Unmanned aerial vehicle stable landing device applied to public safety

Abstract

The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle stable landing device applied to public safety, which comprises a vehicle body, and stable landing mechanisms are arranged on both sides of the bottom of the vehicle body; the stable landing mechanism comprises two first supporting plates, the two first supporting plates are symmetrically and fixedly connected to the side wall of the machine body, second supporting plates are slidably installed on the side walls of the two first supporting plates, and the bottom ends of the two second supporting plates are jointly and fixedly connected with a square shell. When the unmanned aerial vehicle is in a flying state and needs to land, the lengths of the two undercarriages can be flexibly adjusted, so that the unmanned aerial vehicle can adapt to smooth landing on an uneven ground as much as possible, for example, the unmanned aerial vehicle can land on a slope or an uneven ground, and the unmanned aerial vehicle is convenient to use. The bottoms of the two undercarriages of the unmanned aerial vehicle can expand to form two air bags, under the action of the air bags, the impact force can be reduced to a great extent when the unmanned aerial vehicle is in forced landing, and the unmanned aerial vehicle is prevented from being damaged.

Description

Technical Field

[0001] The present invention relates to the technical field of drones, and specifically to a drone smooth landing device applied to public safety. Background Art

[0002] A drone is an aircraft that can fly without human piloting and is controlled by a radio remote control device or an autonomous program. The application of drones in the field of public safety (such as emergency rescue, disaster investigation, security monitoring, etc.) is becoming increasingly widespread. Existing drones mainly rely on landing gears to achieve smooth landing on the ground.

[0003] However, the existing landing gears of drones are inconvenient to adjust the length during flight to adapt to the smooth landing on uneven ground. If an electric push rod is installed to control the elongation and shortening of the landing gear, since the electric push rod itself has a certain length and is relatively heavy, this will increase the space occupied by the drone and the resistance during flight; if a manually adjustable landing gear with variable length is used, the length cannot be adjusted during flight, and it is not convenient to use.

[0004] Secondly, when a drone encounters an emergency and needs to make an emergency landing, the bottom area of the existing landing gear is small and rigid, and the impact force generated when landing on the ground is likely to cause damage to the drone. At the same time, when making an emergency landing or normal use on the water surface or soft ground in the wild (soft ground such as snow, swamp), the drone will directly get waterlogged or stuck. If measures such as replacing and disassembling the corresponding landing gear are taken for different environments, the operation will be cumbersome. Summary of the Invention

[0005] The purpose of the present invention is to provide a drone smooth landing device applied to public safety to solve the problems raised in the above background art.

[0006] To achieve the above purpose, the present invention provides the following technical solution: A drone smooth landing device applied to public safety, including a fuselage, and smooth landing mechanisms are provided on both sides of the bottom of the fuselage;

[0007] The smooth landing mechanism includes two support plates I, the two support plates I are symmetrically and fixedly connected to the side wall of the fuselage, and support plates II are slidably installed on the side walls of the two support plates I. The bottom ends of the two support plates II are commonly fixedly connected to a square shell, and elastic mechanisms are provided between the two support plates II and the two support plates I respectively, and a retracting and extending mechanism is provided between the two support plates II and the fuselage. An expansion mechanism is provided on the square shell;

[0008] The expansion mechanism includes an airbag and two bottom plates. The airbag is fixedly connected to the inner top end of the square shell. The two bottom plates are symmetrically attached to the lower end face of the square shell, and elastic mechanisms are provided between the two bottom plates and the square shell. An inflation assembly is provided between the airbag and the second support plate.

[0009] Preferably, a T-shaped block is fixedly connected to the side wall of the first support plate corresponding to the second support plate, and the T-shaped block slidably penetrates into the side wall of the second support plate corresponding to the first support plate.

[0010] Preferably, the elastic mechanism includes a splicing block and a cylindrical groove. The splicing block is fixedly connected to the side wall of the second support plate near the square shell, and a sliding column is fixedly connected to the upper end of the splicing block. The sliding column slidably penetrates into the lower inner wall of the first support plate. The cylindrical groove is opened in the inner wall of the first support plate. A limiting disk is fixedly connected to the top end of the sliding column. The limiting disk is slidably matched with the cylindrical groove. A spring is fixedly connected between the upper end of the splicing block and the lower end of the first support plate. The spring is slidably sleeved on the outer wall of the sliding column.

