Chemical defense rotor unmanned aerial vehicle mounting mechanism

Abstract

The utility model relates to the field of unmanned aerial vehicles, and discloses a chemical defense rotor unmanned aerial vehicle mounting mechanism which comprises an unmanned aerial vehicle body, a dismounting assembly is arranged on the lower surface of the unmanned aerial vehicle body, a buffer assembly is arranged at the right end of the unmanned aerial vehicle body, the dismounting assembly comprises a fixing shell, and the fixing shell is fixedly connected to the lower surface of the unmanned aerial vehicle body. A clamping jaw is in contact with the inner wall of the fixing shell, a first rectangular groove is formed in the right surface of the top end of the clamping jaw, a sliding plate is slidably connected to the rear surface of the fixing shell in a penetrating mode, the buffering assembly comprises a hinge block, and the hinge block is fixedly connected to the outer wall of the right end of the unmanned aerial vehicle body. According to the clamping jaw device, the clamping jaw can be fixed only by inserting the clamping jaw into the inner wall of the fixing shell and then starting the motor, the mode of rotating multiple sets of bolts is not needed, the clamping jaw device is rapid and convenient to use, the working efficiency is improved, meanwhile, when the clamping jaw loses efficacy and cannot throw objects, the clamping jaw can be limited through contact of the motor, the objects can be thrown, and practicability is improved.

Description

Technical Field

[0001] The utility model relates to the field of unmanned aerial vehicles, and in particular to a mounting mechanism for a chemical defense rotary-wing unmanned aerial vehicle. Background Art

[0002] A drone is an aircraft that does not require personnel to operate it. It is operated by a remote control, a pre-set route or an autonomous program. The chemical defense rotor drone has the characteristics of strong controllability, vertical take-off and landing, and hovering. Therefore, it is suitable for low-altitude, low-speed missions that require vertical take-off and landing, and hovering. The chemical defense rotor drone has a mounting mechanism at the bottom. The chemical defense rotor drones in the military can carry grenades, explosives, chemical defense detection equipment, rifle shooting, loudspeakers and other functions through the mounting mechanism at the bottom, providing combat capabilities for war.

[0003] In the prior art, the mounting mechanisms of some chemical-resistant rotorcraft UAVs are installed and fixed by multiple sets of bolts. When replacing different types of hooks, tools are required to rotate multiple sets of bolts for fixing, which is too inefficient. At the same time, the mounting mechanisms of some chemical-resistant rotorcraft UAVs may malfunction during use, making it impossible to throw out the mounted items, which may affect the use effect. Therefore, a chemical-resistant rotorcraft UAV mounting mechanism is proposed to solve the above problems. Utility Model Content

[0004] In order to make up for the above shortcomings, the utility model provides a chemical defense rotor UAV mounting mechanism, which aims to improve the problem that some chemical defense rotor UAV mounting mechanisms in the prior art are fixed to the UAV by multiple sets of bolts, which are too troublesome to disassemble and assemble and have low practicality.

[0005] In order to achieve the above-mentioned purpose, the utility model adopts the following technical scheme: a chemical defense rotor UAV mounting mechanism, including a UAV body, a disassembly and assembly component is arranged on the lower surface of the UAV body, a buffer component is arranged on the right end of the UAV body, the disassembly and assembly component includes a fixed shell, the fixed shell is fixedly connected to the lower surface of the UAV body, the inner wall of the fixed shell is in contact with a clamp, the right surface of the top of the clamp is provided with a rectangular groove, and a slide plate is slidably connected to the rear surface of the fixed shell.

[0006] As a further description of the above technical solution:

[0007] The buffer assembly includes a hinge block, which is fixedly connected to the outer wall of the right end of the drone body. A sliding rod is hinged on the inner wall of the bottom end of the hinge block. A sleeve is slidably connected to the outer wall of the sliding rod. Multiple groups of sliding rods are provided, and multiple groups of sliding rods are slidably connected to the lower surface of the sleeve. An air hole is opened on the rear surface of the sleeve.

[0008] As a further description of the above technical solution:

[0009] The left surface of the slide plate is fixedly connected to a limiting block, the left end of the limiting block contacts the inner wall of the rectangular groove 1, and the limiting block is slidably connected to the inner wall of the fixed shell.

[0010] As a further description of the above technical solution:

[0011] A bidirectional threaded rod is threadedly connected to the right surface of the rear end of the limit block, a motor is fixedly connected to the right surface of the bidirectional threaded rod, and a left surface of the front end of the motor is fixedly connected to the right surface of the rear end of the fixed shell.

