A blade anti-loosening device for a drone

Abstract

The present invention provides a blade anti-loosening device for an unmanned aerial vehicle, comprising an unmanned aerial vehicle body, four arms, four motor assemblies, four blade structures, and a plurality of locking mechanisms; the four arms are evenly distributed on the unmanned aerial vehicle body, the motor assemblies are arranged at the ends of the arms away from the unmanned aerial vehicle body, and the outer rotor housing of one motor assembly is connected to one blade structure via a plurality of locking mechanisms; the locking mechanism comprises a first anti-loosening structure, a fixing bolt, and a buffer assembly; the fixing bolt passes through the first anti-loosening structure and the mounting plate of the blade structure and is connected to the outer rotor housing of the motor assembly; the buffer assembly is arranged on the lower end face of the first anti-loosening structure. The blade anti-loosening device for an unmanned aerial vehicle described in the present invention solves the problem that improper design of the blade fixing structure in the related art easily causes damage to the surface of the blade made of carbon fiber, wood, or plastic, which not only affects the structural integrity of the blade but also easily leads to the failure of the anti-loosening effect.

Description

Technical Field

[0001] The invention belongs to the technical field of unmanned aerial vehicles (UAVs), and in particular relates to a blade anti-loosening device for UAVs. Background Art

[0002] A drone's propeller blades are key components for generating lift and propulsion, and are typically made of lightweight materials such as carbon fiber or composite materials. The design of the propeller blades directly impacts a drone's flight performance, stability, and efficiency. Securely securing the propeller blades prevents them from coming loose due to vibration or collision during flight, thus avoiding potential flight accidents.

[0003] The propeller blades of drones currently on the market are usually fixed with screws. However, the commonly used anti-loosening measure - screw glue - may fail in complex environments such as high temperature or oil pollution, resulting in a weakened protective effect. In addition, due to improper design of the blade fixing structure in related technologies, it is easy to cause damage to the surface of the carbon fiber, wood or plastic blades, which not only affects the structural integrity of the blades, but also easily leads to the failure of the anti-loosening effect, thereby causing the risk of the blades loosening during flight. The accumulation of the above problems may lead to a decline in the performance of the drone, or even serious damage accidents. Therefore, it is crucial to improve the blade fixing and anti-loosening mechanism to ensure the safe operation and long-term use of the drone. Summary of the Invention

[0004] In view of this, the present invention aims to solve one of the related technical problems at least to a certain extent.

[0005] To achieve the above object, the technical solution of the present invention is achieved as follows:

[0006] A propeller blade anti-loosening device for a drone, comprising a drone body, four arms, four motor assemblies, four propeller blade structures, and multiple locking mechanisms;

[0007] The four arms are evenly distributed on the UAV body, the motor assembly is arranged at the end of the arm away from the UAV body, and the outer rotor housing of one motor assembly is connected to one blade structure through a plurality of locking mechanisms;

[0008] The locking mechanism includes a first anti-loosening structure, a fixing bolt, and a buffer assembly. The fixing bolt passes through the first anti-loosening structure and the mounting plate of the blade structure and is connected to the outer rotor housing of the motor assembly. The buffer assembly is arranged on the lower end surface of the first anti-loosening structure.

[0009] The first anti-loosening structure includes a first gasket, multiple first teeth and multiple locking plates. The multiple first teeth are evenly arranged on the outer end surface of the first gasket. The multiple locking plates are evenly arranged on the upper end surface of the first gasket. The mounting plate of the blade structure is provided with one or more locking holes that can cooperate with the first teeth. The locking plate can limit and fix the countersunk head of the bolt or the outer surface of the nut. The locking plate and the first teeth can both bend. The buffer assembly is arranged on the lower end surface of the first gasket.

[0010] Furthermore, the locking mechanism also includes a second anti-loosening structure, a plurality of wedge blocks are evenly arranged circumferentially on the lower end surface of the first gasket, the second anti-loosening structure includes a second gasket and a plurality of second teeth, the plurality of second teeth are evenly arranged circumferentially on the outer end surface of the second gasket, the upper end surface of the second gasket is provided with a plurality of limiting grooves that can cooperate with the wedge blocks, and a first notch for placing the second gasket is provided on the mounting plate of the blade structure, and the inner wall of the first notch cooperates with the second teeth through the first tooth groove.

