Locking structure of unmanned aerial vehicle disassembly structure

Abstract

The application relates to a locking structure of a dismounting structure of a unmanned aerial vehicle. The locking structure of the dismounting structure of the unmanned aerial vehicle comprises a connecting assembly and a locking assembly, the connecting assembly comprises a connecting base and a rotating piece for outputting power; the rotating piece is hinged to the connecting base; the locking assembly comprises a locking piece hinged to the connecting base, the locking piece is provided with a locking portion, and the locking portion is connected with the rotating piece when the connecting assembly is in a connecting state to prevent the included angle between the rotating piece and the connecting base from increasing. The application can ensure that the connecting state is relatively stable, prevent the occurrence of unhooking, facilitate the operation of dismounting the parts of the unmanned aerial vehicle by holding the rotating piece with hands, ensure that the jacking protrusion does not interfere with the rotation of the rotating piece to be opened, enable the tongue to automatically move away from the supporting body, and facilitate the dismounting of the parts of the unmanned aerial vehicle.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a locking structure for UAV assembly and disassembly. Background Technology

[0002] To ensure the convenience and safety of storage and transportation, drone products generally adopt a modular design, meaning that the entire drone can be disassembled into multiple modules such as the fuselage, wings, tail, landing gear, and payload. During use, rapid assembly and disassembly can be achieved by operating the relevant disassembly and locking mechanisms.

[0003] Currently, the most common quick-release structures on the market are threaded locking, shaft pins, elastic buckles, bag hooks or butterfly locks. For example, the connection between the wings and the fuselage of a large drone is achieved by inserting carbon tubes of different diameters embedded in the structural frame of the two. At the same time, large power and signal connectors are arranged nearby. In this case, the resistance to plugging and unplugging the fuselage and wings is very large.

[0004] In summary, the existing technology has at least the following technical problems:

[0005] First, the disassembly and assembly of drone components requires tools such as screwdrivers, which is quite troublesome.

[0006] Second, the reliability of disassembling and assembling drone components with the drone itself is low. Summary of the Invention

[0007] One object of the present invention is to solve or alleviate the first technical problem mentioned above.

[0008] The present invention employs a locking structure for the assembly and disassembly of a drone, comprising a connecting component and a locking component. The connecting component includes a connecting base and a rotating component for outputting power; the rotating component is hinged to the connecting base; the locking component includes a locking component hinged to the connecting base, the locking component being provided with a locking part, and when the connecting component is in the connected state, the locking part is connected to the rotating component to prevent the included angle between the rotating component and the connecting base from increasing.

[0009] The effect achieved by this invention is to ensure a relatively stable connection and prevent decoupling.

[0010] In a further technical solution, when the connecting component is in the connected state, the connection method between the locking part and the rotating part is plug-in, magnetic connection and / or snap-fit ​​connection.

[0011] A further technical solution is that the locking part is a snap-fit ​​that abuts against the top surface of the rotating part.

[0012] A further technical solution is that the locking component is fixedly provided with a lifting protrusion, which is located below the rotating component.

[0013] It facilitates the disassembly of drone parts by holding the rotating parts by hand.

[0014] In a further technical solution, when the locking component is in the locked state, a buffer gap is provided between the lifting protrusion and the bottom surface of the rotating component.

[0015] It facilitates the disassembly of drone parts by holding the rotating component by hand, while the raised protrusions have few or no interference with the rotation of the component.

[0016] A further technical solution is that the buffer gap corresponds to the lifting angle, the locking part corresponds to the yield angle, and the yield angle is less than or equal to the lifting angle.

[0017] It facilitates the disassembly of drone parts by holding the rotating component by hand, while ensuring that the raised part does not interfere with the rotation and opening of the component.

[0018] In a further technical solution, the locking assembly also includes retaining elastic elements, which are connected to the rotating elements respectively, so that the locking part has a tendency to rotate toward the connecting ear.

[0019] It allows the tongue holder to automatically move away from the connecting ear, making it easier to disassemble drone parts.

