UAV self-correcting folding propeller structure

Abstract

This invention aims to provide a self-correcting folding propeller structure for unmanned aerial vehicles (UAVs). The structure includes a base and a propeller assembly. The base is fixed to the output shaft of a motor and has a conical protrusion. The propeller assembly includes a propeller seat, a straightening locking member, and two propeller blades. The center of the propeller seat is rotatably mounted on the base and abuts against the conical protrusion. One end of each of the two propeller blades is rotatably mounted on either end of the propeller seat. The straightening locking member is mounted on the propeller seat and is used to lock the two propeller blades in a straight line. Thus, by utilizing the conical protrusion to abut against the propeller seat, the propeller assembly can quickly self-correct and return to a horizontal state when tilted by turbulence, thereby better coping with turbulent operating environments.

Description

Technical Field

[0001] This invention relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to a self-correcting folding propeller structure for UAVs. Background Technology

[0002] With the continuous development of drone technology, drone propellers have evolved from fixed, non-foldable propeller structures to foldable and storage structures. When the drone is not in use, folding the propellers makes it easy to store and store.

[0003] For example, Chinese patent document CN119551235A discloses a drone rotor device and a drone, including a folding blade assembly and a folding blade limiting assembly. The folding blade assembly includes a folding blade and a blade mounting mechanism. The folding blade is rotatably connected to the blade mounting mechanism. The folding blade limiting assembly includes a blade limiting member, which is detachably connected to the blade mounting mechanism. The blade limiting member is provided with a limiting mechanism, which includes at least two limiting blocks distributed on both sides of the folding blade.

[0004] It also includes an arm assembly, a motor assembly, and a shock absorption assembly. The arm assembly includes a connected arm mounting base and an arm connecting tube. The arm connecting tube is used to connect to the UAV fuselage. The motor assembly is flexibly connected to the arm mounting base through the shock absorption assembly. The motor assembly is connected to the propeller mounting mechanism to drive the folding propeller assembly to rotate.

[0005] As can be seen, in the prior art, the blade mounting mechanism is fixedly mounted on the motor assembly, so that the motor assembly can drive the folding blade assembly to rotate through the blade mounting mechanism.

[0006] However, this fixed installation method has the following problems in actual use: As the operating environment of drones becomes increasingly complex, for example, when facing windy or unstable airflow, the existing drones with wings fixed to the motor are very prone to loss of control of the propellers when facing unstable airflow. At best, the drone will crash and cause property damage; at worst, the drone may fall from a high altitude and pose a great risk.

[0007] Therefore, in order to solve the problems of the existing fixed-wing method, the self-correcting folding propeller structure of the UAV proposed in this application is proposed. Summary of the Invention

[0008] The purpose of this invention is to overcome the shortcomings of the prior art and provide a self-correcting folding propeller structure for UAVs that can adapt to unstable airflow environments and has good propeller flight stability.

[0009] The objective of this invention is achieved through the following technical solution: A self-correcting folding propeller structure for unmanned aerial vehicles includes: A base for fixing to the output shaft of a motor, the base having a convex cone portion; The propeller assembly includes a propeller base, a straight-locking member, and two propeller blades. The middle part of the propeller base is rotatably mounted on the base, and the propeller base abuts against the convex cone portion. One end of each of the two propeller blades is rotatably mounted on both ends of the propeller base. The straight-locking member is mounted on the propeller base and is used to lock the two propeller blades so that the two propeller blades are in a straight line.

[0010] Optionally, the base includes a base plate and two support ears, the two support ears being disposed at intervals on the base plate, the convex cone being disposed on the base plate and located between the two support ears, and the paddle seat being rotatably connected to the two support ears.

[0011] Optionally, the convex cone portion includes two inclined surfaces, the included angle between the two inclined surfaces is less than 180° and greater than 120°, and the connection position between the two inclined surfaces 121 is a rounded corner structure.

[0012] Optionally, the propeller base includes a base body, a clamping cover, two first pins, and two first locking pins. The two first pins are respectively inserted through both ends of the base body, and the two first locking pins are respectively inserted through both ends of the clamping cover to be screwed onto the two first pins. The two propeller blades are respectively rotatably mounted on the two first pins, and both propeller blades are located between the clamping cover and the base body.

