Drones

Abstract

Provided is a drone capable of spraying liquid, comprising a container for the liquid, a spraying portion for spraying the liquid, and a connecting portion connecting the container and the spraying portion, wherein the connecting portion has a buffer portion for buffering stress generated in the connecting portion. The container may be an aerosol container. The connecting portion may have a rigid portion connected to the buffer portion and having a higher rigidity than the buffer portion.

Description

Technical Field

[0001] The invention relates to a drone. Background Art

[0002] Conventionally, there is known a drone equipped with a fluid ejection nozzle (for example, see Patent Document 1).

[0003] [Background Technology Literature]

[0004] [Patent Document]

[0005] [Patent Document 1] Japanese Patent Application Publication No. 2019-18589 Summary of the invention

[0006] [Problems to be solved by the invention]

[0007] In conventional drones, when the nozzle comes into contact with an obstacle, the nozzle may be damaged or the flight of the drone may be affected.

[0008] [Technical means to solve the problem]

[0009] In order to solve the above-mentioned problem, a first form of the present invention provides an unmanned aerial vehicle capable of spraying liquid, comprising a container for the liquid, a spraying portion for spraying the liquid, and a connecting portion connecting the container and the spraying portion, wherein the connecting portion has a buffer portion for buffering stress generated in the connecting portion.

[0010] The container may be an aerosol container.

[0011] The connecting portion may include a rigid portion connected to the buffer portion and having a higher rigidity than the buffer portion.

[0012] The buffer portion may be longer than the rigid portion in the connecting portion.

[0013] The drone may include a connection portion for inserting one of the buffer portion and the rigid portion into the other.

[0014] The buffer portion may be provided in the connecting portion on the container side relative to the rigid portion.

[0015] The buffer portion may be provided in the connection portion on the ejection portion side relative to the rigid portion.

[0016] The buffer portion may include: a tube portion for supplying the liquid from the container to the ejection portion; and a support portion for supporting the tube portion.

[0017] The support portion is provided with an injection port for injecting gas, and a supporting force for the tube portion can be obtained by sealing in the gas.

[0018] The drone may further include a gas supply unit for supplying gas to the support unit, and the gas supply unit may maintain the pressure of the support unit.

[0019] The gas supply may be an aerosol container.

[0020] The tube portion may be extended using a supporting force from the supporting portion.

[0021] At least one supporting portion may be provided along the side surface of the tube portion.

[0022] The tube portion may be formed by the side walls of the support portion.

[0023] In addition, the above summary of the invention does not list all the essential features of the present invention. In addition, sub-combinations of these feature groups may also constitute other inventions. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1A An example of the configuration of the drone 100 is shown.

[0025] Figure 1B It is a diagram for explaining stress buffering by the buffer portion 42 .

[0026] Figure 1C It is an enlarged cross-sectional view of the vicinity of the connection portion 43 .

[0027] Figure 2A An example of the configuration of the drone 100 is shown.

[0028] Figure 2B It is a diagram for explaining stress buffering by the buffer portion 42 .

[0029] Figure 2C It is an enlarged cross-sectional view of the vicinity of the connection portion 43 .

[0030] Figure 3A An example of the configuration of the drone 100 is shown.

[0031] Figure 3B It is an enlarged perspective view showing the structure of the buffer portion 42 .

[0032] Figure 3C An example is shown in which the supporting portion 48 is one.

[0033] Figure 3D An example is shown in which the tube portion 46 is constituted by the side wall of the support portion 48 .

[0034] Figure 3E An example of the injection port 49 for injecting gas into the support portion 48 is shown.

[0035] Figure 4A An example of the configuration of the drone 100 is shown.

[0036] Figure 4B It is an enlarged perspective view of the vicinity of the connection portion 43 .

[0037] Figure 4CIt is an enlarged cross-sectional view of the vicinity of the connection portion 43 .

[0038] Figure 5A An example of the configuration of the drone 100 is shown.

