 150 can abut against the blades 160 when the blades 160 are folded, so as to limit the center of gravity of the blades 160 from crossing the rotation axis of the base 120.

[0061] In this embodiment, the base 120 can be sleeved on the output shaft of the driving assembly 200 and is tightly connected to the output shaft, so that the base 120 can rotate with the output shaft. Specifically, a connecting hole 122 that matches the output shaft of the driving assembly 200 is provided in the middle of the base 120. The connecting hole 122 is used to be sleeved on the output shaft of the propeller seat 220, and the pressing plate 124 is tightened with a nut to achieve a tight connection between the base 120 and the output shaft. The base 120 and the output shaft need to rotate synchronously, and the matching form is not limited to that shown in the figure, and can be adjusted as needed, such as locking with a locking pin, or using an output shaft with a polygonal cross-section to match the connecting hole 122.

[0062] In this embodiment, there are two mounting structures 130, which are symmetrical with respect to the rotation axis of the base 120 to ensure the balance of the entire propeller assembly 100. The present application is not limited thereto, and the number of mounting structures 130 can be appropriately adjusted according to actual needs.

[0063] In this embodiment, each mounting structure 130 includes two mounting plates 131 spaced apart in the circumferential direction of the base 120 and a pin 133 disposed between the two mounting plates 131, and the pin 133 can be rotatably connected to the root of the blade 160. Specifically, each mounting plate 131 is provided with a pin hole 132, and the pin holes 132 on the two mounting plates 131 belonging to the same mounting structure 130 correspond to each other. The pin 133 can penetrate the root of the blade 160 and be detachably inserted into the pin holes 132 of the two mounting plates 131. The portion of the pin 133 located between the two mounting plates 131 is used for rotatably connecting to the root of the blade 160.

[0064] Optionally, the two mounting plates 131 are parallel to each other and are parallel to the rotation axis of the base 120 .

[0065] Optionally, the base 120 includes a cylindrical first connection portion 121 and a second connection portion 123 arranged circumferentially of the first connection portion 121. The first connection portion 121 is sleeved on the output shaft of the drive assembly 200 and can rotate with the output shaft, and one end of the second connection portion 123 away from the first connection portion 121 is connected to two mounting plates 131.

[0066] Optionally, one end of the first connection portion 121 away from the driving assembly 200 is aligned with one end of the second connection portion 123 away from the driving assembly 200, and one end of the first connection portion 121 close to the driving assembly 200 protrudes out of one end of the second connection portion 123 close to the driving assembly 200.

[0067] Optionally, the dimension of the mounting plate 131 along the rotation axis direction of the base 120 is greater than the dimension of the second connecting portion 123 along the rotation axis direction of the base 120, the first limiting member 152 protrudes from the surface of the second connecting portion 123, and the second limiting member 154 protrudes from the surface of the other end of the second connecting portion 123.

[0068] Optionally, both ends of the pin shaft 133 are fastened to the two mounting plates 131 by fasteners (such as nuts), but the present application is not limited to this, and the two ends of the pin shaft 133 can also be connected to the two mounting plates 131 in other ways.

[0069] In this embodiment, the paddle clamp 110 further includes an elastic member 140 . The elastic member 140 is disposed between the two mounting plates 131 and is used to provide a retracting force to the paddle 160 .

[0070] Optionally, each mounting structure 130 further includes a mounting shaft 135 disposed between the two mounting plates 131, and the mounting shaft 135 is used to mount the elastic member 140. Specifically, each mounting plate 131 is further provided with a mounting hole 134, and the mounting holes 134 on the two mounting plates 131 belonging to the same mounting structure 130 correspond to each other, and the mounting shaft 135 is passed through the two mounting holes 134 and the two ends are respectively fastened to the two mounting plates 131.

[0071] Optionally, both ends of the mounting shaft 135 are fastened to the two mounting plates 131 by fasteners (such as nuts), but the present application is not limited thereto, and both ends of the mounting shaft 135 may also be connected to the two mounting plates 131 in other ways.

[0072] Optionally, the elastic member 140 is a torsion spring, which is sleeved on the mounting shaft 135 , and one of the elastic arms of the torsion spring can abut against the blade 160 to provide a retracting force to the blade 160 .