[0011] Furthermore, the locking mechanism also includes a third anti-loosening structure, which includes a third gasket, a rubber sleeve, multiple elastic tightening mechanisms and multiple third teeth. The bottom of the first slot is provided with a second slot for placing the third gasket, and the inner wall of the second slot cooperates with the third tooth through a second tooth-shaped groove. Multiple third teeth are evenly arranged on the outer end face of the third gasket. The third gasket is provided with a circular hole for placing the rubber sleeve, and multiple elastic tightening mechanisms are evenly arranged on the inner side of the circular hole. One end of the elastic tightening mechanism is connected to the inner wall of the circular hole, and the other end of the elastic tightening mechanism is arranged in the channel for installing the fixing bolt. When the fixing bolt is installed, the elastic tightening mechanism squeezes the bottom of the rubber sleeve so that the top of the rubber sleeve presses the lower end face of the second gasket.

[0012] Furthermore, the elastic tightening mechanism includes a guide rod, a return spring and a tightening pressure block, one end of the guide rod is connected to the inner wall of the circular hole, the outer end of the guide rod is slidingly engaged with the tightening pressure block, the return spring is arranged on the guide rod, one end of the return spring is against the tightening pressure block, and the other end of the return spring is against the bottom of the rubber sleeve, and the end of the tightening pressure block is provided with a slope, and the slope is arranged in the channel where the fixing bolt is installed.

[0013] Furthermore, the first gasket is provided with a plurality of square holes for placing locking plates, and the plurality of square holes are evenly arranged around the circumference of the first gasket.

[0014] Furthermore, the number of the locking pieces and the number of the square holes are both 4.

[0015] Furthermore, the buffer component is an annular rubber ring.

[0016] Furthermore, the outer rotor housing of a motor assembly is connected to one of the blade structures through four of the locking mechanisms.

[0017] Compared with the prior art, the blade anti-loosening device for a UAV described in the present invention has the following advantages:

[0018] 1. Multiple first teeth evenly distributed around the outer circumference of the first gasket engage with the locking holes on the propeller mounting plate, forming a direct mechanical interlock. When the propeller is subjected to vibration, the engagement of the first teeth with the locking holes effectively inhibits relative rotation between the propeller and the motor assembly, preventing the bolt from loosening due to circumferential shear forces. A flexible locking plate above the first gasket wraps around the countersunk head of the mounting bolt or the outer surface of the nut, generating a continuous compressive force through its elastic deformation. This elastic restraint not only offsets the attenuation of the bolt preload caused by vibration, but also directly limits the bolt's rotational freedom through physical resistance. The annular rubber ring at the lower end of the first gasket acts as a buffer, absorbing energy generated by the high-frequency vibration of the drone's motor during flight and reducing the vibration amplitude transmitted to the mounting bolt. By reducing the dynamic load on the bolt, loosening due to fatigue is delayed. Both the locking plate and the first teeth are designed to be flexible, allowing for localized elastic deformation when subjected to vibration or impact. This prevents stress concentration or structural fracture caused by excessive rigidity, improving the device's adaptability to complex operating conditions.

[0019] 2. The multiple wedge-shaped blocks at the lower end of the first gasket and the limiting groove at the upper end of the second gasket form an inclined locking structure. The second tooth piece on the outer side of the second gasket engages with the first tooth-shaped groove on the inner wall of the first notch of the mounting plate to form a second anti-rotation barrier. Even if the first tooth piece of the first anti-loosening structure fails to cooperate with the lock hole, the second tooth piece can still prevent the relative movement between the blade and the outer rotor housing of the motor assembly through rigid engagement. The second anti-loosening structure transfers the load of the first anti-loosening structure to the first notch of the mounting plate through the second gasket, thereby expanding the force contact area and avoiding stress concentration on a single component (such as the first gasket or bolt). This layered design significantly improves the fatigue resistance of the overall structure.