[0039] Figure 5B It is an enlarged cross-sectional view of the vicinity of the gas supply unit 80 .

[0040] Figure 6 An example of the control system 200 of the drone 100 is shown. DETAILED DESCRIPTION

[0041] Hereinafter, the present invention will be described by way of the embodiments of the invention, but the following embodiments do not limit the invention according to the claims. In addition, all combinations of features described in the embodiments are not necessarily essential to the solving means of the invention.

[0042] Figure 1A An example of the configuration of the drone 100 is shown. The drone 100 of this example includes a main body 10, a leg 15, a propulsion unit 20, an arm 24, a container holding unit 30, a connection unit 40, and a discharge unit 60. The container holding unit 30 holds a container 70.

[0043] The drone 100 is an aircraft that flies in the air and can spray the liquid contained in the container 70 .

[0044] The main body 10 stores various control circuits and power supplies of the drone 100. In addition, the main body 10 can function as a structure that connects the components of the drone 100. The main body 10 of this example is connected to the propulsion unit 20 by the arm 24.

[0045] The camera 12 is provided in the main body 10 to photograph the surroundings of the drone 100. The camera 12 may be a movable camera whose photographing direction can be changed, or a fixed camera whose photographing direction is fixed. A plurality of cameras 12 may also be provided at different positions of the drone 100. The camera 12 may photograph the spraying range of the liquid. In one example, the image photographed by the camera 12 is transmitted to the terminal device of the drone 100. The operator of the drone 100 may operate the drone 100 based on the image photographed by the camera 12.

[0046] The propulsion unit 20 generates a propulsion force for propelling the drone 100. The propulsion unit 20 has a rotary wing 21 and a rotation drive unit 22. The drone 100 of this example has four propulsion units 20. The propulsion unit 20 is mounted on the main body 10 via an arm 24. In addition, the drone 100 may also be an aircraft having a fixed wing as the propulsion unit 20.

[0047] The rotor blades 21 generate propulsion force by rotating. Four rotor blades 21 are provided around the main body 10 , but the arrangement of the rotor blades 21 is not limited to this example. The rotor blades 21 are provided at the front end of the arm 24 via the rotation drive unit 22 .

[0048] The rotation drive unit 22 has a power source such as a motor to drive the rotor 21. The rotation drive unit 22 may have a braking mechanism for the rotor 21. The rotor 21 and the rotation drive unit 22 may be directly mounted on the main body 10 without the arm 24.

[0049] The arm 24 is radially extended from the main body 10. The drone 100 of this example includes four arms 24 provided corresponding to the four propulsion units 20. The arm 24 may be fixed or movable. Other components such as a camera may be fixed to the arm 24.

[0050] The legs 15 are landing legs connected to the main body 10 and are used to maintain the posture of the drone 100 when landing. The legs 15 maintain the posture of the drone 100 when the propulsion unit 20 is stopped. The drone 100 of this example has two legs 15, but the present invention is not limited thereto.

[0051] The container holding part 30 holds the container 70 and connects the container 70 to the main body 10. The container holding part 30 may be connected to a member other than the main body 10, such as the arm 24 or the leg 15. The container holding part 30 can change the direction of the container 70. The container holding part 30 may be a gimbal for controlling the position of the container 70 in three-axis directions. In one example, the container holding part 30 adjusts the ejection direction of the ejection part 60 by changing the position of the container 70.

[0052] The container 70 is a container for storing liquid. In one example, the container 70 is an aerosol container. The aerosol container uses the gas pressure of the liquefied gas or compressed gas filled inside to spray the liquid. The container 70 in this example is a metal aerosol can, but it can also be a pressure-resistant plastic container. In addition, as the propellant, liquefied gases such as hydrocarbons (liquefied petroleum gas) (LPG), dimethyl ether (DME), hydrofluorocarbons (HFO-1234ze), carbon dioxide (CO 2 ), nitrogen (N 2 ), nitric oxide (N 2 O) and other compressed gases.

