Folding paddle for preventing unmanned aerial vehicle from falling and being damaged

Abstract

The utility model discloses a folding paddle for preventing an unmanned aerial vehicle from falling and being damaged, which comprises a vehicle arm, a power pedestal and a wing panel, the power pedestal is arranged at the outer end part of the vehicle arm, and the wing panel is arranged at the top end of the power pedestal; the power pedestal comprises a guide bushing, an elastic core and a reset piece, the elastic core is connected with the inner bottom wall of the guide bushing through the reset piece, and vertical through grooves are formed in the two sides of the top end of the elastic core; each wing panel is composed of a blade and a convergent rod, and the inner end of each convergent rod is hinged to the interior of the corresponding vertical through groove. When the unmanned aerial vehicle detects the falling risk, the fins are gradually folded, the length and the area of the fins are reduced after the fins are completely folded, the damage risk is reduced, the folded fins become more compact, the strength of the fins is relatively increased, the damage probability of the fins during collision is further reduced, the blades are folded in a folding mode, the structure is stable, the failure rate is low, and the unmanned aerial vehicle is convenient to use. Compared with a traditional folding driver, the design of elastic core retraction and wing panel folding has certain advantages in weight and cost.

Description

Technical Field

[0001] The utility model relates to the technical field of UAV safety protection, in particular to a folding blade for preventing UAV from falling and being damaged. Background Art

[0002] During the flight of a UAV, it may fall due to reasons such as operation errors, technical failures or external interferences. An accidental fall will not only cause damage to the equipment, but also pose potential safety hazards to personnel and property.

[0003] At present, in order to protect the blades of a UAV from being damaged during a fall, a common technique is to adopt a parachute descent system. When the UAV detects a fall risk, the system will automatically release the parachute, and the deceleration effect of the parachute is used to reduce the falling speed of the UAV, thereby reducing the impact force and protecting the fuselage and blades from serious damage. However, although the parachute descent method reduces the damage of the UAV during the fall to a certain extent, there is still a risk of blade damage, and the deployment of the parachute may be affected by environmental factors such as wind speed and wind direction, and there is a risk of failure to deploy successfully.

[0004] To solve the technical problems existing in the parachute descent method, those skilled in the art have proposed a folding design for the blades, that is, through a foldable joint and a folding driver, the blades can be automatically folded when the UAV falls, which can greatly reduce the contact area between the blades and the ground or other obstacles. However, the structure of the current automatically folding blades is relatively complex. Although the design tries to be lightweight as much as possible, the addition of the folding mechanism will still affect the overall weight and volume of the UAV. Summary of the Invention

[0005] To solve the above technical problems, the utility model provides a folding blade for preventing a UAV from falling and being damaged. To have a basic understanding of some aspects of the disclosed embodiments, a simple summary is given below. This summary part is not a general review, nor is it intended to identify key / important constituent elements or delineate the protection scope of these embodiments. Its sole purpose is to present some concepts in a simple form as a preface to the subsequent detailed description.

[0006] The utility model adopts the following technical solutions:

[0007] Provide a folding blade for preventing a UAV from falling and being damaged, including: an arm, a power pedestal, and a wing. The power pedestal is arranged at the outer end of the arm, and the wing is arranged at the top of the power pedestal; the power pedestal includes: a guide bushing, a core, and a reset member. The core is arranged in the guide bushing and is connected to the inner bottom wall of the guide bushing through the reset member. Vertical through grooves are opened on both sides of the top end of the core; the wing is composed of a blade and a converging rod. The blade is connected to the outer end of the converging rod, and the inner end of the converging rod is hinged in the vertical through groove.

[0008] Further, the power pedestal further includes: a locking component, which is arranged on the side wall of the guiding bushing; the locking component includes: a locking block, an electromagnet main body, and a moving iron core; the locking block is located below the bullet core, and a sliding piece for pressing against the lower surface of the bullet core is arranged on the top of the locking block, and the moving iron core is arranged on the locking block.

[0009] Further, the locking component further includes: a guiding housing and an elastic element; a through hole is formed in the side wall of the guiding bushing, the opening of the guiding housing is arranged in the through hole, the locking block is arranged in the guiding housing and is connected to the inner bottom wall of the guiding housing through the elastic element, and the electromagnet main body is arranged in the guiding housing.

[0010] Further, the power pedestal further includes: a rotating support platform, a motor mounting seat, and a driving motor; the motor mounting seat is arranged at the outer end of the machine arm, the driving motor is arranged on the motor mounting seat, the rotating support platform is connected to the power output end of the driving motor; the guiding bushing is arranged on the rotating support platform.

