Folding paddle assembly and unmanned aerial vehicle

Abstract

The invention relates to a folding propeller assembly and an unmanned aerial vehicle. The folding propeller assembly comprises a propeller clamp and a propeller, the paddle is rotatably clamped between the paddle clamps so as to selectively have a folding position and an unfolding position; the adjusting assembly is arranged between the paddle and the paddle clamp and is used for dynamically adjusting the clamping force of the paddle clamp to the paddle; wherein the adjusting assembly comprises a hollow air bag structure, and the hollow air bag structure is used for providing elastic clamping force for the paddle; or the adjusting assembly comprises a magnetic piece, and the magnetic piece is used for providing magnetic clamping force for the paddle. According to the technical scheme, the rotating friction force of the paddles can be adjusted in a unified mode through the folding paddle assembly.

Description

Technical Field

[0001] This disclosure relates to the field of unmanned aerial vehicle (UAV) technology, and more specifically, to a folding propeller assembly and a UAV. Background Technology

[0002] Folding propeller drones commonly suffer from uneven friction due to dimensional tolerances of various parts during flight, which affects their flight performance.

[0003] In related technologies, the pressure of the propeller clamp on the propeller blade is mainly adjusted by regulating the torque of the locking screw between the upper and lower propeller clamps, thereby regulating the rotational friction of the propeller blade. However, the torque of the locking screw in this method cannot be fixed; it requires measuring the friction force while adjusting the screw torque, resulting in low production efficiency, high operational difficulty, and difficulty in mass production. Therefore, there is an urgent need for a folding propeller assembly that can uniformly regulate the rotational friction of the propeller blade. Summary of the Invention

[0004] The purpose of this disclosure is to provide a folding propeller assembly and a drone that can uniformly adjust the rotational friction of the propeller blades.

[0005] To achieve the above objectives, this disclosure provides a folding propeller assembly, comprising: a propeller clamp; a propeller blade rotatably clamped between the propeller clamp to selectively have a folded position and an unfolded position; and an adjustment assembly disposed between the propeller blade and the propeller clamp for dynamically adjusting the clamping force of the propeller clamp on the propeller blade; wherein the adjustment assembly includes an air bladder structure for providing an elastic clamping force to the propeller blade; or, the adjustment assembly includes a magnetic element for providing a magnetic clamping force to the propeller blade.

[0006] Optionally, the air bladder structure is formed of a polymer elastomer; and / or, the air bladder structure is a closed air bladder or an open air bladder.

[0007] Optionally, the airbag structure is an annular structure; and / or, the open airbag has an inner annular wall and an outer annular wall, and the inner annular wall and the outer annular wall are respectively provided with a plurality of first air holes and a plurality of second air holes communicating with the interior of the open airbag, the plurality of first air holes being arranged at intervals along the circumference of the inner annular wall, and the plurality of second air holes being arranged at intervals along the circumference of the outer annular wall.

[0008] Optionally, a first lubricant is provided between the side of the blade away from the air bladder structure and the blade clamp, and a second lubricant is provided between the air bladder structure and the blade clamp, and between the air bladder structure and the blade.

[0009] Optionally, the magnetic component includes a first magnetic component and a second magnetic component, which are arranged in a suspended manner relative to each other, with one component disposed on the blade and the other disposed on the blade clip, wherein the same magnetic poles of the first magnetic component and the second magnetic component are opposite to each other.

[0010] Optionally, both the first magnetic element and the second magnetic element are permanent magnets, and both the first magnetic element and the second magnetic element are constructed in a ring shape, or are constructed to include a plurality of magnetic elements arranged at equal intervals along the ring.

[0011] Optionally, along the lift direction of the airflow, the adjustment component is located between the upstream side of the blade and the blade clamp, and the folding blade assembly further includes a first lubricant disposed between the downstream side of the blade and the blade clamp.

[0012] Optionally, the propeller clamp includes an upper propeller clamp and a lower propeller clamp located on both sides of the propeller blade, and a rotating shaft extending between the upper and lower propeller clamps. The propeller blade is rotatably mounted on the rotating shaft. The adjusting assembly is annular and arranged around the rotating shaft. A first end of the rotating shaft is fixedly connected to one of the upper and lower propeller clamps, and a second end is fastened to the other by a locking screw. A receiving groove is formed on the propeller clamp, and the second end of the rotating shaft is inserted into the receiving groove. A fastening hole is formed on the bottom surface of the receiving groove for the locking screw to pass through.