[0053] The connection part 40 connects the container 70 and the ejection part 60 so that the liquid ejected from the container 70 flows to the ejection part 60. The connection part 40 can extend in the ejection direction of the ejection part 60. By setting the connection part 40 to be sufficiently long, for example, even if there are obstacles around the target position of the ejected liquid and the drone 100 cannot approach the target position, it can still be ejected relatively accurately to the target position.

[0054] The connecting portion 40 has a buffering portion 42 for buffering the stress generated in the connecting portion 40. For example, the buffering portion 42 buffers the stress by deforming according to the stress generated in the connecting portion 40. The buffering portion 42 can be deformed by utilizing the flexibility of the material of the buffering portion 42 itself, or can have a deformable shape or structure. After the buffering portion 42 is deformed by the stress on the connecting portion 40, once the stress is eliminated, it can return to the shape and size before the stress is applied. The buffering portion 42 of this example has a bellows structure that can be extended and bent.

[0055] The connecting portion 40 may further include a rigid portion 44 connected to the buffer portion 42. The buffer portion 42 and the rigid portion 44 are connected via a connecting portion 43. Details of the connecting portion 43 will be described below. The rigid portion 44 has a higher rigidity than the buffer portion 42. The material of the rigid portion 44 may be a hard material such as metal or plastic. The rigid portion 44 of this example has a generally cylindrical shape with a hollow interior. In the connecting portion 40 of this example, the buffer portion 42 is arranged closer to the container 70 than the rigid portion 44.

[0056] The ejection part 60 is connected to the container 70 via the connection part 40, and ejects the liquid contained in the container 70. For example, the ejection part 60 is a nozzle for ejecting the liquid. The ejection part 60 can be designed to eject the liquid in a mist or bubble form. The ejection part 60 can eject the liquid radially or linearly.

[0057] Figure 1B 4 is a diagram for explaining stress buffering using the buffer portion 42. Figure 1B As shown, when the ejection portion 60 contacts an obstacle such as a wall during the flight of the drone 100, the buffer portion 42 bends by the expansion and contraction of the bellows. As a result, the stress generated in the connection portion 40 due to the contact with the obstacle is buffered, and damage to the connection portion 40 can be prevented. In addition, the stress generated by the contact with the obstacle can be suppressed from being transmitted to the body of the drone 100 via the connection portion 40, thereby preventing the flight of the drone 100 from being affected. Therefore, even if the connection portion 40 is long and easily contacts an obstacle, the impact on the drone 100 caused by the contact can be suppressed.

[0058] Figure 1CIt is an enlarged cross-sectional view near the connecting portion 43. In the connecting portion 43, the buffer portion 42 and the rigid portion 44 are connected by inserting any one of the buffer portion 42 and the rigid portion 44 into the other. In the connecting portion 43 of this example, the rigid portion 44 is inserted into the buffer portion 42. For example, the end of the buffer portion 42 is formed of a stretchable material, and the rigid portion 44 is inserted into the end of the buffer portion 42 by press-fitting. As another example, the ends of the buffer portion 42 and the rigid portion 44 may be threaded, and one may be inserted into the other by screwing. The buffer portion 42 and the rigid portion 44 may be connected by insertion and then joined by an adhesive or welding.

[0059] In addition, if Figure 1C As shown, in the direction perpendicular to the direction in which the connecting portion 40 extends, the region where the buffer portion 42 and the rigid portion 44 overlap can be used as the connecting portion 43. In addition, in this example, the container 70 is connected to the end of the buffer portion 42 on the opposite side of the rigid portion 44, but the container 70 can also be inserted into the buffer portion 42 in the same manner as the rigid portion 44.