[0011] Preferably, the retracting and extending mechanism includes a fixed block and a motor. The fixed block and the motor are respectively fixedly connected to the lower end of the machine body near the front and rear edges. A winding column is fixedly connected to the output shaft end of the motor. The end of the winding column away from the motor is rotatably connected to the rear end of the fixed block. Sliders are provided between the winding column and the two first support plates. A linkage mechanism is provided between the two sliders, the motor and the machine body. Pulling ropes are fixedly connected to the outer wall of the winding column corresponding to the two first support plates respectively. The ends of the two pulling ropes away from the winding column respectively pass through the two first support plates movably, and the ends of the two pulling ropes away from the winding column are respectively two T-shaped blocks, and the ends of the two pulling ropes away from the winding column are respectively fixedly connected to the upper ends of the two second support plates.

[0012] Preferably, the linkage mechanism includes two connecting blocks and two first gears. The two connecting blocks are fixedly connected to the lower end of the machine body near the fixed block and the motor respectively. A bidirectional lead screw is rotatably connected between the two connecting blocks, and a guide post is fixedly connected between the two connecting blocks. The guide post is located below the bidirectional lead screw. The two sliders are both threadedly sleeved on the outer wall of the bidirectional lead screw. The guide post movably penetrates through the two sliders. One of the first gears is fixedly sleeved on the outer output shaft of the motor, and the other first gear is fixedly sleeved on the outer wall of the bidirectional lead screw. The two first gears are meshed with each other.

[0013] Preferably, the elastic mechanism includes two grooves which are respectively formed at the front and rear edge positions of the bottom plate. The inner walls of the two grooves are fixedly connected with rotating columns. Rotating sleeves are sleeved on the outer walls of the two rotating columns. One end of each of the two L-shaped blocks away from the rotating column is fixedly connected to the lower edge position of the side wall of the square shell. Torsion springs are fixedly connected between the two L-shaped blocks and the two grooves respectively. The two torsion springs are respectively sleeved on the outer walls of the two rotating columns in a sliding manner.

[0014] Preferably, the inflation assembly includes a fixing plate. One end of the fixing plate is fixedly connected to the rear end of one of the second supporting plates. The other end of the fixing plate is fixedly connected with a high-pressure small gas cylinder. A connecting pipe is communicated between the air outlet end of the high-pressure small gas cylinder and the upper end surface of the airbag. The connecting pipe movably penetrates through the upper end of the square shell. The valve rotating end of the high-pressure small gas cylinder is fixedly connected with a second gear.

[0015] Preferably, a connecting frame is fixedly connected to the front end of one of the first supporting plates. A rack is fixedly connected to the end of the connecting frame away from the first supporting plate.

[0016] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0017] 1. Through the mutual cooperation of the smooth landing mechanism, elastic mechanism, retracting and deploying mechanism, expansion mechanism, elastic force mechanism and inflation assembly, when the drone is in a flying state and needs to land, the lengths of the two landing gears can be flexibly adjusted. A retractable pull rope is used as traction, and the components driving the movement of the pull rope are all hidden at the bottom of the drone. Moreover, the main driving part, the motor, is light in weight, so that it will not occupy too much space and will not increase the flight resistance of the drone too much. The drone can still fly smoothly, so that the drone can adapt to the smooth landing on uneven ground as much as possible. For example, on a slope or an uneven ground, it is convenient to use.

[0018] 2. When the drone needs to make an emergency landing, two airbags can expand at the bottoms of the two landing gears of the drone. Under the action of the airbags, the impact force can be greatly reduced when the drone makes an emergency landing, avoiding damage to the drone. Moreover, the airbags can also enable the drone to make a normal emergency landing on the water surface or soft ground (soft ground such as snow and swamp). The airbags can provide sufficient buoyancy and the contact area with the soft ground, avoiding the drone from getting water or getting stuck. The inflation mechanism of the airbags can also enable the drone to be conveniently used on the water surface or soft ground. Therefore, when facing different environments, there is no need to replace and disassemble the corresponding landing gears, and the operation is convenient. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 is a schematic diagram of the overall structure of the present invention;

[0020] Figure 2Bottom view of the present invention;

[0021] Figure 3 Of the present invention Figure 2 Enlarged view of the structure at position A;

[0022] Figure 4 Cross-sectional view of the first support plate, T-shaped block and second support plate of the present invention;

[0023] Figure 5 Of the present invention Figure 4 Enlarged view of the structure at position B;

[0024] Figure 6 Of the present invention Figure 4 Enlarged view of the structure at position C;

[0025] Figure 7 Cross-sectional view of the square shell of the present invention;

[0026] Figure 8 Of the present invention Figure 7 Enlarged view of the structure at position D.