[0013] Optionally, the propeller clamp has a connecting portion at its center for connection with a drive device. The propeller blades include a plurality of blades and are clamped on the propeller clamp at equal intervals around the connecting portion. A limiting member is provided between each propeller blade and the connecting portion. The limiting member has a first limiting surface and a second limiting surface that respectively cooperate with a first side and a second side of the propeller blade. The folding position includes a first folding position to which the propeller blade rotates clockwise relative to the propeller clamp and a second folding position to which it rotates counterclockwise. The first limiting surface and the second limiting surface correspond to the first folding position and the second folding position, respectively.

[0014] Based on the above technical solution, this disclosure also provides a drone, including the aforementioned folding propeller assembly.

[0015] Through the above technical solution, in the folding propeller assembly provided in this disclosure, by adjusting the dynamic adjustment of the component, on the one hand, the dimensional tolerances of each component in the folding propeller assembly can be absorbed throughout the entire assembly process and even during operation. This ensures that the propeller clamps in all folding propeller assemblies can reliably contact the propeller blades, maintaining a basically constant clamping force applied by the propeller clamps to the propeller blades, and ensuring that the propeller clamps can reliably clamp the propeller blades. In this way, during the assembly process of the folding propeller assembly, the propeller clamps and propeller blades can be locked and fixed in one step by locking screws, avoiding the need to measure the friction between the propeller blades and propeller clamps while adjusting the torque of the locking screws. Therefore, this can unify the locking torque of the locking screws of all folding propeller assemblies during assembly, thereby reducing assembly difficulty, improving production efficiency, and achieving mass production. On the other hand, this can also adaptively adjust the friction between the propeller blades and propeller clamps when switching between the folded and unfolded positions, thereby improving the flexibility of the folding propeller assembly during use.

[0016] Other features and advantages of this disclosure will be described in detail in the following detailed description section. Attached Figure Description

[0017] The accompanying drawings are provided to further illustrate the present disclosure and form part of the specification. They are used together with the following detailed description to explain the present disclosure, but do not constitute a limitation thereof. In the drawings: Figure 1 This is a schematic diagram of the structure of a folding propeller assembly provided in an exemplary embodiment of the present disclosure, wherein the propeller blades are in a folded state and the upper propeller clamp is located on top; Figure 2 yes Figure 1 Enlarged view of point A in the middle; Figure 3 yes Figure 2 A cross-sectional view at point BB, where the adjusting component is an elastic element; Figure 4 yes Figure 2 A cross-sectional view at point BB, showing that the adjustment component is a magnetic element; Figure 5 This is a schematic diagram of the structure of a folding propeller assembly provided in an exemplary embodiment of the present disclosure, wherein the propeller blades are in a folded state and the lower propeller clamp is located on top; Figure 6 yes Figure 5 Enlarged view of point D in the middle; Figure 7 yes Figure 6 A cross-sectional view at the EE section, where the adjusting component is an elastic element; Figure 8 yes Figure 6 A cross-sectional view at the EE section, showing that the adjustment component is a magnetic element; Figure 9 This is a schematic diagram of the structure of a folding propeller assembly provided in an exemplary embodiment of the present disclosure, wherein the propeller blades are in a folded state and the upper propeller clamp has been removed; Figure 10 yes Figure 9 A magnified view of a section at point C; Figure 11 This is a schematic diagram of the structure of a folding propeller assembly provided in an exemplary embodiment of the present disclosure, wherein the propeller blades are in an unfolded state and the upper propeller clamp is located above; Figure 12 This is a partial structural schematic diagram of the enclosed airbag in the folding propeller assembly provided in an exemplary embodiment of the present disclosure; Figure 13 This is a schematic diagram of the structure of the open airbag in the folding propeller assembly provided in an exemplary embodiment of the present disclosure.

