A reed-based foldable propeller for drones

Abstract

The present invention relates to the technical field of foldable propellers and proposes a foldable propeller for unmanned aerial vehicles based on a reed structure, comprising a hub, blades, a main reed, and a secondary reed, wherein the secondary reed is connected to a transmission locking mechanism. The main reed is fixedly arranged on one side of the hub and abuts against the blades when the blades are folded to provide the elastic force required for the blades to unfold. The secondary reed and the transmission locking mechanism are fixedly arranged on the other side of the hub, and the transmission locking mechanism is connected to the secondary reed via a connecting rod. The transmission locking mechanism is used to control the movement of the secondary reed according to the signal of propeller rotation and lock the blades when the propeller is rotating. The propeller structure realizes a fast and reliable automatic deployment mechanism through the design of the reed, effectively improving the response speed of the propeller during startup. At the same time, it has higher structural stability during flight, significantly reducing the problem of flight deviation caused by blade shaking.

Description

Technical Field

[0001] The present invention relates to the technical field related to foldable propellers, and in particular to a reed-based foldable propeller for a drone. Background Art

[0002] The statements in this section merely provide background information related to the present invention and do not necessarily constitute prior art.

[0003] Folding drones, due to their portability and rapid deployment capabilities, are now widely used in a variety of scenarios, including emergency rescue, military reconnaissance, and field surveys. To accommodate canister launches and limited storage and transportation space, a folding propeller structure has become a key component. Compared to traditional, integrated, non-folding propellers, folding propellers significantly reduce the drone's size when not in use, improving storage efficiency and transport convenience. Consequently, they have become the mainstream configuration for folding drones.

[0004] Existing foldable propellers still have many technical defects in practical applications. On the one hand, the response speed of some folding propellers during the deployment process is slow, which makes it difficult to meet the rapid startup requirements of time-sensitive tasks. Especially in emergencies, delayed deployment can easily lead to the failure of UAV deployment, affecting the timely execution of the task. On the other hand, after the propeller is deployed, the blades are prone to shaking or jittering during high-speed rotation, which seriously affects the stability and accuracy of the flight, and then leads to blurred image acquisition, increased navigation deviation, and even safety hazards such as increased structural fatigue and increased vibration of the whole machine. Therefore, there is an urgent need for a folding propeller structure with rapid deployment capability and high stability to meet the high-performance operation requirements of UAVs in complex environments. Summary of the Invention

[0005] To address the slow deployment response and poor flight stability of existing foldable propellers, this invention proposes a foldable propeller for drones based on a reed structure. This propeller structure achieves a fast and reliable automatic deployment mechanism through the reed design, effectively improving the propeller's response speed during startup. It also offers greater structural stability during flight, significantly reducing flight deviations caused by blade oscillation. This invention is widely applicable to drone applications requiring fast response and high-precision flight, demonstrating significant technological breakthroughs and promotional value.

[0006] In order to achieve the above object, the present invention adopts the following technical solutions:

[0007] One or more embodiments provide a reed-based foldable propeller for a drone, comprising a hub, blades, a main reed, and a secondary reed, wherein the secondary reed is connected to a transmission locking mechanism;

[0008] A main spring is fixed on one side of the propeller hub. When the propeller blade is folded, the main spring rests against the propeller blade to provide the elastic force required for the propeller blade to unfold.

[0009] A secondary spring and a transmission locking mechanism are fixedly arranged on the other side of the hub. The transmission locking mechanism is connected to the secondary spring through a connecting rod. The transmission locking mechanism is used to control the movement of the secondary spring according to the signal of propeller rotation and lock the blades when the propeller is rotating.

[0010] Compared with the prior art, the present invention has the following beneficial effects:

[0011] The present invention achieves rapid deployment and stable locking of the propeller through the cooperation of a main spring and a secondary spring. A main spring is provided on the inner side of the blade. The main spring stores elastic force when the blade is folded, and quickly releases the elastic force after the drone leaves the launch tube, pushing the blade to deploy outward, thereby achieving rapid and automatic deployment of the propeller. The secondary spring is driven by a transmission locking mechanism and moves along a preset path. The connecting rod drives the secondary spring according to the rotation state of the blade, and when the propeller rotates, the secondary spring is pressed into the corresponding part of the blade to achieve locking. The above-mentioned structural cooperation enables rapid deployment and position locking after the propeller is deployed, effectively suppresses shaking during the rotation of the blade, improves flight stability, and enhances the structural reliability and mission execution accuracy of the drone during flight.

