Self-locking opposite-insertion quick-release system for unmanned aerial vehicle

Abstract

The invention relates to the technical field of unmanned aerial vehicles, in particular to a self-locking opposite-insertion quick-release system for an unmanned aerial vehicle, the system comprises a first connecting piece, a second connecting piece and a screwing piece, one end of the first connecting piece is provided with a first connecting cavity, and the end, away from the first connecting cavity, of the first connecting piece is in insertion fit with the second connecting piece; the screwing piece is in threaded connection with the first connecting piece and limits the second connecting piece, a limiting part is arranged on the first connecting piece, and the limiting part and the screwing piece can be clamped and limited. According to the device, quick connection and accurate limiting of structural modules are achieved, the inserting strength and the anti-loosening effect are ensured, and the assembly efficiency and the connection safety are improved.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to a self-locking plug-in and quick-release system for UAVs. Background Art

[0002] With the rapid development of drone technology, lightweight structures, assembly efficiency, and modular maintenance capabilities have become key design considerations for various drone systems. In particular, the rapid assembly and disassembly of carbon fiber components in multi-rotor, fixed-wing, and hybrid drones directly impacts the efficiency of transport, maintenance, and operational deployment.

[0003] Currently, the mainstream carbon tube connection structures of drones mostly use threaded connection and staple pin connection.

[0004] Among them, the threaded connection method is used to screw the two connection ends together through internal and external threads, which has high connection stability. However, it has the following disadvantages: there is a lack of a tightening tightness control device, and the assembler needs to determine the tightening torque by feel, which may cause human error; and there is no anti-loosening structure. After a strong earthquake or a long flight, the thread may produce a slight retreat due to vibration, which may eventually lead to loosening; the installation and disassembly operations are relatively cumbersome and not suitable for rapid replacement and modular task requirements.

[0005] The pin-and-pin connection method uses elastic pins or pins to clamp the two sections of the docking structure to complete the locking, which is quick to install. However, it also has the following defects: the contact surface is small and only relies on the cross-sectional card points to bear the load; long-term use can easily cause metal fatigue or deformation, resulting in loose connections; the seismic performance is poor and it cannot work stably for a long time in a high-frequency vibration environment. For example, the proximal end of the rotor cannot work stably for a long time in a high-frequency vibration environment.

[0006] Overall, the existing connection structure is difficult to meet the requirements of "high strength, anti-loosening, and rapid assembly" at the same time, especially in key structural parts where vibration sources are concentrated, such as the junction of the flight arm and the fuselage. Traditional connection solutions are prone to loosening, which may lead to flight accidents in severe cases. Summary of the Invention

[0007] In order to solve the above technical problems, the present invention discloses a self-locking plug-in quick-release system for drones, which solves the problems existing in the prior art, such as loose assembly, poor vibration resistance, large influence of human factors, and small contact surface that is easy to deform, thereby improving the safety of structural connections and assembly efficiency.

[0008] The present invention discloses a self-locking plug-in quick-release system for drones, comprising a first connecting member, a second connecting member and a screwing member. One end of the first connecting member is provided with a first connecting cavity, and the end away from the first connecting cavity is plugged into and cooperates with the second connecting member. The screwing member is threadedly connected to the first connecting member and limits the second connecting member. A limiting portion is provided on the first connecting member, and the limiting portion can be clamped and limited with the screwing member.

[0009] Optionally, the first connecting member has an inserting portion, and the second connecting member has an inserting slot. The shapes of the inserting portion and the inserting slot are adapted to each other and limit the relative rotation of the first connecting member and the second connecting member. The axial length of the inserting portion is not greater than the depth of the inserting slot.

[0010] Optionally, the first connecting member is provided with a connecting portion, the connecting portion is provided with an external thread, and the screwing member is provided with an internal thread, and the first connecting member and the screwing member are connected via the external thread and the internal thread.

[0011] Optionally, at least two limiting portions are provided on the first connecting member, and the limiting portions can be elastically engaged with the screwing member.

[0012] Optionally, an annular groove is provided on the screwing member, and the limiting portion is clamped on the annular groove.

[0013] Optionally, the limiting portion includes a limiting base provided on the first connecting member, and a ball screw for limiting is installed on the limiting base.

[0014] Optionally, the ball screw includes a spring, a steel ball and a shell. The shell has a hollow cylindrical structure inside, one end of the shell is threaded, and the other end is an opening. The steel ball and the spring are accommodated inside the shell, and the spring squeezes the steel ball to abut against the opening. The diameter of the opening is smaller than the diameter of the steel column.