[0018] Explanation of reference numerals in the attached figures 1-Propeller clamp; 11-Upper propeller clamp; 12-Lower propeller clamp; 13-Rotating shaft; 14-Receiving groove; 141-Fasting hole; 15-Connecting part; 2-Propeller blade; 21-First side; 22-Second side; 3-Adjusting assembly; 31-Elastic element; 311-Inner airbag structure; 3111-Closed airbag; 3112-Open airbag; 3112a-Inner circumferential wall; 3112b-Outer circumferential wall; 3112c-First air hole; 3112d-Second air hole; 32-Magnetic element; 321-First magnetic element; 322-Second magnetic element; 4-First lubricating element; 5-Second lubricating element; 6-Locking screw; 7-Limiting element; 71-First limiting surface; 72-Second limiting surface. Detailed Implementation

[0019] The specific embodiments of this disclosure will be described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are for illustration and explanation only and are not intended to limit this disclosure.

[0020] In this disclosure, unless otherwise stated, directional terms such as "above" and "below" refer to above and below the lift direction of the airflow when the UAV is in flight, respectively. Furthermore, "inner" and "outer" refer to "inner" and "outer" relative to the contour of the corresponding component itself. Additionally, the terms "first," "second," etc., used in this disclosure are for distinguishing one element from another and do not have sequential or importance implications. Furthermore, in the following description, when referring to the accompanying drawings, unless otherwise explained, the same reference numerals in different drawings denote the same or similar elements. The above definitions are for explanation and illustration only and should not be construed as limiting this disclosure.

[0021] This disclosure provides a folding propeller assembly, with reference to... Figures 1 to 13As shown, the folding propeller assembly includes: a propeller clamp 1; a propeller blade 2 rotatably clamped between the propeller clamp 1 to selectively have a folded position and an unfolded position; and an adjustment assembly 3 disposed between the propeller blade 2 and the propeller clamp 1 for dynamically adjusting the clamping force of the propeller clamp 1 on the propeller blade 2.

[0022] Through the above technical solution, in the folding propeller assembly provided in this disclosure, by dynamically adjusting component 3, on the one hand, the dimensional tolerances of each component in the folding propeller assembly can be absorbed throughout the entire assembly process and even during operation, ensuring that the propeller clamps 1 in all folding propeller assemblies can reliably contact the propeller blades 2, so as to maintain the clamping force applied by the propeller clamps 1 to the propeller blades 2 basically constant, ensuring that the propeller clamps 1 can reliably clamp the propeller blades 2. In this way, during the assembly process of the folding propeller assembly, the propeller clamps 1 and the propeller blades 2 can be locked and fixed in one step by the locking screws 6, avoiding the need to measure the friction between the propeller blades 2 and the propeller clamps 1 while adjusting the torque of the locking screws 6. Therefore, this can unify the locking torque of the locking screws 6 in all folding propeller assemblies during the assembly process, thereby reducing assembly difficulty, improving production efficiency, and realizing mass production. On the other hand, this can also adaptively adjust the friction between the propeller blades 2 and the propeller clamps 1 when switching between the folded and unfolded positions, thereby improving the flexibility of the folding propeller assembly during use.

[0023] It should be noted that due to the structural characteristics of the folding propeller assembly—that is, a larger number of components in the lift direction and a smaller number of components perpendicular to the lift direction—controlling the dimensional tolerances of the components in the lift direction is more difficult in actual use. Therefore, in designing this folding propeller assembly, the adjustment component 3 primarily absorbs and adjusts the dimensional tolerances and frictional forces in the lift direction. For example, in the lift direction of the airflow, when the dimensional tolerances of the blade 2 and the blade clamp 1 are at their lower limits, the gap between the blade 2 and the blade clamp 1 will be larger. The adjustment component 3 can then adaptively compensate for this gap to ensure that the clamping force applied by the blade clamp 1 to the blade 2 remains essentially constant.

[0024] It should also be noted that since frictional force is equal to the product of normal force and friction coefficient, under the premise that the friction coefficient is constant, adjusting component 3 to maintain the normal force applied by the blade clamp 11 to the blade 2 in the lift direction is basically constant, which can ensure that the frictional force between the blade 2 and the blade clamp 1 is basically constant.

[0025] The adjustment component 3 can be implemented in any suitable manner, and this disclosure does not impose any restrictions on it. Alternatively, in the exemplary embodiments provided in this disclosure, the adjustment component 3 can be implemented in the following two ways: In the first implementation, the adjustment component 3 may include an elastic element 31, which provides an elastic clamping force to the blade 2, thereby keeping the clamping force applied by the blade clamp 1 to the blade 2 substantially constant. Optionally, the adjustment component 3 includes an air bladder structure 311, that is, the air bladder structure 311 may be configured as an elastic element 31 for providing an elastic clamping force to the blade 2.