[0012] The advantages of the present invention and its additional aspects will be described in detail in the following specific embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] The accompanying drawings, which constitute a part of the present invention, are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their description are used to explain the present invention but do not constitute a limitation of the present invention.

[0014] Figure 1 1 is a schematic structural diagram of a reed-based foldable propeller for a UAV according to Example 1 of the present invention;

[0015] Figure 2 Schematic diagram of a reed-based foldable propeller of a UAV folded in a launch barrel according to Example 1 of the present invention;

[0016] Figure 3 This is a partial enlarged view of the end portion A of the reed-based foldable propeller of the UAV folded in the launch barrel according to Example 1 of the present invention;

[0017] Figure 4 Schematic diagram of the arrangement of the main spring of the propeller of Example 1 of the present invention;

[0018] Figure 5 1 is a schematic structural diagram of a bionic fairing according to embodiment 1 of the present invention;

[0019] Figure 6 1 is a schematic diagram of an intermediate state of the propeller of Example 1 of the present invention unfolded from a folded state;

[0020] Figure 7 1 is a schematic diagram of the propeller of Example 1 of the present invention after being deployed;

[0021] Among them, 1. hub, 2. blade clamp, 3. blade, 4. main reed, 5. screw, 6. nut, 7. bionic fairing, 8. controller, 9. micro motor gear set, 10. cam gear mechanism, 11. micro battery, 12. connecting rod, 13. connecting rod fixing seat, 14. shoulder, 15. spring, 16. secondary reed. DETAILED DESCRIPTION

[0022] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0023] It should be noted that the following detailed descriptions are exemplary and intended to provide further explanation of the present invention. Unless otherwise specified, all technical and scientific terms used herein have the same meaning as commonly understood by those skilled in the art to which the present invention belongs.

[0024] It should be noted that the terms used herein are only for the purpose of describing specific embodiments and are not intended to limit exemplary embodiments according to the present invention. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components and / or combinations thereof. It should be noted that, in the absence of conflict, the various embodiments of the present invention and the features in the embodiments can be combined with each other. The embodiments will be described in detail below with reference to the accompanying drawings.

[0025] Example 1

[0026] In the technical solutions disclosed in one or more embodiments, Figures 1 to 7 As shown, a reed-based foldable propeller for a UAV includes a hub 1, blades 3, a main reed 4 and a secondary reed 16, wherein the secondary reed 16 is connected to a transmission locking mechanism;

[0027] A main spring 4 is fixedly provided on one side of the hub 1. When the blade 3 is folded, the main spring 4 abuts against the blade 3 to provide the elastic force required for the blade 3 to unfold.

[0028] A secondary spring 16 and a transmission locking mechanism are fixedly arranged on the other side of the hub 1, and the transmission locking mechanism is connected to the secondary spring 16 through a connecting rod 12; the transmission locking mechanism is used to control the movement of the secondary spring 16 according to the signal of propeller rotation and lock the blade 3 when the propeller is rotating.

[0029] In this embodiment, the propeller is rapidly deployed and stably locked by the cooperation of the main spring 4 and the auxiliary spring 16. The main spring 4, disposed on the inner side of the blade 3, stores elastic force when the blade 3 is folded. After the drone is launched from the launch tube, the elastic force is rapidly released, pushing the blade 3 outward to deploy, achieving rapid and automatic deployment of the propeller. The auxiliary spring 16, driven by the transmission locking mechanism, moves along a preset path. The connecting rod 12 drives the auxiliary spring 16 according to the rotational state of the blade 3. As the propeller rotates, the auxiliary spring 16 is pressed into the corresponding portion of the blade 3 to achieve locking. This structural cooperation enables rapid deployment and position locking after the propeller is deployed, effectively suppresses shaking of the blade 3 during rotation, improves flight stability, and enhances the structural reliability and mission execution accuracy of the drone during flight.

[0030] In some embodiments, the blade 3 can be folded and fixed on the hub 1; the end of the hub 1 can be set to a U-shape, and the middle of the side wall of the U-shaped end forms an accommodating space for the fixed end of the blade 3. The U-shaped side wall and the fixed end of the blade 3 are respectively provided with a first through hole, and a screw 5 is provided through the first through hole. The screw 5 is fixed by a nut 6, and the fixed end of the blade 3 is fixed in the middle of the U-shaped side wall; the blade 3 can be folded with the screw 5 as the central axis;

[0031] The screw 5 can be a double-headed screw to improve assembly flexibility.