[0073] Since the blade 160 rotates at high speed in operation, the force between the blade 160 and the air is the direct power source for the aircraft to fly, so the installation accuracy and strength of the blade 160 will affect the power of the aircraft. For example, if the clearance between the blade 160 and the pin 133 is large, or the sliding amount of the blade 160 along the pin 133 is large, it will cause the propeller assembly 100 to produce large vibrations during operation, which will have a negative impact on the power. The role of the elastic member 140 is to retract the blade 160 when the propeller assembly 100 stops running, so it is only necessary for the elastic member 140 to provide a restoring force to the blade 160, and a high installation accuracy is not required. Therefore, compared with the elastic member 140, the blade 160 has a higher requirement for installation accuracy. If the elastic member 140 and the blade 160 are installed on the same shaft, the elastic member 140 can easily affect the installation accuracy of the blade 160. Therefore, by respectively arranging the mounting shaft 135 and the pin shaft 133 between the two mounting plates 131, the elastic member 140 and the blade 160 can be respectively arranged on different shafts (the mounting shaft 135 and the pin shaft 133), thereby ensuring the installation accuracy of the blade 160 and avoiding the negative impact of the elastic member 140 on the installation accuracy of the blade 160.

[0074] Optionally, the mounting shaft 135 is parallel to the pin shaft 133 and spaced apart. The mounting shaft 135 is parallel to the pin shaft 133, so that the force direction of the elastic member 140 on the blade 160 is consistent with the rotation direction of the blade 160 during the folding process, so that the blade 160 can be folded better. The spacing distance between the mounting shaft 135 and the pin shaft 133 can be determined according to the specific size and shape of the elastic member 140.

[0075] In this embodiment, each mounting structure 130 is connected to a limiting structure 150, and the limiting structure 150 includes a first limiting member 152 and a second limiting member 154. In this embodiment, the first limiting member 152 and the second limiting member 154 are both plate-shaped, and the first limiting member 152, the second limiting member 154 and the two mounting plates 131 together form an installation space to accommodate the root of the blade 160.

[0076] like Figure 7 and Figure 8 As shown, the two ends of the first stopper 152 are respectively connected to the edge of the two mounting plates 131 on the side away from the driving assembly 200 (ie Figure 7 , 8 The ends of the second stopper 154 are respectively connected to the edges of the two mounting plates 131 on one side close to the drive assembly 200 (i.e. Figure 7 , 8The first stopper 152 is provided at the bottom edge of the middle mounting plate 131, the first stopper 152 can abut against the blade 160 when the blade 160 is folded, so as to limit the center of gravity of the blade 160 from passing the axis of the output shaft of the driving assembly 200; the second stopper 154 is spaced apart from the first stopper 152 in the extending direction of the rotation axis of the base 120, and the second stopper 154 can limit the unfolding angle of the blade 160 when the blade 160 is unfolded. Optionally, the first stopper 152 is connected to the base 120 on one side close to the base 120, and the second stopper 154 is connected to the base 120 on one side close to the base 120.

[0077] Optionally, a first transition surface is formed at a connection between the first limiting member 152 and the base 120 , and a second transition surface is formed at a connection between the second limiting member 154 and the base 120 . The first transition surface and the second transition surface are smooth curved surfaces.

[0078] Among them, the distance between the outer edge of the first stopper 152 and the second stopper 154 and the base 120 can determine the two extreme positions of the rotation of the blade 160. When the distance between the outer edge of the first stopper 152 and the rotation axis of the base 120 is small, the blade 160 is closer to the rotation axis of the base 120 when folded, so that the folded volume is smaller; when the distance between the outer edge of the second stopper 154 and the rotation axis of the base 120 is relatively large, the angle (second angle β) of the blade 160 exceeding the unfolding plane when over-expanded can be prevented from being too large, thereby avoiding interference with other structures of the drone. Of course, the distance between the outer edge of the first stopper 152 and the rotation axis of the base 120, and the distance between the outer edge of the second stopper 154 and the rotation axis of the base 120 can be adjusted according to specific circumstances. The outer edge of the first limiting member 152 refers to the edge of the first limiting member 152 away from the base 120 ; the outer edge of the second limiting member 154 refers to the edge of the second limiting member 154 away from the base 120 .

