An unmanned aerial vehicle task load locking device

Abstract

The utility model relates to unmanned aerial vehicle load technical field, concretely points to a kind of unmanned aerial vehicle task load locking device, including locking structure, locking structure includes fastening frame structure and lock catch structure;Fastening frame structure includes annular frame, is equipped with opening in annular frame below, there is receiving ring groove, plug-in ring groove in annular frame, there is limit rod in receiving ring groove, there is stopper in receiving ring groove, annular frame outside is fixed with with transmission frame;Lock catch structure both sides are equipped with with limit rod cooperation annular groove, lock catch structure upside is equipped with with stopper cooperation recess, lock catch structure one end side surface is equipped with through-hole, transmission structure is equipped between lock catch structure and fastening frame structure (1), positioning structure is equipped between lock catch structure and plug-in ring groove.The utility model has solved the problem that the existing to weak vibration resistance airflow resistance ability of clamping type structure, easy to loosen and fall off, manual disassembly and assembly time-consuming, difficult to adapt to emergency replacement;Rigid deficiency of connecting rod structure, flight vibration is easy to cause deformation, destroys transmission link.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) payload technology, specifically to a UAV mission payload locking device. Background Technology

[0002] With the widespread application of drone technology in fields such as aerial surveying and mapping, power line inspection, and emergency rescue, the demand for installation stability and rapid assembly / disassembly of mission payloads is becoming increasingly prominent.

[0003] The locking structures in existing technologies are generally clamp-type structures. During flight, vibrations and airflow impacts can easily disrupt the force balance on both sides of the clamp-type structure, causing the lock to loosen or even the load to fall off. It often requires manual adjustment of bolts or clips to tighten or loosen the clamp, which is time-consuming and cannot meet the rapid changeover requirements of UAV emergency operations. Furthermore, most of them are linkage structures, and the rigidity of the linkage is insufficient. Severe vibrations during flight may cause the linkage to deform and damage the transmission link. Utility Model Content

[0004] The technical problem this invention aims to solve is that existing clamp-type structures have weak vibration and airflow resistance, are prone to loosening and falling off, require time-consuming manual disassembly and assembly, and are difficult to adapt to emergency replacements; the linkage structure lacks rigidity, and is prone to deformation due to flight vibrations, which can damage the transmission link.

[0005] To solve the above problems, the technical solution adopted by this utility model is a UAV mission payload locking device, including a locking structure, which includes a fastening frame structure and a latching structure.

[0006] The fastening frame structure includes an annular frame with an opening at the bottom. A receiving annular groove is provided at one end of the annular frame, and an insertion annular groove is provided at the other end of the annular frame. Limiting rods are symmetrically fixed on both sides of one end of the receiving annular groove, and a stop block is fixed on one side of one end of the receiving annular groove. A transmission frame connected to the receiving annular groove is fixed on the outside of the annular frame.

[0007] Both sides of the locking structure have annular grooves that cooperate with the limiting rod to prevent the locking structure from disengaging from the receiving annular groove. The upper side of the locking structure has a groove that cooperates with the stop block to facilitate stable movement of the locking structure. One end of the locking structure has a through hole to facilitate locking and positioning with the positioning rod. A transmission structure is provided between the locking structure and the fastening frame structure, and a positioning structure is provided between the locking structure and the insertion annular groove.

[0008] As a further embodiment of this utility model: the arc length of the receiving ring groove is equal to the arc length of the locking structure, which facilitates its storage; the arc length of the locking structure is greater than the opening width, which facilitates locking.

[0009] As a further embodiment of this utility model: a locking hole is provided on one side of the annular frame at the through hole, which facilitates locking and positioning with the positioning rod.

[0010] As a further embodiment of this utility model: the transmission structure includes a gear rotatably disposed inside the transmission frame, and a tooth groove that meshes with the gear is opened on the outer side of the locking structure. A micro motor is fixed on one side of the transmission frame, and the output end of the micro motor is fixed to one side of the gear. The micro motor drives the gear to rotate, which can drive the locking structure to move along the receiving ring groove.