[0032] Another feasible structure is to provide through holes in the U-shaped side wall and the fixed end of the blade 3, and to fix the fixed end of the blade 3 in the U-shaped side wall by riveting.

[0033] In a feasible structure, the main spring 4 is configured as a straight sheet-shaped spring, and the end of the sheet-shaped structure is tilted to abut against the blade 3;

[0034] Another possible structure is Figure 4 As shown, the main spring 4 is an arched sheet structure, with both sides being provided with straight sheet structures, which are attached to the outer surface of the hub 1 to achieve the fixation of the main spring 4; the middle structure is bent outward relative to the two sides, forming an arched arc surface relative to the two sides, forming a naturally raised arc-shaped sheet structure to abut against the folded blade 3. The arc-shaped sheet structure has a preset curvature in the middle when no force is applied, and has good elastic deformation ability;

[0035] The arched, sheet-like main spring 4, with its two sides attached to the outer surface of the hub 1, provides elastic support when the blades 3 are folded. The raised center section of the main spring 4 forms an elastic deformation zone. When the blades 3 are folded and press against the main spring 4, this central, raised area first elastically deforms, storing sufficient elastic force. When the blades 3 are released, this deformed center section quickly returns to its original shape, releasing the elastic force that propels the blades 3 to unfold.

[0036] Achievable, such as Figure 4 As shown, the blade 3 and the main spring 4 can be fixed to the hub 1 by means of a screw 5 and a nut 6, so that the blade 3 can be folded and unfolded relative to the hub 1;

[0037] Optionally, the main reed 4 can be made of 50CrMo chromium alloy spring steel, which has good elastic modulus, high elastic limit and high fatigue resistance.

[0038] Optionally, the thickness of the main reed 4 is controlled in the range of 0.2-0.5 mm;

[0039] The main spring 4 of this embodiment is made of chromium alloy spring steel, which exhibits excellent mechanical properties. Its high elastic modulus provides a stable and continuous spring force during operation, ensuring reliable deployment of the blades 3. Its high elastic limit prevents permanent deformation of the spring under significant external forces, effectively extending its service life. Its excellent elastic stability maintains consistent elastic properties under varying temperature, humidity, and pressure conditions, ensuring reliable operation of the propeller under complex operating conditions. Furthermore, this material exhibits excellent fatigue resistance, allowing it to withstand frequent folding and unfolding cycles, reducing wear and tear and maintenance frequency, thereby improving overall efficiency and reliability.

[0040] Furthermore, a propeller clamp 2 is connected to the center point of the propeller hub 1 and is connected to the drone through the propeller clamp 2;

[0041] Optionally, a threaded hole is set at the center point of the hub 1, and the threaded end on the propeller clamp 2 is inserted into the threaded hole of the hub 1. The propeller clamp 2 is connected to the pushback motor shaft on the drone to ensure that it is concentric with the motor shaft.

[0042] The propeller clamp 2 is used to connect the propeller hub 1 and the drone. One end of the propeller clamp 2 is provided with a threaded end that can be screwed into the center hole of the propeller hub 1, and the other end is a hole structure that can be plugged into the push-back motor shaft, so that the propeller clamp 2 and the motor shaft are installed concentrically, thereby ensuring the rotational stability and coaxial accuracy between the propeller assembly and the motor output end.

[0043] In the above structure, during the UAV launch preparation stage, the propeller is folded and stored in the launch barrel together with the UAV. At this time, the side wall of the aircraft launch barrel effectively restricts the deployment of the blade 3, such as Figure 2 As shown, the propeller is a tail thrust propeller, which is located at the innermost end of the launch barrel. When the aircraft is launched, the propeller is ejected along the launch barrel along with the drone, and the launch direction is as follows: Figure 2 Indicated by the arrow. Figure 3 yes Figure 2A partial enlarged view of the middle end area A shows that when the drone is out of the barrel, the outer side of the blade 3 is no longer constrained by the launch barrel. The blade 3 is unfolded under the elastic force of the main spring 4. The blade 3 rotates around the screw 5. The deployment is completed when the trailing edge of the blade 3 contacts the auxiliary spring 16. At this time, the auxiliary spring 16 prevents the blade 3 from expanding too much. Figure 7 shown.