[0013] Optionally, the base further includes a second pin and a second pin. The second pin is disposed on one of the support ears, and the second pin passes through the other support ear and the clamp in sequence to be screwed to the second pin so that the clamp is rotatably connected to the support ear.

[0014] Optionally, the seat body is further provided with a cushioning pad, which abuts against the convex cone portion.

[0015] Optionally, a metal gasket, a wear-resistant washer, and a shock-absorbing washer are sequentially arranged between the blade and the base / clamp.

[0016] Optionally, the locking member includes an elastic member and two locking covers, both of which are rotatably connected to the two supporting ears. The elastic member pushes the two locking covers respectively, so that the two locking covers are respectively fastened to the two blades.

[0017] Optionally, the locking member further includes a locking pin, which is connected to two of the supporting ears respectively. Both of the locking covers are rotatably mounted on the locking pin, and the elastic element is sleeved on the locking pin.

[0018] Optionally, the lock cover includes two opposing blocks, and a silicone pad is provided on the side of the two blocks that are close to each other. The two blocks are used to cover the blade, so that the two silicone pads respectively clamp the opposing sides of the blade.

[0019] Compared with the prior art, the present invention has at least the following advantages: The self-correcting folding propeller structure for unmanned aerial vehicles (UAVs) of the present invention includes a base and a propeller assembly. The base is fixed on the output shaft of a motor and has a convex cone portion. The propeller assembly includes a propeller seat, a straightening locking member, and two propeller blades. The middle part of the propeller seat is rotatably mounted on the base and abuts against the convex cone portion. One end of each of the two propeller blades is rotatably mounted on both ends of the propeller seat. The straightening locking member is mounted on the propeller seat and is used to lock the two propeller blades so that the two propeller blades are in a straight line state.

[0020] In this way, by using the convex cone to abut against the propeller seat, the propeller assembly can quickly recover to a horizontal state when tilted in turbulent flow, thus better coping with turbulent operating environments. Attached Figure Description

[0021] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of the present invention and should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 This is a schematic diagram of a self-correcting folding propeller structure for an unmanned aerial vehicle according to one embodiment of the present invention. Figure 2 for Figure 1 A top view of the self-correcting folding propeller structure of the UAV shown; Figure 3 for Figure 2 AA section view; Figure 4 This is a schematic diagram of the structure of the convex cone portion according to one embodiment of the present invention; Figure 5 This is a schematic diagram of the assembly structure of the propeller holder and the propeller blade according to one embodiment of the present invention. Figure 6 for Figure 3 A schematic diagram of the enlarged B-structure; Figure 7 This is a schematic diagram of the structure of a locking cover according to one embodiment of the present invention.

[0023] Explanation of reference numerals in the attached figures: 10. UAV self-correcting folding propeller structure; 110. Base; 200. Propeller assembly; 120. Conical part; 210. Propeller seat; 220. Straightening locking component; 230. Propeller blade; 121. Inclined surface; 111. Base plate; 112. Support ear; 211. Seat body; 212. Clamp cover; 213. First pin; 214. First locking pin; 215. Compression spring; 113. Second pin; 114. Second pin; 216. Buffer pad; 241. Metal washer; 242. Wear-resistant washer; 243. Shock-absorbing washer; 221. Elastic component; 222. Locking cover; 223. Straightening pin; 224. Stop block; 225. Silicone pad. Detailed Implementation

[0024] To facilitate understanding of the present invention, a more comprehensive description of the present invention will be given below with reference to the accompanying drawings.

[0025] The accompanying drawings illustrate a preferred embodiment of the invention.

[0026] like Figures 1 to 4 As shown, a self-correcting folding propeller structure 10 for a drone includes a base 110 and a propeller assembly 200. The base 110 is fixed to the output shaft of a motor and has a cone portion 120. The propeller assembly 200 includes a propeller seat 210, a straightening member 220, and two propeller blades 230. The middle part of the propeller seat 210 is rotatably mounted on the base 110 and abuts against the cone portion 120. One end of each of the two propeller blades 230 is rotatably mounted on both ends of the propeller seat 210. The straightening member 220 is mounted on the propeller seat 210 and is used to clamp the two propeller blades 230 so that the two propeller blades 230 are in a straight state.