[0020] In a further technical solution, the locking component also includes a locking pin, and the locking member is hinged to the connecting base through the locking pin. The retaining elastic member includes a first elastic end, a curled section, and a second elastic end connected in sequence. The locking pin passes through the curled section, and the first elastic end and the second elastic end abut against the locking member and the connecting base, respectively.

[0021] It facilitates the assembly of connecting components.

[0022] A further technical solution is that the rotating component has a closed clearance groove, and the locking component is provided with a rotation limit body. When the locking component is in the unlocked state, the rotation limit body abuts against the connecting base.

[0023] To facilitate the installation of drone components, the locking part connects with the rotating part, while ensuring a seal within the connection base.

[0024] A further technical solution involves setting a limit arm on the locking component, locking the component in a locked state, and rotating parts fitting against the limit arm.

[0025] It can ensure the positioning of the rotating parts, so that the top surface of the rotating parts is roughly horizontal.

[0026] In summary, the present invention can achieve the following technical effects:

[0027] 1} This ensures a relatively stable connection and prevents the connection from disengaging.

[0028] 2) It facilitates the disassembly of drone parts by holding the rotating component by hand, while ensuring that the raised protrusion does not interfere with the rotation and opening of the rotating component.

[0029] 3) It enables the tongue holder to automatically move away from the connecting ear, making it easier to disassemble drone parts. Attached Figure Description

[0030] Figure 1 This is a schematic diagram of a drone quick-assembly and disassembly structure according to a first embodiment of the present invention.

[0031] Figure 2 This is a three-dimensional exploded view of the rapid assembly and disassembly structure of a drone according to the first embodiment of the present invention.

[0032] Figure 3 This is a three-dimensional exploded view of the quick-assembly and disassembly component 2 according to the first embodiment of the present invention.

[0033] Figure 4 This is an exploded perspective view of the quick-release assembly 2 according to the first embodiment of the present invention; the base hinge shaft 338 is not shown.

[0034] Figure 5 This is a top view schematic diagram of a drone quick-assembly and disassembly structure according to the first embodiment of the present invention.

[0035] Figure 6 This is a schematic diagram of section SEC1; the connecting component 3 is in the connected state; the locking component 4 is in the locked state; arrow 1 ARR1 indicates the direction in which rotating the rotating part 33 causes the tongue abutment 321 to approximately translate during the process of connecting component 3 changing from the connected state to the disassembled state; arrow 2 ARR2 indicates the direction in which the tongue abutment 321 approximately translates and abuts against the disassembled guide surface 121 during the process of connecting component 3 changing from the connected state to the disassembled state, causing the tongue abutment 321 to move approximately; line 2 LINE2 indicates the circle formed by the imaginary rotation of the farthest point 335 around the base hinge axis 338.

[0036] Figure 7 This is a schematic diagram of detail 1, DTL1; line 1 represents the circle formed by the imaginary rotation of the top point 415 around the locking pin 49; line 2 represents the circle formed by the imaginary rotation of the farthest point 335 around the base hinge axis 338; line 3 represents the arc formed by the imaginary rotation of the yield point 47 of the locking part 411 around the locking pin 49.

[0037] Figure 8 This is a three-dimensional schematic diagram of a drone quick-assembly and disassembly structure according to a second embodiment of the present invention.

[0038] Figure 9This is a three-dimensional exploded view of the rapid assembly and disassembly structure of a drone according to the second embodiment of the present invention.

[0039] Figure 10 This is a three-dimensional exploded view of the rapid assembly and disassembly structure of a drone according to the second embodiment of the present invention.

[0040] Figure 11 This is a top view schematic diagram of a drone quick-assembly and disassembly structure according to a second embodiment of the present invention.

[0041] Figure 12 This is a schematic diagram of section SEC2; arrow 3 ARR3 indicates the rotation direction of the rotating output rod 344 during the process of connecting component 3 changing from the connected state to the disassembled state; arrow 4 ARR4 indicates the rotation direction of the hook connector 343 during the process of connecting component 3 changing from the connected state to the disassembled state.

[0042] Figure 13 This is a partially enlarged schematic diagram of section 2, SEC2.