[0079] In the present embodiment, the installation space is an open box-like structure, and the opening of the box-like structure faces away from the rotation axis of the base 120. The distance between the outer edge of the first limit member 152 and the rotation axis of the base 120 is smaller than the distance between the outer edges of the two mounting plates 131 and the rotation axis of the base 120, so that a gap is formed on the side of the box-like structure away from the drive assembly 200, and the paddle 160 can rotate into the gap and abut against the first limit member 152. Among them, the outer edge of the mounting plate 131 refers to the edge of the mounting plate 131 on the side away from the base 120. In the present embodiment, the distance between the outer edge of the first limit member 152 and the rotation axis of the base 120 is determined based on the angle required for the two paddles 160 to be retracted; and the distance between the outer edge of the mounting plate 131 and the rotation axis of the base 120 is determined in order to leave enough installation space for other components on the mounting plate 131 (such as the pin 133 and the mounting shaft). Based on this, Figure 7 and Figure 8 In the embodiment, the distance between the outer edge of the first limiting member 152 and the rotation axis of the base 120 is smaller than the distance between the outer edges of the two mounting plates 131 and the rotation axis of the base 120, thereby forming a gap.

[0080] The torsion spring as the elastic member 140 has two elastic arms respectively abutting against the blade 160 and the second stopper 154 (i.e., one elastic arm of the torsion spring can abut against the blade 160, and the other elastic arm can abut against the second stopper 154), so that the blade 160 can be automatically retracted after the propeller assembly 100 stops rotating and the centrifugal force of the blade 160 disappears. In order to enable the force of the torsion spring on the blade 160 to provide a tendency for the blade 160 to retract, the distance between the mounting shaft 135 and the first stopper 152 is greater than the distance between the pin shaft 133 and the first stopper 152; the distance between the mounting shaft 135 and the rotation axis of the base 120 is less than the distance between the pin shaft 133 and the rotation axis of the base 120. The hinges between the elastic member 140 and the mounting shaft 135 and the hinges between the blade 160 and the pin shaft 133 are both accommodated in the installation space formed by the limiting structure 150 and the mounting structure 130. The integrity of the overall structure is good. The limiting structure 150 and the mounting structure 130 can also protect the installation and matching positions of the blade 160 and the elastic member 140, and are not easily damaged during use and transportation.

[0081] In addition, the dimensions of the mounting structure 130 and the limiting structure 150 should be able to meet the requirements of the folding and unfolding of the blades 160. Figure 4 and Figure 7In this embodiment, the ultimate retracted position of the blade 160 is limited by the first limit member 152. When the blade 160 abuts against the first limit member 152, the blade 160 forms a first angle α with the unfolding plane. The first angle α can be selected in the range of 20° to 80°, such as any angle value among 20°, 25°, 30°, 35°, 40°, 45°, 50°, 55°, 60°, 65°, 70°, 75°, 80°, or an angle value between any two of the above angle values. , the first angle α in this embodiment is preferably 50°; the extreme deployment position of the blade 160 is limited by the second limiter 154. When the blade 160 abuts against the second limiter 154, the blade 160 forms a second angle β with the deployment plane. The optional range of the second angle β is 3° to 10°, such as any angle value among 3°, 4°, 5°, 6°, 7°, 8°, 9°, 10° or an angle value between any two of the above angle values. The second angle β in this embodiment is preferably 5°. It should be understood that in this embodiment, the position of the blade 160 when it abuts against the first limiter 152 and the position of the blade 160 when it abuts against the second limiter 154 are respectively located on both sides of the deployment plane. When the first angle α is set to be relatively large, the angle between the two blades 160 after being folded can be reduced as small as possible, the distance from the ground can be increased, and the blades 160 can be prevented from colliding with the ground or other objects. However, if the first angle α is too large, it will be unfavorable for the blades 160 to be deployed quickly. Based on the above considerations, the first angle α of the blades 160 relative to the deployment plane when folded is 50°, which can take into account both the folding effect and the deployment speed. Each blade 160 can be over-expanded by a margin of the second angle β relative to the unfolding plane. There are two reasons for this design: first, to avoid the unfolding angle of the two blades 160 being less than 180° due to dimensional errors between the blade clamp 110 and the blade 160, which would reduce the windward surface and affect the power; second, to avoid the violent unfolding of the blade 160 during high-speed starting, which would easily cause a collision with the blade clamp 110 (specifically the second limit member 154 in this embodiment). After the margin of the second angle β is set, the blade 160 will not collide with the blade clamp 110 immediately after it rotates quickly to the unfolding plane, but can continue to rotate slightly by a certain angle (less than the second angle β) to be buffered by the elastic member 140. Therefore, allowing the blade 160 to over-expand by a certain angle is equivalent to providing additional buffer space for the blade 160.

