Split type unmanned aerial vehicle and docking mechanism

Abstract

The utility model is applicable to the field of unmanned aerial vehicles, and provides a split unmanned aerial vehicle and a docking mechanism, the docking mechanism comprises a fixing unit mounted on a fuselage, a guide unit mounted on a wing, a stretching unit mounted on the guide unit, and an unlocking unit arranged on the stretching unit through a pin shaft. The technical problems that in the prior art, a fuselage and wings of an unmanned aerial vehicle cannot be disassembled, so that transportation is inconvenient, part of the unmanned aerial vehicle can be disassembled, but later assembly is difficult are solved.

Description

Technical Field

[0001] The utility model belongs to the field of unmanned aerial vehicles, and in particular relates to a split type unmanned aerial vehicle and a docking mechanism. Background Art

[0002] Currently, all drones are integrated. Due to the wings, transportation is extremely inconvenient. Therefore, drones need to be quickly disassembled and assembled to a certain extent to facilitate transportation. Therefore, the fuselage and wings of the drone need to be disassembled. After the disassembly, the docking structure needs to be reliable and easy to operate. Some of the drones on the market now have the wings and the fuselage directly fixed together, which greatly increases the packaging size, transportation costs and inconvenience of transportation; although some of the drones have been disassembled, they are disassembled by screwing. Each time the wings and the fuselage are disassembled, tools must be used for disassembly, and the screwing method is relatively time-consuming. Utility Model Content

[0003] The utility model aims to provide a split type UAV and a docking mechanism, aiming to solve the technical problems in the prior art that the fuselage and wings of the UAV cannot be separated, resulting in inconvenience in transportation, while the UAV can be separated but difficult to assemble later.

[0004] The utility model is implemented in this way, a docking mechanism of a split-type unmanned aerial vehicle, the docking mechanism includes a fixing unit installed on the fuselage, a guiding unit installed on the wing, a stretching unit installed on the guiding unit, and a locking and unlocking unit arranged on the stretching unit through a pin shaft.

[0005] A further technical solution of the utility model is: the docking mechanism also includes a damping unit installed on the stretching unit and penetrated by the stretching unit.

[0006] A further technical solution of the utility model is: the fixing unit comprises a bottom clamping seat, and a hook groove seat used in conjunction with the bottom clamping seat and having a hook groove on the top.

[0007] A further technical solution of the utility model is: the guide unit comprises a fixed bottom plate, and a guide seat which is arranged on the fixed bottom plate and has a through hole.

[0008] A further technical solution of the utility model is: the damping unit comprises a pad groove seat and a nylon pad arranged on the pad groove seat.

[0009] A further technical solution of the utility model is: the lock and unlock unit is a cam handle; and the nylon pad is a concave structure.

[0010] A further technical solution of the utility model is: the stretching unit comprises a pull head with a T-shaped structure, a pull rod with a connecting hole at the tail, and a screw connecting the pull head and the pull rod.

[0011] A further technical solution of the utility model is: the tail end of the pull head is an internal thread hole or an external thread, the front end of the pull rod is an internal thread hole or an external thread, and the screw rod is an external thread rod or an internal thread rod.

[0012] A further technical solution of the utility model is that the stretching unit is a draw hook with a T-shaped structure and a connecting hole at the tail.

[0013] Another object of the present invention is to provide a split-type UAV, which includes the docking mechanism, a fuselage, and wings; the wings are mounted on the fuselage through the docking mechanism.

[0014] The beneficial effects of the utility model are as follows: the docking mechanism can separate the fuselage and wings of the UAV, which is convenient for transportation, and has simple structure, simple operation, high practicality and convenient installation; and the overall versatility of the mechanism is relatively high, and the length and size of the stretching unit can be adjusted according to the size of the UAV and the deviation of the installation position. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a structural diagram of a docking mechanism of a split type UAV provided in an embodiment of the utility model;

[0016] Figure 2 It is an exploded view of a docking mechanism of a split type UAV provided by an embodiment of the utility model;

[0017] Figure 3 This is an exploded view of the installation of a docking mechanism of a split type UAV provided by an embodiment of the utility model;

[0018] Figure 4 This is a front cross-sectional view of a split-type UAV docking mechanism provided by an embodiment of the utility model after installation;

[0019] Figure 5 It is a side sectional view of a split-type UAV docking mechanism provided by an embodiment of the utility model after installation. DETAILED DESCRIPTION

[0020] Figure numerals: 1 - bottom card seat 2 - hook groove seat 3 - guide seat 4 - screw 5 - pad groove seat 6 - nylon pad 7 - lock and unlock unit 8 - fixing unit 9 - guide unit 10 - stretching unit 11 - damping unit 12 - fixed bottom plate 13 - pull head 14 - pull rod 15 - fuselage 16 - wing 17 - support seat.