[0011] As a further embodiment of this utility model: the positioning structure includes a telescopic rod fixed to one side of the annular frame, a connecting plate fixed to one end of the telescopic rod, and a positioning rod inserted into the locking hole and the through hole fixed to one side of the connecting plate. The telescopic rod can drive the positioning rod to move, so as to facilitate insertion into and release from the locking hole and the through hole.

[0012] As a further embodiment of this utility model: a connecting frame is fixed at the top of the annular frame, and a battery and a control unit are provided inside the connecting frame. The battery and the control power supply are electrically connected to the micro motor and the telescopic rod, which facilitates the control of the opening, closing and locking of the latch structure.

[0013] Compared with the prior art, the advantages of this utility model are as follows: 1. This application achieves all-round circumferential load bearing by using the ring-shaped frame and the locking structure in a ring-shaped fit design, combined with the precise positioning of the limiting rod and the ring groove, the stop block and the groove, avoiding uneven local load bearing, effectively resisting flight vibration and airflow impact, and completely solving the hidden danger of loosening and falling off; 2. It adds a gear and tooth groove meshing transmission to replace the linkage mechanism. The gear transmission has stronger rigidity, more accurate transmission ratio, no cumulative backlash and assembly error, and the transmission structure is enclosed in the transmission frame, which can effectively resist the intrusion of dust and foreign objects and avoid the damage to the transmission link caused by vibration. Attached Figure Description

[0014] The accompanying drawings are provided to further illustrate the present invention and form part of the specification. They are used together with the embodiments of the present invention to explain the present invention, but do not constitute a limitation thereof. In the drawings:

[0015] Figure 1 This is a perspective view of the overall structure of a drone mission payload locking device according to the present invention.

[0016] Figure 2 This is a cross-sectional view of the overall structure of a UAV mission payload locking device according to the present invention.

[0017] Figure 3 This is a partial structural cross-section of a UAV mission payload locking device according to the present invention. Figure 1 .

[0018] Figure 4 This is a partial structural cross-section of a UAV mission payload locking device according to the present invention. Figure 2 .

[0019] Figure 5 This is a partial structural cross-section of a UAV mission payload locking device according to the present invention. Figure 3 .

[0020] Figure 6 This is a partial cross-sectional view of the locking structure in a UAV mission payload locking device according to the present invention.

[0021] In the attached image:

[0022] 1. Fastening frame structure; 11. Annular frame; 12. Opening; 13. Receiving ring groove; 14. Insertion ring groove; 15. Limiting rod; 16. Stop block; 17. Transmission frame; 18. Locking hole;

[0023] 2. Locking structure; 21. Annular groove; 22. Groove; 23. Through hole;

[0024] 3. Transmission structure; 31. Gear; 32. Tooth groove; 33. Miniature motor;

[0025] 4. Positioning structure; 41. Telescopic rod; 42. Connecting plate; 43. Positioning rod;

[0026] 5. Connecting frame; 51. Battery; 52. Control unit. Detailed Implementation

[0027] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0028] This utility model provides a technical solution to address the existing problems mentioned in the background art.

[0029] Combined with appendix Figure 1 , 2 4. First, assemble the components. Fix the connecting frame 5 to the top of the annular frame 11 of the fastening frame structure 1. Install the battery 51 and the control unit 52 inside the connecting frame 5. Weld the transmission frame 17, which is connected to the storage ring groove 13, to the outside of the annular frame 11. Rotate the gear 31 through the shaft to the inside of the transmission frame 17. Fix the micro motor 33 to one side of the transmission frame 17 with bolts. Weld the output end of the micro motor 33 to one side of the gear 31. Weld the limiting rods 15 symmetrically to the two sides of one end of the storage ring groove 13 inside the annular frame 11. Weld the stop block 16 to one side of one end of the storage ring groove 13. Open the locking hole 18 on one side of the annular frame 11 at the corresponding position of the through hole 23.