[0026] In the second implementation, the adjustment component 3 may include a magnetic element 32, which is used to provide a magnetic clamping force to the blade 2, so that the clamping force applied by the blade clamp 1 to the blade 2 can be kept substantially constant.

[0027] In the exemplary embodiments provided in this disclosure, when the adjustment component 3 adopts the first implementation described above, that is, when the adjustment component 3 includes an elastic element 31, the elastic element 31 can be a polymer elastomer, such as silicone or thermoplastic polyurethane rubber, and the polymer elastomer can be formed as a solid structure or a hollow air bladder structure 311. When the polymer elastomer is formed as a hollow air bladder structure 311, the hollow air bladder structure 311 can be a closed air bladder 3111 or an open air bladder 3112. Among them, the processing and manufacturing of the solid structure polymer elastomer is simpler and more convenient, and the elastic adjustment effect of the polymer elastomer with the hollow air bladder structure 311 is better. Therefore, the specific polymer elastomer structure selected as the adjustment component 3 in this disclosure can be flexibly selected according to the actual situation, and this disclosure does not limit it.

[0028] In the exemplary embodiments provided in this disclosure, reference is made to Figure 3 , Figure 7 , Figure 12 as well as Figure 13 As shown, in order to adapt to the structure of the propeller clip 1, the air bladder structure 311 can be set as a ring structure. When the open air bladder 3112 in the air bladder structure 311 adopts a ring structure, the open air bladder 3112 can be set to have an inner ring peripheral wall 3112a and an outer ring peripheral wall 3112b. The inner ring peripheral wall 3112a and the outer ring peripheral wall 3112b are respectively provided with a plurality of first air holes 3112c and a plurality of second air holes 3112d communicating with the interior of the open air bladder 3112. The plurality of first air holes 3112c are arranged at intervals along the circumference of the inner ring peripheral wall 3112a, and the plurality of second air holes 3112d are arranged at intervals along the circumference of the outer ring peripheral wall 3112b.

[0029] In the exemplary embodiments provided in this disclosure, reference is made to Figure 3 and Figure 7As shown, in order to reduce the frictional force on the blade 2 itself and the elastic element 31 (e.g., the air bladder structure 311) during rotation relative to the blade clamp 1, a first lubricant 4 can be provided between the side of the blade 2 away from the elastic element 31 and the blade clamp 1, while second lubricants 5 are respectively provided between the elastic element 31 and the blade clamp 1 and between the elastic element 31 and the blade 2. Here, the first lubricant 4 and the second lubricant 5 can be implemented in any suitable manner, and this disclosure does not limit them. Exemplarily, the first lubricant 4 and the second lubricant 5 can be Teflon gaskets.

[0030] In the exemplary embodiments provided in this disclosure, when the adjustment component 3 adopts the second implementation described above, that is, when the adjustment component 3 includes the magnetic element 32, refer to Figure 4 and Figure 8 As shown, the magnetic component 32 may include a first magnetic component 321 and a second magnetic component 322. The first magnetic component 321 and the second magnetic component 322 are arranged in a relatively suspended manner, with one of them disposed on the blade 2 and the other disposed on the blade clip 1. The same magnetic poles of the first magnetic component 321 and the second magnetic component 322 are opposite each other. With this arrangement, the repulsive force between the same magnetic poles of the first magnetic component 321 and the second magnetic component 322 can be used to absorb the dimensional tolerance of the folding propeller assembly during the assembly process, and at the same time, the frictional force experienced by the blade 2 when switching between the folded position and the unfolded position during the use of the folding propeller assembly can be adjusted.