[0015] Optionally, a stop portion is provided at one end of the second connecting member close to the first connection, and a convex ring is provided at one end of the screwing member close to the second connecting member, and the convex ring abuts against the stop portion to limit the position.

[0016] Optionally, the second connecting member includes a second connecting cavity, and the second connecting cavity is provided with a second positioning hole; the first connecting member includes a first connecting cavity, and the first connecting cavity is provided with a first positioning hole.

[0017] A drone comprises the self-locking plug-in quick-release system for drones, a first carbon tube, and a second carbon tube. The first carbon tube and the second carbon tube are connected by the self-locking plug-in quick-release system for drones, the first carbon tube is connected to the first connecting piece, and the second carbon tube is connected to the second connecting piece.

[0018] The technical solution provided by the embodiments of the present invention has the following advantages over the prior art:

[0019] The self-locking plug-in quick-release system for drones described in the present invention has multiple advantages such as compact structure, efficient assembly, firm connection, and excellent anti-loosening performance. Through the plug-in fit of the first connector and the second connector and the thread limit of the screw, rapid installation and reliable locking can be achieved; the shape fit of the plug-in part and the plug-in slot can limit rotation and improve torsion resistance; the limiting structures such as ball screws can achieve automatic snap-in and multi-point locking, effectively avoiding loosening caused by vibration during flight; the matching positioning holes and stop structures ensure accurate assembly direction and enhance module interchangeability; at the same time, the screw is provided with a knurled or ratchet structure to improve operational convenience and anti-misoperation performance. The entire device supports high-strength, repeatable and rapid disassembly and assembly of carbon tube structures, and is particularly suitable for drone platforms with high-frequency maintenance, high vibration and multi-scene operations. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a structural diagram of the plug-in quick-release device in an embodiment of the present disclosure;

[0021] Figure 2 This is a schematic structural diagram of the first connecting member in an embodiment of the present disclosure;

[0022] Figure 3 is a top view of the first connecting member in an embodiment of the present disclosure;

[0023] Figure 4 is a front view of the first connecting member in an embodiment of the present disclosure;

[0024] Figure 5 for Figure 4 Sectional view along line AA;

[0025] Figure 6 for Figure 4 Cross-sectional view along line BB;

[0026] Figure 7 is a schematic structural diagram of the second connecting member in an embodiment of the present disclosure;

[0027] Figure 8 is a top view of the second connecting member in an embodiment of the present disclosure;

[0028] Figure 9 is a front view of the second connecting member in the embodiment of the present disclosure;

[0029] Figure 10 for Figure 9 Cross-sectional view along line CC;

[0030] Figure 11 Schematic diagram of the structure of the screwing part in the embodiment of the present disclosure. DETAILED DESCRIPTION

[0031] In order to more clearly understand the above-mentioned objectives, features and advantages of the present disclosure, the scheme of the present disclosure will be further described below. It should be noted that the embodiments of the present disclosure and the features therein can be combined with each other without conflict.

[0032] In the following description, many specific details are set forth to facilitate a full understanding of the present disclosure, but the present disclosure may also be implemented in other ways different from those described herein; it is obvious that the embodiments in the specification are only part of the embodiments of the present disclosure, rather than all of the embodiments.

[0033] The present invention provides a plug-in quick-release device for connecting the structure of an unmanned aerial vehicle. Through a unique limiting structure, a ball screw assembly and a screwing part, it can achieve efficient assembly and vibration self-locking functions while achieving carbon tube docking.

[0034] Combine Figure 1-11 As shown, this embodiment discloses a self-locking plug-in quick-release system for drones. The device includes a first connector 1, a second connector 2, and a screwing member 3. One end of the first connector is provided with a first connecting cavity 11, and the end away from the first connecting cavity 11 is plugged into the second connector 2. The screwing member 3 is threadedly connected to the first connector and limits the position of the second connector 2. The first connector is provided with a limit portion 14, which can be engaged with the screwing member 3 for positional limitation. This device achieves rapid connection and precise positioning of structural modules, ensures plug-in strength and anti-loosening effect, and improves assembly efficiency and connection security.