[0027] In the attached drawings, the list of components represented by each reference numeral is as follows: 1, body; 2, first support plate; 3, fixing plate; 4, high-pressure small gas cylinder; 5, square shell; 6, second support plate; 7, bottom plate; 8, T-shaped block; 9, pulling rope; 10, first gear; 11, motor; 12, guide post; 13, bidirectional lead screw; 14, winding column; 15, slider; 16, fixed block; 17, connecting block; 18, connecting frame; 19, splicing block; 20, spring; 21, sliding post; 22, cylindrical groove; 23, limiting disc; 24, rack; 25, second gear; 26, connecting pipe; 27, airbag; 28, torsion spring; 29, L-shaped block; 30, rotating column; 31, groove. Detailed implementation manners

[0028] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0029] The present invention provides a technical solution: As Figures 1-8 shown, a drone steady landing device applied to public safety, including a body 1, and steady landing mechanisms are provided on both sides of the bottom of the body 1;

[0030] The stable landing mechanism includes two first support plates 2, which are symmetrically and fixedly connected to the side wall of the fuselage 1. The side walls of the two first support plates 2 are both slidably installed with second support plates 6. The bottom ends of the two second support plates 6 are jointly and fixedly connected with a square shell 5. Elastic mechanisms are provided between the two second support plates 6 and the two first support plates 2 respectively, and a retracting and extending mechanism is provided between the two second support plates 6 and the fuselage 1. An expansion mechanism is provided on the square shell 5;

[0031] The expansion mechanism includes an airbag 27 and two bottom plates 7. The airbag 27 is fixedly connected to the inner top end of the square shell 5. The two bottom plates 7 are symmetrically attached to the lower end surface of the square shell 5. Elastic mechanisms are provided between the two bottom plates 7 and the square shell 5 respectively. An inflation assembly is provided between the airbag 27 and the second support plate 6.

[0032] A T-shaped block 8 is fixedly connected to the side wall of the first support plate 2 corresponding to the second support plate 6. The T-shaped block 8 is slidably inserted into the side wall of the second support plate 6 corresponding to the first support plate 2.

[0033] The elastic mechanism includes a splicing block 19 and a cylindrical groove 22. The splicing block 19 is fixedly connected to the side wall of the second support plate 6 near the square shell 5. The upper end of the splicing block 19 is fixedly connected with a sliding column 21. The sliding column 21 is slidably inserted into the lower inner wall of the first support plate 2. The cylindrical groove 22 is opened in the inner wall of the first support plate 2. The top end of the sliding column 21 is fixedly connected with a limit disk 23. The limit disk 23 is slidably matched with the cylindrical groove 22. A spring 20 is fixedly connected between the upper end of the splicing block 19 and the lower end of the first support plate 2. The spring 20 is slidably sleeved on the outer wall of the sliding column 21.

[0034] The retracting and extending mechanism includes a fixed block 16 and a motor 11. The fixed block 16 and the motor 11 are respectively fixedly connected to the front and rear edge positions near the lower end of the fuselage 1. The output shaft end of the motor 11 is fixedly connected with a winding column 14. The end of the winding column 14 far from the motor 11 is rotatably connected to the rear end of the fixed block 16. Sliders 15 are provided between the winding column 14 and the two first support plates 2 respectively. A linkage mechanism is provided between the two sliders 15, the motor 11 and the fuselage 1. Pulling ropes 9 are fixedly connected to the outer wall of the winding column 14 corresponding to the two first support plates 2 respectively. The ends of the two pulling ropes 9 far from the winding column 14 respectively pass through the two first support plates movably, and the ends of the two pulling ropes 9 far from the winding column 14 are respectively the two T-shaped blocks 8, and the ends of the two pulling ropes 9 far from the winding column 14 are respectively fixedly connected to the upper ends of the two second support plates 6.

