Unmanned aerial vehicle rotor folding mechanism and unmanned aerial vehicle

Abstract

The utility model provides a kind of unmanned plane rotor folding mechanism, folding mechanism is fixedly installed on unmanned plane rack, including fixed seat, rotating shaft, rotary socket and lock catch;Fixed seat one end is fixedly installed on unmanned plane rack, and fixed seat is half-open structure, and limiting portion is formed in the half-open end of fixed seat, rotary socket is sleeved in the half-open end of fixed seat, and fixed seat and rotary socket are rotatably connected by rotating shaft, rotary socket can rotate around rotating shaft relative to fixed seat, when the axis of rotary socket coincides with the axis of fixed seat, rotary socket and fixed seat inner wall are attached;Fixed seat is additionally provided with lock catch assembly outside one end portion close to rotary socket.The unmanned plane rotor folding mechanism involved in the utility model can quickly complete unmanned plane rotor assembly and disassembly, folding, unfolding and locking action in short time, improve operation efficiency and have higher stability and reliability.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicles (UAVs), and in particular to a UAV rotor folding mechanism. Background Technology

[0002] With the increasing demand for drones across various fields, people are placing higher demands on their functionality. As a crucial component of drones, the optimized design of the rotor's assembly and disassembly mechanism is of great significance for improving maintenance efficiency, reducing costs, and enhancing overall performance. However, existing drone rotor assembly and disassembly mechanisms have certain limitations and shortcomings, such as complex operation, long processing times, and susceptibility to damage, which to some extent restricts the application scope and efficiency of drones. Therefore, in-depth research on drone rotor assembly and disassembly mechanisms is needed to explore more efficient and reliable solutions.

[0003] Currently, research on rotor assembly / disassembly solutions mainly includes two aspects: rotor assembly / disassembly locking mechanisms and modular design. Rotor assembly / disassembly locking mechanisms achieve efficient locking through optimized locking mechanisms, while modular design divides the rotor into several modules, enabling rapid replacement and maintenance between modules. However, UAV rotor folding mechanisms are typically complex in design, difficult to operate, and challenging to deploy quickly. Furthermore, the lack of effective locking mechanisms between modules often leads to loosening, affecting the overall rigidity of the rotor and resulting in decreased reliability. Utility Model Content

[0004] In view of the shortcomings of the prior art described above, the purpose of this utility model is to provide a drone rotor folding mechanism to meet the needs of rapid replacement, disassembly and folding of drone rotors, and to ensure the stability of the drone structure.

[0005] To achieve the above objectives, this utility model provides a drone rotor folding mechanism. The folding mechanism is fixedly installed on the drone frame and includes a fixed base, a rotating shaft, a rotating socket, and a latch. One end of the fixed base is fixedly installed on the drone frame, and the end of the fixed base away from the drone frame is a semi-open structure. A limiting part is formed at the semi-open end of the fixed base. The rotating socket is sleeved inside the semi-open end of the fixed base. The fixed base and the rotating socket are rotatably connected by the rotating shaft. The rotating socket can rotate relative to the fixed base around the rotating shaft. When the axis of the rotating socket coincides with the axis of the fixed base, the rotating socket is in contact with the inner wall of the fixed base.

[0006] The fixed base is also equipped with a limiter. When the rotary socket is in the folded state, the rotary socket abuts against the limiter.

[0007] The fixed base is also provided with a locking assembly at one end near the rotating socket. The locking assembly includes a pressure head, a connecting rod, a first lock body and a second lock body connected in sequence. The non-connecting end of the second lock body is provided with a slot, and the connecting end of the pressure head can be inserted into the slot.

[0008] Furthermore, the non-connecting end of the pressure head is provided with a locking clip, and a locking clip groove is provided at a corresponding position on the first lock body, so that the locking clip can be inserted into the locking clip groove.

[0009] Preferably, the limiter is also provided with a damping baffle.

[0010] Furthermore, the damping baffle is made of an elastic material.

[0011] This utility model also provides a drone, including the drone rotor folding mechanism described above.