[0035] In one embodiment, the first connector has a plug portion 12, and the second connector 2 has a plug slot 23. The plug slot 23 is an arc-shaped groove. The plug portion 12 and the plug slot 23 are shaped to match and restrict relative rotation between the first connector 1 and the second connector 2. The axial length of the plug portion 12 is no greater than the depth of the plug slot 23, and the length of the plug portion 12 of the first connector 1 is no less than 1.5 times its outer diameter. This shape-limited design prevents rotational deviation, enhances torque transmission capability, improves shear strength, and improves connection stability, making it suitable for high-load drone structures.

[0036] In one embodiment, the first connecting member 1 is provided with a connecting portion 13, which is provided with an external thread, and the screwing member 3 is provided with an internal thread 31, and the first connecting member 1 and the screwing member 3 are connected by the external thread and the internal thread 31. This design ensures that the screwing member 3 can reliably cover and clamp the second connecting member 2, forming an axial limit and effectively preventing the connection from loosening.

[0037] In one embodiment, the materials of the first connector 1 and the second connector 2 are selected from one or more of the following: aluminum alloy, carbon fiber reinforced plastic, stainless steel, and titanium alloy. The optimal material configuration is selected based on the aircraft's intended use, balancing weight, strength, and corrosion resistance to adapt to different flight environments and mission requirements.

[0038] In one embodiment, at least two stoppers 14 are provided on the first connector 1, and the stoppers 14 can be elastically engaged with the screw member 3. Multiple stoppers enhance the anti-loosening effect, while increasing the connection rigidity and improving the anti-vibration performance during flight.

[0039] In one embodiment, the screwing member 3 is provided with an annular groove 32, with multiple V-shaped or U-shaped grooves formed on its walls. Guide slopes are provided on either side of the groove, through which the multiple stoppers 14 slide, achieving multi-point locking. This progressive locking mechanism during the screwing process creates an automatic "alignment and slotting" action, ensuring proper locking and preventing disengagement, enhancing the assembly experience.

[0040] In one embodiment, the outer surface of the screw 3 is provided with an anti-slip texture or knurled structure to facilitate the user's screwing operation. This design enhances the convenience of human-computer interaction and is particularly suitable for quick assembly and disassembly when wearing gloves or in slippery conditions.

[0041] In one embodiment, a ratchet structure is provided within the screw member 3, which, in conjunction with the rotation limiter structure, provides a one-way rotation locking function. The ratchet structure effectively prevents reverse rotation, forms a one-way limit, improves the anti-seismic and automatic anti-loosening performance, and is suitable for high-frequency vibration scenarios.

[0042] In one embodiment, the limiting portion 14 includes a limiting base provided on the first connector 1, on which a ball screw for limiting is mounted. The ball screw includes a spring, a steel ball, and a housing. The housing has a hollow cylindrical structure, one end of which is threaded and the other end is open. The steel ball and the spring are housed within the housing. The spring presses the steel ball against the opening, the diameter of which is smaller than the diameter of the steel column. This forms a pop-up mechanical limiting structure that automatically embeds into the slot to form a self-locking structure, while also having certain buffering properties to extend the life of the connector.

[0043] In a further embodiment, a spring is pre-compressed and placed in a housing, with one end resting against the bottom of the housing (or secured by a slot) and the other end against a steel ball. The steel ball (or nylon sphere) is placed at the open end of the housing and is pushed out of the housing surface by the spring's elastic force, but is limited by the constriction design of the housing opening, preventing the steel ball from completely escaping. The housing is pressed into a pre-machined mounting hole using a press or hand tool and secured by a threaded connection. The open end of the housing is machined to form a constriction with a diameter slightly smaller than the steel ball to prevent the steel ball from completely escaping due to the spring pressure. A slot or boss is designed at the bottom of the housing to secure one end of the spring and prevent it from deflecting during compression. This structure facilitates standardized assembly and mass production, while enhancing the rebound accuracy and stability of the steel ball and improving the speed and reliability of the limit response.

[0044] In one embodiment, a stopper 22 is provided at one end of the second connector 2, which is adjacent to the first connector. A protruding ring 33 is provided at one end of the screwing member 3, which is adjacent to the second connector 2. The protruding ring 33 abuts against the stopper 22 to limit the screwing position. This physical limit structure ensures that the screwing depth is controlled, preventing over-tightening that may cause the connection surface to become overtightened or material deformation, thereby extending the service life of the device.

[0045] In one embodiment, the second connector 2 includes a second connection cavity 12 with a second positioning hole 211; the first connector 1 includes a first connection cavity 11 with a first positioning hole 111. Locating pins can be used to ensure consistent connection direction and accurate insertion, improving module interchangeability and ease of maintenance.