[0035] The linkage mechanism includes two connecting blocks 17 and two first gears 10. The two connecting blocks 17 are fixedly connected to the lower end of the body 1 near the fixed block 16 and the motor 11 respectively. A bidirectional lead screw 13 is rotatably connected between the two connecting blocks 17, and a guide post 12 is fixedly connected between the two connecting blocks 17. The guide post 12 is located below the bidirectional lead screw 13. The two sliders 15 are both threadedly sleeved on the outer wall of the bidirectional lead screw 13, and the guide post 12 movably penetrates through the two sliders 15. One of the first gears 10 is fixedly sleeved on the output shaft of the motor 11, and the other first gear 10 is fixedly sleeved on the outer wall of the bidirectional lead screw 13. The two first gears 10 are meshed with each other.

[0036] The elastic mechanism includes two grooves 31. The two grooves 31 are respectively opened at the front and rear edge positions of the bottom plate 7, and the inner walls of the two grooves 31 are both fixedly connected with rotating columns 30. Rotating sleeves of L-shaped blocks 29 are sleeved on the outer walls of the two rotating columns 30. One ends of the two L-shaped blocks 29 far away from the rotating columns 30 are fixedly connected to the lower edge positions of the side walls of the square shell 5, and torsion springs 28 are fixedly connected between the two L-shaped blocks 29 and the two grooves 31 respectively. The two torsion springs 28 are respectively slidably sleeved on the outer walls of the two rotating columns 30.

[0037] The inflation assembly includes a fixing plate 3. One end of the fixing plate 3 is fixedly connected to the rear end of one of the second supporting plates 6, and the other end of the fixing plate 3 is fixedly connected with a high-pressure small gas cylinder 4. A connecting pipe 26 is communicated between the air outlet end of the high-pressure small gas cylinder 4 and the upper end surface of the airbag 27. The connecting pipe 26 movably penetrates through the upper end of the square shell 5. The valve rotating end of the high-pressure small gas cylinder 4 is fixedly connected with a second gear 25.

[0038] A connecting frame 18 is fixedly connected to the front end of one of the first supporting plates 2. One end of the connecting frame 18 far away from the first supporting plate 2 is fixedly connected with a rack 24.

[0039] Working principle: When the body 1 is in flight and needs to land, if it is desired to adjust the length of one of the landing gears, first start a motor 11 (the motor 11 can be electrically connected to the remote controller of the body 1, and the remote controller is used to control the start and stop of the motor 11, that is, the remote controller sends an electrical signal to the flight control system, and the flight control then triggers the drive circuit of the motor 11, which conforms to the typical control link of "remote controller - flight control - actuator" and belongs to the well-known remote control logic, so it will not be elaborated here). The motor 11 can drive a winding column 14 to rotate, and the motor 11 can also drive the second gear 25 connected thereto to rotate. This second gear 25 can drive another second gear 25 to rotate, and the other second gear 25 will drive the bidirectional lead screw 13 to rotate.

[0040] As described above, first, the winding column 14 can drive the two pulling ropes 9 to continuously wind around the outside of the winding column 14. Second, the rotation of the bidirectional lead screw 13 and the cooperation with the guide post 12 can drive the two sliders 15 to move closer to each other. The two sliders 15 will drive the pulling ropes 9 inside their respective sides to move together, so that the two pulling ropes 9 can be evenly stored outside the winding column 14, rather than being concentrated and stored in one place outside the winding column 14, which may cause the winding diameter of the pulling rope 9 to continuously increase and touch the body 1. Each pulling rope 9 will slide inside the corresponding support plate one 2 and the T-shaped block 8. The two pulling ropes 9 will also drive the corresponding support plate two 6 connected to them to slide upward along the corresponding T-shaped block 8. And each support plate two 6 will drive the splicing block 19 to move together. Each splicing block 19 will drive the corresponding sliding column 21 connected to it to slide upward inside the corresponding support plate one 2. Each sliding column 21 will drive the corresponding limit disk 23 connected to it to slide upward inside the corresponding cylindrical groove 22. And each splicing block 19 will squeeze the spring 20 connected between it and the corresponding support plate one 2. The two support plates two 6 can drive the square shell 5 to move upward, thereby shortening the length of the landing gear.