[0030] Combined with appendix Figure 4-6 The telescopic rod 41 of the positioning structure 4 is fixed to one side of the annular frame 11 by bolts. The telescopic end of the telescopic rod 41 is welded to the connecting plate 42. The positioning rod 43 is welded to one side of the connecting plate 42. The size of the positioning rod 43 is adapted to the locking hole 18 and the through hole 23. The annular grooves 21 on both sides of the locking structure 2 are slidably engaged with the limiting rod 15 in the receiving annular groove 13 to install the locking structure 2 into the receiving annular groove 13. This ensures that the tooth groove 32 on the outside of the locking structure 2 meshes with the gear 31 in the transmission frame 17. At the same time, the groove 22 on the upper side of the locking structure 2 is slidably adapted to the stop block 16 to ensure that the locking structure 2 can move stably along the receiving annular groove 13 without disengaging. The arc length of the receiving annular groove 13 is equal to the arc length of the locking structure 2 to ensure that the locking structure 2 can be completely received into the receiving annular groove 13. The arc length of the locking structure 2 is greater than the width of the opening 12 below the annular frame 11, providing a structural basis for subsequent locking.

[0031] Combined with appendix Figure 2-6 The battery 51 and control unit 52 are electrically connected to the micro motor 33 and telescopic rod 41 respectively via wires to achieve power supply and linkage control. When the task load needs to be installed, the operator puts the task load into the annular frame 11 through the opening 12 below the annular frame 11. The operator sends a locking command to the control unit 52 through the UAV control system or independent control terminal. After receiving the command, the control unit 52 starts the micro motor 33. The micro motor 33 drives the gear 31 to rotate clockwise. The gear 31 meshes with the tooth groove 32 of the locking structure 2, driving the locking structure 2 to move along the receiving annular groove 13 towards the insertion annular groove 14. During the movement, the locking structure 2 slides along the limiting rod 15 through the annular groove 21, and the groove 22 is guided along the stop block 16 to ensure accurate movement trajectory until one end of the locking structure 2 is attached to the outside of the task load and the locking structure 2 completely covers the opening 12 of the annular frame 11. At this time, the side of one end of the locking structure 2 is closed. The through hole 23 is coaxially aligned with the locking hole 18 of the annular frame 11. The control unit 52 then controls the telescopic rod 41 to extend. The telescopic rod 41 pushes the connecting plate 42 and the positioning rod 43 to move towards the locking hole 18. The positioning rod 43 is inserted into the locking hole 18 and the through hole 23 in sequence to complete the positioning and locking of the locking structure 2, thereby achieving circumferential fixation of the task load. When it is necessary to disassemble the task load, an unlocking command is sent to the control unit 52 through the control terminal. The control unit 52 first controls the telescopic rod 41 to retract. The telescopic rod 41 drives the connecting plate 42 and the positioning rod 43 to move in the opposite direction, so that the positioning rod 43 is completely disengaged from the through hole 23 and the locking hole 18. After the positioning restriction is released, the control unit 52 controls the micro motor 33 to rotate counterclockwise. The gear 31 drives the locking structure 2 to retract along the receiving annular groove 13 in the opposite direction until the locking structure 2 is completely received in the receiving annular groove 13. The opening 12 below the annular frame 11 opens, and the operator can take out the task load.