[0044] In some embodiments, the auxiliary spring 16 and the main spring 4 are arranged opposite to each other on the hub 1, and act on the opposite sides of the blade 3 respectively to realize the expansion action and the limit of the blade 3, such as Figure 1 As shown, the auxiliary reed 16 is arranged on the other side opposite to the main reed 4, and the auxiliary reed 16 is nested outside the hub 1 to form a unique auxiliary reed group structure.

[0045] Furthermore, the auxiliary spring 16 and the connecting rod 12 are connected in sequence with the transmission locking mechanism, which includes a control device, a drive motor, a micromotor gear set 9 and a cam gear mechanism 10 connected in sequence, and the control device includes a controller 8 and a speed sensor;

[0046] The controller 8 controls the operation of the drive motor according to the rotation speed of the propeller measured by the speed sensor, drives the cam gear mechanism 10 to move through the micromotor gear set 9, the cam gear mechanism 10 drives the connecting rod 12 to move, and drives the auxiliary spring 16 to move through the connecting rod 12; after the auxiliary spring 16 is extended, it rests on the blade 3 to fix the blade 3 and improve the stability of the propeller movement.

[0047] It is achievable that the surface of the blade 3 is provided with a first groove corresponding to the auxiliary spring 16, and the size of the first groove is adapted to the size of the moving end of the auxiliary spring 16, so that the auxiliary spring 16 can cooperate with the first groove after being extended to achieve locking of the position of the blade 3;

[0048] In the default position of the secondary spring 16, that is, when it is unlocked, the secondary spring 16 cooperates with the first groove to keep the blades 3 deployed at an angle of less than 130 degrees. After locking, the centerlines of the two blades 3 are parallel. Specifically, when the secondary spring 16 first contacts the first groove, the blades 3 are deployed at an angle of less than 130 degrees. As the secondary spring 16 extends, it slides within the first groove, gradually entering the groove and gradually reducing the blades' deployment angle until the secondary spring 16 contacts the bottom of the first groove. The blades 3 are locked at a flat angle.

[0049] Furthermore, the micromotor gear set 9 includes a group of small-module gears and a planetary reduction gear structure. The small-module gears are fixedly connected to the output shaft of the drive motor and are used to convert the high-speed rotation of the motor into medium-low speed and high-torque output; the planetary reduction mechanism is coaxially connected to the input end of the cam gear mechanism 10 to ensure the smoothness of the power output process and the accuracy of the gear meshing.

[0050] The micro-motor gear set 9 of this embodiment has a compact overall structure and is installed inside the hub 1 or in an adjacent structure thereof, thus having high spatial adaptability.

[0051] Furthermore, the cam gear mechanism 10 includes a driven gear and a cam fixed to the output end of the micromotor gear set 9, the driven gear is linked to the cam, and the outer periphery of the cam is provided with an eccentric profile for converting the rotational motion into periodic axial movement;

[0052] Optionally, the cam of the cam gear mechanism 10 may be connected to the connecting rod 12 via a shaft pin. As the cam rotates, the connecting rod 12 is driven to perform linear reciprocating motion along a preset direction, thereby driving the secondary spring 16 to extend or retract.

[0053] Optionally, the auxiliary spring 16 can be made of a carbon fiber corrugated spring; the carbon fiber material has the properties of lightness, high strength, and corrosion resistance. The corrugated spring made from it can not only significantly enhance the strength of the overall structure, but also provide additional locking force under specific working conditions.

[0054] The transmission locking mechanism of this embodiment features a simple structure, fast response, excellent mechanical stability, and repeatable motion accuracy, enabling the secondary spring 16 to effectively lock the position of the blade 3 even at high rotational speeds. By monitoring the rotational speed of the blade 3 in real time, once a set threshold is reached, the transmission locking mechanism rapidly responds, driving the secondary spring assembly into motion, forming a reliable redundant protection mechanism. This further improves the stability of the blade 3 during flight, effectively preventing accidental propeller folding, reducing vibration and noise, and reducing vibration and impact, thereby reducing component wear, ensuring stable power output, and enhancing the safety of the UAV's flight.

[0055] As a further technical solution, the controller 8 is also connected to a plurality of sensor components, which include but are not limited to acceleration sensors, temperature sensors, etc., and can collect a variety of data of the propeller in different working conditions in real time through a multimodal perception network formed by the sensors.