[0043] Arrow 1 ARR1; Arrow 2 ARR2; Arrow 3 ARR3; Arrow 4 ARR4; Section 1 SEC1; Section 2 SEC2; Detail 1 DTL1; Detail 2 DTL2; Line 1 LINE1; Line 2 LINE2; Line 3 LINE3; Connected base 1; Connecting ear 11; Connecting support surface 111; Hidden groove 12; Disassembly guide surface 121; Hook 13; Hook opening 131; Connecting cavity 132; Guide protrusion 133; Hook opening width 138; Quick-release assembly 2; Connecting assembly 3; Connecting base 31; Hinge ear 318; Second base 319; Connecting tongue 32; Tongue support body 321; Guide section 322; Tongue connecting arm 329; Rotating component 33; Reinforcing rib 333; Connecting socket 334; farthest point 335; clearance groove 337; base hinge shaft 338; tongue hinge shaft 339; hook connector 34; first linkage rod 341; second linkage rod 342; hook connector 343; rotating output rod 344; rotating transmission rod 345; connector thickness 348; connecting notch surface 349; locking assembly 4; locking element 41; locking part 411; limiting arm 412; lifting protrusion 413; buffer gap 414; lifting point 415; lifting angle 416; clearance angle 417; rotating limiting body 418; operating end 419; retaining elastic element 42; first elastic end 421; second elastic end 422; curled section 423; clearance point 47; critical point 48; locking pin 49. Detailed Implementation

[0044] The specific embodiments of the present invention will now be described with reference to the accompanying drawings.

[0045] As a specific embodiment, the first embodiment of the UAV quick-assembly and disassembly structure of the present invention includes a connected base 1 and a quick-assembly and disassembly component 2.

[0046] The connected base 1 is provided with a connecting ear 11.

[0047] The quick-release assembly 2 includes a connecting assembly 3; the connecting assembly 3 includes a connecting base 31, a connecting tongue 32, and a rotating component 33.

[0048] The connecting tongue 32 is provided with a tongue support 321 and is hinged to the rotating member 33 (the connecting tongue 32 and the rotating member 33 are hinged through the tongue hinge shaft 339).

[0049] The rotating component 33 is hinged to the connecting base 31 (the rotating component 33 and the connecting base 31 are hinged through the base hinge shaft 338 embedded in the hinge ear 318).

[0050] The tongue-holding body 321 abuts against the connecting ear 11, and the axis of hinge between the rotating member 33 and the connecting base 31 (i.e., the axis of hinge shaft 338 of the base) is located between the axis of hinge between the connecting tongue 32 and the rotating member 33 (i.e., the axis of hinge shaft 339 of the tongue) and the connecting ear 11; at this time, if Figure 1 As shown, the connecting component 3 is in a connected state. In a specific embodiment, when the connecting component 3 is in the connected state, the connected base 1 and the connecting base 31 abut against each other. Of course, in a specific embodiment, when the connecting component 3 is in the connected state, a gap is provided between the connected base 1 and the connecting base 31.

[0051] In a specific embodiment, the axis of hinge between the rotating member 33 and the connecting base 31, and the axis of hinge between the connecting tongue 32 and the rotating member 33 are approximately parallel.

[0052] The working principle is as follows: before use, one of the connected base 1 and quick-release assembly 2 (connecting base 31 of quick-release assembly 2) is fixed (by screws, etc.) to the first part of the drone (not shown in the attached diagram, such as the wing, etc.), and the other of the connected base 1 and quick-release assembly 2 (connecting base 31 of quick-release assembly 2) is fixed to the second part of the drone (not shown in the attached diagram, such as the fuselage, etc.).

[0053] When connecting the first component of the drone to the second component of the drone, bring the first component and the second component of the drone close to each other until, when viewed from above, the connecting ear 11 is located between the tongue abutment 321 and the tongue hinge axis 339. Then rotate the rotating component 33 to reduce the angle between the rotating component 33 and the connecting base 31 until the tongue abutment 321 and the connecting ear 11 abut against each other. The axis of hinge between the rotating component 33 and the connecting base 31 (i.e., the axis of hinge axis 338 of the base) is located between the axis of hinge between the connecting tongue 32 and the rotating component 33 (i.e., the axis of hinge axis 339 of the tongue) and the connecting ear 11. At this time, the connecting component 3 is in the connected state, and the first component and the second component of the drone are connected, enabling the drone to fly.

