Quick release mechanism for load of unmanned aerial vehicle

Abstract

The utility model discloses an unmanned aerial vehicle load quick release mechanism, which comprises an upper cover plate, a rotating ring, an upper mounting seat, a lower cover plate, a lower mounting seat and a driving motor, an annular non-full circular step is arranged on the inner ring of the upper mounting seat and is used for mounting the rotating ring, and the upper cover plate is mounted at the upper end of the upper mounting seat and limits the axial movement of the rotating ring; a lower cover plate is mounted at the upper end of the lower mounting seat, a driving motor is mounted at the lower end, and a floating joint male head is mounted in the center; the device further comprises an unlocking mechanism, and the upper mounting base and the lower mounting base are quickly unlocked and disassembled through the unlocking mechanism. The unmanned aerial vehicle connecting device is compact in structure, small in size, light in weight, capable of conducting electrical connection while conducting mechanical connection, easy to operate and capable of achieving rapid mounting and dismounting of an unmanned aerial vehicle load.

Description

Technical Field

[0001] The present application relates to unmanned aerial vehicles and application fields, and in particular to a quick-release mechanism for a load on an unmanned aerial vehicle. Background Art

[0002] Due to the different functions and uses of drones, drones are often used as carriers to mount different devices such as gimbals, speakers, and lighting to expand the functions of drones.

[0003] Most existing UAV payload attachment modes involve mechanical connection followed by electrical secondary connection, which is cumbersome and time-consuming. In addition, most attachment structures are relatively complex, with large size and mass, which increases processing costs and affects the overall weight of the UAV. Summary of the invention

[0004] The purpose of the utility model is to provide a UAV load quick release mechanism to solve the problems raised in the above background technology.

[0005] To achieve the above object, the present invention provides the following technical solutions:

[0006] A quick-release mechanism for a drone load comprises an upper cover plate, a rotating ring, an upper mounting seat, a lower cover plate, a lower mounting seat, and a driving motor. The inner ring of the upper mounting seat is provided with an annular non-circular step for mounting the rotating ring. The upper cover plate is mounted on the upper end of the upper mounting seat and limits the axial movement of the rotating ring. The upper end of the lower mounting seat is mounted with the lower cover plate, the lower end is mounted with the driving motor, and the center is mounted with a floating joint male head. The unlocking mechanism is also included, and the upper mounting seat and the lower mounting seat are quickly unlocked and disassembled through the unlocking mechanism.

[0007] Preferably, the rotating ring is a flange structure with a notch, a limit hole is provided on the outer ring, and a pair of anti-fool columns of different sizes are provided on the lower end face. The anti-fool columns cooperate with the corresponding axial holes of the anti-fool holes of the lower cover plate, and a floating joint female head is installed in the center, and can rotate a certain angle in the circumferential direction of the mounting seat.

[0008] Preferably, an annular limiting flange is provided on the inner side of the lower end of the upper mounting seat.

[0009] Preferably, an annular hanging flange is provided on the outer ring of the lower mounting seat, and the lower mounting seat is connected to the annular limiting flange on the inner side of the lower end of the upper mounting seat through the hanging flange.

[0010] Preferably, the unlocking mechanism includes a guide block, a guide notch, a compression spring, a limit pin, a cylindrical boss, a transmission shaft, a circumferential guide groove, a rear limit pin, a button and a fixing block.

[0011] Preferably, the outer ring of the upper mounting seat is provided with a square mounting hole for installing a guide block, the mounting guide block is provided with a flange shape with a guide notch, the outer ring is provided with a compression spring, the inner ring is provided with a transmission shaft, the transmission shaft is a hollow cylindrical structure and has a circumferential guide groove, a front limit pin and a rear limit pin are respectively installed at the front and rear of the inner ring of the transmission shaft, and the outer rings of the front limit pin and the rear limit pin are provided with symmetrical cylindrical bosses.

[0012] Preferably, the cylindrical boss slides in the guide notch of the installation guide block and the circumferential guide groove of the transmission shaft, the rear limit pin is fixedly connected to the button, and the fixed block is installed on the upper mounting seat and limits the button from sliding outward.