[0020] 3. The rubber sleeve is squeezed by the elastic tightening mechanism when the fixing bolt is installed, generating axial preload compensation. When the bolt becomes slightly loose due to vibration or temperature changes, the elastic recovery force of the rubber sleeve can automatically fill the gap, continuously pressing the second gasket and the third gasket to prevent the preload from decaying. The third tooth piece on the outside of the third gasket engages with the second tooth groove on the inner wall of the second notch to form a third anti-rotation barrier. Even if the first and second anti-loosening structures fail, the third tooth piece can still prevent relative rotation between the blade and the motor assembly through rigid engagement. The first anti-loosening structure (first tooth piece-lock hole), the second anti-loosening structure (wedge block-limiting groove) and the third anti-loosening structure (third tooth piece-second tooth groove) form a three-level anti-rotation protection, covering vibration loads of different directions and frequencies, and improving the system's fault tolerance. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The accompanying drawings, which constitute part of the present invention, are provided to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are provided to explain the present invention and do not constitute an undue limitation of the present invention. In the accompanying drawings:

[0022] Figure 1 This is a schematic diagram of a blade anti-loosening device for a drone according to an embodiment of the present invention;

[0023] Figure 2 This is a schematic diagram of the combined structure of the blade structure and the motor assembly according to an embodiment of the present invention;

[0024] Figure 3 This is a schematic diagram of the installation position of the locking mechanism according to an embodiment of the present invention;

[0025] Figure 4 This is a schematic diagram of the mounting plate structure of the blade structure according to an embodiment of the present invention;

[0026] Figure 5 This is a schematic diagram of the first tooth plate before installation according to an embodiment of the present invention;

[0027] Figure 6 This is a schematic diagram of the first tooth plate after installation according to an embodiment of the present invention;

[0028] Figure 7 This is a schematic diagram of the first anti-loosening structure according to an embodiment of the present invention;

[0029] Figure 8 This is a schematic structural diagram of the locking mechanism according to an embodiment of the present invention;

[0030] Figure 9 The wedge block structure according to the embodiment of the present invention;

[0031] Figure 10 This is a schematic diagram of a second anti-loosening structure according to an embodiment of the present invention;

[0032] Figure 11 This is a schematic diagram of a third anti-loosening structure according to an embodiment of the present invention;

[0033] Figure 12 This is a schematic structural diagram of the elastic tightening mechanism according to an embodiment of the present invention.

[0034] Description of reference numerals:

[0035] 100. UAV body; 200. Arm; 210. Motor assembly; 300. Locking mechanism; 310. First gasket; 311. First tooth plate; 312. Locking plate; 313. Buffer assembly; 314. Wedge block; 315. Locking hole; 320. Second gasket; 321. Second tooth plate; 322. Limiting groove; 330. Third gasket; 331. Third tooth plate; 332. Rubber sleeve; 333. Tightening block; 334. Return spring; 335. Guide rod; 400. Blade structure; 410. Mounting plate. DETAILED DESCRIPTION

[0036] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other.

[0037] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying 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 limiting the present invention. In addition, the terms "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, features defined as "first", "second", etc. may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0038] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed connections, detachable connections, or integral connections; mechanical connections or electrical connections; direct connections or indirect connections through an intermediate medium; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0039] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0040] A blade anti-loosening device for a UAV, such as Figure 1 As shown, it includes a drone body 100, four arms 200, four motor assemblies 210, four blade structures 400 and multiple locking mechanisms 300; the four arms 200 are evenly distributed on the drone body 100, the motor assembly 210 is arranged at the end of the arm 200 away from the drone body 100, and the outer rotor shell of one motor assembly 210 is connected to one blade structure 400 through multiple locking mechanisms 300; in this example, the outer rotor shell of one motor assembly 210 is connected to one blade structure 400 through four locking mechanisms 300.

[0041] The locking mechanism 300 includes a first anti-loosening structure, a fixing bolt, and a buffer assembly 313. The fixing bolt passes through the first anti-loosening structure and the mounting plate 410 of the blade structure 400 and is connected to the outer rotor housing of the motor assembly 210. The buffer assembly 313 is disposed on the lower end surface of the first anti-loosening structure.