[0082] In this embodiment, after calculation and testing, the range of the first angle α is set to 20°~80°, and the range of the second angle β is set to 3°~10°, then the rotatable angle of the blade 160 is -10°~80°, which can take into account the requirements of various performances. In addition, the selection of the size parameters of the paddle clamp 110 can consider the following factors: if the distance between the pin shaft 133 and the first stopper 152 is relatively far, the weight and moment of inertia of the paddle clamp 110 will be increased, and the area of ​​the mounting plate 131 will be increased, thereby increasing the rotation resistance; if the distance between the pin shaft 133 and the first stopper 152 is relatively close, when the first stopper 152 abuts against the blade 160, the limit arm will be short. When the blade 160 abuts against the first stopper 152, a large force will be generated on the first stopper 152 and the pin shaft 133, so that the pin shaft 133 and the first stopper 152 may have insufficient strength. In addition, the torsion spring as elastic member 140 needs to have a sufficient force arm to support blade 160 so as to generate sufficient torque on blade 160. If the mounting hole 134 is too close to the rotation axis of blade clamp 110, the distance between the contact position between the spring arm of the torsion spring and blade 160 and the rotation axis of blade 160 will be shortened, resulting in a shorter force arm applied by the torsion spring and failure to generate sufficient torque; if the mounting hole 134 is too far from the rotation axis of blade clamp 110, in order to allow the installation space to accommodate the torsion spring, blade clamp 110 needs to be enlarged, which increases the overall weight and the rotating windward area, and will interfere with the excessive rotation of blade 160, affecting the design of the deflection margin of blade 160.

[0083] In order to facilitate the normal installation of the blade 160, the inner width of the installation space needs to be larger than the root width of the blade 160. Optionally, the inner width of the installation space is 0.1-0.3 mm larger than the root width of the blade 160. In this case, the blade 160 can be normally installed and a small matching gap is ensured.

[0084] It should be understood that in the present embodiment, the limiting structure 150 is connected to the mounting structure 130 and the base 120, and in other embodiments of the present application, the limiting structure 150 may be directly connected to only one of the mounting structure 130 or the base 120. The limiting structure 150, the mounting plate 131 of the mounting structure 130 and the base 120 in the present embodiment are integrally formed, and in other optional embodiments, they may also be separately configured to be detachable. In other embodiments of the present application, the elastic member 140 may also be of other types, such as a spring. In other embodiments, the number of blades 160 and mounting structures 130 may also be further increased, and each mounting structure 130 and blade 160 should be evenly spaced around the circumference of the base 120.

[0085] The working principles of the propeller clamp 110, the propeller assembly 100 and the power device 010 provided in this embodiment are:

[0086] When the blade 160 of the propeller assembly 100 is in the retracted state, the elastic member 140 pushes the blade 160 to a position abutting against the first stop member 152. At this time, the center of gravity of the blade 160 does not exceed the rotation axis of the propeller assembly 100. Figure 4 As shown. When the driving assembly 200 of the power device 010 drives the paddle clamp 110 to rotate, the blades 160 are unfolded under the action of centrifugal force, and the torsion spring is compressed during the unfolding process. Finally, the two blades 160 are fully unfolded, and the two are at an angle of 180°. If the unfolding speed is too fast, the blades 160 are over-expanded, and there is still a 5° margin for buffering. The second limiter 154 can limit the angle of over-expansion. When the driving assembly 200 stops running, the blades 160 stop rotating, the centrifugal force disappears, and the blades 160 will be retracted under the action of the elastic member 140, which can prevent the blades 160 from colliding with the ground or other objects.