[0031] In the exemplary embodiments provided in this disclosure, the first magnetic element 321 and the second magnetic element 322 can be permanent magnets, such as permanent magnets. Furthermore, to adapt to the structural design of the propeller clamp 1, both the first magnetic element 321 and the second magnetic element 322 can be constructed as rings, with the ring-shaped first magnetic element 321 and the ring-shaped first magnetic element 321 and the ring-shaped first magnetic element 322 arranged around the rotation axis 13 of the propeller clamp 1. Alternatively, both the first magnetic element 321 and the second magnetic element 322 can be constructed as including multiple magnetic elements 32 arranged at equal intervals along the ring, wherein the first magnetic element 321 and the second magnetic element 322, composed of multiple magnetic elements 32, are arranged around the rotation axis 13 of the propeller clamp 1. With this arrangement, at the connection between the propeller blade 2 and the propeller clamp 1, the propeller blade 2 can be uniformly subjected to magnetic clamping force from the magnetic elements 32 around its periphery. Thus, during the rotation of the propeller blade 2, because the force is uniform around its periphery, it can be ensured that the propeller blade 2 can rotate smoothly and avoid wobbling. The propeller clamp 1 includes the rotation axis 13, and the arrangement of the rotation axis 13 will be described in detail below.

[0032] In the exemplary embodiments provided in this disclosure, reference is made to Figure 3 , Figure 4 , Figure 7 as well as Figure 8As shown, along the lift direction of the airflow, the adjusting component 3 is located between the upstream side of the blade 2 and the blade clip 1. Thus, when this folding propeller assembly is applied to a drone, regardless of how the folding propeller assembly is positioned... Figure 3 and Figure 4 The configuration shown is upright, meaning the folding propeller assembly is positioned above the drone arm in the lift direction, and the upper propeller clamp 11 and lower propeller clamp 12 are arranged sequentially from top to bottom, as shown in the diagram. Figure 7 and Figure 8 The method shown is reversed, that is, the folding propeller assembly is located below the drone arm in the lift direction, and the upper propeller clamp 11 and the lower propeller clamp 12 are arranged sequentially from bottom to top. The adjustment components 3 can dynamically adjust the clamping force applied by the propeller clamp 1 to the propeller blade 2 in the lift direction. In this way, when the propeller blade 2 rotates relative to the propeller clamp 1, it can always be subjected to a basically constant clamping force from the propeller clamp 1 in the lift direction, so as to ensure the smooth operation of the propeller blade 2.

[0033] Among them, when the folding propeller assembly adopts such Figure 3 and Figure 4 When mounted in the manner shown, the upstream side of blade 2 refers to the side of blade 2 closest to the lower blade clip 12. However, when the folding blade assembly is mounted as shown... Figure 7 and Figure 8 When the blade 2 is installed in reverse as shown, the upstream side of the blade 2 refers to the side of the blade 2 closest to the upper blade clamp 11. The details regarding the blade clamp 1, including the upper blade clamp 11 and the lower blade clamp 12, and the arrangement of the upper blade clamp 11 and the lower blade clamp 12, will be described in detail below.

[0034] Furthermore, the folding propeller assembly may also include a first lubricant 4, which is disposed between the downstream side of the propeller blade 2 and the propeller clamp 1. With this arrangement, when the folding propeller assembly is applied to a drone, the friction experienced by the propeller blade 2 during rotation is reduced when the propeller blade 2 switches from a folded position to an unfolded position relative to the propeller clamp 1, thus making the rotation of the propeller blade 2 smoother. Here, the first lubricant 4 can be implemented in any suitable manner, and this disclosure does not limit it. Exemplarily, the first lubricant 4 can be a Teflon gasket.

[0035] In the exemplary embodiments provided in this disclosure, reference is made to Figure 3 , Figure 4 , Figure 7 as well as Figure 8As shown, the propeller clamp 1 may include an upper propeller clamp 11 and a lower propeller clamp 12 located on both sides of the propeller blade 2, and a rotating shaft 13 extending between the upper propeller clamp 11 and the lower propeller clamp 12. The propeller blade 2 is rotatably sleeved on the rotating shaft 13. The adjusting assembly 3 is constructed in annular shape and arranged around the rotating shaft 13. The first end of the rotating shaft 13 is fixedly connected to one of the upper propeller clamp 11 and the lower propeller clamp 12, and the second end is fastened to the other by a locking screw 6. A receiving groove 14 is formed on the propeller clamp 1. The second end of the rotating shaft 13 is inserted into the receiving groove 14, and a fastening hole 141 for the locking screw 6 to pass through is formed on the bottom surface of the receiving groove 14.