[0042] The first anti-loosening structure includes a first gasket 310, a plurality of first teeth 311, and a plurality of locking plates 312. The plurality of first teeth 311 are evenly arranged around the outer end surface of the first gasket 310, and the plurality of locking plates 312 are evenly arranged around the upper end surface of the first gasket 310. The mounting plate 410 of the blade structure 400 is provided with one or more locking holes 315 that can engage with the first teeth 311. The locking plates 312 can limit and secure the countersunk head of the bolt or the outer surface of the nut. Both the locking plates 312 and the first teeth 311 are flexible. A buffer assembly 313 is provided on the lower end surface of the first gasket 310. The first gasket 310 is provided with a plurality of square holes for receiving the locking plates 312. The plurality of square holes are evenly arranged around the circumference of the first gasket 310. There are four locking plates 312 and four square holes. The buffer assembly 313 is an annular rubber ring. The multiple first teeth 311 evenly distributed on the outer circumference of the first gasket 310 cooperate with the lock hole 315 on the blade mounting plate 410 to form a direct mechanical interlocking structure. When the blade is vibrated, the engagement of the first teeth 311 with the lock hole 315 can effectively suppress the relative rotation between the blade and the motor assembly 210, preventing the bolt from loosening due to circumferential shear force. The flexible lock piece 312 above the first gasket 310 wraps around the countersunk head or the outer surface of the nut of the fixing bolt, and uses the elastic deformation of the lock piece 312 to generate a continuous clamping force. This elastic limit can not only offset the attenuation of the bolt preload caused by vibration, but also directly limit the rotational freedom of the bolt through physical obstruction. The annular rubber ring at the lower end of the first gasket 310 serves as a buffer component 313, which can absorb the energy generated by the high-frequency vibration of the motor during flight of the drone and reduce the vibration amplitude transmitted to the fixing bolt. By reducing the dynamic load of the bolt, loosening due to fatigue is delayed. The locking piece 312 and the first tooth piece 311 are both designed as bendable structures, allowing local elastic deformation when subjected to vibration or impact, avoiding stress concentration or structural fracture due to excessive rigidity, and improving the adaptability of the device to complex working conditions.

[0043] The locking mechanism 300 also includes a second anti-loosening structure. Multiple wedge-shaped blocks 314 are evenly arranged around the lower end surface of the first gasket 310. The second anti-loosening structure includes a second gasket 320 and multiple second teeth 321. The multiple second teeth 321 are evenly arranged around the outer end surface of the second gasket 320. The upper end surface of the second gasket 320 is provided with multiple retaining grooves 322 that engage with the wedge-shaped blocks 314. The mounting plate 410 of the blade structure 400 is provided with a first notch for accommodating the second gasket 320. The inner wall of the first notch engages with the second teeth 321 via first tooth-shaped grooves. The multiple wedge-shaped blocks 314 at the lower end of the first gasket 310 and the retaining grooves 322 at the upper end of the second gasket 320 form an inclined locking structure. The second teeth 321 on the outer side of the second gasket 320 engage with the first tooth-shaped grooves on the inner wall of the first notch of the mounting plate 410, forming a second anti-rotation barrier. Even if the first tooth piece 311 of the first anti-loosening structure fails to engage the lock hole 315, the second tooth piece 321 can still prevent relative movement between the blade and the outer rotor housing of the motor assembly 210 through rigid engagement. The second anti-loosening structure transfers the load of the first anti-loosening structure to the first notch of the mounting plate 410 via the second gasket 320, expanding the contact area and preventing stress concentration on a single component (such as the first gasket 310 or the bolt). This layered design significantly improves the fatigue resistance of the overall structure.

[0044] The locking mechanism 300 also includes a third anti-loosening structure, comprising a third gasket 330, a rubber sleeve 332, multiple elastic tensioning mechanisms, and multiple third teeth 331. A second notch is provided at the bottom of the first notch to accommodate the third gasket 330. The inner wall of the second notch engages with the third teeth 331 via a second toothed groove. Multiple third teeth 331 are evenly distributed around the outer end surface of the third gasket 330. The third gasket 330 has a circular hole to accommodate the rubber sleeve 332. Multiple elastic tensioning mechanisms are evenly distributed around the inner wall of the circular hole. One end of each elastic tensioning mechanism is connected to the inner wall of the circular hole, and the other end is located in the hole for mounting the fixing bolt. When the fixing bolt is installed, the elastic tensioning mechanism compresses the bottom of the rubber sleeve 332, causing the top of the rubber sleeve 332 to press against the lower end surface of the second gasket 320. When the fixing bolt is installed, the rubber sleeve 332 is compressed by the elastic tensioning mechanism, generating axial preload compensation. When the bolt becomes slightly loose due to vibration or temperature changes, the elastic recovery force of the rubber sleeve 332 can automatically fill the gap, continuously pressing the second gasket 320 and the third gasket 330 to prevent the preload force from fading. The third tooth piece 331 on the outside of the third gasket 330 engages with the second tooth groove on the inner wall of the second slot, forming a third anti-rotation barrier. Even if the first and second anti-loosening structures fail, the third tooth piece 331 can still prevent relative rotation between the blade and the motor assembly 210 through rigid engagement. The first anti-loosening structure (first tooth piece-locking hole 315), the second anti-loosening structure (wedge block 314-limiting groove 322) and the third anti-loosening structure (third tooth piece 331-second tooth groove) form a three-level anti-rotation protection, covering vibration loads of different directions and frequencies, and improving the system's fault tolerance.

