Aircraft spray device, anti-drip component, and control method of aircraft spray device

Abstract

A spraying device for an aircraft is used, which sprays a liquid substance from a nozzle mounted on an aircraft body and includes a cover body capable of opening and closing a spraying port of the nozzle.

Description

Technical Field

[0001] The present invention relates to an aircraft spray device, a dripping prevention member, and a control method for an aircraft spray device, and in particular to a technology for preventing dripping from a spray device mounted on a mobile body such as an unmanned aircraft. Background Art

[0002] Conventionally, as a spraying device for such an unmanned aerial vehicle (mobile body), there is known a bee expelling device such as that described in Patent Document 1. That is, the bee expelling device has a medicine supplying unit inside the body for supplying medicine to a beehive, and a spraying tool is installed on the medicine supplying unit as a spraying device.

[0003] Prior art literature

[0004] Patent Literature

[0005] [Patent Document 1] Japanese Patent Application Publication No. 2017-104063 Summary of the invention

[0006] Problems to be solved by the invention

[0007] Here, when a liquid substance is discharged from the ejection device, a part of the discharged substance adheres to the nozzle of the ejection device. When the amount of the adhered substance increases, the liquid substance may become droplets, causing dripping. Such dripping is not desirable from the perspective of the impact on the surrounding environment.

[0008] An object of the present invention is to provide a technology for preventing liquid from dripping from a discharge device mounted on an aircraft.

[0009] Solutions for solving problems

[0010] In order to achieve the above object, the present invention is a jetting device for an aircraft.

[0011] Liquid is discharged from the nozzle installed in the machine.

[0012] A cover body is provided which can open and close the spray port of the nozzle.

[0013] By using such a discharge device, it is possible to prevent dripping from the nozzle.

[0014] The discharge device can be configured as follows.

[0015] 1. It has a driving unit for opening and closing the cover.

[0016] Since the cover can be opened and closed, the nozzle can be opened during discharge and closed at other times.

[0017] 2. The cover body is hinged to open and close the spray port.

[0018] By using a hinge, smooth opening and closing action is possible.

[0019] 3. The hinge is configured so that when the aircraft is in flight, the hinge is located vertically above the ejection port.

[0020] This can prevent liquid dripping from occurring even when the switch mechanism fails.

[0021] 4. The cover body has a recessed portion, which is arranged at a position opposite to the ejection port in a closed state, for preventing interference with the ejection port.

[0022] This can prevent members from abutting against each other.

[0023] 5. The cover body opens and closes the discharge port by sliding in a direction perpendicular to the discharge direction of the liquid material.

[0024] 6. The cover body slides by rotational movement or linear movement.

[0025] 7. The cover body is a diaphragm mechanism having a plurality of diaphragm sheets.

[0026] As a method of controlling the cover body, these various methods can be utilized.

[0027] 8. The cover body and the spout are arranged at positions where the spout does not abut against the cover body when the cover body is in a closed state.

[0028] Thereby, even if the cover is opened and closed, it will not come into contact.

[0029] 9. When the cover is in a closed state, an absorbent material for absorbing the liquid is provided at a position of the cover facing the spray port.

[0030] This makes it possible to absorb liquid substances dripping down near the cover body, thereby preventing dripping.

[0031] 10. A jetting device for an aircraft,

[0032] The cover is opened and closed by pressure when the liquid is ejected.

[0033] This can simplify the structure of the switch mechanism.

[0034] In order to achieve the above object, the present invention is a jetting device for an aircraft.

[0035] Liquid is sprayed from the nozzle mounted on the machine.

[0036] A solidifying portion is provided for receiving and fixing the liquid substance dripping from the nozzle,

[0037] This can fix the dripping liquid and prevent it from spilling outside.

[0038] The discharge device can be configured as follows.

[0039] 1. The solidification part includes an absorbent material.

[0040] This makes it possible to absorb liquid substances without spilling them.

[0041] 2. A cover body is provided which can open and close the discharge port of the nozzle, and the curing part is provided at a position facing the discharge port when the cover body is in a closed state.

[0042] This can effectively solidify the liquid overflowing from the ejection port.

[0043] 3. A protruding portion protrudes forward from the ejection port in the ejection direction, and the curing portion is provided on the protruding portion.

[0044] 4. The protruding portion is constituted by the solidified portion.

[0045] The liquid can thereby be solidified by the solidifying portion provided on or formed by the protrusion.

[0046] 5. The curing section includes a permeable portion that allows the liquid substance protruding from the ejection port to pass therethrough, and the absorbing material that absorbs the liquid substance that has passed through the permeable portion.

[0047] This allows the liquid substance to pass through the permeable portion, and suppresses expansion of the absorbent material that has absorbed the liquid substance.

[0048] In order to achieve the above object, the present invention is a jetting device for an aircraft.

[0049] Liquid is sprayed from the nozzle mounted on the machine.

[0050] A receiving portion is provided, which is arranged in front of the ejection direction of the ejection outlet and is used to receive the liquid substance dripping from the ejection outlet.

[0051] This makes it possible to receive overflowing liquid without leaking to the outside.

[0052] The discharge device can be configured as follows.

[0053] 1. The receiving part has a storage part for storing the liquid substance.

[0054] This makes it possible to cope with a situation where a certain amount of liquid overflows.

[0055] 2. The storage portion is a bag-shaped member provided in front of the ejection direction when viewed from the ejection port.

[0056] This makes it possible to effectively store liquid substances.

[0057] 3. The receiving portion has a protruding surface, which is located below the ejection port in the vertical direction when the aircraft is in flight, and protrudes forward in the ejection direction when viewed from the ejection port.

[0058] This makes it possible to handle dripping that occurs during flight and prevent the liquid from spilling.

[0059] 4. An absorbent material for absorbing the liquid is provided on the protruding surface.

[0060] 5. An interception portion for preventing leakage of the liquid substance is provided on the protruding surface.

[0061] 6. The protruding surface is provided with a recessed portion for storing the liquid substance.

[0062] 7. When viewed from the ejection port, a plurality of the recessed portions are provided in front of the ejection direction.

[0063] In this way, various structures can be used to prevent dripping, so the freedom of design by appropriate selection can be increased.

[0064] 8. A cover body is further provided, which can be opened and closed, and forms a closed space in the ejection direction of the ejection port together with the protruding surface in a closed state, and can eject the liquid substance to the outside from the ejection port in an open state.

[0065] This can further enhance the drip-proof effect.

[0066] 9. The protruding surface is the bottom of the cylindrical portion protruding from the periphery of the ejection port.

[0067] 10. A cover body is further provided, which covers the front end of the cylindrical portion in a closed state and can eject the liquid substance to the outside from the ejection port in an open state.

[0068] By providing a cylindrical portion or providing a cover on the cylindrical portion, the drip-proof effect can be further improved.

[0069] In order to achieve the above object, the present invention is a drip-proof component.

[0070] It can be attached and detached from a spraying device of an aircraft that sprays a liquid substance from a nozzle mounted on the aircraft body.

[0071] This makes it easier to replace the drip prevention member.

[0072] The drip prevention member can be configured as follows.

[0073] 1. A snap-fit ​​portion is provided for mounting the drip-proof member on the ejection device of the aircraft.

[0074] 2. The engaging portion is a threaded portion provided on the drip prevention member, and engages with a threaded portion provided on the ejection device of the aircraft.

[0075] 3. The engaging portion is an engaging portion that engages the drip prevention member and the ejection device of the aircraft by engaging them with each other.

[0076] With these structures, the maintainability of the dripping prevention member is improved.