[0087] The embodiment of the present application also provides a UAV (not shown in the figure), which includes a fuselage and a power device 010 provided in the embodiment of the present application.

[0088] In summary, the propeller clamp of the embodiment of the present application includes a base, a mounting structure and a limiting structure. The base can be connected to the output shaft of the drive assembly in a transmission manner so that the base rotates with the output shaft; the mounting structure is arranged around the rotation axis of the base and can be rotatably connected to the blades so that the blades can rotate relative to the mounting structure to unfold or fold; the limiting structure is connected to the base and / or the mounting structure, and the limiting structure can abut the blades when the blades are folded to limit the center of gravity of the blades from crossing the rotation axis of the base. If the center of gravity of the blades crosses the rotation axis, after the propeller assembly is quickly started, the centrifugal force will cause the blades to have a tendency to rotate in the direction away from the unfolding, resulting in failure to unfold. Through the propeller clamp of the present application, it can be ensured that even when the blades are in the folded state, their center of gravity will not cross the rotation axis of the base. Therefore, after starting the propeller assembly, the blades will be smoothly unfolded under the action of centrifugal force, avoiding equipment failure caused by the inability to unfold the blades.

[0089] The propeller assembly, power device and drone provided in the embodiments of the present application all include the propeller clamp provided in the embodiments of the present application, and therefore also have the advantage of being able to prevent the propeller blades from being unable to unfold normally.

[0090] The above is only a specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed by the present invention should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims

1. A paddle clamp, characterized in that: include: A base, the base being capable of being drivingly connected to an output shaft of a driving assembly so as to enable the base to rotate along with the output shaft; At least two mounting structures are provided on the base, the at least two mounting structures are arranged around the rotation axis of the base, and the mounting structures can be rotatably connected to the blades so that the blades can rotate relative to the mounting structures to be unfolded or retracted; a limiting structure, the limiting structure being connected to the base and / or the mounting structure, and the limiting structure being capable of abutting against the blade when the blade is folded to limit the center of gravity of the blade from crossing the rotation axis of the base; Each of the mounting structures comprises two mounting plates spaced apart in the circumferential direction of the base and a pin disposed between the two mounting plates, wherein the pin can be rotatably connected to the root of the blade; Each of the mounting structures is connected to the limiting structure, and the limiting structure includes a first limiting member, wherein both ends of the first limiting member are respectively connected to the edges of the two mounting plates on a side away from the driving assembly, and the first limiting member can abut against the blades when the blades are folded to limit the center of gravity of the blades from crossing the axis of the output shaft.

2. The propeller clamp according to claim 1, characterized in that: The two mounting plates are parallel to each other and are parallel to the rotation axis of the base.

3. The propeller clamp according to claim 1, characterized in that: The limiting structure also includes a second limiting member, both ends of which are respectively connected to the edges of the two mounting plates on one side close to the driving assembly, and the second limiting member and the first limiting member are spaced apart in the extension direction of the rotation axis of the base, and the second limiting member can limit the expansion angle of the blades when the blades are expanded.

4. The propeller clamp according to claim 3, characterized in that: The first limiting member and the second limiting member are plate-shaped, and the first limiting member, the second limiting member and the two mounting plates together form an installation space to accommodate the root of the blade.

5. The propeller clamp according to claim 4, characterized in that: The installation space is an open box-shaped structure, and the opening of the box-shaped structure is away from the rotation axis of the base.

6. The propeller clamp according to claim 5, characterized in that: The distance between the outer edge of the first limit member and the rotation axis of the base is smaller than the distance between the outer edges of the two mounting plates and the rotation axis of the base, so that a gap is formed on the side of the box-like structure away from the driving assembly, and the paddle can rotate into the gap and abut against the first limit member.