[0054] Conversely, when it is necessary to separate the first part of the drone from the second part of the drone, the rotating component 33 is rotated so that the angle between the rotating component 33 and the connecting base 31 is reduced, and the tongue abutment 321 moves away from the connecting ear 11. At this time, the connecting component 3 is in a disassembled state, and the first part of the drone is separated from the second part of the drone, which is convenient for storage, transportation, etc.

[0055] It should be noted that the connection between the first part of a drone and the second part of a drone can be achieved by using multiple sets of connected bases 1 and quick-release components 2 (such as multiple sets of components around the mating surfaces between the first part and the second part of the drone).

[0056] As can be seen from the above, the drone quick-assembly structure allows for convenient and rapid disassembly and assembly of drone components (i.e., the drone's first component and the drone's second component).

[0057] The connecting ear 11 is provided with a connecting abutment surface 111. When the connecting component 3 is in the connected state, the connecting abutment surface 111 abuts against the tongue abutment body 321; such as Figure 6 As shown, the connecting abutment surface 111 is inclined inward, that is, the connecting abutment surface 111 approaches the connecting base 31 from top to bottom. In a specific embodiment, the connecting abutment surface 111 is a plane. In a specific embodiment, the connecting abutment surface 111 is a curved surface that fits against the tongue abutment body 321. When the connecting assembly 3 is in the connected state, the holding force of the connecting abutment surface 111 against the tongue abutment body 321 ensures that the tongue abutment body 321 will not move upward and disengage (that is, the tongue abutment body 321 moves upward until it separates from the connecting ear 11), thus ensuring the reliability of the connection state.

[0058] like Figure 6As shown, the connecting ear 11 is provided with a connecting abutment surface 111, and the connected base 1 is provided with a hidden groove 12. The connecting ear 11 is disposed in the hidden groove 12, so that the connecting ear 11 is lower than the top surface of the connected base 1. In the connected state, the connecting tongue 32 is lower than the top surface of the connected base 1, which ensures that there is no obvious protrusion on the top surface of the connected base 1. The hidden groove 12 is provided with an inwardly inclined disassembly guide surface 121, that is, the disassembly guide surface 121 approaches the connecting base 31 from top to bottom. As a specific embodiment, the disassembly guide surface 121 is a plane or a curved surface. The distance between the bottom end of the hidden groove 12 and the bottom end of the connecting abutment surface 111 is less than the horizontal movement distance of the tongue abutment 321 during the process of changing from the locked state to the disassembly state. During the transition from a connected state to a disassembled state, the tongue abutment 321 moves away from the connecting base 31 until it abuts against the disassembly guide surface 121. The disassembly guide surface 121 acts as a guide, causing the tongue abutment 321 to move along the disassembly guide surface 121 until it reaches the disassembled state (without manually moving the connecting tongue 321 upwards). This allows the first and second components of the drone to be separated from each other. In other words, it ensures that there is no obvious protrusion on the top surface of the connected base 1, while facilitating the disassembly of drone components.

[0059] When the connecting component 3 is in the connected state, the top surface of the connecting tongue 32, the top surface of the rotating component 33, and the top surface of the connected base 1 are approximately in the same plane.

[0060] The bottom end of the tongue-holding body 321 is rounded to form a guide section 322. This improves the guiding effect of disassembling the guide surface 121.

[0061] The quick-release assembly 2 also includes a locking assembly 4; the locking assembly 4 includes a locking member 41 that is hinged to the connecting base 31 (hinged via a locking pin 49). The locking member 41 is provided with a locking part 411. When the connecting assembly 3 is in the connected state, the locking part 411 is connected to the rotating member 33, preventing the included angle between the rotating member 33 and the connecting base 31 from increasing. At this time, the locking assembly 4 is in the locked state. This ensures a relatively stable connection and prevents disengagement.

[0062] When the connecting component 3 is in the connected state, the connection method between the locking part 411 and the rotating part 33 is plug-in (relying on friction), magnetic connection (relying on magnetic force) and / or snap-fit ​​connection (relying on holding force).