[0060] like Figure 1C As shown, an internal flow tube 45 for allowing liquid to flow can be provided inside the connecting portion 40. The internal flow tube 45 of this example is connected to the container 70 at one end and to the ejection portion 60 at the other end, and allows liquid to flow from the container 70 to the ejection portion 60 inside the buffer portion 42 and the rigid portion 44. In this example, the internal flow tube 45 can be made of a soft material, and can be bent together with the buffer portion 42, for example, when the connecting portion 40 contacts an obstacle. In addition, the internal flow tube 45 may not be provided, and the buffer portion 42 and the rigid portion 44 themselves may be used as a flow path for liquid.

[0061] Figure 2A FIG. 1 shows an example of the structure of the drone 100. The drone 100 of this example has the same structure as the drone 100 except for the structure of the connecting part 40. Figure 1A In the connection portion 40 of this example, the buffer portion 42 is provided on the ejection portion 60 side relative to the rigid portion 44 .

[0062] Figure 2B 4 is a diagram for explaining stress buffering using the buffer portion 42. Figure 2B As shown, when the ejection portion 60 contacts an obstacle during the flight of the drone 100, the buffer portion 42 bends by expanding and contracting the bellows. By configuring as in this example, the stress generated in the connection portion 40 due to contact with the obstacle can also be buffered, thereby suppressing the impact on the flight of the drone 100. In addition, by configuring the buffer portion 42 closer to the ejection portion 60 than the rigid portion 44, the stress generated by contact with the obstacle can be suppressed from being transmitted to the rigid portion 44, thereby further preventing damage to the connection portion 40.

[0063] Figure 2C is an enlarged cross-sectional view of the vicinity of the connection portion 43. In the connection portion 43 of this example, Figure 1C As in the example shown, the rigid portion 44 is inserted into the buffer portion 42. In this example, the ejection portion 60 is connected to the end of the buffer portion 42 opposite to the rigid portion 44, but the ejection portion 60 may be inserted into the buffer portion 42 in the same manner as the rigid portion 44.

[0064] Figure 3A FIG. 1 shows an example of the structure of the drone 100. The drone 100 of this example has the same structure as the drone 100 except for the structure of the connecting part 40. Figure 1A The connecting portion 40 of this example has a buffer portion 42 including a tube portion 46 for supplying the liquid from the container 70 to the ejection portion 60 and a support portion 48 for supporting the tube portion 46 . Figure 3B It is an enlarged perspective view showing the structure of the buffer portion 42 .

[0065] One end of the tube portion 46 is connected to the container 70, and the other end is connected to the ejection portion 60. The tube portion 46 is in the shape of a hollow cylinder, which allows liquid to flow. The tube portion 46 extends along the ejection direction of the liquid to be ejected, so that the ejection portion 60 connected to the end is oriented in the ejection direction. The tube portion 46 can be extended by the supporting force from the support portion 48. The tube portion 46 can be made of a soft material, and may not extend in the ejection direction when the support portion 48 has no supporting force. For example, when the support portion 48 has no supporting force, the tube portion 46 can either hang down by gravity, or can be accommodated in the main body 10 in a rolled-up state.

[0066] The support portion 48 may be a balloon-shaped component made of a stretchable material such as rubber or ethylene, and can expand by generating tension on the surface by supplying fillers to the inside. In addition, the support portion 48 may also be made of a flexible material. For example, the support portion 48 may also be composed of a metal film such as aluminum foil, a monomer such as olefin, nylon, polyester, or a laminate containing them. The support portion 48 extends the tube portion 46 by supporting the tube portion 46 in an expanded state. For example, the support portion 48 expands by sealing in a gas such as air, thereby obtaining a supporting force for the tube portion 46. The amount of gas supplied to the support portion 48 can be adjusted to the following range: the support portion 48 maintains the supporting force for the tube portion 46 and can be deformed relative to a stress exceeding a specific threshold.

[0067] When the tube 46 is extended by the support force from the support part 48, for example, when the ejection part 60 contacts an obstacle during the flight of the drone 100, the buffer part 42 is deformed, thereby buffering the stress generated by the contact. In this example, since the buffer part 42 is provided over the entire connection part 40, the area that can be deformed is larger, and the effect of stress buffering can be improved.