[0077] 4. The drip prevention member has an anti-slip portion on the outer peripheral surface.

[0078] This makes it easier to replace the drip prevention member.

[0079] In order to achieve the above object, the present invention is a notification method.

[0080] It controls the spraying device of the aircraft to spray liquid from the nozzle mounted on the aircraft body.

[0081] A cover body is provided which can open and close the discharge port provided at the nozzle.

[0082] This can prevent dripping from the nozzle.

[0083] In order to achieve the above object, the present invention is a control method for a jet device of an aircraft.

[0084] The ejection device of the aircraft with a switch mechanism has an ejection port capable of opening and closing the nozzle.

[0085] The cover driving part driving the cover is linked with the ejection action of the ejection driving part, and the cover is closed when the ejection action ends, and the cover is opened when the ejection action starts.

[0086] A method for controlling an ejection device of an aircraft.

[0087] This makes it possible to open the nozzle when discharging a liquid substance and prevent dripping from the nozzle when not discharging.

[0088] Effects of the Invention

[0089] As described above, according to the present invention, it is possible to provide a technique for preventing liquid from dripping from a discharge device mounted on an aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0090] Figure 1The spray device of an aircraft equipped with the spray device of the present invention is schematically shown, in which an aerosol container is used as the spray device. (A) is an overall structural diagram of the aircraft, (B) is a cross-sectional view of the spray device, (C) is a view of (B) in the direction of arrow C, (D) is an explanatory diagram before spraying, (E) is a plan view of the spray drive unit of (D), and (F) is an explanatory diagram during spraying.

[0091] Figure 2 (A) is when a radial support is provided Figure 1 A cross-sectional view at right angles to the axis, (B) is a view showing Figure 1 1 is a diagram showing an example of a valve mechanism of an aerosol container, and (C) is a diagram showing an example of using a power supply as a voltage of a flight control unit.

[0092] Figure 3 (A) to (C) are diagrams showing three modes of the ejection drive unit.

[0093] Figure 4 (A) is an explanatory diagram showing an example of remote operation of a control terminal and a discharge operation terminal of an aircraft equipped with a discharge device, and (B) is a control block diagram.

[0094] Figure 5 The figures are cross-sectional views schematically showing the drip prevention member of the aerosol container according to the first embodiment, wherein (A) shows a closed state and (B) shows an open state.

[0095] Figure 6 The drip prevention member of the aerosol container according to the second embodiment is shown, wherein (A) is a cross-sectional view, (B) is a perspective view of an open state, and (C) is a perspective view of a closed state.

[0096] Figure 7 The drip prevention member of the aerosol container according to the third embodiment is shown. (A) is a perspective view of the open state, and (B) is a perspective view of the closed state.

[0097] Figure 8 The drip prevention member of the aerosol container according to the fourth embodiment is shown. (A) is a perspective view of a closed state, and (B) is a perspective view of an opened state.

[0098] Fig. 9 The drip prevention member of the aerosol container according to the fifth embodiment is shown, wherein (A) is a cross-sectional view and (B) is a perspective view.

[0099] Fig.10 A drip prevention member of an aerosol container according to a sixth embodiment is shown.

[0100] Fig.11 The drip prevention member of the aerosol container according to Embodiment 7 is shown, wherein (A) is a cross-sectional view of the intercepting portion, (B) is a cross-sectional view of the recessed portion, and (C) is a perspective view of the recessed portion.

[0101] Fig.12 The drip prevention member of the aerosol container according to the eighth embodiment is shown. (A) is a cross-sectional view of a structure in which an absorbent material is provided in a cylindrical portion, and (B) is a cross-sectional view of a structure in which the cylindrical portion is composed of the absorbent material.

[0102] Fig.13 The drip prevention member of the aerosol container according to the ninth embodiment is shown, wherein (A) is a cross-sectional view and (B) is an exploded perspective view showing the structure of the absorbent material.

[0103] Fig.14 The anti-drip member of the aerosol container according to Embodiment 11 is shown, wherein (A) is a cross-sectional view of the intercepting portion, and (B) is a cross-sectional view of the recessed portion.

[0104] Fig.15 The drip prevention member of the aerosol container according to Embodiment 11 is shown. (A) is a perspective view of a closed state, and (B) is a perspective view of an opened state.

[0105] Fig.16 The structure of the cylindrical portion of the drip prevention member of the aerosol container according to the twelfth embodiment is shown, (A) is a cross-sectional view, and (B) is a perspective view.

[0106] Fig.17 The structure of the cylindrical portion of the drip prevention member of the aerosol container according to Embodiment 13 is shown, (A) is a cross-sectional view, and (B) is a perspective view.

[0107] Fig.18 The aircraft equipped with the ejection device of the present invention is schematically shown, and is an overall configuration diagram of the aircraft in the case where a pump and a liquid tank are used as the ejection device.

[0108] Marking Description

[0109] 1: Spraying device, 10: Aerosol container, 11a: Body, 11b: Bottom, 11d: Sealing cup, 12: Rod, 12a: Spraying flow path, 12b: Rod hole, 13: Valve mechanism, 13a: Washer, 13b: Spring, 14: Actuator, 14a: Main body, 14b: Flange, 15: Nozzle, 15a: Spray hole, 16: Connecting pipe, 16a: Internal space

[0110] 20: sleeve, 21: sleeve body, 21a: radial direction support portion, 22: end cover portion, 221: pressing member, 221a: cylindrical body, 221b: end flange portion, 222: cover body, 23: end cover portion, 223: cylinder, 231: cylindrical portion, 232: end plate

[0111] 30: ejection drive unit, 30A: drive unit, 30B: contact member, 30C: external valve, 30D: pipeline, 31: motor, 32: cam mechanism, 32a: cam, 32b: cam follower,

[0112] 40: Aerosol container assembly, 50: Spray device support portion, 72: Container holding portion, 72a: Circular plate portion, 72b: Annular convex portion, 72c: Connecting shaft portion, 73: Anti-slip material

[0113] 100: aircraft, 101: fuselage, 102: fuselage, 103: arm, 104: rotor, 105: motor, 106: camera, 107: leg, 110: flight control unit, 112: flight communication unit

[0114] 120: control terminal, 160: operation terminal, 161: front end, 163: ejection button, 164: stop button, 167: display screen

[0115] 180: Liquid tank, 182: Pump

[0116] 210: ejection device control unit, 211: ejection device power supply, 212: ejection device communication unit, 301: frame

[0117] 700: prevention member, 710: mounting portion, 711: inner fitting portion, 711: mounting portion, 711: inner fitting portion, 711a: internal space, 711c: crimping portion, 712: outer fitting portion, 713: end surface, 714: front end portion, 715: through hole, 716: inner wall, 718: thread groove, 719: insertion receiving portion

[0118] 720: cover, 722: cover connection part, 723: cover recess, 724: sheet, 725: unit

[0119] 730: prevention member driving part, 731: direct-acting connecting member, 732: direct-acting part, 733: base, 734: driving shaft, 735: motor

[0120] 735: protrusion, 735a: front space, 736: connection portion, 737: wall portion, 740: cylindrical portion, 740a: cylindrical portion space, 744: thread groove, 745: anti-slip portion, 746: insertion portion

[0121] 800: absorbent material, 801: transmission part, 810: interception part, 820: recessed part DETAILED DESCRIPTION

[0122] Hereinafter, the present invention will be described in detail based on the illustrated embodiments.

[0123] The dimensions, materials, shapes, relative arrangements, etc. of the components described in the following embodiments should be appropriately changed according to the configuration and various conditions of the device to which the present invention is applied, and the scope of the present invention is not limited to the following embodiments.