[0056] The drone's master controller, known as the flight control system, integrates and analyzes this sensor data through advanced sensor fusion algorithms, enabling comprehensive monitoring and precise control of propeller status. When the accelerometer detects abnormal vibration, combined with data from the speed sensor, the flight control system can quickly determine whether the problem is due to sudden airflow changes, loose components, or excessive temperatures, and make timely adjustments.

[0057] According to a further technical solution, a connecting rod fixing seat 13 is fixedly provided on the propeller clamp 2, and a second through hole is provided on the connecting rod fixing seat 13. The inner wall of the second through hole matches the outer wall of the connecting rod 12, so that the connecting rod 12 can slide back and forth through the second through hole.

[0058] In this embodiment, the connecting rod fixing base 13 is provided to guide and limit the motion path of the connecting rod 12, thereby improving the force transmission accuracy and stability of the transmission locking mechanism when driving the auxiliary spring 16. As an intermediate support structure, the connecting rod fixing base 13 effectively prevents the connecting rod 12 from shaking, deflecting, or being thrown off during force or rotation. This is particularly important during the flight of a UAV subject to severe vibration or high speed conditions. It ensures stable linear motion of the connecting rod 12 along the set direction, improves the consistency and reliability of the movement of the auxiliary spring 16, and further enhances the operational stability and anti-interference capabilities of the locking mechanism.

[0059] In some embodiments, a shaft shoulder 14 is fixedly provided on the connecting rod 12 , and a spring 15 is nested on the connecting rod 12 between the shaft shoulder 14 and the connecting rod fixing seat 13 .

[0060] Specifically, the shoulder 14 is a raised structure provided on the connecting rod 12;

[0061] In this embodiment, a secondary spring 16 is nested outside the hub 1 and fixedly connected to the connecting rod 12, which abuts the compound cam gear mechanism 10. To prevent the connecting rod 12 and secondary spring 16 from being detached due to centrifugal force, a spring 15 is nested outside the connecting rod 12, between the connecting rod mounting base 13 and the shaft shoulder 14. Spring 15 regulates the movement of secondary spring 16. When the propeller is deployed, to prevent the blades 3 from expanding too far, thereby affecting the propeller's rotation due to centrifugal force after the motor is started, secondary spring 16 abuts against the blades 3, limiting the propeller's expansion angle and ensuring that the expansion angle of the blades 3 remains within 130 degrees.

[0062] The deployment angle of the blade 3 in this embodiment is defined as the angle of transformation after deployment from the folded state, that is, the angle between the center line of the blade 3 in the folded state and the center line of the blade 3 after deployment;

[0063] In a further technical solution, the controller 8 controls the operation of the drive motor according to the rotation speed of the propeller measured by the speed sensor. When the rotation speed exceeds a set value, the transmission locking mechanism triggers the locking mechanism according to the propeller lock control logic pre-set by the flight control system on the UAV;

[0064] Specifically, the speed setting value can be set to 1000 rpm. When the speed exceeds the setting value (1000 rpm), the locking mechanism is triggered;

[0065] Optionally, a microbattery 11 may be provided to provide power to the transmission locking mechanism;

[0066] A further technical solution is to further improve the working efficiency and operating stability of the blade 3. A bionic fairing 7 is provided at the center point of the upper surface of the hub 1. The bionic fairing 7 is an axisymmetric hollow shell that tapers upward. The shell surface of the bionic fairing 7 has multiple groups of shark skin texture grooves evenly distributed along the circumferential direction and the axial direction. The shark skin texture grooves are arranged from bottom to top with a set spacing as a gradient, so as to form a micro-texture characteristic structure of the shark skin surface.

[0067] On the shell surface of the bionic fairing 7, shark skin texture grooves are arranged layer by layer along the axial direction, and the set spacing between layers can be set to 8mm to 15mm. Preferably, the set spacing is set to 10mm; each layer of shark skin texture grooves is evenly distributed along the circumference.

[0068] Furthermore, the surface of the bionic fairing 7 is provided with multi-layer shark skin texture grooves, the depth of which varies between 0.1 mm and 0.3 mm, and the depth decreases from bottom to top along the surface of the bionic fairing 7 in a gradient arrangement, so as to optimize the flow characteristics of different airflow areas;

[0069] Specifically, the bionic fairing 7 is a hollow conical shell structure, and a slot is provided corresponding to the setting position of the connecting rod 12, and the slot is used to provide space for the reciprocating motion of the connecting rod 12; the interior of the hollow conical shell is used to accommodate components of the transmission locking mechanism, providing reliable protection for the control device of the transmission locking mechanism, the micromotor gear set 9, the cam gear mechanism 10 and the microbattery 11; it effectively blocks the intrusion of dust and water stains, and ensures that each component operates in a stable environment.