[0027] It should be noted that the base 110 is fixedly mounted on the output shaft of the drone's motor with screws, so that the motor can drive the base 110 to rotate.

[0028] Furthermore, a conical portion 120 is provided on the base 110. In one embodiment, the conical portion 120 includes two inclined surfaces 121. The included angle between the two inclined surfaces 121 is less than 180° and greater than 120°, and the connection position between the two inclined surfaces 121 is a rounded corner structure.

[0029] For example, the included angle between the two inclined planes 121 is 164°.

[0030] Thus, the two inclined planes 121 tilt upwards and connect in a direction that brings them closer to each other, and the connection point between the two inclined planes 121 forms a rounded corner structure.

[0031] Furthermore, the top side of the middle position of the propeller holder 210 is rotatably connected to the base 110, so that the cone portion 120 abuts against the bottom side of the middle position of the propeller holder 210.

[0032] Two blades 230 are rotatably mounted on both ends of the blade base 210. The two blades 230 can rotate relative to the blade base 210, thus forming a folded state or unfolding into a straight state.

[0033] When the two blades 230 are in a straight line, the locking member 220 can lock the two blades 230, thereby keeping the two blades 230 stably in an extended straight line state.

[0034] Thus, when installed on a drone, the base 110 is driven by a motor to rotate, causing the drone's self-correcting folding propeller structure 10 to rotate as a whole.

[0035] When turbulence occurs in the actual use environment, the propeller disk structure formed by the propeller assembly 200 is blown by the turbulence and is no longer in a horizontal state.

[0036] Instead, the entire propeller disk structure will tilt to a certain extent, that is, the propeller holder 210 is tilted relative to the base 110. At this time, the cone portion 120 no longer abuts against the bottom side of the middle position of the propeller holder 210. However, since the top side of the middle position of the propeller holder 210 is rotatably connected to the base 110, under its own gravity, the propeller holder 210 will tend to swing from the tilted state to a straight state, so that the cone portion 120 abuts against the bottom side of the middle position of the propeller holder 210 again, so that the entire propeller disk structure formed by the blade assembly 200 returns to a horizontal state from the tilt.

[0037] Thus, the UAV self-correcting folding propeller structure 10 of this application can achieve self-correction of the tilting propeller structure when facing turbulent usage scenarios, and has better adaptability to complex environments.

[0038] like Figure 1 , Figure 4 As shown, in one embodiment, the base 110 includes a base plate 111 and two support ears 112. The two support ears 112 are spaced apart on the base plate 111. A convex cone portion 120 is disposed on the base plate 111 and is located between the two support ears 112. The paddle seat 210 is rotatably connected to the two support ears 112.

[0039] It should be noted that the two support ears 112 are located on opposite sides of the same side of the base plate 111, so that there is a gap between the two support ears 112.

[0040] The blade assembly 200 is integrally mounted between the two support lugs 112.

[0041] The cone portion 120 is disposed on the base plate 111 and is located between the two support ears 112.

[0042] In one embodiment, the base plate 111, the cone portion 120, and the two support ears 112 are integrally formed, so that the support ears 112 and the cone portion 120 have sufficient structural strength relative to the base plate 111.

[0043] like Figure 1 , Figure 3 , Figure 5 As shown, in one embodiment, the propeller base 210 includes a base body 211, a clamping cover 212, two first pins 213, and two first locking pins 214. The two first pins 213 are respectively inserted through both ends of the base body 211, and the two first locking pins 214 are respectively inserted through both ends of the clamping cover 212 to be screwed onto the two first pins 213. The two propeller blades 230 are respectively rotatably disposed on the two first pins 213, and both propeller blades 230 are located between the clamping cover 212 and the base body 211.

[0044] It should be noted that the first pin 213 passes through the base 211, the blade 230, and the cover 212 from bottom to top, and the first locking pin 214 passes through the cover 212 to be logically fixed with the first pin 213.

[0045] This allows the blade 230 to rotate relative to the first pin 213.