[0036] Through the above technical solution, on the one hand, the blade 2 can be locked together with the upper blade clamp 11 and the lower blade clamp 12 using the locking screw 6, so that the upper blade clamp 11 and the lower blade clamp 12 can reliably clamp the blade 2 in the lift direction. On the other hand, during the locking process of the blade 2 and the blade clamp 1, the second end of the rotating shaft 13 can be inserted into the receiving groove 14 and abut against the bottom wall of the receiving groove 14, and then locked and fixed in one step by the locking screw 6. This can reduce the assembly difficulty, improve production efficiency, realize mass production, and avoid measuring the friction between the blade 2 and the blade clamp 1 while adjusting the torque of the locking screw 6. Among them, constructing the adjustment component 3 as a ring and setting it around the rotating shaft 13 can make the structure of the adjustment component 3 adaptable to the structural design of the blade clamp 1, making it convenient to install the adjustment component 3 between the blade 2 and the blade clamp 1.

[0037] In the exemplary embodiments provided in this disclosure, reference is made to Figure 1 , Figure 2 , Figure 5 , Figure 6 , Figure 9 , Figure 10 As shown in Figure 11, the propeller clamp 1 has a connecting portion 15 at its center for connection with a drive device, such as a connecting through hole. Multiple propeller blades 2 are clamped onto the propeller clamp 1 at equal intervals around the connecting portion 15. A limiting member 7, such as a limiting block, is provided between each propeller blade 2 and the connecting portion 15. The limiting member 7 has a first limiting surface 71 and a second limiting surface 72 that respectively cooperate with the first side portion 21 and the second side portion 22 of the propeller blade 2. The folding positions include a first folding position achieved by rotating the propeller blade 2 clockwise relative to the propeller clamp 1 and a second folding position achieved by rotating it counterclockwise, wherein the first limiting surface 71 and the second limiting surface 72 correspond to the first folding position and the second folding position, respectively. Here, the drive device can be a drive motor.

[0038] With the above technical solution, when the folding propeller assembly is applied to a drone, the drive device can drive the propeller clamp 1 and the multiple propeller blades 2 clamped in the propeller clamp 1 to rotate through the connecting part 15. During the rotation of the propeller blades 2, due to centrifugal force, the propeller blades 2 will switch from the folded position to the unfolded position. Afterwards, under the action of centrifugal force, the propeller blades 2 will continue to remain in the unfolded position. After the drone finishes flight, for easy storage, the propeller blades 2 need to be switched from the unfolded position to the folded position.

[0039] For example, when there are three blades 2, and folding is required, one blade 2 is usually kept in the unfolded position while the other two blades 2 are folded towards the unfolded blade 2. To prevent the other two blades 2 from colliding with the unfolded blade 2 due to excessive folding angles, the folding angles of the other two blades 2 need to be limited. Specifically, a limiting member 7 can be provided between each blade 2 and the connecting part 15, and a first limiting surface 71 and a second limiting surface 72 corresponding to the first and second folding positions of the blade 2 are formed on the limiting member 7. Thus, regardless of which blade 2 is kept in the unfolded position, the other two blades 2 can limit their folding angles through the corresponding first limiting surface 71 or second limiting surface 72 on the limiting member 7, preventing collisions with the unfolded blade 2.

[0040] For example, when there are three blades 2, for ease of description, these three blades 2 can be referred to as the first blade, the second blade, and the third blade in a clockwise direction, and the corresponding limiting members 7 of these three blades 2 can be referred to as the first limiting member, the second limiting member, and the third limiting member, respectively. When the folding propeller assembly provided in this disclosure needs to be folded, any blade 2 can be kept in the unfolded position. Here, for ease of description, when the second blade is kept in the unfolded position, the first blade rotates clockwise toward the second blade to the first folded position, and the first limiting surface 71 of the first limiting member limits the first side 21 of the first blade. The third blade rotates counterclockwise toward the second blade to the second folded position, and the second limiting surface 72 of the third limiting member limits the second side 22 of the third blade. The same applies when either the first blade or the third blade is kept in the unfolded position. Therefore, to avoid repetition, this disclosure will not elaborate further here.

[0041] Based on the above technical solution, this disclosure also provides a drone, which includes the aforementioned folding propeller assembly. The details regarding the folding propeller assembly have already been described in detail above; therefore, to avoid repetition, this disclosure will not repeat them here.

[0042] The preferred embodiments of this disclosure have been described in detail above with reference to the accompanying drawings. However, this disclosure is not limited to the specific details of the above embodiments. Within the scope of the technical concept of this disclosure, various simple modifications can be made to the technical solutions of this disclosure, and these simple modifications all fall within the protection scope of this disclosure.