[0021] like Figure 1 As shown in FIG. 5 , the utility model provides a docking mechanism for a split-type UAV, which includes a fixing unit 8 installed on a fuselage 15, a guiding unit 9 installed on a wing 16, a stretching unit 10 installed on the guiding unit 9, and a locking and unlocking unit 7 arranged on the stretching unit 10 via a pin shaft. The docking mechanism is installed in two parts, the first part is a fixed unit 8 installed on the frame of the fuselage 15, the second part is a guide unit 9 installed on the frame of the wing 16, a stretching unit 10 installed on the guide unit 9, and a lock and unlock unit 7 installed on the stretching unit 10. When the fuselage 15 and the wing 16 are assembled, the wing 16 is installed to the corresponding position of the fuselage 15. At this time, the stretching unit 10 is opposite to the fixed unit 8, and the front end of the stretching unit 10 extends into the fixed unit 8. At this time, the lock and unlock unit 7 is rotated to drive the stretching unit 10 to rotate, so that the stretching unit 10 is stuck on the fixed unit 8, and then the end of the lock and unlock unit 7 is pressed down to tighten the stretching unit 10 at the front end of the lock and unlock unit 7, so that the wing 16 is locked on the fuselage 15, and the guide unit 9 plays the role of installing the stretching unit 10 and limiting the stretching unit 10.

[0022] The fixing unit 8 includes a bottom card seat 1 and a hook slot seat 2 with a hook slot on the top thereof used in conjunction with the bottom card seat 1. The bottom card seat 1 and the hook slot seat 2 of the fixing unit 8 are connected together by screws and fixed to the frame of the fuselage 15, so that the fixing unit 8 can withstand a larger pulling force, and the fuselage 15 and the wing 16 will not be fixed firmly due to too small pulling force. At the same time, the fixing unit 8 is installed on the frame of the fuselage 15 in this way, which is also convenient for the later maintenance of the fixing unit 8.

[0023] The guide unit 9 includes a fixed bottom plate 12 and a guide seat 3 with a through hole disposed on the fixed bottom plate 12. The fixed bottom plate 12 of the guide unit 9 is fixed to the lower part of the wing 16 frame by screws to ensure the reliability and stability of docking with the fuselage 15. The guide seat 3 with a through hole is installed on the fixed bottom plate 12, firstly to provide a mounting position for the stretching unit 10, and secondly to avoid damage to the wing 16 frame during stretching, and to facilitate later maintenance.

[0024] The lock and unlock unit 7 is a cam handle. The cam handle is used to facilitate tightening the stretching unit 10, because when the cam handle is in the unlocked state, the stretching unit 10 can rotate with the cam handle, which makes locking the fuselage 15 and the wing 16 more convenient and quick, and saves the trouble caused by bolt fixing.

[0025] There are two ways to select the stretching unit 10, namely, an integrated type and a split type, which can be selected according to the type and needs of the drone.

[0026] Compared with the split stretching unit 10, the stretching unit 10 includes a pull head 13 with a T-shaped structure, a pull rod 14 with a connection hole at the tail, and a screw 15 connecting the pull head 13 and the pull rod 14. The tail end of the pull head 13 is an internal thread hole or an external thread, the front end of the pull rod 14 is an internal thread hole or an external thread, and the screw 15 is an external thread rod or an internal thread rod. The T-shaped pull head 13 of the stretching unit 10 serves to connect with the fixing unit 8. When fixing, the pull head 13 is inserted into the hook groove seat 2 through the hook groove, and then the pull head 13 is rotated to make the pull head 13 and the hook groove misaligned, and then the pull head 13 is limited in the hook groove seat 2, and the pull rod 14 is connected to the lock and unlock unit 7 through the connecting hole at the tail, and then the pull head 13 and the pull rod 14 are connected together through the screw 4, and the tail end of the pull head 13 can be made into an internal threaded hole or an external threaded structure, and the front end of the pull rod 14 can also be made into an internal threaded hole or an external threaded structure, and the screw 4 is relative to the tail end of the pull head 13. The structure and the front end structure of the pull rod 14 are made into corresponding adaptation structures, that is, if the pull head 13 and the pull rod 14 are both internally threaded holes, the screw rod 4 is an externally threaded rod; if the pull head 13 and the pull rod 14 are both externally threaded, the screw rod 4 is an internally threaded rod; if the pull head 13 is an internally threaded hole, the pull rod 14 is an externally threaded hole, and the screw rod 4 is adapted to the pull head 13 and the pull rod 14, then one end is an externally threaded rod adapted to the pull head 13, and the other end is an internally threaded rod adapted to the pull 14, and vice versa. Therefore, this split stretching unit 10 can appropriately adjust the length of the stretching unit 10 according to the stretching distance between the fuselage 15 and the wing 16, and is suitable for use in various types of split drones.

[0027] Compared with the integrated stretching unit 10, the stretching unit 10 is a draw hook with a T-shaped structure and a connection hole at the tail. This stretching unit 10 is also a T-shaped structure as a whole, and has the same function as the split stretching unit 10, but does not have the function of adjusting the length, and is suitable for drones with a fixed stretching distance between the fuselage 15 and the wing 16.