[0068] At least one support portion 48 is provided along the side surface of the tube portion 46. In this example, two support portions 48 are connected to the upper and lower sides of the tube portion 46, but the number of support portions 48 is not limited thereto. Figure 3C The example in which the support portion 48 is one is shown. The tube portion 46 and the support portion 48 can be made of the same material. Figure 3D As shown, the tube portion 46 may also be formed by the side walls of the support portion 48 .

[0069] Figure 3D The figure shows an example in which the tube 46 is constituted by the side wall of the support portion 48. In addition, the figure shows a cross section in a direction perpendicular to the extension direction of the tube 46 and the support portion 48. In this example, four support portions 48 are provided, and the side walls of adjacent support portions 48 are joined to each other. Thus, the space surrounded by the side walls of these support portions 48 can be used as the tube 46 for liquid flow. Here, as shown in the figure, the inner surface portion (the portion constituting the tube 46) and the outer surface portion (the portion other than this) of the support portion 48 are respectively formed as a single component, which are bonded to each other, and the bonded portion is sealed by a sealing portion 47, thereby also constituting the tube 46 and the support portion 48. The sealing portion 47 can be a joint portion using an adhesive, welding or thermal fusion.

[0070] Figure 3E An example of an injection port 49 for injecting gas into the support portion 48 is shown. The injection port 49 is an opening provided in the side wall of the support portion 48. The injection port 49 can be provided at any position of the support portion 48. In this example, a valve mechanism 50 is provided for opening and closing the injection port 49. The valve mechanism 50 includes a rod 52 connected to the injection port 49, a plunger 54 capable of sealing the opening of the rod 52, a threaded portion 55 provided at the upper end of the plunger 54, and a nut 56 screwed with the threaded portion 55.

[0071] When the nut 56 is loosened from the state where the plunger 54 seals the opening of the rod 52, the plunger 54 moves downward, and a gap is generated between the rod 52 and the plunger 54. Through this gap, gas can be supplied to the inside of the support portion 48. For example, by connecting a gas injection nozzle 58 connected to a pump to the rod 52, the gas sent from the pump can be supplied to the support portion 48. After the supply of gas is completed, the gas injection nozzle 58 is removed and the nut 56 is tightened, and the plunger 54 seals the opening of the rod 52 again, so that the support portion 48 is hermetically sealed. As a result, for example, even if the drone 100 flies for a long time, gas leakage from the support portion 48 can be prevented, and the pressure of the support portion 48 can be maintained.

[0072] Figure 4A FIG. 1 shows an example of the structure of the drone 100. The drone 100 of this example has the same structure as the drone 100 except for the structure of the connecting part 40. Figure 1AThe connecting portion 40 of this example has: a buffer portion 42, which has Figure 3A The same pipe portion 46 and support portion 48 as in the example; and the rigid portion 44 are connected to the buffer portion 42.

[0073] In the connection part 40 of this example, the buffer part 42 is longer than the rigid part 44. In addition, in this specification, the dimension in the extension direction of the connection part 40 is set as the length of the connection part 40. In addition, the length of the buffer part 42 is set as the length of the longer one of the tube part 46 and the support part 48. In this example, two rigid parts 44 are provided, namely, the rigid part 44 between the buffer part 42 and the container 70, and the rigid part 44 between the buffer part 42 and the ejection part 60. In this case, the length of the buffer part 42 is greater than the sum of the lengths of the two rigid parts 44. By making the buffer part 42 longer than the rigid part 44, the area that can be deformed in the connection part 40 becomes larger, and the effect of stress buffering can be improved.