[0012] As mentioned above, the drone rotor folding mechanism involved in this utility model is simple to manufacture, and most of its components are standard parts, making it highly replaceable and easy to maintain. It can quickly complete the drone rotor assembly, disassembly, folding, unfolding, and locking actions in a short time, improving operational efficiency. When the rotor is in the folded or open state, the parts are in surface contact with each other, which can meet the stability and reliability requirements of drone operation. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the overall structure of the drone rotor folding mechanism;

[0014] Figure 2 for Figure 1 Exploded view;

[0015] Figure 3 This is a schematic diagram of the rotating socket 3;

[0016] Figure 4 This is a schematic diagram showing the relative positions of the rotating socket 3 and the fixing base 2 in the folded state;

[0017] Figure 5 for Figure 4 A schematic diagram of the unfolded state;

[0018] Figure 6 This is a schematic diagram of the locking assembly 4.

[0019] Component designation explanation

[0020] 1 rack

[0021] 2. Fixture

[0022] 21 Limiters

[0023] 22 Damping baffles

[0024] 23 mounting slots

[0025] 3 Rotary socket

[0026] 31 Rotation axis

[0027] 32 bearings

[0028] 4 Locking assembly

[0029] 41 pressure head

[0030] 411 Locking Clip

[0031] 412 Locking Head

[0032] 42 Connecting rod

[0033] 43 First Lock Body

[0034] 431 Locking groove

[0035] 44 Second Lock Body

[0036] 441 Card Slot

[0037] 5. Wings Detailed Implementation

[0038] The following specific embodiments illustrate the implementation of this utility model. Those skilled in the art can easily understand other advantages and effects of this utility model from the content disclosed in this specification.

[0039] It should be understood that the structures, proportions, sizes, etc., depicted in the accompanying drawings are merely for illustrative purposes to aid those skilled in the art and are not intended to limit the scope of this invention. Therefore, they have no substantial technical significance. Any modifications to the structure, changes in proportions, or adjustments to size, without affecting the effectiveness and purpose of this invention, should still fall within the scope of the disclosed technical content. Furthermore, the terms "upper," "lower," "left," "right," "middle," and "one" used in this specification are merely for clarity and not intended to limit the scope of this invention. Changes or adjustments to their relative relationships, without substantially altering the technical content, should also be considered within the scope of this invention.

[0040] It should also be noted that when a component is referred to as being "fixed to" or "set on" another component, it can be directly on the other component or may be connected to an intermediary component. When a component is referred to as being "connected to" another component, it can be directly connected to the other component or indirectly connected to the other component through an intermediary component.

[0041] Furthermore, the use of terms such as "first" and "second" in this application is for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. Additionally, the technical solutions of the various embodiments can be combined with each other, but only on the basis of being achievable by those skilled in the art. When the combination of technical solutions is contradictory or impossible to implement, such a combination of technical solutions should be considered non-existent and not within the scope of protection claimed in this application.

[0042] like Figures 1 to 5 As shown, this utility model provides a drone rotor folding mechanism. The folding mechanism is fixedly installed on the frame 1 of the drone body and connects the drone body and the wing 5, which can realize the rapid folding or unfolding of the drone wing 5.

[0043] The folding mechanism includes a fixed base 2, a rotating shaft 31, a rotating socket 3, and a latch. One end of the fixed base 2 is fixedly mounted on the drone frame 1. In this invention, one end of the fixed base 2 is fixedly mounted to the corresponding mounting position of the drone frame 1 by means of bolts, welding, or a slot 441, ensuring stability during flight. The other end of the fixed base 2, i.e., the end away from the drone frame 1, is a semi-open structure. In this invention, it is preferably a U-shaped groove or a C-shaped opening, and this semi-open structure can be formed as a limiting part. The size of the semi-open structure matches the shape of the rotating socket 3. The rotating socket 3 is fitted inside the semi-open structure of the fixed base 2 and can rotate within the fixed base 2. The rotating socket 3 is fixedly connected to the wing 5, and the opening and folding of the wing 5 is achieved by rotating the rotating socket 3.