[0012] As a further description of the above technical solution:

[0013] A round rod is slidably connected to the upper surface of the fixed shell, and the round rod is slidably connected to the lower surface of the drone body. A spring 1 is sleeved on the outer wall of the round rod, and one end of the spring 1 is fixedly connected to the inner wall of the drone body, and the other end of the spring 1 is fixedly connected to the lower surface of the round rod.

[0014] As a further description of the above technical solution:

[0015] A push plate is fixedly connected to the lower surface of the round rod, the push plate is slidably connected to the inner wall of the fixed shell, and the lower surface of the push plate contacts the upper surface of the clamping claw.

[0016] As a further description of the above technical solution:

[0017] The bottom ends of the multiple groups of sliding rods are hinged with concave blocks, the front surface of the concave blocks are elastically connected to the bottom plate through spring 2, the upper surface of the bottom plate is provided with rectangular groove 2, the concave blocks are slidably connected to the inner wall of rectangular groove 2, one end of spring 2 is fixedly connected to the inner wall of rectangular groove 2, and the other end of spring 2 is fixedly connected to the front surface of the concave block.

[0018] As a further description of the above technical solution:

[0019] A piston block is fixedly connected to the lower surface of the slide rod, and the piston block piston is connected to the inner wall of the sleeve. A spring three is sleeved on the outer wall of the slide rod, and one end of the spring three is fixedly connected to the upper surface of the piston block, and the other end of the spring three is fixedly connected to the upper surface of the piston block.

[0020] The utility model has the following beneficial effects:

[0021] 1. In the utility model, it is only necessary to insert the clamp into the inner wall of the fixed shell and then start the motor to fix the clamp, without rotating multiple sets of bolts. It is quick and convenient, and improves work efficiency. At the same time, when the clamp fails and objects cannot be thrown, the motor can be used to contact the limit of the clamp to perform throwing, thereby improving practicality.

[0022] 2. In the utility model, the buffer component is provided to ensure that the impact force on the drone is reduced when it lands and contacts the ground, thereby avoiding excessive impact force during landing that may damage the electronic components inside the drone, thereby improving the practicality and service life of the drone. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a schematic diagram of the three-dimensional structure of the overall device in the utility model;

[0024] Figure 2 It is a schematic diagram of the disassembled cross-section of the three-dimensional structure of the disassembly and assembly components in the utility model;

[0025] Figure 3 It is a schematic diagram of the disassembled cross-section of the three-dimensional structure of the sliding rod and the sleeve in the utility model;

[0026] Figure 4 For the utility model Figure 2 An enlarged schematic diagram of the three-dimensional structure of the A region.

[0027] Legend:

[0028] 1. UAV body; 2. Disassembly and assembly components; 21. Fixed shell; 22. Round rod; 23. Clamp; 24. Spring 1; 25. Rectangular groove 1; 26. Slide plate; 27. Limit block; 28. Bidirectional threaded rod; 29. ​​Motor; 210. Push plate; 3. Buffer assembly; 31. Bottom plate; 32. Articulated block; 33. Slide rod; 34. Sleeve; 35. Concave block; 36. Rectangular groove 2; 37. Spring 2; 38. Spring 3; 39. Piston block; 310. Air hole. DETAILED DESCRIPTION

[0029] 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.

[0030] Reference Figure 1 - Figure 2 , Figure 4The utility model provides an embodiment: a chemical defense rotor UAV mounting mechanism, including a UAV body 1, the UAV body 1 is a prior art, which is a chemical defense rotor UAV, and can be implemented by technicians in this field. Since it is a prior art, it will not be described in detail in this case. A disassembly and assembly component 2 is provided on the lower surface of the UAV body 1, and a buffer component 3 is provided on the right end of the UAV body 1. The disassembly and assembly component 2 includes a fixed shell 21, which is fixedly connected to the lower surface of the UAV body 1. The inner wall of the fixed shell 21 is in contact with a clamp 23, and the clamp 23 is a prior art. It is controlled to open and close by electronic components inside the UAV, and can be implemented by technicians in this field. Since it is a prior art, it will not be described in detail in this case. A rectangular groove 25 is provided on the right surface of the top of the clamp 23, and a slide plate 26 is slidably connected to the rear surface of the fixed shell 21.

[0031] Reference Figure 1 , Figure 3 The buffer assembly 3 includes a hinge block 32, which is fixedly connected to the outer wall of the right end of the drone body 1. A sliding rod 33 is hinged on the inner wall of the bottom end of the hinge block 32. A sleeve 34 is slidably connected to the outer wall of the sliding rod 33. There are multiple groups of sliding rods 33, and multiple groups of sliding rods 33 are slidably connected to the lower surface of the sleeve 34. An air hole 310 is opened on the rear surface of the sleeve 34. Multiple groups of sliding rods 33 are arranged to drive multiple groups of piston blocks 39 to perform piston movement on the inner wall of the sleeve 34. At the same time, by squeezing the air on the inner wall of the sleeve 34, the air squeezed by the air will flow through the air hole 310 and have a certain resistance. The resistance will offset the impact force of the drone body 1 falling and avoid damage to the electronic components inside the drone body 1.