[0124] [Implementation Method 1]

[0125] First, refer to Figure 1 (A) to (C) illustrate the overall composition. Figure 1 The ejection device of the aircraft according to the first embodiment of the present invention is schematically shown. Figure 1 (A) is a perspective view of the entire aircraft equipped with the ejection device. Figure 1 (B) is a cross-sectional view of the ejection device mounted on the aircraft. Figure 1 (C) is a view of (B) viewed from direction C.

[0126] exist Figure 1 In (A), 100 represents an aircraft. The aircraft 100 is an unmanned aerial vehicle such as a so-called multi-rotor helicopter, and a fuselage 101 has a fuselage body 102, four arms 103 extending radially from the fuselage body 102, and legs 107 for take-off and landing. At the front end of the arm 103, four rotors 104 are respectively provided via motors 105. In the example shown in the figure, a quad-rotor helicopter with four rotors 104 is illustrated, but it is also applicable to various well-known multi-rotor helicopters such as three (three-rotor helicopter) and six (six-rotor helicopter). The yaw axis of the fuselage 101 is the up-and-down direction of the paper, the roll axis is the left-and-right direction of the paper, the pitch axis is the inside-and-out direction of the paper, the upper side of the paper is the top of the fuselage 101, and the left side of the paper is the front of the fuselage 101.

[0127] In the illustrated example, a spray device 1 containing an aerosol container is mounted on the outside of a body 101 of the aircraft 100 below a body section 102 via a spray device support 50. The spray device 1 is elongated, with the elongated direction facing the roll axis, and a nozzle 15 protrudes from its front end toward the front of the body.

[0128] The ejection device 1 is as follows Figure 1 As shown in (B), an aerosol container 10 is provided, and the contents of the aerosol container 10 are sprayed out while being mounted on a body 101. The sprayed contents are not limited to liquids, but may include gas, gas such as air, powder, etc. in liquids.

[0129] The aerosol container 10 is mounted on the body 101 in a state of being contained in a sleeve (containing member) 20. The sleeve 20 has a built-in ejection drive unit 30 for ejecting the contents from the aerosol container 10. The sleeve 20 and the aerosol container 10 can be replaced as a whole, and in the following description, the assembly in which the aerosol container 10 is contained in the sleeve 20 is referred to as an aerosol container assembly 40. The structure of each part is described below.

[0130] [About aerosol containers]

[0131] The aerosol container 10 is a container that sprays out the contents by the gas pressure of the compressed gas or liquefied gas filled inside. Existing metal aerosol containers can be used, and pressure-resistant plastic containers can also be used. In the aerosol container 10, various actuators are installed on the rod 12, and the actuator forms a flow path according to the spraying direction and the spraying method. In the example shown in the figure, an example in which the actuator 14 is installed on the rod 12 of the aerosol container 10 is shown. The actuator 14 is configured to have: a linear main body 14a, which has a straight spraying flow path; and a flange portion 14b, which extends from the main body 14a at right angles to the axis. Via the connecting pipe 16 connected to the main body 14a of the actuator 14, a flange portion 14b having a spray hole 15a (reference Figure 1 (C)) nozzle 15. The contents are sprayed in a mist form or as a straight jet, and the spraying method and spraying direction of the contents are appropriately selected.

[0132] In the example shown in the figure, since the aerosol container 10 is horizontally mounted below the body 101 for use, the form of the enclosed propellant and the contents can be an isolation type in which the stock solution is contained in the inner bag and the propellant is contained between the outer periphery of the inner bag and the inner periphery of the container body. If it is an isolation type, the posture of the aerosol container is horizontal (the position of the rod is horizontal) or downward (the position of the rod is downward), and it can be sprayed. When spraying a liquid as the contents of the aerosol container 10, the liquid is sometimes sprayed in a gel, mist, etc. in addition to water droplets.

[0133] However, it is not limited to the isolation type. When the aerosol container 10 is used with the rod 12 upward during discharge, a container with an immersion tube two-phase system or a three-phase system can be used. When the aerosol container 10 is used with the rod 12 downward, a container without an immersion tube two-phase system or a three-phase system can be used.

[0134] In addition, as the propellant, compressed gases such as carbon dioxide (CO2), nitrogen (N2), and nitrous oxide (N2O) are preferred. In addition, liquefied gases such as common hydrocarbons (liquefied petroleum gas) (LPG), dimethyl ether (DME), and fluorocarbons (HFO-1234ZE) can be used. However, when considering the safety against fire during heating, non-flammable fluorocarbons, carbon dioxide, nitrogen, and nitric oxide are preferred, and particularly, when considering the environmental load, nitrogen is preferred.

[0135] [Configuration of the sleeve 20]

[0136] The sleeve 20 may be made of a material having high strength and light weight, such as metal such as aluminum, plastic or carbon fiber. In addition, it is not limited to hard materials, and soft materials such as rubber materials such as silicone rubber and polyurethane foam may also be used. In short, various materials that can maintain the shape of the housing portion that houses the aerosol container 10 may be used. The term "sleeve" is used to mean a cylindrical member that houses the cylindrical aerosol container 10.

[0137] The sleeve 20 is composed of a cylindrical sleeve body 21 having a larger diameter than the aerosol container 10 , a first end cover 22 covering one end of the sleeve body 21 , and a second end cover 23 provided at the other end.

[0138] The first end cover portion 22 is detachably screwed and fixed to the sleeve body 21 via a screw portion, and the second end cover portion 23 is non-detachably fixed to the sleeve body 21. The second end cover portion 23 and the sleeve body 21 may be integral.

[0139] The first end top cover 22 is composed of a dome-shaped top cover body 222 and a threaded barrel 223 of a sleeve threaded portion screwed into the sleeve body 21. The top cover body 222 is reduced in diameter in a manner that gradually becomes a small diameter toward the top in consideration of aerodynamics, and the front end is a conical or dome-shaped curved surface with rounded corners. By setting it to such a shape with good aerodynamic effects, the influence of horizontal wind (crosswind) is reduced, and flight stabilization can be achieved.

[0140] The ejection drive unit 30 is accommodated in the second end cover 23 located at the bottom side of the aerosol container 10. The second end cover 23 is composed of a cylindrical portion 231 having one end fixed to the rear end of the sleeve body 21 (the end on the bottom side of the aerosol container 10), and an end plate 232 that closes the other end of the cylindrical portion 231.

[0141] [Support Structure of Aerosol Container 10]

[0142] The inner diameter of the sleeve 20 is larger than the outer diameter of the body 11a of the aerosol container 10. In the sleeve 20 of this structure, the aerosol container 10 is supported by the container holding portion 72 and the first end top cover portion 22 at both ends such as the head and the bottom to determine the position. As shown in the figure, when the aerosol container 10 is supported at a certain distance from the wall surface of the sleeve 20, a heat insulating material or a heat storage material can be installed in the interval space. However, the body 11a of the aerosol container 10 may not be supported at a distance from the inner wall of the sleeve 20.

[0143] In addition, you can Figure 1 As shown in (B), a plurality of radial support portions 21a for supporting the aerosol container 10 in a direction intersecting the axial direction of the container are provided on the inner wall of the sleeve 20. The radial support portions 21a support the aerosol container 10 in a manner that allows axial movement relative to the sleeve 20 and prevents movement in an orthogonal direction. For each radial support portion 21a, a support structure in which the body 11a of the aerosol container 10 is partially contacted at multiple locations in the circumferential direction may be provided, or a structure in which the entire circumference is supported by an annular wall.