[0028] The docking mechanism further includes a damping unit 11 installed on the stretching unit 10 and penetrated by the stretching unit 10. The damping unit 11 includes a pad groove seat 5 and a nylon pad 6 arranged on the pad groove seat 5. The nylon pad 6 is a concave structure. The damping unit 11 acts as a gasket, effectively preventing the hard friction between the lock and unlock unit 7 and the guide unit 9. At the same time, the nylon pad 6 has a certain elasticity to ensure that the lock and unlock unit 7 is pressed to the bottom in the locked state, thereby ensuring the stability of the locked state.

[0029] When the fuselage 15 and the wing 16 are docked through the docking structure, the bottom card seat 1 and the hook slot seat 2 are fixed at the end of the fuselage 15, and the remaining guide units 9, stretching units 10, lock and unlock units 7 and damping units 11 are all at the end of the wing 16. By rotating the cam handle at the end of the wing 16 upward, the stretching unit 10 can obtain a certain amount of travel; rotating the cam handle left and right drives the T-shaped stretching unit 10 to rotate, and slides into the hook slot seat 2 after being flush with the one-line hook slot, and then rotates 90 degrees after sliding into the hook slot seat 2, so that the stretching unit 10 and the hook slot seat 2 are in a hook-stop state. In the hook-stop state, the cam handle is rotated downward again, and the wing 16 and the fuselage 15 are in a docking and pressing state; similarly, Rotate the cam handle left and right to drive the stretching unit 10 of the T-shaped structure to rotate, and slide out after being flush with the straight hook groove of the hook groove seat 2. The stretching unit 10 and the hook groove seat 2 are in a decoupled state, and the wing 16 and the fuselage 15 are in a loose docking state. The wing 16 and the fuselage 15 can be separated at any time. At the same time, it can also be used in conjunction with the support seat 17 during use, which can further increase the height of the cam handle so that the cam handle can be directly operated on the mounting position on the top of the wing 16 frame. The support seat 17 is used to increase the height because the wing 16 skin cannot withstand too much force alone. Therefore, the support seat 17 is installed on the wing 16 frame to prevent excessive extrusion and deformation from causing the skin to rupture.

[0030] The docking mechanism cleverly utilizes a rotating hook structure and a cam handle to allow the mechanism to obtain a certain preload force, perfectly solving the problem of rapid assembly and disassembly of the fuselage 15 and the wing 16. In terms of line docking, in order to save time, the manual flexible plug-in is changed to a plate-type hard connection.

[0031] A split-type UAV includes the docking mechanism, a fuselage 15, and wings 16; the wings 16 are mounted on the fuselage 15 through the docking mechanism.

[0032] This docking mechanism can separate the fuselage and wings of the drone for easy transportation. It also has a simple structure, simple operation, high practicality and easy installation. The overall versatility of the mechanism is relatively high, and the length and size of the stretching unit can be adjusted according to the size of the drone and the deviation of the installation position.

[0033] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A docking mechanism for a split type UAV, characterized in that: The docking mechanism comprises a fixing unit installed on the fuselage, a guiding unit installed on the wing, a stretching unit installed on the guiding unit, and a locking and unlocking unit arranged on the stretching unit through a pin shaft.

2. The docking mechanism according to claim 1, characterized in that: The docking mechanism further includes a damping unit installed on the stretching unit and penetrated by the stretching unit.

3. The docking mechanism according to claim 2, characterized in that: The fixing unit comprises a bottom card seat and a hook slot seat which cooperates with the bottom card seat and has a hook slot on the top.

4. The docking mechanism according to claim 3, characterized in that: The guide unit comprises a fixed bottom plate and a guide seat which is arranged on the fixed bottom plate and has a through hole.

5. The docking mechanism according to claim 4, characterized in that: The damping unit includes a pad groove seat and a nylon pad arranged on the pad groove seat.

6. The docking mechanism according to claim 5, characterized in that: The lock and unlock unit is a cam handle; the nylon pad is a concave structure.

7. The docking mechanism according to any one of claims 1 to 5, characterized in that: The stretching unit comprises a pull head with a T-shaped structure, a pull rod with a connecting hole at the tail, and a screw connecting the pull head and the pull rod.

8. The docking mechanism according to claim 7, characterized in that: The tail end of the pull head is an internal thread hole or an external thread, the front end of the pull rod is an internal thread hole or an external thread, and the screw rod is an external thread rod or an internal thread rod.

9. The docking mechanism according to any one of claims 1 to 5, characterized in that: The stretching unit is a draw hook with a T-shaped structure and a connecting hole at the tail.

10. A split type UAV, characterized in that: The split-type UAV includes the docking mechanism described in any one of claims 1 to 9, and also includes a fuselage and wings; the wings are mounted on the fuselage through the docking mechanism.

Images