[0043] It should also be noted that the various specific technical features described in the above specific embodiments can be combined in any suitable manner without contradiction. In order to avoid unnecessary repetition, this disclosure will not describe the various possible combinations separately.

[0044] Furthermore, various different embodiments of this disclosure can be combined in any way, as long as they do not violate the spirit of this disclosure, they should also be regarded as the content disclosed in this disclosure.

Claims

1. A folding oar assembly, characterized by, The utility model relates to a folding oar assembly, comprising: an oar clamp; an oar blade rotatably clamped between the oar clamp to have a folding position and an unfolding position selectively; and an adjusting assembly arranged between the oar blade and the oar clamp to dynamically adjust the clamping force of the oar clamp on the oar blade; wherein the adjusting assembly comprises a hollow air bag structure for providing elastic clamping force to the oar blade; or the adjusting assembly comprises a magnetic member for providing magnetic clamping force to the oar blade.

2. The folding oar assembly of claim 1, wherein, The hollow air bag structure is formed by a high-molecular elastomer; and / or The hollow air bag structure is a closed air bag or an open air bag.

3. The folding oar assembly of claim 2, wherein, The hollow air bag structure is an annular structure; and / or The open air bag has an inner circumferential wall and an outer circumferential wall, and a plurality of first air holes and a plurality of second air holes are respectively formed on the inner circumferential wall and the outer circumferential wall to communicate with the inside of the open air bag, the plurality of first air holes are arranged along the circumferential direction of the inner circumferential wall at intervals, and the plurality of second air holes are arranged along the circumferential direction of the outer circumferential wall at intervals.

4. The folding oar assembly of claim 1, wherein, A first lubricating member is arranged between the side of the oar blade facing away from the hollow air bag structure and the oar clamp, and a second lubricating member is arranged between the hollow air bag structure and the oar clamp and between the hollow air bag structure and the oar blade respectively.

5. The folding oar assembly of claim 1, wherein, The magnetic member comprises a first magnetic member and a second magnetic member, the first magnetic member and the second magnetic member are oppositely arranged in suspension and one is arranged on the oar blade and the other is arranged on the oar clamp, wherein the same-named magnetic poles of the first magnetic member and the second magnetic member are opposite.

6. The folding oar assembly of claim 5, wherein, The first magnetic member and the second magnetic member are both permanent magnets, and the first magnetic member and the second magnetic member are both configured as an annular shape or as a plurality of magnetic members arranged at intervals along a ring shape.

7. The folded oar assembly of claim 1 or 5, wherein, In the direction of lift of the air flow, the adjusting assembly is located between the upstream side of the oar blade and the oar clamp, and the folding oar assembly further comprises a first lubricating member arranged between the downstream side of the oar blade and the oar clamp.

8. The folding oar assembly of any of claims 1-6, wherein, The oar clamp comprises an upper oar clamp and a lower oar clamp located on both sides of the oar blade, and a rotating shaft extending between the upper oar clamp and the lower oar clamp, the oar blade is rotatably sleeved on the rotating shaft, the adjusting assembly is configured as an annular shape and arranged around the rotating shaft, a first end of the rotating shaft is fixedly connected to one of the upper oar clamp and the lower oar clamp, and a second end is fastened to the other through a locking screw, the oar clamp is formed with a receiving groove, the second end of the rotating shaft is inserted into the receiving groove, and the bottom surface of the receiving groove is formed with a fastening hole for the locking screw to pass through.

9. The folding oar assembly of claim 1, wherein, The oar clamp has a connecting portion in the center for connecting with a driving device, the oar blade comprises a plurality of oar blades and is clamped on the oar clamp at intervals around the connecting portion, a limiting member is arranged between each oar blade and the connecting portion, the limiting member has a first limiting surface and a second limiting surface matched with a first side and a second side of the oar blade respectively, The folding positions include a first folding position reached by the propeller blade rotating clockwise relative to the propeller clamp and a second folding position reached by rotating counterclockwise, wherein the first limiting surface and the second limiting surface correspond to the first folding position and the second folding position, respectively.

10. A drone, characterized in that, Includes the folding propeller assembly according to any one of claims 1-9.

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