[0044] A rotating shaft 31 is provided on the fixed base 2. The rotating shaft 31 passes through the corresponding shaft holes of the fixed base 2 and the rotating socket 3, forming a hinge point. The fixed base 2 and the rotating socket 3 are rotatably connected by the rotating shaft 31, and the rotating socket 3 can rotate relative to the fixed base 2 around the rotating shaft 31. In this utility model, a bearing 32 is also provided outside the rotating shaft 31 to better realize the rotation function. The rotating socket 3 can fold or unfold relative to the fixed base 2 around the rotating shaft 31. The rotation angle range is set according to the design requirements of the UAV. During operation, when the axis of the rotating socket 3 coincides with the axis of the fixed base 2, the wing 5 is in a fully opened state. At this time, the rotating socket 3 is in contact with the inner wall of the fixed base 2. At this time, the limiting part plays a limiting role for the rotating socket 3. In addition, the limiting part can also simplify the operation process of the operator, without the need to calibrate the fully opened position of the wing 5. When the rotating socket 3 is in contact with the fixed base 2, it means that it has been opened in place and subsequent locking operations can be performed.

[0045] Furthermore, a limiter 21 is preferably provided on the fixed base 2, its position corresponding to the folding end point of the rotary socket 3. When the rotary socket 3 is folded to its limit position, the end face of the rotary socket 3 abuts against the limiter 21, which can prevent excessive folding from causing structural damage. Further still, the limiter 21 can be a protruding stop, a limiting plate, or a stepped structure, and the material can be metal or high-strength engineering plastic to ensure sufficient impact resistance. However, this utility model is not limited to this; any other structure or material that can achieve this function falls within the protection scope of this utility model.

[0046] Preferably, a damping baffle 22 is also provided on the surface of the limiter 21 that abuts against the rotary socket 3. The damping baffle 22 provides damping force by utilizing the elastic deformation of the material, preferably an elastic material such as silicone rubber, polyurethane, or spring steel sheet. The damping baffle 22 is fixed to the abutting surface of the limiter 21 and can be embedded by means of bonding, bolting, or slot 441. For example, a groove is made on the stop surface of the limiter 21, and the elastic damping baffle 22 is embedded in the groove, so that it generates buffering resistance when it contacts the rotary socket 3. When the rotary socket 3 is folded to the position of the limiter 21, the damping baffle 22 generates damping force through elastic compression, which on the one hand avoids rigid collision and acts as a buffer during folding, and on the other hand acts as a shock absorber to prevent the rotor from loosening due to vibration during transportation and handling.

[0047] To improve stability, the rotor folding mechanism also includes a locking assembly 4 when the drone's wings 5 ​​are deployed or fully folded. For example... Figure 6 As shown, the locking assembly 4 is fixedly mounted on the outside of the fixed base 2 near one end of the rotating socket 3. In this utility model, the rotating socket 3 has an external mounting groove, and the locking assembly can be fixed to the socket by bolts or other fixing methods. The assembly includes a pressure head 41, a connecting rod 42, a first locking body 43, and a second locking body 44 connected in sequence. These components are connected sequentially by pins, threads, or welding to form a linkage structure. A locking head 412 is formed at the end of the pressure head 41 that connects to the connecting rod 42. A slot 441 is provided at the corresponding position of the non-connecting end of the second locking body 44. When the locking assembly 4 is locked, the connecting end of the pressure head 41 can be engaged in the slot 441.

[0048] The non-connecting end of the pressure head 41 is provided with a locking clip 411, and a locking clip groove 431 matching the shape of the locking clip 411 is opened at the corresponding position on the first lock body 43, so that the locking clip 411 can be inserted into the locking clip groove 431.

[0049] In this utility model, the locking clip 411 can be an elastic metal clip or a plastic hook structure, and the locking clip groove 431 can be a U-shaped groove or a rectangular groove, etc., but this utility model is not limited to these. The locking clip 411 can be inserted into the locking clip groove 431.

[0050] When locking is required, lift the pressure head 41, using the pressure head 41 and connecting rod 42 to move and clamp the first lock body 43 and the second lock body 44; the locking head 412 at one end of the pressure head 41 is engaged into the slot 441 at the end of the second lock body 44, forming a preliminary lock; then press down the pressure head 41, causing the locking clip 411 on the pressure head 41 to engage into the locking clip slot 431 on the first lock body 43, achieving a secondary lock through elastic deformation or mechanical engagement, preventing the latch assembly 4 from loosening. When unlocking is required, push the pressure head 41 outwards, causing the locking clip 411 to disengage from the locking clip slot 431, and simultaneously remove the locking head 412 at one end of the pressure head 41 from the slot 441, thus releasing the lock.