[0144] In addition, the sleeve 20 may not be a sealed structure, but a partially breathable structure. For example, structures such as a mesh structure and a punching hole can be used. If so, there is a self-cooling when the aerosol is sprayed by the external gas to ease the effect of lightening the sleeve 20.

[0145] The bottom portion 11 b of the aerosol container 10 is supported by the container holding portion 72 disposed on the second end cover portion 23 side, and the head side of the aerosol container 10 is supported by the pressing member 221 provided on the first end cover portion 22 .

[0146] The pressing member 221 includes: a cylindrical body 221a, which protrudes from the top end of the first end cover portion 22 toward the rod 12 along the central axis direction of the aerosol container 10; and an end flange portion 221b, which is fixed to the first end cover portion 22 provided at one end of the cylindrical body 221a. The connecting pipe 16 connected to the actuator 14 and the nozzle 15 is inserted into the inner periphery of the cylindrical body 221a of the pressing member 221 so as to slide freely in the axial direction, and the front end surface of the cylindrical body 221a abuts or is close to the flange portion 14b of the actuator 14. The pressing member 221 can be integrally formed with the second end cover portion 23.

[0147] Next, refer to Figure 1 (D) to (F) describe the ejection drive unit 30.

[0148] The ejection drive unit 30 is arranged in the second end top cover 23 so as to be closer to the second end top cover 23 than the bottom 11b of the aerosol container 10. The ejection drive unit 30 is fixed relative to the second end top cover 23, moves the aerosol container 10 in the axial direction, and controls the ejection and stop of the contents of the aerosol container 10.

[0149] The ejection drive unit 30 pushes the aerosol container 10 axially from the bottom 11b side to move the aerosol container 10 to the axial head side. As the aerosol container 10 moves, the actuator 14 is pressed by the cylindrical body 221a of the pressing member 221, and the rod 12 is pressed into the aerosol container 10 by its reaction force, and the valve mechanism in the aerosol container 10 opens. When the valve mechanism opens, the contents are automatically ejected by air pressure.

[0150] The ejection drive unit 30 has a motor 31 as a rotation drive source, and a cam mechanism 32 for converting the rotation of the motor 31 into a linear movement of the container holding portion 72. The motor 31 and the cam mechanism 32 are mounted on a frame 301, which is fixed on the second end top cover portion 23. The cam mechanism 32 is provided with: a cam 32a, which is driven by the motor 31; and a cam follower 32b, which moves along the cam surface of the cam 32a. The rotation of the cam 32a is transmitted to the container holding portion 72 on the driven side via the cam follower 32b, so that it moves in a linear direction along the container center axis N direction of the aerosol container 10. The cam 32a shown in the figure is an oval disc cam, and the cam shaft is orthogonal to the center axis of the aerosol container 10. Through this structure, the rotation of the cam 32a is converted into a linear movement of the aerosol container 10. The cam 32a is a disc cam, and an energizing unit such as a spring for making the cam 32a and the cam follower 32b constantly abut can be appropriately provided.

[0151] Normally, the smallest diameter portion of the cam 32a abuts against the cam follower 32b, the container holding portion 72 is located at the retreat limit position, and the valve mechanism of the aerosol container 10 remains in the closed state ( Figure 1 (D)). The cam 32a is rotated by the motor 31, and the container holding portion 72 moves forward in the axial direction. That is, in the backward limit position, the diameter of the contact position of the cam follower 32b abutting the cam 32a is set to be smaller than the rotation center, and in the forward limit position, the diameter of the contact position of the cam follower 32b abutting the cam 32a is set to be larger than the rotation center. In the example shown in the figure, the valve is opened by moving from the smallest diameter portion to the largest diameter portion, rather than the largest diameter portion of the cam 32a, but it can also be configured to open the valve by the largest diameter portion.

[0152] [Valve structure]

[0153] Figure 2(B) shows an example of the valve mechanism 13 of the aerosol container 10 which is opened by the above-mentioned discharge drive device 30.

[0154] That is, the rod 12 is provided with a discharge flow path 12a of a predetermined size extending from the front end opening in the axial direction, and a rod hole 12b serving as a valve hole is opened on the side of the rod 12. The valve hole 12b is blocked by the inner circumferential surface of a gasket 13a installed on the edge of the hole of the sealing cup (mounting cup) 11d.

[0155] Normally, due to the air pressure and the thrust of the spring 13b, the rod 12 is pushed in the protruding direction, and the inner peripheral edge of the gasket 13a serving as the valve body is pressed in the axial direction, so that the inner peripheral surface of the gasket 13a is sealed with the hole edge of the rod hole 12b constituting the valve seat, thereby maintaining the closed valve state.

[0156] When the container holding portion 72 moves to the forward limit through the cam mechanism 32 of the above-mentioned ejection drive unit 30, the aerosol container 10 moves to the first end cover portion 22 side, and the flange portion 14b of the actuator 14 abuts against the end surface of the pressing member 221, and the rod 12 is pressed into the relative container inner side through its reaction force. When the rod 12 is pressed in, the inner peripheral edge of the gasket 13a bends toward the inner side of the container, and the inner peripheral surface of the gasket 13a leaves the hole edge of the rod hole 12b, the valve opens, and the squeezed content is ejected from the ejection flow path 12a of the rod 12 by air pressure.

[0157] The valve mechanism 13 shown in the figure is an example, and is not limited to such a structure, and various structures that normally maintain a closed valve state and open the valve by pressing the rod 12 can be applied.

[0158] In this example, the rotational movement of the motor 31 is converted into linear movement by the cam mechanism 32, but it is not limited to the cam mechanism 32. For example, if it is a mechanism that converts the rotational movement of the motor 31 into linear movement, such as a feed screw mechanism, a gear rack, etc., it can be applied. In addition, it is also possible to use a linear drive source such as a linear motor for linear drive, an electromagnetic solenoid, etc. instead of a rotary motor, and move the aerosol container 10 in the axial direction without using a movement conversion mechanism.

[0159] In addition, the nozzle 15 has various anti-drip components 700 as described later, or the nozzle 15 itself functions as the anti-drip component 700. In addition, in the nozzle, a component that is particularly important for exerting the dripping function and is located further forward than the ejection port in the ejection direction can be used as the anti-drip component 700. In the case where electrical control is required to exert the anti-drip effect, such as the anti-drip component 700 having a switch mechanism of the cover body, the anti-drip component 700 is connected to the power supply through electrical wiring. In addition, the power supply can be arranged on the anti-drip component 700. The anti-drip component 700 is configured to be attachable to and detachable from the ejection device.

[0160] [Container holding portion 72]

[0161] use Figure 1 (D) to (F) of FIG. 7 illustrate the container holding portion 72 .

[0162] The container holding portion 72 includes: a circular plate portion 72a, which abuts against the bottom 11b of the aerosol container 10; an annular convex portion 72b, which holds the bottom side end of the body 11a of the aerosol container 10 at the outer diameter end of the circular plate portion 72a; and a connecting shaft portion 72c, which is provided at the central part of the motor side surface of the circular plate portion 72a. An anti-slip material 73 is installed on the annular convex portion 72b to increase the friction with the container body.

[0163] [Configuration Example of Discharge Drive Section]

[0164] Figure 1 The ejection drive unit 30 shown is an example, and other configurations can be applied as the ejection drive unit 30. Figure 3 In the manner shown. Figure 3 In FIG. 2 , the sleeve 20 is simplified and represented by a quadrilateral.