[0074] Figure 4B is an enlarged stereoscopic view of the vicinity of the connection portion 43. Figure 4C 4 is an enlarged cross-sectional view of the vicinity of the connection portion 43. In this example, the rigid portion 44 has a shape along the outer shape of the pipe portion 46 and the support portion 48 of the buffer portion 42. The buffer portion 42 and the rigid portion 44 are connected by pressing the pipe portion 46 and the support portion 48 into the rigid portion 44. That is, in the connection portion 43 of this example, the buffer portion 42 is inserted into the rigid portion 44. In addition, Figure 4B and Figure 4C , the connection portion 43 between the rigid portion 44 on the container 70 side and the buffer portion 42 is shown, but the connection portion 43 between the rigid portion 44 on the ejection portion 60 side and the buffer portion 42 may have the same structure.

[0075] like Figure 4C As shown, an internal flow tube 45 for passing liquid can be provided inside the connection part 40. The internal flow tube 45 of this example is connected to the container 70 at one end and to the tube part 46 at the other end, and the liquid flows from the container 70 to the tube part 46 inside the rigid part 44. In addition, the internal flow tube 45 may not be provided, and the rigid part 44 itself may be used as a flow path for the liquid.

[0076] Figure 5A An example of the structure of the drone 100 is shown. The drone 100 of this example further includes a gas supply unit 80. The other structures are similar to those of Figure 4A The gas supply unit 80 supplies gas to the support unit 48 to maintain the pressure of the support unit 48. For example, as described above, the gas supply unit 80 maintains the pressure of the support unit 48 within the following range: the support unit 48 maintains the supporting force for the tube unit 46 and is deformable with respect to the stress exceeding the threshold.

[0077] Figure 5BIt is an enlarged cross-sectional view near the gas supply part 80. The gas supply part 80 may be an aerosol container that uses the gas pressure of the liquefied gas or compressed gas filled inside to eject the gas. The gas supply part 80 is connected to the injection port 49 of the support part 48 by the gas supply pipe 82. A gas supply control part 84 is provided on the gas supply pipe 82. The gas supply control part 84 has, for example, a solenoid valve to open and close the gas supply pipe 82. When the gas supply pipe 82 is opened, the gas ejected from the gas supply part 80 is supplied to the support part 48. The gas supply control part 84 may have a pressure sensor that detects the pressure of the support part 48, and can open and close the gas supply pipe 82 according to the detected pressure. For example, when the pressure of the support part 48 is lower than a specific threshold value, the gas supply control part 84 opens the gas supply pipe 82, thereby supplying gas from the gas supply part 80 to the support part 48, and pressurizing the support part 48.

[0078] Thus, by providing the gas supply unit 80, the pressure of the support unit 48 can be appropriately maintained during the flight of the drone 100. Therefore, even if, for example, gas leaks from the support unit 48 or the pressure of the support unit 48 changes due to a change in the external gas pressure during flight, the extended state of the buffer unit 42 can be maintained, and the stress buffering effect can be maintained.

[0079] Figure 6 1 shows an example of a control system 200 for the drone 100. The control system 200 of this example includes the drone 100 and a terminal device 300. The terminal device 300 includes a display unit 310 and a controller 320.

[0080] The display unit 310 displays the image captured by the camera 12. When the camera 12 includes a fixed camera and a movable camera, the display unit 310 can display the image captured by each camera. For example, the display unit 310 displays the images of the fixed camera and the movable camera in a split screen. The display unit 310 can communicate with the drone 100 directly or indirectly via the controller 320. The display unit 310 can also be connected to an external server.

[0081] The controller 320 is operated by the user to control the drone 100. In addition to instructing the flight of the drone 100, the controller 320 can also instruct the ejection of liquid by the ejection unit 60. The controller 320 can be connected to the display unit 310 by wire or wirelessly. A plurality of controllers 320 can also be provided, which are used separately for operating the drone 100 and controlling the ejection of liquid. In addition, the controller 320 can also instruct the gas supply control unit 84 to supply gas from the gas supply unit 80 to the support unit 48.