[0063] The locking part 411 is a snap-fit ​​(i.e., the connection is achieved by snap-fit) and abuts against the top surface of the rotating part 33.

[0064] The locking member 41 is fixedly provided with a lifting protrusion 413, which is located below the rotating member 33. When the locking member 41 is rotated so that the lifting protrusion 413 approaches the rotating member 33 and the locking part 411 rotates synchronously, the locking part 411 rotates synchronously until it no longer abuts the top surface of the rotating member 33 to unlock. The lifting protrusion 413 lifts the rotating member 33, so that a gap is created between the rotating member 33 and the connecting base 31, which makes it easier to hold the rotating member 33 by hand to disassemble the parts of the drone.

[0065] When the locking component 4 is in the locked state, a buffer gap 414 is provided between the lifting protrusion 413 and the bottom surface of the rotating component 33. During the process of rotating the locking component 41 to bring the lifting protrusion 413 closer to the rotating component 33 and the locking part 411 rotating synchronously, the lifting protrusion 413 lifts the rotating component 33 after the locking part 411 rotates synchronously, so that a gap is created between the rotating component 33 and the connecting base 31, which makes it easier to hold the rotating component 33 by hand to disassemble the parts of the drone. At the same time, the lifting protrusion 413 interferes less or not at all with the rotation of the rotating component 33 to open.

[0066] The buffer gap 414 corresponds to the apex angle 416, (e.g.) Figure 7 As shown, the point where the lifting protrusion 413 can hypothetically rotate and abut against the rotating part 33 is the lifting point 415. The angle formed by connecting the lifting point 415, the locking pin 49, and the point where the lifting protrusion 413 can hypothetically rotate and abut against the rotating part 33 is the lifting angle 416. The locking part 411 corresponds to the clearance angle 417. Figure 7As shown, when viewed from above, the point furthest from the axis of the base hinge shaft 338 of the overlapping portion of the rotating part 33 and the locking part 411 is the farthest point 335. The point of the locking part 411 closest to the axis of the base hinge shaft 338 is the yield point 47. The intersection of the circle formed by the imaginary rotation of the yield point 47 around the axis of the locking pin 49 and the circle formed by the imaginary rotation of the farthest point 335 around the axis of the base hinge shaft 338 is the critical point 48. The included angle formed by connecting the yield point 47, the axis of the locking pin 49, and the critical point 48 in sequence is the yield angle 417. The yield angle 417 is less than or equal to the lifting angle 416. When the yield angle 417 equals the lifting angle 416, during the process of rotating the locking member 41 to bring the lifting protrusion 413 closer to the rotating member 33 and the locking part 411 rotating synchronously, when the lifting protrusion 413 lifts the rotating member 33, the yield point 47 coincides with the critical point 48, and the locking part 411 contacts the rotating member 33. The lifting protrusion 413 does not interfere with the rotation of the rotating member 33. When the yield angle 417 is less than the lifting angle 416, during the process of rotating the locking member 41 to bring the lifting protrusion 413 closer to the rotating member 33 and the locking part 411 rotating synchronously, when the lifting protrusion 413 lifts the rotating member 33, there is a gap between the yield point 47 and the critical point 48, and a gap between the locking part 411 and the rotating member 33. The lifting protrusion 413 does not interfere with the rotation of the rotating member 33. That is, it is convenient to hold the rotating member 33 by hand to disassemble the parts of the drone, while ensuring that the lifting protrusion 413 does not interfere with the rotation of the rotating member 33.

[0067] The locking assembly 4 also includes a retaining elastic element 42, which is connected to either the rotating element 33 or the connecting tongue 32 (the connection method with the retaining elastic element 42 is not shown in the figure), causing the locking part 411 to tend to rotate toward the connecting ear 11. After the locking part 411 is disconnected from the rotating element 33 (at which point the locking assembly 4 is in the unlocked state), the elastic force provided by the retaining elastic element 42 allows the tongue abutment 321 to automatically move away from the connecting ear 11, facilitating the disassembly of the drone's components. As a specific embodiment, the retaining elastic element 42 is connected to both the connecting tongue 32 and the connecting base 31, causing the connecting tongue 32 to tend to move closer to the connecting base 31 (not shown in the figure). For example, the retaining elastic element 42 can be a spring, with both ends hooked to the connecting tongue 32 and the connecting base 31 respectively, to improve the reliability of the connection state.