[0032] The working principle of this application is as follows: Based on gear meshing transmission and a dual-positioning locking mechanism, the control unit 52 coordinates the working states of the micro motor 33 and the telescopic rod 41 to achieve automated locking and unlocking of the task load. During locking, after receiving the locking command, the control unit 52 controls the battery 51 to supply power to the micro motor 33. The micro motor 33 outputs torque to drive the gear 31 within the transmission frame 17 to rotate. Because the locking structure 2 is slidably limited by the annular groove 21 and the limiting rod 15, and the tooth groove 32 meshes with the gear 31, the rotational motion of the gear 31 is converted into linear movement of the locking structure 2 along the receiving annular groove 13. The cooperation between the stop block 16 and the groove 22 further ensures the stability of the movement of the locking structure 2. Utilizing the design that the arc length of the locking structure 2 is greater than the width of the opening 12, the opening 12 is gradually closed during movement, forming a circumferential wrapping around the task load within the annular frame 11, preventing… To address the issue of uneven localized force in traditional clamp-type structures, when the through hole 23 aligns with the locking hole 18, the control unit 52 controls the extension rod 41 to extend, and the positioning rod 43 inserts into the two holes to form a secondary positioning. This double-fixing structure effectively resists flight vibrations and airflow impacts, preventing the load from loosening and falling off. During the unlocking process, the control unit 52 first controls the extension rod 41 to retract, and after the positioning rod 43 disengages, it releases the positioning restriction of the locking structure 2. Then, it controls the micro motor 33 to rotate in the opposite direction, and the gear 31 drives the locking structure 2 to retract to the storage ring groove 13. The opening 12 opens to facilitate the loading and unloading of the load. The gear meshing transmission replaces the traditional linkage mechanism, improving transmission rigidity and accuracy, eliminating accumulated backlash, and the transmission structure is enclosed within the transmission frame 17, which can resist the intrusion of dust and foreign objects and avoid damage to the transmission link caused by vibration. The integrated battery 51 and control unit 52 enable rapid automated operation, meeting the rapid reloading needs of UAV emergency operations.

[0033] The present invention and its embodiments have been described above. This description is not restrictive, and the accompanying drawings are only one embodiment of the present invention; the actual structure is not limited thereto. In conclusion, if those skilled in the art are inspired by this description and design similar structures and embodiments without departing from the inventive spirit of the present invention, such designs should fall within the protection scope of the present invention.

Claims

1. A UAV mission payload locking device, characterized in that: It includes a locking structure, which includes a fastening frame structure (1) and a latching structure (2); The fastening frame structure (1) includes an annular frame (11), with an opening (12) at the bottom of the annular frame (11), a receiving annular groove (13) at one end of the annular frame (11), and a plug-in annular groove (14) at the other end of the annular frame (11). Limiting rods (15) are symmetrically fixed on both sides of one end of the receiving annular groove (13), and a stop block (16) is fixed on one side of one end of the receiving annular groove (13). A transmission frame (17) connected to the receiving annular groove (13) is fixed on the outside of the annular frame (11). Both sides of the locking structure (2) are provided with annular grooves (21) that cooperate with the limiting rod (15). The upper side of the locking structure (2) is provided with a groove (22) that cooperates with the stop block (16). One side of the locking structure (2) is provided with a through hole (23). A transmission structure (3) is provided between the locking structure (2) and the fastening frame structure (1). A positioning structure (4) is provided between the locking structure (2) and the insertion ring groove (14).

2. The UAV mission payload locking device according to claim 1, characterized in that: The arc length of the receiving ring groove (13) is equal to the arc length of the locking structure (2), and the arc length of the locking structure (2) is greater than the width of the opening (12).

3. The UAV mission payload locking device according to claim 1, characterized in that: A locking hole (18) is provided on one side of the annular frame (11) at the through hole (23).

4. The UAV mission payload locking device according to claim 1, characterized in that: The transmission structure (3) includes a gear (31) rotatably disposed inside the transmission frame (17), and a tooth groove (32) meshing with the gear (31) is provided on the outer side of the locking structure (2). A micro motor (33) is fixed on one side of the transmission frame (17), and the output end of the micro motor (33) is fixed to one side of the gear (31).

5. The UAV mission payload locking device according to claim 1, characterized in that: The positioning structure (4) includes a telescopic rod (41) fixed to one side of the annular frame (11), a connecting plate (42) fixed to one end of the telescopic rod (41), and a positioning rod (43) inserted into the locking hole (18) and the through hole (23) fixed to one side of the connecting plate (42).

6. The UAV mission payload locking device according to claim 1, characterized in that: The top of the annular frame (11) is fixed with a connecting frame (5), and a battery (51) and a control unit (52) are provided inside the connecting frame (5). The battery (51) and the control power supply are electrically connected to the micro motor (33) and the telescopic rod (41).

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