[0011] Further, an arc-shaped transition surface is formed at the top end of the guiding bushing.

[0012] Further, the machine arm includes: two plate pieces that are symmetrically arranged and spaced apart by a certain distance; one ends of the two plate pieces are connected to the drone fuselage, and the other ends are connected by an arc-shaped plate, and the motor mounting seat is connected to the plate pieces and the arc-shaped plate.

[0013] Further, the distance between the two plate pieces gradually decreases from the end connected to the drone fuselage to the end connected to the arc-shaped plate, and the top edge of the plate piece gradually slopes downward.

[0014] Further, weight-reducing holes are formed in the plate pieces.

[0015] The beneficial effects brought by the present utility model: When the drone detects a risk of falling, the resetting member pulls the bullet core to retract it into the guiding bushing. During this process, the wing pieces gradually close, and the bottom end part is embedded in the guiding bushing. First, the length and area of the wing pieces are reduced after being completely closed, reducing the risk of damage. Second, the closed wing pieces become more compact, and their strength is relatively increased, thereby further reducing the damage probability of the wing pieces during impact. In addition, the folding of the propeller blades is achieved through the closing method, which not only has a stable structure and low failure rate, but also has certain advantages in terms of weight and cost compared with traditional folding drives in the design of the retraction of the bullet core and the closing of the wing pieces. Description of the Drawings

[0016] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0017] Figure 1 It is a schematic structural diagram when the wing of the present invention is unfolded;

[0018] Figure 2 It is a schematic structural diagram when the wing of the present invention is retracted;

[0019] Figure 3 It is a schematic structural diagram of a folding blade for preventing a drone from falling and being damaged according to the present invention;

[0020] Figure 4 It is a schematic internal structure diagram of the power pedestal of the present invention. Detailed implementation manners

[0021] The following will describe the embodiments of the present invention in detail with reference to the drawings. It should be clear that the described embodiments are only some embodiments of the present invention, rather than all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts belong to the scope of protection of the present invention.

[0022] As Figures 1-4 shown, in some illustrative embodiments, a folding blade for preventing a drone from falling and being damaged is provided, including: an arm 1, a power pedestal 2, and a wing 3.

[0023] The arm 1 is used to connect the fuselage and the flight control surface. In this embodiment, the flight control surface refers to the wing 3. The drone fuselage is equipped with four arms 1, which are respectively located in the four directions of right front, right rear, left rear, and right rear, helping to balance the center of gravity of the drone and improve its stability in the air. The power pedestal 2 is arranged at the outer end of the arm 1, and the wing 3 is arranged at the top of the power pedestal 2. The power pedestal 2 is used to realize the rotation and retraction of the wing 3, and 2 - 4 wings 3 can be equipped on each power pedestal 2.

[0024] The power pedestal 2 includes: a guide bushing 201, a cartridge 202, a reset member 203, a locking assembly 4, a rotating support platform 204, a motor mounting base 205, and a driving motor.

[0025] The motor mount 205 is arranged at the outer end of the arm 1. Its main body is a hollow columnar structure with an open upper end. The driving motor is arranged inside the motor mount 205, and the power output end of the driving motor extends out from the open upper end of the motor mount 205 and is connected to the rotary support platform 204, so as to realize that the driving motor can drive the rotary support platform 204 to rotate. At the same time, in order to ensure the rotation stability, a bearing is equipped for the rotary support platform 204. The bearing can reduce the friction during rotation, reduce the energy consumption, and ensure the smoothness and accuracy of the rotational movement. The above structural design provides good rigidity, helps to maintain stability during high-speed flight or under bad weather conditions, is convenient for the installation and disassembly of the motor, and can also reduce the overall weight.

[0026] The guide bushing 201 is arranged on the rotary support platform 204 to guide the movement of the bullet core 202, and the inner wall of the guide bushing 201 has good sliding performance to reduce friction and wear. At the same time, a dust-proof and waterproof seal is designed to prevent the influence of the external environment on the internal components. The locking component 4 is arranged on the side wall of the guide bushing 201. The locking component 4 is used to limit the position of the bullet core 202, that is, when the wing 3 is deployed, the locking component 4 limits the position of the bullet core 202 so that it cannot move into the guide bushing 201, that is, the top part of the bullet core 202 will not retract into the guide bushing 201, to ensure that the guide bushing 201 will not affect the deployment and rotation of the wing 3. When the wing 3 needs to be folded, the locking component 4 acts to release the limit on the bullet core 202 and allows the wing 3 to be folded.