[0068] In a specific implementation, the locking assembly 4 further includes a locking pin 49. The locking member 41 is hinged to the connecting base 31 via the locking pin 49. The retaining elastic member 42 includes a first elastic end 421, a coiled section 423, and a second elastic end 422 connected in sequence. The locking pin 49 passes through the coiled section 423, and the first elastic end 421 and the second elastic end 422 abut against the locking member 41 and the connecting base 31, respectively. This causes the locking part 411 to have a tendency to rotate toward the connecting ear 11, facilitating the assembly of the connecting assembly 3.

[0069] In a specific embodiment, the rotating member 33 has a clearance groove 337, and the locking part 411 passes through the clearance groove 337 and abuts against the top surface of the rotating member 33. The clearance groove 337 is either closed (completely isolated from the outside) or semi-closed (part of the clearance groove 337 is connected to the outside).

[0070] The rotating component 33 has a closed clearance groove 337 (i.e., the clearance groove 337 is completely isolated from the outside). The locking component 41 is provided with a rotation limiter 418. When the locking component 4 is in the unlocked state, the rotation limiter 418 abuts against the connecting base 31, limiting the angle of the locking part 411. This prevents the locking part 411 from rotating excessively due to the elastic force of the elastic member 42 when the unlocked state is in the unlocked state. As a result, when the rotating component 33 rotates and the included angle between the rotating component 33 and the connecting base 31 decreases, the clearance groove 337 cannot be aligned with the locking part 411. This facilitates the connection between the locking part 411 and the rotating component 33 when the drone parts are installed, while also ensuring the seal within the connecting base 31 (the sealed clearance groove 337 results in a smaller exposed area from the rotating component 33).

[0071] The locking component 41 is provided with a limiting arm 412. When the locking component 4 is in the locked state, the rotating component 33 is in contact with the limiting arm 412. As the rotating component 33 rotates, the angle between the rotating component 33 and the connecting base 31 decreases, which ensures the positioning of the rotating component 33 and makes the top surface of the rotating component 33 approximately horizontal.

[0072] The drone quick-assembly and disassembly structure of the second embodiment of the present invention is generally used in situations requiring greater connection strength, such as the disassembly and assembly of components of a larger drone.

[0073] As a specific embodiment, the second embodiment of the UAV quick-assembly and disassembly structure of the present invention includes a connected base 1 and a quick-assembly and disassembly component 2.

[0074] The connected base 1 is provided with a hook 13; the hook 13 is provided with a hook opening 131 and a connecting cavity 132 communicating with the hook opening 131, and the hook opening 131 is connected to the outside.

[0075] The quick-release assembly 2 includes a connecting assembly 3; the connecting assembly 3 includes a connecting base 31, a rotating part 33, and a hook connector 34 that is hinged to the connecting base 31.

[0076] The connecting assembly 3 also includes a second base 319, to which the hook connector 34 is hinged. The second base 319 can be separate from or integrated with the connecting base 31. In use, the second base 319 and the connecting base 31 are respectively fixed to components of the drone, ensuring relative fixation between them, thereby allowing the hook connector 34 to be hinged to the connecting base 31. When the second base 319 is separate from the connecting base 31, the connecting base 31 can be made smaller, reducing costs and facilitating installation.

[0077] The rotating component 33 is hinged to the connecting base 31 (the rotating component 33 and the connecting base 31 are hinged through the base hinge shaft 338 embedded in the hinge ear 318).

[0078] The hook connector 34 is provided with a hook connector body 343 with a circular cross section. The hook connector 34 is provided with a connecting notch surface 349 or parallel connecting notch surfaces 349 (the case of two parallel connecting notch surfaces 349 is not shown in the attached figure).

[0079] The width of the connection between the hook opening 131 and the connecting cavity 132 is the hook opening width 138.