[0165] Figure 3 (A) is a configuration in which the actuator 14 side of the aerosol container 10 is fixed to the sleeve 20, and the low structure member 30B abutting against the bottom 11b of the aerosol container 10 is pressed upward by the driving unit 30A. Figure 1 The ejection drive unit 30 is an example of this method. In this method, the actuator 14 side mounted on the rod 12 is fixed, so the ejection position is highly accurate. In addition, it is possible to cope with aerosol containers 10 of various diameters.

[0166] Figure 3 (B) is configured as follows: the aerosol container 10 is fixed relative to the sleeve 20, and the rod 12 is pressed down by the ejection drive unit 30 via the actuator 14. That is, the ejection drive unit 30 drives the abutment member 30B that abuts against the actuator 14 in the downward pressing direction through the drive unit 30A. In this way, the mechanical components can be concentrated on one side of the aerosol container 10, forming a compact and easily exchangeable structure. In addition, it is possible to cope with aerosol containers 10 of various heights.

[0167] in addition, Figure 3 The structure of the driving part 30A of (A) and (B) only needs to be a mechanism that drives in a linear direction. A movement conversion mechanism such as a cam or feed screw mechanism that converts the rotational movement of a rotary motor into a linear direction can be used. Alternatively, a linear motor, an electromagnetic solenoid, etc. for linear drive can be used instead of a rotary motor.

[0168] Figure 3In (C), the control is performed by an external valve 30C instead of the internal valve of the aerosol container 10. In the figure, the external valve 30C is conceptually recorded, so it can be set to a structure that is opened and closed by a solenoid valve or the like. When the external valve 30C is used, the pipeline 30D is only connected to the rod 12 of the aerosol container 10, so the installation of the aerosol container 10 is easy, and the opening and closing control is also easy. When using an existing aerosol container 10, for example, it is configured to press the rod 12 into the normally open state of the internal valve when assembling the aerosol container 10.

[0169] [Electrical equipment]

[0170] Next, return to Figure 1 (A) The electrical equipment for driving the ejection drive unit 30 will be described. Figure 1 (A) schematically shows the electrical equipment carried by the aircraft.

[0171] The ejection device control unit 210, which is a control device for controlling the ejection drive unit 30, is provided separately from the flight control unit 110 for controlling the flight of the aircraft 100, and is provided on the body 101 side together with the flight control unit 110. In addition, the ejection device power supply 211 for driving the ejection drive unit 30 is provided separately from the power supply for driving the aircraft 100 (which is assumed to be incorporated into the flight control unit 110, not shown), and is mounted on the body 101 side.

[0172] Furthermore, the ejection device signaling unit 212 including an antenna for remotely controlling the ejection device 1 and the flight communication unit 112 including an antenna for remotely controlling the aircraft 100 are provided separately and mounted on the aircraft body 101 side.

[0173] The ejection control unit 210, the ejection device communication unit 212, and the ejection device power supply 211 may have some or all of the functions of the flight control unit 110, the flight communication unit 112, and the flight power supply. Figure 2 (C) is an example in which the power supply provided in the flight control unit 110 is shared.

[0174] In addition, when a control unit, a power supply unit and a communication unit are required to operate the drip prevention member 700, the ejection device control unit 210, the ejection device power supply 211 and the ejection device communication unit 212 can serve as the control unit, power supply unit and communication unit.

[0175] [Supporting structure with the machine body]

[0176] The ejection device support portion 50 that supports the ejection device 1 on the machine body 101 may be constructed as a sliding interlocking structure of a slide rail and a T-slot, a bayonet connection that enables suspension and removal along the rotation direction, and various support units that are easy to disassemble and install, such as screw clamps, clip connections, and clamps. The ejection device support portion 50 may be provided with a direction changing device such as a pan / tilt head.

[0177] In addition, an electrical connection point for electrically connecting the ejection device control unit 210 and the ejection device power supply 211 disposed on the body 101 side to the motor 31 of the ejection drive unit 30 may be provided on the ejection device support unit 50, and a cable may be directly connected from the sleeve 20 to a connector disposed on the body 101. In addition, a power source such as a secondary battery and a wireless communication device may be provided in the sleeve 20, and an electrical signal from the flight control unit 110 disposed on the body 101 side may be sent and received with the flight control unit 210 in the sleeve 20 through wireless communication.

[0178] Next, the operation of the ejection device of the aircraft of the present invention will be described.

[0179] [Change job]

[0180] like Figure 1 As shown in (B), a replacement aerosol container assembly 40 in which the aerosol container 10 is contained in the sleeve 20 is prepared in advance. When replacing, the aerosol container assembly 40 is removed from the spray device support portion 50 and a new aerosol container assembly 40 is installed. By setting the spray device support portion 50 to a structure that can be easily disassembled by manual operation without using tools, replacement becomes easy. For the replaced aerosol container assembly 40, the aerosol container 10 is removed from the sleeve 20, and the gas and contents are completely released and discarded. The sleeve 20 can be reused. In addition, in the present embodiment, the sleeve 20 can also be kept fixed on the body 101, and only the aerosol container 10 is replaced.

[0181] [Spraying operation]

[0182] Next, refer to Figure 4 Describe spraying operations. Figure 4 (A) is an explanatory diagram showing an example of remote operation of a control terminal and an operation terminal of an aircraft equipped with an ejection device, and (B) is a simple control block diagram.

[0183] Spraying operations such as Figure 4 As shown in (A), the flight of the aircraft 100 is remotely controlled by the control terminal 120, and the ejection device 1 is remotely controlled by the operation terminal 160. The operation terminal 160 is also used as a controller of the camera 106 mounted on the aircraft 100. The operation terminal 160 is provided with, for example, an ejection button 163, a stop button 164, and a display screen 167.

[0184] When the operator presses the ejection button 163, the ejection operation is performed. At this time, an ejection command signal is sent, and the ejection device carried by the aircraft 100 receives it using the communication unit 212, and the contents are ejected. That is, when the image on the display 167 is viewed and the ejection button 163 is pressed, an ejection command signal is sent, and the ejection device carried by the aircraft 100 receives it using the communication unit 212, and the ejection device control unit 210 drives the ejection drive unit 30, and the rod 12 of the aerosol container 10 is pressed in, and the contents are ejected. When the stop button 164 is pressed, a stop command signal is sent, and the ejection drive unit 30 releases the pressing of the rod 12, and the ejection stops.

[0185] Here, when the drip prevention member 700 needs to be controlled during spraying, for example, a switchable cover is provided, and if the cover needs to be opened during spraying, control to open the cover manually or automatically is performed before starting spraying.

[0186] [Configuration example of drip prevention member]

[0187] Figure 5 (A) shows the situation where the drip prevention member 700 is closed. Figure 5 (B) indicates the open state. The drip prevention member 700 of this embodiment generally includes a mounting portion 710 that maintains connection with the connection pipe 16 when mounted, a cover 720 that can be opened and closed, and a prevention member driving portion (driving portion) 730 for opening and closing the cover.

[0188] The mounting portion 710 shown in the cross-section line in the figure is a structure for interlocking with the connecting pipe 16, and has an inner fitting portion 711 and an outer fitting portion 712. The inner fitting portion 711 is a short cylindrical member, which protrudes in a manner of being inserted into the pipe when interlocked along the length direction. The outer circumference of the inner fitting portion 711 is smaller than the inner circumference of the connecting pipe 16. In addition, a crimping portion 711c is provided near the protruding front end of the inner fitting portion 711. The outer circumference of the crimping portion 711c is larger than the inner diameter of the connecting pipe 16, so when the elastic inner fitting portion 711 is inserted into the connecting pipe, pressure is applied to the connecting pipe 16 from the inner side of the crimping portion 711c, so that the friction between the connecting pipe 16 and the inner fitting portion 711 is increased to maintain the connection.