7. The propeller clamp according to claim 3, characterized in that: A side of the first limiting member close to the base is connected to the base, and a side of the second limiting member close to the base is connected to the base.

8. The propeller clamp according to claim 7, characterized in that: A first transition surface is formed at a connection between the first limiting member and the base, and a second transition surface is formed at a connection between the second limiting member and the base. The first transition surface and the second transition surface are smooth curved surfaces.

9. The propeller clamp according to any one of claims 3 to 8, characterized in that: When the blade abuts against the first stopper, the blade forms a first angle with the unfolding plane, and the angle range of the first angle is 20° to 80°; When the paddle is in contact with the second stopper, the paddle and the unfolding plane form a second angle, and the second angle ranges from 3° to 10°.

10. The propeller clamp according to any one of claims 1 to 8, characterized in that: The mounting plate is provided with a pin hole, and the pin shaft can penetrate the root of the blade and be detachably inserted into the pin holes of the two mounting plates.

11. The oar clamp according to claim 1, characterized in that: The paddle clamp further comprises an elastic member, which is arranged between the two mounting plates and is used for providing a folding force to the paddle.

12. The oar clamp according to claim 11, characterized in that: The mounting structure further comprises a mounting shaft arranged between the two mounting plates. The elastic member is a torsion spring, which is sleeved on the mounting shaft. One of the elastic arms of the torsion spring can abut against the blade to provide a retracting force to the blade.

13. The oar clamp according to claim 12, characterized in that: The installation shaft is parallel to the pin shaft and is spaced apart from each other.

14. The oar clamp according to claim 12, characterized in that: The limiting structure further comprises a second limiting member arranged on the edge of the two mounting plates on one side close to the driving assembly, and the other elastic arm of the torsion spring can abut against the second limiting member.

15. The oar clamp according to claim 14, characterized in that: The distance between the installation shaft and the first limit member is greater than the distance between the pin shaft and the first limit member; the distance between the installation shaft and the rotation axis of the base is less than the distance between the pin shaft and the rotation axis of the base.

16. The oar clamp according to claim 1, characterized in that: The base includes a cylindrical first connecting portion and a second connecting portion arranged circumferentially of the first connecting portion; the first connecting portion is sleeved on the output shaft of the driving assembly and can rotate with the output shaft, and the second connecting portion is connected to the two mounting plates at one end away from the first connecting portion.

17. The oar clamp according to claim 16, characterized in that: One end of the first connection portion away from the driving assembly is aligned with one end of the second connection portion away from the driving assembly, and one end of the first connection portion close to the driving assembly protrudes out from one end of the second connection portion close to the driving assembly.

18. The oar clamp according to claim 17, characterized in that: The limiting structure further comprises a second limiting member arranged on the edge of one side of the two mounting plates close to the driving assembly; The dimension of the mounting plate along the rotation axis direction of the base is greater than the dimension of the second connection part along the rotation axis direction of the base, the first limit member protrudes from the surface of the second connection part, and the second limit member protrudes from the surface of the other end of the second connection part.

19. The propeller clamp according to any one of claims 1 to 8, characterized in that: The number of the mounting structures is two, and the two mounting structures are symmetrical relative to the center of the rotation axis of the base.

20. The propeller clamp according to any one of claims 1 to 8, characterized in that: A connecting hole matching with the output shaft is arranged in the middle of the base.

21. The propeller clamp according to any one of claims 1 to 8, characterized in that: The limiting structure is connected to the base and the mounting structure.

22. The propeller clamp according to any one of claims 1 to 8, characterized in that: The base, the limiting structure and the mounting plate of the mounting structure are integrally formed.

23. A propeller assembly, characterized in that: The invention comprises at least two blades and the blade clamp according to any one of claims 1 to 22, wherein the at least two blades are rotatably connected to the mounting structure of the blade clamp in a one-to-one correspondence.

24. A power device, applied to an aircraft, characterized in that: The power device includes a drive assembly and the propeller assembly according to claim 23, and the output shaft of the drive assembly is drivingly connected to the base of the propeller clamp.

25. A drone, characterized in that: Comprising the power device as described in claim 24.

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