[0045] The elastic tightening mechanism includes a guide rod 335, a return spring 334 and a tightening block 333. One end of the guide rod 335 is connected to the inner wall of the circular hole, and the outer end of the guide rod 335 slides with the tightening block 333. The return spring 334 is set on the guide rod 335. One end of the return spring 334 is against the tightening block 333, and the other end of the return spring 334 is against the bottom of the rubber sleeve 332. The end of the tightening block 333 is provided with an inclined surface, which is set in the channel for installing the fixing bolt.

[0046] How this example works

[0047] Attach the first washer 310 to the bolt / nut and engage the upward-facing locking plate 312 with the hexagonal face of the bolt or nut. This locks the first washer 310 with the screw in the desired rotational direction, allowing the washer to rotate with the screw. Similarly, when the first tooth 311 engages the locking hole 315, the first washer 310 secures the blade structure 400, securing the fixing bolt along with the first washer 310, preventing the screw from loosening. Place the blade structure 400 on the outer rotor housing of the drone motor, aligning the four fixing bolt holes with the motor's mounting holes. The holes surrounding the blade structure 400's screw holes, with the multiple locking holes 315 facing upward, are then threaded through the workpiece and tightened to maximum tightening.

[0048] Align the perimeter of the first washer 310 with the first tooth 311 of the locking hole 315 of the blade being secured, press it downward, and snap it into the hole. This secures the first washer 310 to the blade, thus completing the anti-loosening structure by securing the blade to the washer. The washer is then secured to the bolt and nut. Figure 6 shows the buckle locked state.

[0049] The relationship between the number of teeth on the first tooth piece 311 and the number of snap holes on the workpiece being installed will affect the screw's fixing resolution. For example, if the number of teeth on the gasket is 36 and the angle of each first tooth piece is 10 degrees, if the number of holes in the lock hole 315 is divisible by 36, then multiple first tooth pieces 311 can be locked at the same time, and the resolution of the bolt or nut tightening is 10 degrees. If the number of holes in the lock hole 315 is not divisible by 36, for example, the number of holes is 5, then only one first tooth piece 311 is locked in the tightening state, and the tightening resolution is 10 degrees / 5, which is equal to 2 degrees. In principle, the angle variation rate of the screw tightening is calculated as follows:

[0050] (1) The number of snap holes on the mounting plate 410 cannot be divided evenly by the number of teeth on the gasket, 360 degrees / number of teeth on the gasket / number of snap holes on the fixed part.

[0051] (2) The number of snap holes on the mounting plate 410 is divisible by the number of teeth on the gasket, 360 degrees / number of teeth on the gasket.

[0052] The angular resolution of the tightening of the fixing bolt also refers to the acceptable looseness angle of the product. For example, if the fixing angle resolution is 2 degrees, then when we tighten the screw to any position, there must be a lock hole 315 within ±1 degree of this position that can be aligned with the first tooth piece 311.

[0053] To remove the fixing bolts, use a socket tool to press down the first gasket 310. The lower surface of the socket will flatten the upturned locking piece 312 of the first gasket 310. The bolts and nuts can be removed normally. The first gasket 310 has a certain metal elasticity and can be restored to its original shape. The originally bent first tooth piece 311 can be restored and used again using tools such as pliers.