[0013] Compared with the prior art, the beneficial effects of the utility model are:

[0014] The utility model discloses a UAV load quick-release mechanism, which has a compact structure, a small size, and a light weight. It performs electrical connection while performing mechanical connection, is easy to operate, and can realize quick mounting and dismounting of the UAV load. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is an exploded view of the utility model;

[0016] Figure 2 It is a front view and a full cross-sectional view of the utility model;

[0017] Figure 3 It is a schematic diagram of the mechanical docking part of the utility model;

[0018] Figure 4 This is a schematic diagram of the fool-proof principle of the utility model;

[0019] Figure 5 This is a schematic diagram of the rotating ring limiting hole of the utility model;

[0020] In the figure:

[0021] Upper cover plate 01, floating joint female head 02, rotating ring 03, anti-foolproof column 0301, limit hole 0302, upper mounting seat 04, limit flange 0401, lower cover plate 05, anti-foolproof hole 0501, floating joint male head 06, lower mounting seat 07, suspension flange 0701, drive motor 08, guide block 09, guide notch 0901, compression spring 10, front limit pin 11, cylindrical boss 1101, transmission shaft 12, circumferential guide groove 1201, rear limit pin 13, button 14, fixing block 15. DETAILED DESCRIPTION

[0022] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0023] See also Figure 1-5 , the utility model provides a technical solution:

[0024] A quick-release mechanism for a drone load, characterized in that it includes an upper cover plate 01, a floating joint female head 02, a rotating ring 03, an anti-fool column 0301, an upper mounting seat 04, a limit flange 0401, a lower cover plate 05, an anti-fool hole 0501, a floating joint male head 06, a lower mounting seat 07, a suspension flange 0701, a drive motor 08, a guide block 09, a compression spring 10, a limit pin 11, a transmission shaft 12, a button 13, and a fixing block 14.

[0025] An annular non-circular step is provided on the inner ring of the upper mounting seat 04 for mounting the rotating ring 03. The rotating ring 03 is a flange structure with a notch. A limiting hole 0302 is provided on the outer ring. A pair of anti-fool columns 0301 of different sizes are provided on the lower end face to cooperate with the corresponding axial holes of the anti-fool holes 0501 of the lower cover plate 05. A floating joint female head 02 is installed in the center and can rotate a certain angle in the circumferential direction of the mounting seat 04.

[0026] A pair of fool-proofing columns 0301 of different sizes are provided on the lower end surface of the rotating ring 03 to cooperate with the corresponding shaft holes of the fool-proofing holes 0501 of the lower cover 05, which can prevent the male and female heads of the floating connector from being inserted incorrectly and avoid damage to the electrical appliance.

[0027] The upper cover plate 01 is mounted on the upper end of the upper mounting seat 04 and limits the axial movement of the rotating ring 03 .

[0028] The floating joint male 06 is installed in the center of the lower mounting seat 07, and the outer ring is provided with an annular suspension flange 0701, the upper end is provided with a lower cover plate 05, the lower end is provided with a driving motor 08, and the inner side of the lower end of the upper mounting seat 04 is provided with an annular limiting flange 0401. The lower mounting seat 07 can be screwed into the upper mounting seat 04 at a certain angle, at which time the suspension flange 0701 and the limiting flange 0401 are in conflict with each other, and the limiting pin 11 is inserted into the limiting hole 0302 on the rotating ring 03 to achieve the relative fixation of the lower mounting seat 07 and the upper mounting seat 04.