[0051] The drone rotor folding mechanism involved in this utility model is simple, with most of the components being standard parts, making it highly replaceable and easy to maintain. It can quickly complete the drone rotor assembly, disassembly, folding, unfolding, and locking actions in a short time, improving work efficiency. When locked, the contact surfaces between the parts, such as the rotating socket 3 and the fixed base 2, and the locking head 412 and the slot 441, are in surface contact, which can meet the stability and reliability requirements of the drone during operation.

[0052] This utility model also provides a drone equipped with the aforementioned drone rotor folding mechanism. Drones typically have multiple rotors, each equipped with a rotor folding mechanism. The rotor folding mechanism is installed at the connection point between the frame 1 and the rotor. Each rotor arm is connected to the frame 1 via a corresponding folding mechanism, enabling synchronous folding and unfolding of multiple rotors. After unfolding, the drone rotors are locked by the locking assembly 4, ensuring safety and reliability.

[0053] After the operation is completed, unlock the locking assembly 4, rotate the socket 3 around the rotating axis 31 until it abuts against the limiter 21, and fold the rotor arm to the side of the frame 1 to reduce the storage volume of the drone. At this time, the quick unlocking of the rotor folding mechanism enables quick disassembly, improving efficiency.

[0054] The UAV rotor folding mechanism and UAV involved in this utility model can quickly complete the assembly, disassembly and locking of the rotor arm through the linkage design of the locking component 4, improving work efficiency; in the folded or unfolded state, the parts are in surface contact, which is not easy to loosen and has high reliability; in addition, the component structure is simple and the replacement cost is low; for example, the easily damaged parts such as the damping baffle 22 can be disassembled and replaced separately, and the maintenance time is short.

[0055] In summary, the drone rotor folding mechanism and the drone involved in this utility model effectively overcome the various shortcomings of the prior art and have high industrial application value.

[0056] The above embodiments are merely illustrative of the principles and effects of this utility model and are not intended to limit the scope of this utility model. Any person skilled in the art can modify or alter the above embodiments without departing from the spirit and scope of this utility model. Therefore, all equivalent modifications or alterations made by those skilled in the art without departing from the spirit and technical concept disclosed in this utility model should still be covered by the claims of this utility model.

Claims

1. A drone rotor folding mechanism, wherein the folding mechanism is fixedly mounted on the drone frame, characterized in that, The folding mechanism includes a fixed base, a rotating shaft, a rotating socket, and a latch. The fixed base is fixedly installed on the drone frame. The end of the fixed base away from the drone frame is a semi-open structure. A limiting part is formed at the semi-open end of the fixed base. The rotating socket is sleeved inside the semi-open end of the fixed base. The fixed base and the rotating socket are rotatably connected by the rotating shaft. The rotating socket can rotate relative to the fixed base around the rotating shaft. When the axis of the rotating socket coincides with the axis of the fixed base, the rotating socket is in contact with the inner wall of the fixed base. The fixed base is also provided with a limiter. When the rotating socket is in the folded state, the rotating socket abuts against the limiter. The fixed base is also provided with a locking assembly at one end near the rotating socket. The locking assembly includes a pressure head, a connecting rod, a first lock body, and a second lock body connected in sequence. The non-connecting end of the second lock body is provided with a slot, and the connecting end of the pressure head can be inserted into the slot. After being inserted, the end face of the connecting end of the pressure head contacts the bottom surface of the slot.

2. The UAV rotor folding mechanism according to claim 1, characterized in that: The non-connecting end of the pressure head is provided with a locking clip, and the first lock body is provided with a locking clip groove at a corresponding position, and the locking clip can be inserted into the locking clip groove.

3. The UAV rotor folding mechanism according to claim 1, characterized in that: The limiter is also equipped with a damping baffle.

4. The UAV rotor folding mechanism according to claim 3, characterized in that: The damping baffle is made of an elastic material.

5. An unmanned aerial vehicle (UAV), characterized in that: Includes the drone rotor folding mechanism as described in any one of claims 1 to 4.

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