[0041] It should be noted that the length of the other landing gear is also adjusted as described above. Thus, when the body 1 is in flight and needs to land, the lengths of the two landing gears can be flexibly adjusted. Moreover, the retractable pulling rope 9 is used as the traction, and the components driving the movement of the pulling rope 9 Figure 2 are all arranged at the bottom of the body 1. And the main driving motor 11 is light in weight, so it will not occupy too much space and will not increase the flight resistance of the body 1 too much, and the body 1 can still fly smoothly. At the same time, under the action of the spring 20, after the winding column 14 stops rotating, the two support plates two 6 can remain stationary. And Figure 1 seen from this, the spring 20 is inclined while the square shell 5 is horizontal, that is, the spring 20 will not be squeezed when the square shell 5 lands vertically. To sum up, through the online length adjustment of the two landing gears, the body 1 can be made to adapt to the smooth landing on uneven ground as much as possible. For example, it is convenient to use on slopes or uneven ground.

[0042] When the aircraft body 1 needs to make an emergency landing: By starting all the motors 11, each support plate two 6 slides obliquely upward outside the corresponding T-shaped block 8. Two of the support plates two 6 will drive the high-pressure small gas cylinders 4 connected to them respectively to tilt upward together through the fixed plate 3 until the gears two 25 at the valve rotating ends of each high-pressure small gas cylinder 4 move to contact the two racks 24 respectively. During this process, the gears two 25 will mesh and rotate on the racks 24. Then, the motors 11 are turned off to stop the oblique upward movement of each support plate two 6. When the two gears two 25 rotate, they will drive the valve rotating ends of the corresponding high-pressure small gas cylinders 4 to rotate, thereby opening the valves of the two high-pressure small gas cylinders 4. At this time, the high-pressure air inside the two high-pressure small gas cylinders 4 will quickly enter the interiors of the two airbags 27 respectively through the connecting pipes 26, causing the two airbags 27 to expand rapidly. And the expansion force will push open the two bottom plates 7 under each square shell 5. During this process, the bottom plates 7 will drive the two rotating columns 30 to rotate within the corresponding L-shaped blocks 29 respectively and twist the torsion springs 28. Under the action of the two airbags 27, the impact force can be greatly reduced when the aircraft body 1 makes an emergency landing, avoiding damage to the aircraft body 1. Moreover, the two inflated airbags 27 can also enable the aircraft body 1 to make a normal emergency landing on the water surface or soft ground (soft ground such as snow, swamp). The airbags 27 can provide sufficient buoyancy and contact area with the soft ground, avoiding the aircraft body 1 from getting waterlogged or stuck. Secondly, the inflation mechanism of the airbags 27 can also make it convenient for the aircraft body 1 to be used normally on the water surface or soft ground. Thus, when facing different environments, there is no need to replace and disassemble the corresponding landing gear, and the operation is convenient.

[0043] It is worth mentioning that when the airbags 27 are stored inside the square shells 5, the two bottom plates 7 can seal the airbags 27 to prevent the airbags 27 from being outside the square shells 5 due to gravity and affecting the flight and landing of the aircraft body 1.

[0044] It should be noted that in this article, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the term "comprising", "including" or any other variant thereof is intended to cover non-exclusive inclusion, so that a process, method, article or device comprising a series of elements not only includes those elements, but also includes other elements not expressly listed, or also includes elements inherent to such process, method, article or device.

[0045] Although the embodiments of the present invention have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A drone smooth landing device applied to public safety, comprising a fuselage (1), characterized in that: Both sides of the bottom of the body (1) are provided with stable landing mechanisms; The stable landing mechanism includes two first support plates (2), the two first support plates (2) are symmetrically and fixedly connected to the side wall of the body (1), and the side walls of the two first support plates (2) are both slidably installed with second support plates (6). The bottom ends of the two second support plates (6) are commonly fixedly connected with a square shell (5), and elastic mechanisms are respectively arranged between the two second support plates (6) and the two first support plates (2), and a retracting and deploying mechanism is arranged between the two second support plates (6) and the body (1). An inflation mechanism is arranged on the square shell (5); The inflation mechanism includes an airbag (27) and two bottom plates (7). The airbag (27) is fixedly connected to the inner top end of the square shell (5). The two bottom plates (7) are symmetrically attached to the lower end surface of the square shell (5), and elastic mechanisms are respectively arranged between the two bottom plates (7) and the square shell (5). An inflation assembly is arranged between the airbag (27) and the second support plate (6).

2. The drone smooth landing device applied to public safety according to claim 1, characterized in that: A T-shaped block (8) is fixedly connected to the side wall of the first support plate (2) corresponding to the second support plate (6), and the T-shaped block (8) is slidably inserted into the side wall of the second support plate (6) corresponding to the first support plate (2).