[0189] The outer fitting portion 712 is a short cylindrical member into which the connecting pipe 16 is inserted and has an inner peripheral diameter larger than the outer peripheral diameter of the connecting pipe 16 .

[0190] A front end portion 714 protruding outward is provided on the end face 713 of the mounting member 710. By providing a liquid passage hole 715 inside the front end portion 714, the shape of the ejection outlet can be changed by simply replacing the front end portion 714, compared with simply providing a hole as an ejection outlet on the end face 713, which can improve versatility.

[0191] With this configuration, a liquid passage region is formed by the internal space 16 a of the connection duct 16 , the internal space 711 a of the mounting portion 710 , and the passage hole 715 , and the discharge port is disposed at the front end of the passage hole 715 .

[0192] The drip prevention member 700 of this structure can be installed without changing the existing connection pipe 16, and the ejection performance as the nozzle 15 can be maintained. In addition, the structure of the mounting portion is not limited to this, for example, the outer fitting portion 712 can be abutted against the connection pipe 16 and fixed by friction, or the outer fitting portion 712 and the inner fitting portion 711 can be abutted against the connection pipe 16. In addition, the position can be determined by making the front end portion 161 of the connection pipe 16 abut against the inner wall 716 of the base of the mounting portion 710.

[0193] The cover body 720 has a flat cover body main body 721 connected to the mounting portion 710 via a cover body connecting portion 722. The cover body main body 721 has an area at least large enough to cover the front end portion 161. The cover body connecting portion 722 has a hinge structure and rotatably supports the cover body main body 721. In the cover body main body 721, a position opposite to the front end portion 714 in the closed state is Figure 5 As shown in (B), a cover body recess 723 is provided with a size that the front end portion 714 does not interfere with (contact) the cover body main body 721 even in the closed state.

[0194] The cover body main body 721 is connected to the linear motion portion 732 of the prevention member driving portion 730 (driving portion) via the linear motion connecting member 731. Both ends of the linear motion connecting member 731 are configured as hinges.

[0195] The prevention member driving unit 730 of this embodiment is an electromagnetic actuator. A direct-acting unit 732 is arranged at the base 733 of the prevention member driving unit 730, which can move left and right in the figure according to the command of the ejection device control unit 210. In addition, the driving unit is not limited to the electromagnetic actuator, and artificial muscle actuators such as electroactive polymer actuators and dielectric elastomers can be used, and a rack and pinion mechanism, a worm rack mechanism, and a sliding cam mechanism using an electric motor can be used as long as it is a switch mechanism that can open and close the cover body 721.

[0196] In the example shown in the figure, the hinge of the cover connecting part 722 for connecting the cover body 721 to the mounting part 710 is arranged to be vertically above the nozzle when the aircraft is in flight. With this arrangement, even if the driving part fails during flight and the switch mechanism does not work, the cover body 721 is still in a state of covering the nozzle due to gravity, thereby preventing dripping before the aircraft returns.

[0197] If the prevention member driving unit 730 (cover body driving unit) of this structure is used, the nozzle is closed when no spraying is performed, and is opened only during spraying. When the spraying is completed, it can be closed again, thereby preventing dripping from the front end of the nozzle.

[0198] The trigger for opening and closing the cover can also be a direct instruction from the operator. In this case, on the operation terminal 160, an opening button and a closing button of the cover can be set separately in addition to the ejection button 163 and the stop button 164. Alternatively, it can be set to the closed state in advance under normal circumstances, and the ejection device control unit 210 is linked to the pressing of the ejection button 163 to drive the electromagnetic actuator to open the nozzle. In this way, by linking the ejection action with the opening action and closing action of the cover, it is possible to take into account both ejection and dripping prevention.

[0199] In addition, even if there is no structure having a mechanism for opening and closing the cover body by power, the cover body can be opened and closed by the pressure when the liquid is ejected. In this case, the structure of the opening and closing mechanism can be simplified.

[0200] <Modification>

[0201] In the above-mentioned embodiment, the aerosol container is configured as a container of a liquid substance, and the discharge device is configured as an aerosol discharge device. However, the discharge device in the present invention is not limited to an aerosol discharge device.

[0202] Fig.18 This is an example of an unmanned aerial vehicle, which has a liquid tank 180, a pump 182 for delivering the liquid to the nozzle, a connecting pipe 16 as a pipe for the flow path of the liquid from the pump to the nozzle, and a spraying device including a nozzle 15 as a spraying port. The liquid tank 180 holds the liquid to be sprayed. When the spraying operation starts, the liquid is delivered by operating the pump 182. The liquid passes through the connecting pipe 184 and is sprayed from the nozzle 15. The nozzle 15 has the above-mentioned anti-drip member to prevent dripping of the spraying device.

[0203] Next, another embodiment of the discharge device of the present invention will be described. In the following description, only the parts different from the above-mentioned embodiment will be described, and the same components will be given the same reference numerals and their description will be omitted.

[0204] [Implementation Method 2]

[0205] use Figure 6 (A) to (C) illustrate the drip prevention member 700 of embodiment 2. The drip prevention member of this embodiment also has a cover 720, but the opening and closing mechanism of the cover is different. That is, this embodiment is a mode in which the cover 720 changes its position in a direction intersecting the direction in which the spray is ejected.

[0206] like Figure 6As shown in (A), the structure of the installation portion 710 and the passage of the liquid is the same as that of the first embodiment. In this embodiment, there is a cylindrical portion 740, and a cover body 720 is provided at its end. The length of the cylindrical portion 740 is not limited to the example in the figure, as long as it is a length that the cover body main body 721 does not contact the front end portion 714 at least when the switch is actuated. The presence of the cylindrical portion 740 can prevent the front end portion 714 from contacting the cover body main body 721. The cylindrical portion 740 will be described in detail later.

[0207] The cover body 721 of this embodiment is substantially circular and is mounted in a connection portion 736 near the circumference so as to be rotatable around a drive shaft 734. In addition, the prevention member driving portion 730 of this embodiment is a motor 735 that rotates the drive shaft 734. As the rotation moves, the cover body 721 Figure 6 The nozzle is rotated as shown in (B) and (C). As a result, the state of the nozzle is switched between the open state (B) and the closed state (C). When the rotation of the motor 735 of the prevention member driving unit 730 starts and ends, the ejection device control unit 210 controls the rotation angle, thereby switching the open state and the closed state. That is, according to this embodiment, the opening and closing control of the ejection outlet of the nozzle can be performed by a relatively simple structure and control, thereby preventing dripping when not ejecting.

[0208] In addition, even if the cover body 720 does not rotate but moves linearly by sliding in a direction intersecting the ejection direction, the opening and closing of the ejection port can be controlled.

[0209] [Implementation method 3]

[0210] This embodiment is also a mode in which the cover 720 changes position in a direction intersecting the ejection direction. In the second embodiment, the cover 720 is rotated or slid, but in this embodiment, a diaphragm mechanism is used as the cover 720.

[0211] use Figure 7 (A) and (B) illustrate the drip prevention member 700 of embodiment 3. The cover 720 is a diaphragm mechanism provided at the end of the cylindrical portion 740. The diaphragm mechanism includes: a plurality of diaphragm sheets 724, and a diaphragm unit 725 having a cam or the like and accommodating the diaphragm sheets 724. As the diaphragm mechanism, a mechanism similar to the diaphragm mechanism used for a camera can be used.

[0212] The configuration of this embodiment can also prevent liquid from dripping from the discharge port.