[0070] In this embodiment, the bionic fairing 7 is installed on the upper part of the hub 1 and can be fixed in position by connecting with the propeller clamp 2; the shell surface of the bionic fairing 7 has multiple fine grooves evenly distributed in the circumferential direction and the axial direction. These grooves are arranged from bottom to top according to a gradient of 10mm spacing, simulating the micro-texture characteristics of the shark skin surface, and have a good aerodynamic optimization effect.

[0071] The special shark skin texture provided on the fairing surface in this embodiment has the characteristics of reducing water flow resistance and improving swimming efficiency, which can effectively solve aerodynamic problems.

[0072] On the one hand, the shark skin texture grooves on the surface of the fairing are distributed from bottom to top according to the gradient of the set spacing, which can be highly adapted to the complex and changeable airflow characteristics at different flight speeds: in the medium and low speed flight stages, the grooves can reduce the turbulence of the airflow attached to the surface of the fairing and improve the airflow slip effect; during high-speed flight, the grooves can interrupt the vortex structure appearing in the boundary layer, reduce airflow separation, and improve the overall thrust / thrust output stability of the propeller; thereby reducing the pressure difference and interference between the fairing and the airflow, and significantly reducing the vibration and noise caused by uneven flow.

[0073] This design significantly reduces air resistance, ensuring blades 3 maintain good stability during high-speed rotation, significantly improving propeller efficiency and comprehensively optimizing the drone's flight performance. It also significantly reduces vibration and noise generated by the propeller during operation. By meticulously optimizing the airflow, the bionic fairing 7 reduces the irregular impact of airflow on blades 3, achieving highly stable propeller operation. This smooth operation not only improves flight comfort and controllability but also effectively reduces wear on propeller components, significantly extending the propeller's service life and reducing maintenance costs and replacement frequency.

[0074] On the other hand, the fairing improves the airflow environment around the propeller. With the same power input, a propeller equipped with a fairing can generate greater pull or thrust: the fairing reduces airflow interference and drag loss through aerodynamic optimization, while the shark skin-like grooves on its surface enhance boundary layer control, making the airflow more stable and concentrated on the blades 3, thereby improving overall propulsion efficiency. In drone applications, this means that the propeller can generate greater lift, enabling the drone to carry heavier payloads or fly longer distances while carrying the same payload. This performance improvement not only expands the application range of drones but also improves their mission execution capabilities and economic benefits.

[0075] The working method of the above-mentioned reed-based foldable propeller for drones is described in detail as follows:

[0076] When the propeller is folded, the outer side of the blade 3 is kept in the folded state by the force of the launch tube wall. At the same time, the main spring 4 set on the inner side of the blade 3 presses against the blade 3, and the main spring 4 stores elastic force. Figure 1 Status;

[0077] After the drone leaves the launch tube, the elastic force is quickly released. Figure 2 The arrow direction is the direction of the drone exiting the tube. When the drone is on the inner side of the folded blade 3, the main spring 4 pushes the blade 3 outward to realize the rapid and automatic deployment of the propeller. At the same time, the drone body exits the tube first and maintains an upward angle. Under the action of wind resistance and gravity, as shown in FIG. Figure 6 As shown, relative to Figure 1 The folded state, Figure 6 The middle blade 3 is in a reverse folded state;

[0078] The propeller starts to rotate under the action of the motor shaft of the drone through the propeller clamp 2. The trajectory of the drone body after it comes out of the tube is a parabola. After passing the highest point of the parabola, the drone body is adjusted to the blade 3 on the top and the drone body on the bottom under the action of gravity. The propeller blade 3 basically rotates at a horizontal angle. When it reaches a certain rotation speed, it relies on the power provided by the microbattery 11 to drive the small gear in the micromotor gear set 9 through the drive motor to start rotating. Under the efficient drive of the small gear, the cam gear mechanism 10 rotates smoothly, and the cam exerts its mechanical effect to push the connecting rod 12 open. Driven by the connecting rod 12, the secondary spring 16 extends outward along the predetermined motion trajectory and finally gets stuck in the first groove on the surface of the blade 3. Through this series of precise mechanical actions, the blade 3 is reliably locked. Figure 7 In the locked position shown, the centerlines of the two blades 3 are parallel. This locking method effectively resists interference from complex factors such as vibration and airflow during flight, fundamentally preventing the possibility of accidental folding of the blades 3. It also reduces unnecessary shaking of the blades 3 during rotation, significantly lowering vibration and noise levels, and further improving the operating efficiency and stability of the blades 3.