3. The drone smooth landing device applied to public safety according to claim 1, characterized in that: The elastic mechanism includes a splicing block (19) and a cylindrical groove (22). The splicing block (19) is fixedly connected to the side wall of the second support plate (6) near the square shell (5), and a sliding column (21) is fixedly connected to the upper end of the splicing block (19). The sliding column (21) is slidably inserted into the lower inner wall of the first support plate (2). The cylindrical groove (22) is opened in the inner wall of the first support plate (2). A limiting disk (23) is fixedly connected to the top end of the sliding column (21). The limiting disk (23) is slidably matched with the cylindrical groove (22). A spring (20) is fixedly connected between the upper end of the splicing block (19) and the lower end of the first support plate (2). The spring (20) is slidably sleeved on the outer wall of the sliding column (21).

4. The drone smooth landing device applied to public safety according to claim 2, characterized in that: The retracting and deploying mechanism includes a fixed block (16) and a motor (11). The fixed block (16) and the motor (11) are respectively fixedly connected to the lower end of the body (1) near the front and rear edges. The output shaft end of the motor (11) is fixedly connected with a winding column (14). The end of the winding column (14) away from the motor (11) is rotatably connected to the rear end of the fixed block (16). Sliders (15) are respectively arranged between the winding column (14) and the two first support plates (2). Linkage mechanisms are arranged between the two sliders (15), the motor (11) and the body (1). Pulling ropes (9) are respectively fixedly connected to the outer wall of the winding column (14) corresponding to the two first support plates (2). The ends of the two pulling ropes (9) away from the winding column (14) respectively pass through the two first support plates (2) movably, and the ends of the two pulling ropes (9) away from the winding column (14) are respectively the two T-shaped blocks (8), and the ends of the two pulling ropes (9) away from the winding column (14) are respectively fixedly connected to the upper ends of the two second support plates (6).

5. The drone smooth landing device applied to public safety according to claim 4, characterized in that: The linkage mechanism includes two connecting blocks (17) and two first gears (10). The two connecting blocks (17) are fixedly connected to the lower end of the machine body (1) near the fixed block (16) and the motor (11) respectively. A bidirectional lead screw (13) is rotatably connected between the two connecting blocks (17), and a guide post (12) is fixedly connected between the two connecting blocks (17). The guide post (12) is located below the bidirectional lead screw (13). The two sliders (15) are both threadedly sleeved on the outer wall of the bidirectional lead screw (13), and the guide post (12) movably penetrates through the two sliders (15). One of the first gears (10) is fixedly sleeved on the output shaft of the motor (11), and the other first gear (10) is fixedly sleeved on the outer wall of the bidirectional lead screw (13). The two first gears (10) are meshed with each other.

6. The drone smooth landing device applied to public safety according to claim 1, characterized in that: The elastic mechanism includes two grooves (31). The two grooves (31) are respectively opened at the front and rear edge positions of the bottom plate (7), and the inner walls of the two grooves (31) are both fixedly connected with rotating columns (30). L-shaped blocks (29) are rotatably sleeved on the outer walls of the two rotating columns (30). The ends of the two L-shaped blocks (29) far away from the rotating columns (30) are fixedly connected to the lower edge positions of the side walls of the square shell (5), and torsion springs (28) are fixedly connected between the two L-shaped blocks (29) and the two grooves (31) respectively. The two torsion springs (28) are respectively slidably sleeved on the outer walls of the two rotating columns (30).

7. The drone smooth landing device applied to public safety according to claim 1, characterized in that: The inflation assembly includes a fixing plate (3). One end of the fixing plate (3) is fixedly connected to the rear end of one of the second support plates (6), and the other end of the fixing plate (3) is fixedly connected with a high-pressure small gas cylinder (4). A connecting pipe (26) is communicated between the gas outlet end of the high-pressure small gas cylinder (4) and the upper end surface of the airbag (27). The connecting pipe (26) movably penetrates through the upper end of the square shell (5). The valve rotating end of the high-pressure small gas cylinder (4) is fixedly connected with a second gear (25).

8. The drone smooth landing device applied to public safety according to claim 1, characterized in that: A connecting frame (18) is fixedly connected to the front end of one of the first support plates (2), and a rack (24) is fixedly connected to the end of the connecting frame (18) far away from the first support plate (2).

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