[0029] The outer ring of the upper mounting seat 04 is provided with a square mounting hole for installing the guide block 09. The guide block 09 is provided with a flange shape with a guide notch 0901. The outer ring is installed with a compression spring 10, and the inner ring is installed with a transmission shaft 12. The transmission shaft 12 is a hollow cylindrical structure and has a circumferential guide groove 1201. The front and rear inner rings of the transmission shaft 12 are respectively installed with a front limit pin 11 and a rear limit pin 13. The outer rings of the front limit pin 11 and the rear limit pin 13 are provided with symmetrical cylindrical bosses 1101. The cylindrical bosses 1101 slide in the guide notch 0901 of the guide block 09 and the circumferential guide groove 1201 of the transmission shaft 12. The rear limit pin 13 is fixedly connected to the button 14. The fixing block 15 is installed on the upper mounting seat 04 and limits the button 14 from sliding outward. By pressing the button 14 , the rear limit pin 13 moves inward, driving the transmission shaft 12 to rotate, and the transmission shaft 12 drives the front limit pin 11 to move outward, and the front limit pin 11 escapes from the limit hole 0302 , thereby unlocking the lower mounting seat 07 on the upper mounting seat 04 .

[0030] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations of the present invention. A person skilled in the art may change, modify, replace and vary the above embodiments within the scope of the present invention.

Claims

1. A UAV load quick release mechanism, characterized by: The invention comprises an upper cover plate (01), a rotating ring (03), an upper mounting seat (04), a lower cover plate (05), a lower mounting seat (07), a driving motor (08) and an unlocking mechanism; an inner ring of the upper mounting seat (04) is provided with an annular non-circular step for mounting the rotating ring (03); the upper cover plate (01) is mounted on the upper end of the upper mounting seat (04) and limits the axial movement of the rotating ring (03); the upper end of the lower mounting seat (07) is mounted with a lower cover plate (05), the lower end is mounted with a driving motor (08), and a floating joint male head (06) is mounted in the center; the upper mounting seat (04) and the lower mounting seat (07) are quickly unlocked and disassembled through the unlocking mechanism.

2. The UAV load quick release mechanism according to claim 1, characterized in that: The rotating ring (03) is a flange structure with a notch, a limiting hole (0302) is provided on the outer ring, and a pair of anti-fool columns (0301) of different sizes are provided on the lower end surface. The anti-fool columns (0301) cooperate with the corresponding axial holes of the anti-fool holes (0501) of the lower cover plate (05), and a floating joint female head (02) is installed in the center, and can rotate a certain angle in the circumferential direction of the mounting seat (04).

3. The UAV load quick release mechanism according to claim 1, characterized in that: An annular limiting flange (0401) is provided on the inner side of the lower end of the upper mounting seat (04).

4. The UAV load quick release mechanism according to claim 1, characterized in that: The outer ring of the lower mounting seat (07) is provided with an annular hanging flange (0701), and the lower mounting seat (07) is connected to the annular limiting flange (0401) on the inner side of the lower end of the upper mounting seat (04) through the hanging flange (0701).

5. The UAV load quick release mechanism according to claim 2, characterized in that: The unlocking mechanism comprises a guide block (09), a guide notch (0901), a compression spring (10), a limit pin (11), a cylindrical boss (1101), a transmission shaft (12), a circumferential guide groove (1201), a rear limit pin (13), a button (14) and a fixing block (15).

6. The UAV load quick release mechanism according to claim 5, characterized in that: The outer ring of the upper mounting seat (04) is provided with a square mounting hole for mounting a guide block (09); the mounting guide block (09) is provided with a flange shape with a guide notch (0901); the outer ring is provided with a compression spring (10); the inner ring is provided with a transmission shaft (12); the transmission shaft (12) is a hollow cylindrical structure and has a circumferential guide groove (1201); a front limit pin (11) and a rear limit pin (13) are respectively installed at the front and rear of the inner ring of the transmission shaft (12); the outer rings of the front limit pin (11) and the rear limit pin (13) are provided with symmetrical cylindrical bosses (1101).

7. The UAV load quick release mechanism according to claim 6, characterized in that: The cylindrical boss (1101) slides in the guide notch (0901) of the installation guide block (09) and the circumferential guide groove (1201) of the transmission shaft (12), the rear limit pin (13) is fixedly connected to the button (14), and the fixed block (15) is installed on the upper mounting seat (04) and limits the button (14) from sliding outward.

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