[0032] Reference Figure 2 , Figure 4 The left surface of the slide plate 26 is fixedly connected to a limit block 27, and the left end of the limit block 27 contacts the inner wall of the rectangular groove 25. The limit block 27 is slidably connected to the inner wall of the fixed shell 21. The right surface of the rear end of the limit block 27 is threadedly connected with a bidirectional threaded rod 28. The bidirectional threaded rod 28 is a prior art. It makes two sets of threads with different rotation directions set at both ends of the outer wall. When rotating, the structure of the threaded connection on the outer walls at both ends will move relative or oppositely. At the same time, it has a certain self-locking characteristic to ensure the stability of the structural connection. The right surface of the bidirectional threaded rod 28 is fixedly connected to a motor 29. The motor 29 is a prior art and can be implemented by technicians in this field. Since it is a prior art, it will not be described in detail in this case. The left surface of the front end of the motor 29 is fixedly connected to the right surface of the rear end of the fixed shell 21.

[0033] Reference Figure 2 , Figure 4A round rod 22 is slidably connected to the upper surface of the fixed shell 21, and the round rod 22 is slidably connected to the lower surface of the drone body 1. A spring 24 is sleeved on the outer wall of the round rod 22. The spring 24 always pulls the round rod 22 downward by its own elasticity to ensure that when the clamp 23 is released from the limit, it will quickly pop out from the inner wall of the fixed shell 21 by the elasticity of the spring 24. One end of the spring 24 is fixedly connected to the inner wall of the drone body 1, and the other end of the spring 24 is fixedly connected to the lower surface of the round rod 22. A push plate 210 is fixedly connected to the lower surface of the round rod 22, and the push plate 210 is slidably connected to the inner wall of the fixed shell 21, and the lower surface of the push plate 210 contacts the upper surface of the clamp 23.

[0034] Reference Figure 1 , Figure 3 The bottom ends of the multiple groups of slide bars 33 are hinged with concave blocks 35, and the front surfaces of the concave blocks 35 are elastically connected to the bottom plate 31 through springs 37. The springs 37 themselves have a certain elasticity. When the drone body 1 falls and is subjected to impact force, the concave blocks 35 will slide on the inner wall of the rectangular groove 36 to squeeze or stretch the springs 37. The springs 37 will buffer the impact force through their own elasticity. A rectangular groove 36 is provided on the upper surface of the bottom plate 31. The concave blocks 35 are slidably connected to the inner wall of the rectangular groove 36. One end of the spring 37 is fixedly connected to the inner wall of the rectangular groove 36, and the other end of the spring 37 is fixedly connected to the front surface of the concave blocks 35.

[0035] Reference Figure 1 , Figure 3 A piston block 39 is fixedly connected to the lower surface of the slide rod 33. The piston of the piston block 39 is connected to the inner wall of the sleeve 34. A spring three 38 is sleeved on the outer wall of the slide rod 33. The spring three 38 can buffer the impact force through its own elasticity, thereby improving the buffering effect. One end of the spring three 38 is fixedly connected to the upper surface of the piston block 39, and the other end of the spring three 38 is fixedly connected to the upper surface of the piston block 39.

[0036] Working principle: When the clamping jaw 23 needs to be replaced during use, it is only necessary to start the motor 29, and the motor 29 will drive the bidirectional threaded rod 28 to rotate. At this time, the bidirectional threaded rod 28 will drive the slide plate 26 connected to its outer wall to move linearly, and the slide plate 26 will drive the limit block 27 to move until the limit block 27 is separated from the inner wall of the rectangular groove 25. At this time, the spring 24 will pull the round rod 22 downward through its own elasticity, and the round rod 22 will drive the push plate 210 to move downward to push the clamping jaw 23 out. When installing, it is only necessary to insert the top end of the clamping jaw 23 into the inner wall of the fixed shell 21. During the insertion process, the clamping jaw 23 will drive the push plate 210 to move, and the push plate 210 will drive the round rod 22 to move, and the round rod 22 will stretch the spring 24. When the clamping jaw 23 is completely inserted into the inner wall of the fixed shell 21, the motor 29 is started to drive the bidirectional threaded rod 28 to reverse. The latter structural coordination method is the same as above. When the clamping jaw 23 fails when the drone is parachuting, the object can be ejected by this method, which improves practicality.