[0213] [Implementation Method 4]

[0214] use Figure 8(A) and (B) illustrate the drip-proof component 700 of embodiment 4. The drip-proof component of this embodiment is composed of a cover body 720 and a cylindrical portion 740. The cylindrical portion 740 is a component that covers a predetermined range of space in the ejection direction from the ejection port, and forms a cylindrical space 740a in front of the ejection direction. Due to the existence of the cylindrical portion 740, a certain degree of drip-proof effect can be obtained even if the cover body 721 is in an open state. Secondly, by making the cover body 721 in a closed state, the drip-proof effect is further improved. The cylindrical portion will be described in detail later.

[0215] exist Figure 8 Although an electromagnetic actuator is used as the opening and closing mechanism of the cover, the invention is not limited to this, and any method can be adopted.

[0216] [Implementation method 5]

[0217] Fig. 9 The ejection device shown in the (A) cross-sectional view and (B) stereoscopic view has a protrusion 738, which has a protruding surface protruding from the nozzle to the front in the ejection direction of the liquid. The protrusion 738 has a portion that comes to the lower side than the ejection port when the aircraft is in flight. Thus, the protrusion 738 functions as a receiving portion for receiving the liquid that drips. In addition, the protrusion 738 can be provided integrally with the mounting portion 710, or it can be provided separately from the mounting portion 710 and used in combination.

[0218] exist Fig. 9 In the example of , the wall-like portion 737 is provided perpendicularly from the front end portion in the ejection direction on the protruding surface of the protruding portion 738. Therefore, even if the amount of liquid substance that drips is large, the protruding portion functions as a storage portion for the liquid substance, and the possibility of the liquid substance leaking to the outside is reduced. However, even in the absence of the wall-like portion 737, the protruding portion 738 functions as a receiving portion, so a certain degree of anti-drip performance can be obtained.

[0219] According to this embodiment, a mechanism for opening and closing the cover is not required, so the possibility of failure can be reduced and a drip-proof effect can be obtained. However, in the drip-proof component 700 of this embodiment, a cover body that covers the front space 735a of the ejection outlet in the ejection direction can be provided to form a closed space between the cover body and the protrusion to improve the leakage prevention effect. As the opening and closing mechanism of the cover body, any mechanism such as the mechanism described in other embodiments can be used.

[0220] [Implementation Method 6]

[0221] Fig.10The ejection device has a cylindrical portion 740 that protrudes from the nozzle periphery toward the front of the ejection direction of the liquid. The cylindrical portion 740 is integrally formed with the mounting portion 710, or is a cylindrical member mounted on the mounting portion 710. By providing the cylindrical portion 740, even if dripping occurs, the effect of making it difficult for the droplets to fall outside the machine body can be obtained. The cylindrical portion 740 functions as a receiving portion for the liquid.

[0222] In addition, in this embodiment and other embodiments, the name "cylindrical portion" is used, but the shape is not limited to a strict cylindrical shape. For example, the cross section can be a flat ellipse. In addition, it can be a shape having a flat bottom surface, a top surface and a side surface, which are connected by a flat surface or a curved surface. In addition, the cylindrical portion can also be considered as a type of protrusion.

[0223] [Implementation method 7]

[0224] use Fig.11 (A) to (C) illustrate a dripping prevention member 700 according to Embodiment 7. The dripping prevention member of this embodiment has a tubular portion 740 similar to that of Embodiment 6, and is further provided with a liquid storage portion (storage portion) used when the tubular portion 740 drips.

[0225] Fig.11 (A) shows a case where an intercepting portion 810 is provided as a liquid storage portion in the cylindrical portion 740. The intercepting portion 810 is a wall-like portion provided at the bottom of the cylindrical portion 740 (the portion that comes to the bottom when in the flying state) to prevent the amount of dripping liquid from leaking from the front end of the cylindrical portion 740.

[0226] Fig.11 The (B) cross-sectional view and (C) stereoscopic view show the case where the concave portion 820 is provided as a liquid storage portion in the cylindrical portion 740. The concave portion 820 is a groove-shaped portion provided at the bottom of the cylindrical portion 740 (the portion that comes to the bottom when in the flying state), and has the function of storing the amount of liquid droplets. In the example shown in the figure, a plurality of concave portions 820 are arranged in a direction intersecting (orthogonal) with the ejection direction.

[0227] In this way, in addition to the cylindrical portion 740, the intercepting portion 810 and the recessed portion 820 are provided, thereby effectively preventing the dripping liquid from overflowing to the outside. In addition, the number and position of the intercepting portion 810 and the number and position of the recessed portion 820 are not limited to the example shown in the figure. In addition, a bagged member can also be used as a liquid storage portion (storage portion) for the liquid. In this case, by continuously providing the bagged member from the protruding surface as a receiving portion for the liquid, the liquid can be smoothly guided.

[0228] [Embodiment 8]

[0229] use Fig.12(A) and (B) will describe a dripping prevention member 700 according to Embodiment 8. The dripping prevention member of this embodiment includes an absorbent material 800 as a solidified portion of a liquid substance.

[0230] Fig.12 The ejection device of (A) has a cylindrical portion 740 in front of the ejection direction, and an absorbent material 800 is arranged on the inner circumferential surface of the cylindrical portion 740. In addition, if the absorbent material 800 is arranged at least on the bottom surface of the cylindrical portion, the effect of absorbing the liquid substance of the dripping liquid can be exerted. As a method for arranging the absorbent material 800, any method such as pasting using an adhesive or the like, fixing using a band or the like, embedding and fixing can be adopted. The absorbent material 800 can be directly arranged on the cylindrical portion, but a clamp for facilitating the carrying and arrangement of the absorbent material can also be used.

[0231] A material that can effectively absorb the sprayed substance is used as the absorbent material 800. For example, if the sprayed liquid substance is mainly composed of water, it is preferable to use a high molecular absorbent material such as a highly water-absorbent polymer.

[0232] Fig.12 In the ejection device of (B), the cylindrical portion 740 is formed by the absorbent material 800. In order to form the absorbent material 800 into a cylindrical shape, it is preferred to use a frame made of resin or metal. In addition, the absorbent material 800 may be formed of a material having a certain degree of rigidity and capable of absorbing liquid substances, such as felt, diatomaceous earth, or unglazed pottery (ceramic).

[0233] Here, the absorbent is formed into a cylindrical shape, but a protrusion may be provided at least below the discharge port.

[0234] According to the present embodiment, the absorbent material 800 as a solidified material solidifies the liquid material dripping from the discharge port, so that the dripping prevention effect is improved.

[0235] [Implementation Method 9]

[0236] use Fig.13 (A) and (B) will describe the dripping prevention member 700 of Embodiment 9. The dripping prevention member of this embodiment also has an absorbent material 800 as a solidified portion of a liquid substance.

[0237] Fig.13 The ejection device of (A) has a cylindrical portion 740 in front of the ejection direction, and an absorbent material 800 is provided on the inner peripheral surface of the cylindrical portion 740. Furthermore, a permeable portion 801 made of a stainless steel mesh through which liquid substances can pass is provided further inside the absorbent material 800. This structure is, for example, Fig.13 As shown in (B), it is possible to install the absorbent material 800 on the inner peripheral surface of the cylindrical portion 740, and further install the permeable portion 801 on the inner peripheral surface thereof.