[0046] The first pin 213 passes through the blade 230 and extends to a certain depth inside the cover 212.

[0047] In one embodiment, the first locking pin 214 passes through the compression spring 215 and is then screwed onto the first pin 213.

[0048] In this way, the first locking pin 214 is screwed tightly to the first pin 213, which can clamp and fix the blade 230 between the cover 212 and the seat 211, so that the blade 230 can rotate stably relative to the first pin 213 without moving along the axial direction of the first pin 213.

[0049] like Figure 1 , Figure 3 , Figure 5 As shown, in one embodiment, the base 110 further includes a second pin 113 and a second pin 114. The second pin 114 is disposed on one of the support ears 112, and the second pin 113 is sequentially passed through the other support ear 112 and the clamp 212 to be screwed with the second pin 114 so that the clamp 212 is rotatably connected to the support ear 112.

[0050] It should be noted that the cover 212 and the base 211 form a double-layer structure, with the cover 212 located on top of the base 211.

[0051] The top side of the middle part of the propeller mount 210 is rotatably connected to the support lug 112.

[0052] Specifically, the second pin 114 is fixed to one of the support ears 112, the second pin 113 passes through the other support ear 112, then through the clip 212, and finally is logically fixed to the second pin 114.

[0053] Thus, the middle position of the clamp cover 212 rotates relative to the second pin 113, causing the bottom side of the middle position of the propeller seat 211 to abut against the cone portion 120 under its own weight.

[0054] Thus, when flying in a turbulent environment, if the propeller disk structure formed by the propeller base 210 and the propeller blade 230 tilts, the propeller disk structure can self-correct to a horizontal state under its own gravity.

[0055] like Figure 3 As shown, in one embodiment, a cushioning pad 216 is also provided on the seat 211, and the cushioning pad 216 abuts against the cone portion 120.

[0056] It should be noted that, in order to further improve the self-correction capability of the blade assembly 200 when facing turbulent operating environments,

[0057] Therefore, a cushioning pad 216 is fixedly installed on the bottom side of the middle position of the seat 211.

[0058] In one embodiment, the cushioning pad 216 is made of silicone, which has a certain degree of softness.

[0059] Thus, the cone portion 120 is pressed into the buffer pad 216, causing the buffer pad 216 to be pressed to undergo a certain deformation.

[0060] Thus, since the cone portion 120 is a structure formed by two inclined surfaces 121, when the cone portion 120 is pressed into the buffer pad 216, since both inclined surfaces 121 tend to contact the buffer pad 216, the final result is that the cone portion 120 is pressed into the buffer pad 216 in a balanced manner.

[0061] In this way, in addition to self-correcting by its own gravity, the pressure of the buffer pad 216 on the cone 120 also makes the blade assembly 200 as a whole correct its tilted posture relative to the cone 120.

[0062] In addition, the cushioning pad 216 is elastic.

[0063] This reduces the vibration generated during the rotation of the propeller blade 230, thereby improving the stability of the entire UAV self-correcting folding propeller structure 10.

[0064] like Figure 3 , Figure 6As shown, in one embodiment, a metal gasket 241, a wear-resistant washer 242, and a shock-absorbing washer 243 are sequentially arranged between the blade 230 and the base 211 / clamp cover 212.

[0065] It should be noted that when the blade 230 rotates relative to the first pin 213 to adjust to a folded or straight state, in order to avoid the blade 230 directly rubbing against the clamp 212 and the seat 211, metal shims 241, wear-resistant washers 242, and shock-absorbing washers 243 are sequentially provided on the side of the blade 230 that is close to the clamp 212 or the seat 211.

[0066] Specifically, the metal gasket 241 contacts the blade 230, the shock-absorbing washer 243 contacts the cover 212 or the seat 211, and the wear-resistant washer 242 is located between the metal gasket 241 and the shock-absorbing washer 243.

[0067] In this way, the friction on the blade 230 is reduced by using the metal gasket 241.

[0068] The vibration generated during the rotation of the propeller blade 230 is reduced by using the shock-absorbing washer 243.

[0069] Wear-resistant washer 242 can reduce wear between metal washer 241 and shock-absorbing washer 243.