[0037] When the drone body 1 lands, the bottom plate 31 will come into contact with the ground. At this time, the concave block 35 will slide on the inner wall of the rectangular groove 2 36, squeezing or stretching the spring 2 37. The spring 2 37 will buffer the impact force through its own elasticity. At the same time, the bottom ends of the multiple sets of slide bars 33 will rotate on the inner wall of the concave block 35, and the other set of slide bars 33 will rotate between the hinge block 32. The multiple sets of slide bars 33 will drive the piston block 39 to move on the inner wall of the sleeve 34, which offsets the impact force through the resistance generated by the air during squeezing. At the same time, the piston block 39 will stretch the spring 38, and the spring 38 will also buffer the impact force through its own elasticity. In this way, damage to the electronic components inside the drone body 1 can be avoided, thereby improving practicality.

[0038] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A chemical protection rotary wing UAV mounting mechanism, comprising a UAV body (1), characterized in that: The lower surface of the drone body (1) is provided with a disassembly assembly (2), the right end of the drone body (1) is provided with a buffer assembly (3), the disassembly assembly (2) comprises a fixed shell (21), the fixed shell (21) is fixedly connected to the lower surface of the drone body (1), the inner wall of the fixed shell (21) is in contact with a clamping claw (23), the right surface of the top end of the clamping claw (23) is provided with a rectangular groove (25), and the rear surface of the fixed shell (21) is penetrated by a sliding plate (26) for sliding connection.

2. The mounting mechanism for a chemical-resistant rotary-wing UAV according to claim 1 is characterized in that: The buffer assembly (3) comprises a hinge block (32), the hinge block (32) is fixedly connected to the outer wall of the right end of the drone body (1), a sliding rod (33) is hingedly connected to the inner wall of the bottom end of the hinge block (32), and a sleeve (34) is slidably connected to the outer wall of the sliding rod (33), and the sliding rod (33) is provided with a plurality of groups, and the plurality of groups of sliding rods (33) are slidably connected to the lower surface of the sleeve (34), and an air hole (310) is opened on the rear surface of the sleeve (34).

3. The mounting mechanism for a chemical-resistant rotary-wing UAV according to claim 1 is characterized in that: The left surface of the slide plate (26) is fixedly connected to a limiting block (27), the left end of the limiting block (27) contacts the inner wall of the rectangular groove (25), and the limiting block (27) is slidably connected to the inner wall of the fixed shell (21).

4. The mounting mechanism for a chemical-resistant rotary-wing UAV according to claim 3 is characterized in that: A bidirectional threaded rod (28) is threadedly connected to the right surface of the rear end of the limit block (27), a motor (29) is fixedly connected to the right surface of the bidirectional threaded rod (28), and a left surface of the front end of the motor (29) is fixedly connected to the right surface of the rear end of the fixed shell (21).

5. The mounting mechanism for a chemical-resistant rotary-wing UAV according to claim 1 is characterized in that: A round rod (22) is slidably connected to the upper surface of the fixed shell (21), and the round rod (22) is slidably connected to the lower surface of the drone body (1). A spring (24) is sleeved on the outer wall of the round rod (22), and one end of the spring (24) is fixedly connected to the inner wall of the drone body (1), and the other end of the spring (24) is fixedly connected to the lower surface of the round rod (22).

6. The mounting mechanism for a chemical-resistant rotary-wing UAV according to claim 5, characterized in that: A push plate (210) is fixedly connected to the lower surface of the round rod (22), and the push plate (210) is slidably connected to the inner wall of the fixed shell (21), and the lower surface of the push plate (210) contacts the upper surface of the clamping claw (23).

7. The mounting mechanism for a chemical-resistant rotary-wing UAV according to claim 2, characterized in that: A plurality of groups of the slide bars (33) are hingedly connected at the bottom end with a concave block (35), the front surface of the concave block (35) is elastically connected to the bottom plate (31) via a second spring (37), the upper surface of the bottom plate (31) is provided with a second rectangular groove (36), the concave block (35) is slidably connected to the inner wall of the second rectangular groove (36), one end of the second spring (37) is fixedly connected to the inner wall of the second rectangular groove (36), and the other end of the second spring (37) is fixedly connected to the front surface of the concave block (35).

8. The mounting mechanism for a chemical-resistant rotary-wing UAV according to claim 2, characterized in that: The lower surface of the slide rod (33) is fixedly connected to a piston block (39), the piston of the piston block (39) is connected to the inner wall of the sleeve (34), the outer wall of the slide rod (33) is sleeved with a spring three (38), one end of the spring three (38) is fixedly connected to the upper surface of the piston block (39), and the other end of the spring three (38) is fixedly connected to the upper surface of the piston block (39).

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