[0079] Example 2

[0080] Based on Example 1, this embodiment provides a drone, which uses the reed-based foldable drone propeller described in Example 1.

[0081] The foregoing description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention are intended to be within the scope of protection of the present invention.

Claims

1. A reed-based foldable propeller for a drone, characterized by: It includes a propeller hub, propeller blades, a main reed and a secondary reed, wherein the secondary reed is connected with a transmission locking mechanism; A main spring is fixed on one side of the propeller hub. When the propeller blade is folded, the main spring rests against the propeller blade to provide the elastic force required for the propeller blade to unfold. A secondary spring and a transmission locking mechanism are fixedly arranged on the other side of the propeller hub. The transmission locking mechanism is connected to the secondary spring through a connecting rod. The transmission locking mechanism is used to control the movement of the secondary spring according to the propeller rotation signal and lock the blades when the propeller is rotating. The transmission locking mechanism includes a control device, a drive motor, a micromotor gear set, and a cam gear mechanism connected in sequence. The control device includes a controller and a speed sensor. The controller controls the drive motor to operate according to the rotation speed of the propeller measured by the speed sensor, thereby driving the cam gear mechanism to operate through the micromotor gear set, which in turn drives the connecting rod to operate, thereby driving the auxiliary spring to move through the connecting rod. After the auxiliary spring is extended, it abuts against the blade to fix the blade. A bionic fairing is provided at the center point of the upper surface of the hub. On the shell surface of the bionic fairing, multiple groups of shark skin texture grooves are evenly distributed along the circumferential direction and the axial direction; the shark skin texture grooves are arranged layer by layer along the axial direction, and the depth of the multi-layer shark skin texture grooves decreases from bottom to top along the surface of the bionic fairing in a gradient manner.

2. The reed-based foldable propeller for a drone as claimed in claim 1, characterized in that: The main spring is an arched sheet structure, with flat sheet structures on both sides, attached to the outer surface of the hub. The middle structure is bent outward relative to the two sides, forming an arched arc surface relative to the two sides to rest on the folded blade.

3. The reed-based foldable propeller for a drone as claimed in claim 1, characterized in that: The surface of the blade is provided with a first groove corresponding to the auxiliary spring, and the size of the first groove is adapted to the size of the moving end of the auxiliary spring.

4. The reed-based foldable propeller for a drone as claimed in claim 1, characterized in that: A connecting rod fixing seat is also fixedly provided on the paddle clamp, and a second through hole is provided on the connecting rod fixing seat. The inner wall of the second through hole matches the outer wall of the connecting rod, so that the connecting rod passes through the second through hole and slides back and forth.

5. The reed-based foldable propeller for a drone as claimed in claim 4, characterized in that: A shaft shoulder is also fixedly provided on the connecting rod, and a spring is nested on the connecting rod between the shaft shoulder and the connecting rod fixing seat.

6. The reed-based foldable propeller for a drone as claimed in claim 1, characterized in that: The bionic fairing is an axisymmetric hollow shell that tapers upward.

7. The reed-based foldable propeller for a drone as claimed in claim 6, characterized in that: The shark skin texture grooves are arranged from bottom to top with a set spacing as a changing gradient to form the micro-texture characteristic structure of the shark skin surface.

8. The reed-based foldable propeller for a drone as claimed in claim 6, characterized in that: The depth of the shark skin texture grooves varies between 0.1mm and 0.3mm, and is arranged in a gradient pattern from bottom to top along the surface of the bionic fairing.

9. The reed-based foldable propeller for a drone as claimed in claim 6, characterized in that: The bionic fairing is a hollow conical shell structure with slots provided corresponding to the setting positions of the connecting rods. The slots are used to provide space for the reciprocating motion of the connecting rods. The interior of the hollow conical shell is used to accommodate the control device of the transmission locking mechanism, the micromotor gear set, the cam gear mechanism and the microbattery.

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