[0070] like Figures 1 to 3 , Figure 7 As shown, in one embodiment, the locking member 220 includes an elastic member 221 and two locking covers 222. The two locking covers 222 are rotatably connected to two support ears 112. The elastic member 221 pushes the two locking covers 222 respectively, so that the two locking covers 222 are respectively fastened to the two blades 230.

[0071] It should be noted that the locking member 220 is used to clamp the two rotatable blades 230, so that the two blades 230 are stably deployed in a straight line.

[0072] Specifically, both locking covers 222 are rotatably connected to the support ears 112, and the elastic members 221 push the two locking covers 222 respectively, so that the locking covers 222 are snapped onto the two propellers 230.

[0073] It should be noted that the rotation axis of the lock cover 222 is perpendicular to the rotation axis of the blade 230.

[0074] For example, the locking cover 222 rotates in the vertical plane, while the blade 230 rotates in the horizontal plane relative to the first pin 213. In this way, the locking cover 222 is used to lock the blade 230 in the horizontal direction. The locking cover 222 is locked and fixed by the push of the elastic member 221, so the blade 230 can no longer rotate in the horizontal plane. That is, the blade 230 is reliably locked into a straight state.

[0075] When it is necessary to fold the two blades 230 that are in a straight position, an upward rotating thrust is applied to the two locking covers 222, causing the locking covers 222 to disengage from the sides of the blades 230. In this way, the two blades 230 can resume folding relative to the first pin 213.

[0076] like Figures 1 to 3 As shown, in one embodiment, the locking member 220 further includes a locking pin 223, which is connected to two support ears 112 respectively. Both locking covers 222 are rotatably mounted on the locking pin 223, and the elastic member 221 is sleeved on the locking pin 223.

[0077] It should be noted that the locking pin 223 is horizontally fixedly connected to the two support ears 112.

[0078] The locking pin 223 passes through the two locking covers 222, so that the two locking covers 222 can rotate relative to the locking pin 223.

[0079] The elastic element 221 is fitted onto the locking pin 223, and the two ends of the elastic element 221 push against the two locking covers 222 respectively.

[0080] In one embodiment, the elastic element 221 is a torsion spring.

[0081] Thus, under the pushing action of the elastic member 221, the lock cover 222 stably engages and fixes the blade 230, and the blade 230 can no longer rotate relative to the first pin 213, thereby causing the two blades 230 to unfold into a straight line.

[0082] like Figure 1 , Figure 7 As shown, in one embodiment, the lock cover 222 includes two opposing blocks 224. A silicone pad 225 is also provided on the side of the two blocks 224 that are close to each other. The two blocks 224 are used to cover the blade 230, so that the two silicone pads 225 respectively clamp the opposing sides of the blade 230.

[0083] It should be noted that the two stops 224 are distributed at intervals on opposite sides of the lock cover 222, so that the two stops 224 surround the two sides of the propeller 230.

[0084] To prevent a gap from appearing between the stop 224 and the blade 230 when the lock cover 222 and the stop 224 are fastened to the blade 230, a silicone pad 225 is provided on the inner side of the stop 224.

[0085] In this way, the silicone pads 225 on both sides can tightly press against the blade 230, preventing the blade 230 from vibrating relative to the lock cover 222 and improving the structural stability of the blade 230.

[0086] Thus, when the blade 230 needs to be folded, an upward rotating force is applied to the two locking covers 222, causing the two stops 224 to drive the two silicone pads 225 away from the sides of the blade 230, and the blade 230 can then resume rotation.

[0087] Furthermore, it should be noted that the lock pin 223 is located in the middle of the two lock covers 222.

[0088] When the elastic element 221 pushes the two locking covers 222 respectively, the pushing force of the elastic element 221 on the two locking covers 222 is the same under natural conditions.

[0089] The natural state refers to the situation where the blade assembly 200 does not wobble or tilt due to turbulence.

[0090] It is foreseeable that when the blade assembly 200 tilts due to turbulence, the whole formed by the elastic element 221 and the two locking covers 222 will also tilt along with the two blades 230.

[0091] This allows the straightening element 220 to also correct the propeller disk structure formed by the propeller seat 210 and the two propeller blades 230. In this way, the three-layer structure formed by the straightening element 220, the clamp cover 212, and the seat 211 can self-correct in turbulent flow.