[0027] The bullet core 202 is arranged inside the guide bushing 201 and is connected to the inner bottom wall of the guide bushing 201 through a reset member 203. Vertical through grooves 206 are opened on both sides of the top of the bullet core 202. The wing 3 is composed of a blade 301 and a converging rod 302. The blade 301 is used to generate lift and control the flight direction of the drone. The blade 301 is connected to the outer end of the converging rod 302, and the inner end of the converging rod 302 is hinged inside the vertical through groove 206, so that the blade 301 can rotate around the hinge point to realize folding. When it is necessary to fly again, the bullet core 202 is pulled out of the guide bushing 201 and the limiting function of the locking component 4 is restored.

[0028] When the drone detects a falling risk, the locking component 4 receives a corresponding control signal and releases the limit on the bullet core 202. At this time, the reset member 203 drives the bullet core 202 to move in the direction of the inside of the guide bushing 201. When the converging rod 302 touches the guide bushing 201, if the bullet core 202 continues to move inward, the guide bushing 201 will generate a thrust on the converging rod 302, causing the blade 301 to flip upward until each wing 3 is folded and the bottom part is embedded inside the guide bushing 201. Preferably, an arc transition surface 2011 is opened at the top of the guide bushing 201 to reduce the wear of the converging rod 302.

[0029] This application has the following advantages:

[0030] First, the length and area of ​​the wing 3 are reduced when it is fully folded, which can effectively reduce the risk of damage compared to the fully unfolded state;

[0031] Second, the wing 3 becomes more compact after being brought together, and its strength is relatively increased, thereby further reducing the probability of damage to the wing 3 during collision;

[0032] Third, the blades can be folded by folding, making the structure more stable and reducing the failure rate.

[0033] Fourth, compared with the traditional folding drive, the design of core retraction and wing folding has certain advantages in weight and cost, and is easier to reset, which means it is more convenient to operate.

[0034] The locking assembly 4 includes: a locking block 401 , an electromagnet body 402 , a moving iron core 403 , a guide housing 404 and an elastic element 405 .

[0035] A through hole is provided on the side wall of the guide bushing 201, and the opening of the guide housing 404 is arranged in the through hole, so that the guide housing 404 is connected to the inside of the guide bushing 201. The locking block 401 is arranged in the guide housing 404 and connected to the inner bottom wall of the guide housing 404 through the elastic element 405, and the locking block 401 can move along the guide housing 404. The electromagnet body 402 is arranged in the guide housing 404 and is used in conjunction with the moving iron core 403, that is, when the electromagnet body 402 is energized, a magnetic force is generated to attract the moving iron core 403. The locking block 401 is located below the elastic core 202 and a sliding piece 406 for pressing with the lower surface of the elastic core 202 is arranged on the top of the locking block 401, and the moving iron core 403 is arranged on the locking block 401.

[0036] When the drone detects a risk of falling, the locking assembly 4 receives a corresponding control signal, the electromagnet body 402 is energized to generate magnetic force, the moving iron core 403 is attracted, and moves toward the side of the electromagnet body 402, driving the locking block 401 to retract into the guide housing 404 to release the limit on the core 202. When it is necessary to fly again, the core 202 is pulled out of the guide bushing 201, the locking assembly 4 receives a corresponding control signal, the electromagnet body 402 is de-energized, and the elastic element 405 pushes the locking block 401 out to restore the limit function.

[0037] When the drone detects a risk of falling, the locking component 4 can quickly receive the control signal and respond. This process is almost instantaneous, enabling the fins to close quickly and reducing the damage during a fall. When it is necessary to fly again, simply pull the cartridge 202 out of the guiding bushing 201 and send a signal to the locking component 4. The process is simple and fast, facilitating operation and enabling the drone to quickly resume the flight state. In summary, the design of the locking component 4 provides the drone with an efficient, reliable and easy-to-operate safety protection mechanism. It can not only respond quickly in case of emergency to protect the drone, but also ensure that the drone can resume the flight state in a short time, thereby improving the overall performance and practicality of the drone.