[0080] The minimum thickness between the connecting notch surfaces 349 is the connecting body thickness 348; when the connecting notch surfaces 349 are parallel to each other, the connecting body thickness 348 is the minimum vertical distance between the two connecting notch surfaces 349; when there is only one connecting notch surface 349, the connecting body thickness 348 is the straight-line distance through the center of the cross-section of the hook connecting body 343.

[0081] Then the following conditions are met: the hook opening width 138 is less than the connector thickness 348, and the connector thickness 348 is less than the diameter of the hook connector 343.

[0082] The rotating component 33 is connected to the hook connector 343, so that the rotating component 33 can drive the hook connector 343 to rotate.

[0083] The hook connector 343 is embedded in the connecting cavity 132. At this time, the connecting notch surface 349 is offset from the hook opening 131. The thickness of the connector 348 is smaller than the diameter of the hook connector 343, so that the hook connector 343 cannot pass through the hook opening 131 and is kept in the connecting cavity 132. The connecting component 3 is in the connected state.

[0084] Rotate the rotating component 33, which drives the hook connector 343 to rotate until the connecting notch surface 349 is aligned with the hook opening 131. The width of the hook opening 138 is smaller than the thickness of the connector 348, allowing the hook connector 343 to pass through the hook opening 131. At this point, the connecting component 3 is in a disassembled state. Then, move the drone components (i.e., the first component and the second component of the drone) along the hook opening 131 to separate the drone components from each other, enabling convenient and quick disassembly and installation of drone components.

[0085] The hook connector 34 also includes a first linkage rod 341 hinged to the connecting base 31. A rotating member 33 is connected to the first linkage rod 341, enabling the rotating member 33 to drive the hook connector 343 to rotate. Multiple hook connectors 343 are respectively fixed to the first linkage rod 341. Multiple connected bases 1 correspond to the hook connectors 343. This design enables multiple connections between drone components, improving connection strength. Simultaneously, rotating one connecting base 31 allows operation of multiple hook connectors 343, facilitating convenient and quick disassembly and installation of drone components.

[0086] The hook connector 34 also includes a second linkage rod 342 hinged to the connecting base 31. The rotating member 33 is connected to the second linkage rod 342, enabling the rotating member 33 to drive the hook connector 343 to rotate. Multiple hook connectors 343 are respectively fixed to the second linkage rod 342. In a specific embodiment, there are multiple second linkage rods 342. This enables multiple sets (one linkage rod corresponds to one set of connections) of UAV components, improving connection strength.

[0087] The hook connector 34 also includes a rotary transmission rod 345 and a rotary output rod 344 fixedly connected to the rotating component 33. The rotary output rod 344 is hinged to one of a set of rotary transmission rods 345 (two rotary transmission rods 345 hinged to each other form a set). The other rotary transmission rod 345 in the set is fixedly connected to the first linkage rod 341 and the second linkage rod 342 respectively. Rotating one connecting base 31 can operate multiple sets of hook connectors 343, which can facilitate the quick and easy disassembly and installation of drone parts.

[0088] The rotating component 33 is fixedly provided with a connecting socket 334, and the rotating output rod 344 is inserted into the connecting socket 334. A bolt passes through the connecting socket 334 and abuts against the rotating output rod 344, so that the rotating component 33 and the rotating output rod 344 can be detachably connected.

[0089] An acute angle (e.g., between the bolts on the bottom end face of the rotating part 33) is provided. Figure 12 (i.e., an acute angle located in the fourth quadrant). When the rotating part 33 is opened and the bolt is rotated with a screwdriver, the rotating part 33 will not interfere with the screwdriver or other tools, making it easy to install the connecting component 3.

[0090] The rotating component 33 is plate-shaped, and its top surface is roughly flush with the top surface of the connecting base 31. The rotating component 33 is provided with reinforcing ribs 333 to improve its strength.

[0091] The terms used in this invention, such as "first," "second," etc., do not indicate any order, quantity, or importance, but are merely for distinction.

[0092] In this invention, terms such as "a," "an," etc., do not indicate a limitation on the quantity, but rather indicate the existence of at least one of the mentioned objects.

[0093] In this invention, terms indicating orientation or location such as top, bottom, side, longitudinal, transverse, middle, center, outside, inside, horizontal, vertical, left, right, above, below, etc., are used to indicate relative positions rather than absolute positions.