[0092] Furthermore, it should be noted that the rotation of the propeller disk structure formed by the propeller base 210 and the two propeller blades 230 in the horizontal plane as described in this application does not mean that the propeller base 210 and the two propeller blades 230 must be distributed in a horizontal straight line, but rather that the rotation normal of the propeller base 210 and the two propeller blades 230 as a whole coincides with the vertical direction.

[0093] Therefore, when the two blades 230 are installed on the propeller base 210, the two blades 230 can be tilted to both ends. At this time, the two blades 230 are not distributed along a straight line. However, the propeller disk structure formed by the propeller base 210 and the two blades 230 rotates along the horizontal plane. Therefore, the tilt of the propeller disk structure formed by the propeller base 210 and the two blades 230 means that the normal of the propeller disk structure no longer coincides with the vertical direction.

[0094] The above embodiments are merely examples of several implementation methods of the present invention, and their descriptions are relatively specific and detailed, but they should not be construed as limiting the scope of the invention patent.

[0095] It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this invention, and these modifications and improvements are all within the scope of protection of this invention.

[0096] Therefore, the scope of protection of this invention patent shall be determined by the appended claims.

Claims

1. A self-correcting folding propeller structure for unmanned aerial vehicles (UAVs), characterized in that, include: A base for fixing to the output shaft of a motor, the base having a convex cone portion; The propeller assembly includes a propeller base, a straight-locking member, and two propeller blades. The middle part of the propeller base is rotatably mounted on the base, and the propeller base abuts against the convex cone portion. One end of each of the two propeller blades is rotatably mounted on both ends of the propeller base. The straight-locking member is mounted on the propeller base and is used to lock the two propeller blades so that the two propeller blades are in a straight line.

2. The self-correcting folding propeller structure of claim 1, wherein, The base includes a base plate and two support ears, which are spaced apart on the base plate. A convex cone is disposed on the base plate and located between the two support ears. The paddle seat is rotatably connected to the two support ears.

3. The self-correcting folding propeller structure of claim 2, wherein, The convex cone portion includes two inclined surfaces, the included angle between the two inclined surfaces is less than 180° and greater than 120°, and the connection position between the two inclined surfaces 121 is a rounded corner structure.

4. The self-correcting folding propeller structure of claim 2, wherein, The propeller base includes a base body, a clamping cover, two first pins, and two first locking pins. The two first pins are respectively inserted through both ends of the base body, and the two first locking pins are respectively inserted through both ends of the clamping cover to be screwed onto the two first pins. The two propeller blades are respectively rotatably mounted on the two first pins, and both propeller blades are located between the clamping cover and the base body.

5. The self-correcting folding propeller structure of claim 4, wherein, The base also includes a second pin and a second pin. The second pin is disposed on one of the support ears, and the second pin passes through the other support ear and the clamp in sequence to be screwed to the second pin so that the clamp is rotatably connected to the support ear.

6. The self-correcting folding propeller structure of drones according to claim 4, wherein, The seat is also provided with a cushioning pad, which abuts against the convex cone portion.

7. The self-correcting folding propeller structure of drones according to claim 4, wherein, A metal gasket, a wear-resistant washer, and a shock-absorbing washer are sequentially arranged between the blade and the base / clamp.

8. The self-correcting folding propeller structure of drones according to claim 4, wherein, The locking component includes an elastic element and two locking covers. The two locking covers are rotatably connected to the two supporting ears. The elastic element pushes the two locking covers respectively, so that the two locking covers are respectively fastened to the two blades.

9. The UAV self-correcting folding propeller structure according to claim 8, characterized in that, The locking component also includes a locking pin, which is connected to two supporting ears respectively. Both locking covers are rotatably mounted on the locking pin, and the elastic element is sleeved on the locking pin.

10. The self-correcting folding propeller structure of drones according to claim 9, wherein, The lock cover includes two opposing blocks, and a silicone pad is provided on the side of the two blocks that are close to each other. The two blocks are used to cover the blade, so that the two silicone pads respectively clamp the opposing sides of the blade.

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