[0238] According to this structure, the liquid substance of the dripping liquid passes through the permeable portion 801 and is absorbed and solidified by the absorbent material 800, so it does not leak to the outside. Furthermore, when the absorbent material 800 is made of a material that absorbs water, such as a high molecular polymer, the permeable portion 801 also functions as a member that suppresses the expansion of the absorbent material that swells when absorbing water, so the expanded absorbent material does not clog the ejection port, and the original ejection performance is not reduced, and it can be continuously used.

[0239] [Implementation 10]

[0240] Here, as a curing unit, in addition to the absorbent material 800, a heating unit that heats and evaporates a liquid substance, and a cooling unit that cools and solidifies it can also be used. As such a curing unit, a Peltier element that can control both heating and cooling is preferred. In addition, if only heating is performed, an electric heating component such as a nickel-chromium wire heater can also be used. In addition, curing by heating or cooling can also be achieved by fixing a heating unit such as a mobile heater, a cooling unit such as a cooling jet, etc. on a protrusion or a cylindrical portion with a bandage or the like. In addition, in the case of setting a cover body, as in the case of the absorbent material, the curing unit that performs heating and cooling can also be set at a position opposite to the ejection port on the inner side of the cover body.

[0241] [Implementation 11]

[0242] In the above embodiments, various methods for preventing dripping liquid, such as using a cover, providing a liquid storage portion, and providing an absorbent material, have been described. These methods can be used in any combination unless there is any conflict.

[0243] For example Fig.14 The structure of (A) has a cover body 721 that can be opened and closed, and an interception portion 810 is provided at the front end of the cylindrical portion 740. In addition, Fig.14 The configuration of (B) includes a cover body main body 721 that can be opened and closed, and a plurality of groove-shaped recessed portions 820 arranged in a direction intersecting the ejection direction are provided in a cylindrical portion 740 .

[0244] also, Fig.15 The configurations of (A) and (B) include a cover body main body 721 that can be opened and closed, and an absorbent material 800 is provided on the inner peripheral surface of the cylindrical portion 740. (A) shows a closed state, and (B) shows an open state.

[0245] By combining various methods, it is possible to enhance the effect of the dripping prevention member 700. For example, in a configuration in which a cover is provided, it is preferable that an absorbent material for absorbing liquid is provided on a portion of the cover that faces the discharge port when the cover is closed.

[0246] [Implementation 12]

[0247] In this embodiment, an example of a method for forming the drip-proof member 700 is described. In this embodiment, the cylindrical portion 740 is the drip-proof member 700. The cylindrical portion 740 can be removed from the mounting portion 710 via a screw member as a snap-fit ​​portion. Fig.16 As shown in (A), the thread groove 744 cut out on the inner surface of the opening of one end of the cylindrical portion 740 is guided to the thread groove 718 provided at the end of the mounting portion 710, whereby the cylindrical portion 740 is screwed into the mounting portion 710 to form the drip-proof member 700. The thread grooves provided on the two members can also be combined to form a threaded portion.

[0248] Here, it is preferred that the outer peripheral surface of the cylindrical portion 740 is as follows Fig.16 As shown in (B), an anti-slip portion 745 is provided. In this embodiment, when the cylindrical portion 740 is installed in the mounting portion 710, the cylindrical portion 740 is rotated and moved with the longitudinal direction as the axis, so a plurality of anti-slip portions extending in a direction orthogonal to the moving direction, i.e., the longitudinal direction, are provided.

[0249] According to the present embodiment, the cylindrical portion 740 can be easily replaced, thereby achieving an effect of improving maintainability.

[0250] [Implementation 13]

[0251] In this embodiment, another example of a method for forming the drip-proof member 700 is described. The cylindrical portion 740 as the drip-proof member in this embodiment can also be removed from the mounting portion 710. Fig.17 As shown in (A), the insertion portion 746 as the engaging portion provided at one end of the cylindrical portion 740 is embedded in the insertion receiving portion 719 provided at the end of the mounting portion 710, thereby forming the drip prevention member 700. The insertion portion 746 and the insertion receiving portion 719 can be combined as a fitting portion.

[0252] Here, it is preferred that the outer peripheral surface of the cylindrical portion 740 is as follows Fig.17 As shown in (B), an anti-slip portion 745 is provided. In this embodiment, when the cylindrical portion 740 is installed in the mounting portion 710, a force acts along the length direction of the cylindrical portion 740, so a plurality of anti-slip portions are provided along a direction orthogonal to the force, that is, the circumferential direction of the cylindrical portion. According to this embodiment, the cylindrical portion 740 can be easily replaced, thereby having an effect of improving maintainability.

[0253] The drip-proof components of the above-mentioned embodiments can be used in any combination within the range that does not conflict with each other. For example, the presence or absence of a cylindrical portion or a protrusion, the presence or absence of an absorbent material, the presence or absence of a recess, an interception portion, etc. can be combined to improve the drip-proof effect.

[0254] In the above-mentioned embodiments, a multi-rotor helicopter is used as an example of an aircraft equipped with a liquid material ejection device, but the ejection device of the mobile body of the present invention can also be applied to helicopters, not only aircraft using rotors (rotors), but also unmanned aircraft such as fixed-wing aircraft, airships, and gliders, and can also be applied to manned aircraft without being limited to unmanned aircraft. In addition, it is not limited to aircraft, but can also be widely used in vehicles running on tracks, vehicles running on roads, and various mobile bodies with or without people.

Claims

1. A discharge device for an aircraft, It is characterized in that Liquid is discharged from the nozzle installed in the machine. A cover body is provided for opening and closing the discharge port of the nozzle, A driving unit is provided to open and close the cover. It also has a cylindrical portion that is arranged to protrude from the periphery of the discharge port in the discharge direction of the liquid substance, and a mounting portion that maintains connection with a connection pipe connected to the nozzle when mounted; The cylindrical portion is integrally formed with the mounting portion, or is a cylindrical component mounted on the mounting portion. The mounting portion has a fitting portion, which is a structure that fits with the connecting pipe. A liquid passage area is formed by the inner space of the connecting pipe, the inner space of the mounting portion and the through hole, and the discharge port is arranged at the front end of the through hole. The nozzle discharges the liquid substance as a straight jet. The interior of the cylindrical portion forms a cylindrical portion space along the discharge direction of the liquid substance. The inner peripheral surface of the cylindrical portion is arranged parallel to the discharge direction.

2. The ejection device of an aircraft according to claim 1, The cover body is rotated by hinges to open and close the discharge port.

3. The ejection device of an aircraft according to claim 2, The hinge is arranged so that when the aircraft is in flight, the hinge is located above the discharge port in the vertical direction.

4. The ejection device of an aircraft according to claim 2, The cover body has a recessed portion, which is disposed at a position opposite to the discharge port in a closed state, for preventing interference with the discharge port.

5. The ejection device of an aircraft according to claim 1, The cover body opens and closes the discharge port by sliding in a direction perpendicular to the discharge direction of the liquid material.

6. The ejection device of an aircraft according to claim 5, The cover body slides by rotational motion or linear motion.

7. The ejection device of an aircraft according to claim 5, The cover body is a diaphragm mechanism having a plurality of diaphragm sheets.

8. The ejection device of an aircraft according to claim 1, The cover body and the discharge port are arranged at positions where the discharge port does not abut against the cover body when the cover body is in a closed state.

9. The ejection device of an aircraft according to claim 1, The cover body is provided with an absorbent material for absorbing the liquid substance at a position opposite to the discharge port when the cover body is in a closed state.

10. The ejection device of an aircraft according to claim 1, The cylindrical portion is in a cylindrical shape.

11. The ejection device of an aircraft according to any one of claims 1 to 10, The discharge device discharges a liquid substance contained in an aerosol container or a liquid tank carried by the body.

Images