[0046] This application discloses a drone, comprising a self-locking plug-in / quick-release system for drones, a first carbon tube, and a second carbon tube. The first carbon tube and the second carbon tube are connected by the self-locking plug-in / quick-release system for drones, with the first carbon tube connected to a first connector 1 and the second carbon tube connected to a second connector 2. This device enables rapid deployment, disassembly, replacement, and modular maintenance of drone flight structures, improving overall operational efficiency and reliability. It is particularly suitable for multi-mission flight platforms and aircraft used in complex environments.

[0047] The specific implementation method and implementation principle are the same as those in the above embodiment, and can bring the same or similar technical effects, which will not be described here one by one. For details, please refer to the description of the above-mentioned upper cover airtightness detection tooling embodiment.

[0048] In the description of the embodiments of the present disclosure, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "height", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing the embodiments of the present disclosure and simplifying the description, and do not indicate or imply that the structure or device referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the embodiments of the present disclosure.

[0049] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "comprises," "comprising," or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, article, or device comprising a series of elements includes not only those elements, but also other elements not explicitly listed, or elements inherent to such process, method, article, or device. In the absence of further limitations, an element defined by the phrase "comprising a ..." does not exclude the presence of other identical elements in the process, method, article, or device comprising the element.

[0050] The foregoing description is intended only to provide specific embodiments of the present disclosure, intended to enable those skilled in the art to understand and implement the present disclosure. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present disclosure. Therefore, the present disclosure is not intended to be limited to the embodiments described herein, but rather to be construed in the broadest manner consistent with the principles and novel features disclosed herein.

Claims

1. A self-locking quick-release system for drones, characterized by: It includes a first connecting member, a second connecting member and a screwing member. One end of the first connecting member is provided with a first connecting cavity, and the end away from the first connecting cavity is plugged into and matched with the second connecting member. The screwing member is threadedly connected to the first connecting member and limits the second connecting member. A limiting part is provided on the first connecting member, and the limiting part can be clamped and limited with the screwing member.

2. The self-locking quick-release system for drones according to claim 1, characterized in that: The first connecting member has an inserting portion, and the second connecting member has an inserting slot. The shapes of the inserting portion and the inserting slot are adapted to each other and limit the relative rotation of the first connecting member and the second connecting member. The axial length of the inserting portion is not greater than the depth of the inserting slot.

3. The self-locking quick-release system for drones according to claim 1, characterized in that: The first connecting member is provided with a connecting portion, the connecting portion is provided with an external thread, and the screwing member is provided with an internal thread. The first connecting member and the screwing member are connected through the external thread and the internal thread.

4. The self-locking quick-release system for drones according to claim 1, characterized in that: At least two limiting portions are provided on the first connecting member, and the limiting portions can be elastically clamped on the screwing member.

5. The self-locking quick-release system for drones according to claim 4, characterized in that: The screwing member is provided with an annular groove, and the limiting portion is clamped on the annular groove.

6. The self-locking quick-release system for drones according to claim 4, characterized in that: The limiting portion includes a limiting base arranged on the first connecting member, and a ball screw for limiting is installed on the limiting base.

7. The self-locking quick-release system for drones according to claim 6, characterized in that: The ball screw includes a spring, a steel ball and a shell. The shell has a hollow cylindrical structure inside. One end of the shell is threaded and the other end is open. The steel ball and the spring are accommodated inside the shell. The spring squeezes the steel ball to abut against the opening. The diameter of the opening is smaller than the diameter of the steel column.

8. The self-locking quick-release system for drones according to claim 1, characterized in that: A stop portion is provided at one end of the second connecting member close to the first connection, and a convex ring is provided at one end of the screwing member close to the second connecting member, and the convex ring abuts against the stop portion for limiting position.

9. The self-locking quick-release system for drones according to claim 1, characterized in that: The second connecting member includes a second connecting cavity, and a second positioning hole is provided on the second connecting cavity; the first connecting member includes a first connecting cavity, and a first positioning hole is provided on the first connecting cavity.

10. A drone, characterized in that: It comprises the self-locking plug-in quick-release system for drones according to any one of claims 1 to 9, a first carbon tube and a second carbon tube, the first carbon tube and the second carbon tube being connected by the self-locking plug-in quick-release system for drones, the first carbon tube being connected to the first connecting piece, and the second carbon tube being connected to the second connecting piece.

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