[0094] Terms used in this invention, such as "approximately," "generally," "approximately," and "similar," are limiting terms used to indicate features that are present but allow for certain deviations. The amount of deviation allowed may vary depending on the specific context; for example, for deviations in dimensions, the specific context may include, but is not limited to, national standards for dimensional tolerances.

Claims

1. A locking structure of a UAV disassembly structure, comprising a connected base (1) and a quick disassembly component (2); the connected base (1) is provided with a connecting lug (11); the quick disassembly component (2) comprises a connecting component (3) and a locking component (4); the connecting component (3) comprises a connecting base (31), a connecting tongue (32) and a rotating member (33) for outputting power; the connecting tongue (32) is provided with a tongue abutting body (321) and is hinged with the rotating member (33); the tongue abutting body (321) abuts against the connecting lug (11), and an axis of the rotating member (33) hinged with the connecting base (31) is located between an axis of the connecting tongue (32) hinged with the rotating member (33) and the connecting lug (11); the locking component (4) comprises a locking member (41) hinged with the connecting base (31), and further comprises a locking pin shaft (49), the locking member (41) is hinged with the connecting base (31) through the locking pin shaft (49), the locking member (41) is provided with a locking portion (411), and when the connecting component (3) is in a connected state, the locking portion (411) abuts against the rotating member (33) to prevent an included angle between the rotating member (33) and the connecting base (31) from increasing; the locking portion (411) is a buckle and abuts against a top end surface of the rotating member (33); the locking member (41) is fixedly provided with a lifting protrusion (413), and the lifting protrusion (413) is located below the rotating member (33); when the locking component (4) is in a locked state, a buffer gap (414) is arranged between the lifting protrusion (413) and a bottom end surface of the rotating member (33); the buffer gap (414) corresponds to a lifting angle (416), a point at which the lifting protrusion (413) can abut against the rotating member (33) is a lifting point (415), and a point at which the lifting point (415), the locking pin shaft (49) and the point at which the lifting protrusion (413) can abut against the rotating member (33) are sequentially connected to form an included angle, which is the lifting angle (416); the locking portion (411) corresponds to a giving angle (417), a point at which an overlapping part of the rotating member (33) and the locking portion (411) farthest away from an axis of a base hinging shaft (338) is a farthest point (335) when viewed from above, a point of the locking portion (411) closest to the axis of the base hinging shaft (338) is a giving point (47), an intersection of a circle formed by the giving point (47) rotating around an axis of the locking pin shaft (49) and a circle formed by the farthest point (335) rotating around the axis of the base hinging shaft (338) is a critical point (48), and an included angle formed by the giving point (47), the axis of the locking pin shaft (49) and the critical point (48) sequentially connected is the giving angle (417), and the giving angle (417) is less than or equal to the lifting angle (416). characterized in that The locking component (4) further comprises a retaining elastic member (42), and the retaining elastic member (42) is connected with the rotating member (33) respectively, so that the locking portion (411) has a tendency to rotate towards the connecting lug (11).

2. The locking structure of the unmanned aerial vehicle disassembly structure according to claim 1, wherein ​ 3. The locking structure of the unmanned aerial vehicle disassembly structure according to claim 2, wherein The retaining elastic member (42) comprises a first elastic end (421), a coiled section (423) and a second elastic end (422) connected in sequence; a locking pin shaft (49) penetrates through the coiled section (423), and the first elastic end (421) and the second elastic end (422) are respectively in abutment with the locking member (41) and the connecting base (31).

4. The locking structure of the unmanned aerial vehicle disassembly structure according to claim 1, wherein The rotating member (33) is provided with a closed accommodation slot (337), the locking member (41) is provided with a rotating limiting body (418), and when the locking assembly (4) is in an unlocked state, the rotating limiting body (418) is in abutment with the connecting base (31).

5. The locking structure of the unmanned aerial vehicle disassembly structure according to claim 1, wherein The locking member (41) is provided with a limiting arm (412), and when the locking assembly (4) is in a locked state, the rotating member (33) is in abutment with the limiting arm (412).

Images