[0082] In addition, the drone 100 of this example is manually operated using the terminal device 300. However, the drone 100 may be automatically operated using a program instead of manually. The user may also operate the drone 100 by directly observing the drone 100 instead of using the screen displayed on the display unit 310. In addition, the operation of the drone 100 may be automatically controlled, and the ejection of the liquid may be manually operated.

[0083] The present invention has been described above using the embodiments, but the technical scope of the present invention is not limited to the scope described in the embodiments. It is clear to those skilled in the art that various changes or improvements can be made to the embodiments. According to the description of the claims, the form to which such changes or improvements are made can also be included in the technical scope of the present invention.

[0084] It should be noted that the execution order of each process such as actions, sequences, steps, and stages in the devices, systems, programs, and methods shown in the claims, specifications, and drawings can be implemented in any order unless it is specifically stated as "before...", "prior to...", etc., and as long as the output of the previous process is not used in the subsequent process. Even if the action flow in the claims, specifications, and drawings is described using "first," "next," etc. for convenience, it does not mean that it must be implemented in this order.

[0085] [Explanation of Symbols]

[0086] 10 Main body

[0087] 15. Feet

[0088] 20 Promotion Department

[0089] 21 Rotary Wing

[0090] 22 Rotation drive unit

[0091] 24 Arm

[0092] 30 Container holding part

[0093] 40 Connection

[0094] 42 Buffer

[0095] 43 Connection

[0096] 44 Rigidity

[0097] 45 Internal flow tube

[0098] 46 Pipe

[0099] 47 Sealing part

[0100] 48 Support

[0101] 49 Injection port

[0102] 50 Valve mechanism

[0103] 52 strokes

[0104] 54 Plunger

[0105] 55 Threaded part

[0106] 56 Nut

[0107] 58 Gas injection nozzle

[0108] 60 ejection part

[0109] 70 Containers

[0110] 80 Gas supply unit

[0111] 82 Gas supply pipe

[0112] 84 Gas supply control unit

[0113] 100 drones

[0114] 200 Control System

[0115] 300 Terminal Device

[0116] 310 Display unit

[0117] 320 Controller

Claims

1. A drone capable of spraying liquids and having: A container for the liquid; a spraying portion for spraying the liquid; and A connecting portion connecting the container and the ejection portion; The connecting portion has: a buffer portion for buffering stress generated in the connection portion due to contact between the ejection portion and an obstacle; a rigid portion connected to the buffer portion and having a higher rigidity than the buffer portion; and Inserting one of the buffer portion and the rigid portion into a connecting portion of the other; and, An internal flow pipe for flowing liquid from the container to the ejection part is provided inside the buffer part and the rigid part.

2. The drone according to claim 1, wherein The container is an aerosol container.

3. The drone according to claim 1, wherein The buffer portion is longer than the rigid portion in the connecting portion.

4. The drone according to any one of claims 1 to 3, wherein The buffer portion is provided in the connecting portion on the container side relative to the rigid portion.

5. The drone according to any one of claims 1 to 3, wherein The buffer portion is provided in the connection portion on the ejection portion side relative to the rigid portion.

6. The drone according to any one of claims 1 to 3, wherein The buffer portion comprises: a pipe portion for supplying the liquid from the container to the ejection portion; and The supporting portion is used to support the tube portion.

7. The drone according to claim 6, wherein The support portion includes an injection port for injecting a gas, and a support force for the tube portion is obtained by sealing the gas.

8. The drone according to claim 6, further comprising a gas supply unit for supplying gas to the support unit, The gas supply unit maintains the pressure of the support unit.

9. The drone according to claim 8, wherein The gas supply unit is an aerosol container. 10 . The drone according to claim 6 , wherein the tube portion is extended using a supporting force from the supporting portion. The drone according to claim 6 , wherein at least one of the support portions is disposed along a side surface of the tube portion. 12 . The drone according to claim 6 , wherein the tube portion is formed by a side wall of the support portion.

Images