[0038] The arm 1 includes: an arc plate 102 and two plate pieces 101 that are symmetrically arranged and spaced apart by a certain distance. One end of the two plate pieces 101 is connected to the drone fuselage, and the other end is connected by the arc plate 102. The arc plate 102 and the outer end portions of the two plate pieces 101 form a semi-circular enclosure structure. The plate piece 101 is responsible for connecting the drone fuselage and the arc plate 102, while the arc plate 102 connects the outer end portions of the two plate pieces 101 to form a semi-circular frame. The semi-circular frame not only enhances the structural strength of the arm, but also provides a protective space for the installation of the power pedestal 2, that is, the motor mount 205 is connected to the plate piece 101 and the arc plate 102.

[0039] The structural design of the two symmetrical plate pieces 101 and the arc plate 102 provides good support and stability, enhancing the overall strength of the arm 1 and enabling the drone to withstand greater loads and impacts during flight. The semi-circular enclosure structure protects the motor mount 205, reducing the damage to the motor caused by collisions or drops during flight or landing. The design of the arc plate 102 provides sufficient space for motor installation without adding excessive weight and volume, helping the drone to remain lightweight and compact.

[0040] From the end connected to the drone fuselage to the end connected to the arc plate 102, the distance between the two plate pieces 101 gradually decreases, and the top edge of the plate piece 101 gradually slopes downward, making the overall shape of the arm 1 gradually shrink. This helps to reduce the aerodynamic interference during the rotation of the fin 3, enabling the fin to rotate more freely and thus improving flight efficiency and maneuverability. Further, weight-reducing holes 103 are provided on the plate piece 101, and the weight reduction can improve the load capacity and endurance of the drone.

[0041] The reset member 203 and the elastic element 405 can be selected as springs.

[0042] The above are only specific embodiments of the present utility model, but the protection scope of the present utility model is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed by the present utility model should be covered within the protection scope of the present utility model. Therefore, the protection scope of the present utility model shall be subject to the protection scope of the claims.

Claims

1. A foldable propeller blade to prevent a drone from falling and being damaged, characterized in that: include: An arm, a power base and a wing, wherein the power base is arranged at the outer end of the arm, and the wing is arranged at the top of the power base; the power base comprises: a guide bushing, an elastic core and a reset member, the elastic core is arranged in the guide bushing and connected to the inner bottom wall of the guide bushing through the reset member, and vertical through grooves are provided on both sides of the top of the elastic core; the wing is composed of a blade and a focusing rod, the blade is connected to the outer end of the focusing rod, and the inner end of the focusing rod is hinged in the vertical through groove.

2. The foldable propeller blade for preventing a drone from falling and being damaged according to claim 1, characterized in that: The power base also includes: a locking assembly, which is arranged on the side wall of the guide bushing; the locking assembly includes: a locking block, an electromagnet body and a moving iron core; the locking block is located below the elastic core and a sliding piece for pressing with the lower surface of the elastic core is arranged on the top of the locking block, and the moving iron core is arranged on the locking block.

3. The foldable propeller blade for preventing a drone from falling and being damaged according to claim 2, characterized in that: The locking assembly also includes: a guide housing and an elastic element; a through hole is provided in the side wall of the guide bushing, the opening of the guide housing is arranged in the through hole, the locking block is arranged in the guide housing and connected to the inner bottom wall of the guide housing through the elastic element, and the electromagnet body is arranged in the guide housing.

4. The foldable propeller blade for preventing a drone from falling and being damaged according to claim 3, characterized in that: The power base also includes: a rotating support platform, a motor mounting seat and a driving motor; the motor mounting seat is arranged at the outer end of the machine arm, the driving motor is arranged on the motor mounting seat, the rotating support platform is connected to the power output end of the driving motor; the guide bushing is arranged on the rotating support platform.

5. The foldable propeller blade for preventing a drone from falling and being damaged according to claim 4, characterized in that: The top end of the guide bushing is provided with an arc-shaped transition surface.

6. The foldable propeller blade for preventing a drone from falling and being damaged according to claim 5, characterized in that: The machine arm comprises: two plates which are symmetrically arranged and spaced a certain distance apart; one end of the two plates is connected to the drone fuselage, and the other end is connected through an arc plate; the motor mounting seat is connected to the plates and the arc plate.

7. The foldable propeller blade for preventing a drone from falling and being damaged according to claim 6, characterized in that: The distance between the two plates gradually decreases from one end connected to the drone fuselage to the other end connected to the arc-shaped plate, and the top edge of the plate gradually tilts downward.

8. The foldable propeller blade for preventing a drone from falling and being damaged according to claim 7, characterized in that: The plate is provided with weight-reducing holes.

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