[0054] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A blade anti-loosening device for a UAV, characterized by: The drone comprises a drone body (100), four arms (200), four motor assemblies (210), four blade structures (400), and a plurality of locking mechanisms (300); The four arms (200) are evenly distributed on the drone body (100), the motor assembly (210) is arranged at an end of the arm (200) away from the drone body (100), and the outer rotor housing of one motor assembly (210) is connected to one blade structure (400) via a plurality of locking mechanisms (300); The locking mechanism (300) comprises a first anti-loosening structure, a fixing bolt and a buffer assembly (313); the fixing bolt passes through the first anti-loosening structure and the mounting plate (410) of the blade structure (400) and is connected to the outer rotor housing of the motor assembly (210); and the buffer assembly (313) is arranged on the lower end surface of the first anti-loosening structure; The first anti-loosening structure includes a first gasket (310), a plurality of first tooth pieces (311) and a plurality of locking pieces (312), wherein the plurality of tooth pieces are evenly arranged on the outer end surface of the first gasket (310), and the plurality of locking pieces (312) are evenly arranged on the upper end surface of the first gasket (310). The mounting plate (410) of the blade structure (400) is provided with one or more locking holes (315) capable of cooperating with the first tooth pieces (311). The locking piece (312) can limit and fix the countersunk head of the bolt or the outer surface of the nut. Both the locking piece (312) and the tooth piece can be bent, and the buffer component (313) is provided on the lower end surface of the first gasket (310). The locking mechanism (300) further includes a second anti-loosening structure, wherein a plurality of wedge-shaped blocks (314) are evenly arranged on the circumference of the lower end surface of the first gasket (310), and the second anti-loosening structure includes a second gasket (320) and a plurality of second tooth pieces (321), wherein the plurality of tooth pieces are evenly arranged on the circumference of the outer end surface of the second gasket (320), and the upper end surface of the second gasket (320) is provided with a plurality of limiting grooves (322) capable of cooperating with the wedge-shaped blocks (314), and a first notch capable of accommodating the second gasket (320) is provided on the mounting plate (410) of the blade structure (400), and the inner wall of the first notch is cooperating with the second tooth piece (321) through a first tooth-shaped groove.

2. The blade anti-loosening device for a UAV according to claim 1, characterized in that: The locking mechanism (300) further includes a third anti-loosening structure, which includes a third gasket (330), a rubber sleeve (332), a plurality of elastic tightening mechanisms and a plurality of third tooth pieces (331). The bottom of the first slot is provided with a second slot capable of accommodating the third gasket (330). The inner wall of the second slot cooperates with the third tooth piece (331) through a second tooth-shaped groove. The plurality of third tooth pieces (331) are uniformly arranged on the outer end face of the third gasket (330). The third gasket (330) is provided with a circular hole capable of accommodating the rubber sleeve (332). The plurality of elastic tightening mechanisms are uniformly arranged on the inner side of the circular hole. One end of the elastic tightening mechanism is connected to the inner wall of the circular hole, and the other end of the elastic tightening mechanism is arranged in the channel where the fixing bolt is installed. When the fixing bolt is installed, the elastic tightening mechanism squeezes the bottom of the rubber sleeve (332), so that the top of the rubber sleeve (332) presses the lower end face of the second gasket (320).

3. The blade anti-loosening device for a UAV according to claim 2, characterized in that: The elastic tightening mechanism comprises a guide rod (335), a return spring (334) and a tightening block (333); one end of the guide rod (335) is connected to the inner wall of the circular hole; the outer end of the guide rod (335) is slidably matched with the tightening block (333); the return spring (334) is arranged on the guide rod (335); one end of the return spring (334) abuts against the tightening block (333); the other end of the return spring (334) abuts against the bottom of the rubber sleeve (332); an end of the tightening block (333) is provided with an inclined surface, and the inclined surface is arranged in the channel where the fixing bolt is installed.

4. A blade anti-loosening device for a UAV according to any one of claims 1 to 3, characterized in that: The first gasket (310) is provided with a plurality of square holes for accommodating locking plates (312), and the plurality of square holes are evenly arranged on the circumference of the first gasket (310).

5. The blade anti-loosening device for a UAV according to claim 4, characterized in that: The number of the locking pieces (312) and the number of the square holes are both four.

6. The blade anti-loosening device for a UAV according to claim 3, characterized in that: The buffer component (313) is an annular rubber ring.

7. The blade anti-loosening device for a UAV according to claim 4, characterized in that: An outer rotor housing of a motor assembly (210) is connected to a blade structure (400) via four locking mechanisms (300).

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