KR102394457B1 - Aircraft with launch device - Google Patents

Abstract

The present invention relates to an air vehicle having a launch device.
According to an embodiment of the present invention, a plurality of air flow means for generating a flow of air are symmetrically arranged in the disc-shaped aircraft frame, and the propeller included in the air flow means is configured not to be exposed to the outside, and for destroying the building glass window Disclosed is an aircraft equipped with a launch device configured to provide a fire suppression function and a rescue function in the event of a disaster such as a fire in a building by having a launch device capable of launching a projectile in the lateral direction.

Description

Aircraft with launch device

The present invention relates to an aircraft having a launch device, and more particularly, a plurality of air flow means for generating a flow of air in a disk-shaped aircraft frame are symmetrically arranged, and a propeller included in the air flow means is exposed to the outside In the case of a disaster such as a fire in a building, the launch device is provided with a launch device capable of launching a projectile for breaking the building window in the lateral direction, and a launch device equipped with a launch device configured to provide a fire suppression function and a rescue function in case of a disaster such as a fire in the building. it's about

Various types of unmanned aerial vehicles capable of flying have been proposed with rotating blades such as propellers. Such an unmanned aerial vehicle is being improved in a form having various additional functions, for example, an unmanned aerial vehicle having an additional function for fire suppression has been proposed.

As an example of such prior art, Korean Patent Registration No. 10-1925078 (registered on November 28, 2018) relates to a drone for fire suppression in a high-rise building, which flies up to the height of the fire and provides water directly to the fire site through the spray nozzle. A drone that suppresses fires occurring on high floors that cannot be sprayed with water in a conventional fire engine by spraying was proposed.

As another example of the prior art, Korean Patent Registration No. 10-1566341 (registered on October 30, 2015) relates to a fire drone for fire suppression, which can freely move on the ground and in flight, and is connected to the central control system to be unmanned from a distance. A fire-fighting drone for fire suppression that operates was proposed.

However, the conventional unmanned aerial vehicle as described above has a limitation in that it can be exposed to safety accidents because the rotating blades such as propellers are exposed to the outside.

In particular, in the case of an unmanned aerial vehicle having a building fire suppression function, water or fire extinguishing agent must be fired by approaching or entering the building. There was a limit to that.

On the other hand, in providing a fire suppression function for a building interior or a rescue function for a person inside a building through an unmanned aerial vehicle, it may be hindered in providing such a function due to the glass window of the building. An effective solution to this problem could not be proposed.

Republic of Korea Patent Registration 10-1925078 (Registered on November 28, 2018) Republic of Korea Patent Registration 10-1566341 (Registered on October 30, 2015)

The present invention has been devised in view of the above problems, in which a plurality of air flow means for generating air flow are symmetrically arranged in a disk-shaped aircraft frame, and the propeller included in the air flow means is configured so that it is not exposed to the outside. It is to provide an aircraft equipped with a launch device configured to provide a fire suppression function and rescue function in the event of a disaster such as a fire in a building by having a launch device capable of launching a projectile for destroying a building window in the lateral direction. .

According to one aspect of the present invention for achieving the above object, the body portion; an outer body portion formed in a ring shape surrounding the outer side of the main body portion and disposed in a state having a gap from the outer side of the main body portion; a connecting frame unit configured to connect and integrally combine the main body and the outer body and allow air to flow in an up-down direction; It is symmetrically disposed in the ring-shaped space between the outer side of the main body and the inner side of the outer body part, is installed based on the connection frame part, and uses a propeller driven by a motor to move air introduced from the upper part to the lower part. a plurality of air flow means configured to be pressurized; and a launch device capable of laterally launching a projectile for destroying a building window loaded in a launch tube installed on one side of the main body.

Preferably, the launch device has an arrow shape including a launch tube installed on one side of the main body, a colliding body on the front side and a gas container on the rear side, and after the gas container is loaded in the canister. When a through hole is formed by an external force at the end, the projectile is launched toward the front side of the canister by the gas pressure ejected through the through hole, and it is installed on the rear side of the projectile and applies an external force to the rear end of the gas container when a control signal is input. and a firing operation mechanism for forming a through hole.

Preferably, the firing operation mechanism comprises: an electromagnet installed at the rearmost side of the canister; a permanent magnet positioned in front of the electromagnet and capable of moving forward in the canister when receiving a repulsive force from the electromagnet; It is provided on the front side of the magnet and is configured to include a needle for a hole configured to form a hole by applying an external force to the rear end of the gas container when the permanent magnet moves forward.

Preferably, the present invention is provided with a device for discharging an extinguishing agent in the firing direction of the projectile.

Preferably, the device for discharging the fire extinguishing agent may pressurize the liquid fire extinguishing agent inside the storage container installed in the main body with a pump, and then spray and discharge in the lateral direction through the spray pipe extended on one side of the main body. it is a device

Preferably, the device for discharging the fire extinguishing agent is a ball type fire extinguishing agent capable of discharging the ball type fire extinguishing agent stored in the discharge pipe installed to have a side discharge direction of the main body through the control of the discharge control mechanism. it is an exhaust device.

Preferably, the ball-type fire extinguishing agent discharging device includes: a discharge pipe installed inside the main body and accommodating one or more ball-type fire extinguishing agents therein, and installed so that the ball-type fire extinguishing agent can be discharged in the lateral direction of the main body by at least its own weight; It is installed on the discharge side of the discharge pipe and is configured to include a discharge control mechanism for controlling the discharge of the ball-type fire extinguishing agent accommodated in the discharge pipe.

Preferably, the discharge control mechanism includes a first state that protrudes into the interior of the discharge pipe so as to be a discharge locking operation that prevents movement by its own weight of the ball type fire extinguishing agent at a point of the discharge pipe, and the weight of the ball type fire extinguishing agent under its own weight. At another point in the longitudinal direction of the first engaging piece and the discharge pipe that can be converted to a second state retracted from the inside of the discharge pipe so as to be a discharge release operation that can be moved by A second locking piece that can be converted into a first state that protrudes into the interior of the discharge pipe to become a blocking operation, and a second state that is retracted from the inside of the discharge pipe to be a discharge release operation that allows movement by its own weight of the ball-type fire extinguishing agent and a driving mechanism for alternately changing the first and second locking pieces into a first state or a second state, respectively.

Preferably, the discharge pipe is installed so that the ball type fire extinguishing agent is put in through the upper opening, stored inside, and discharged through the side opening, and the ball type fire extinguishing agent discharged by the discharge release operation of the discharge control mechanism is discharged. and an accelerated discharge means for further accelerating and discharging through the lateral opening.

Preferably, the acceleration discharge means is capable of transmitting the rotational force in a pressurized contact with the surface of the ball-type fire extinguishing agent passing through the interior of the discharge pipe, and at least two or more are symmetrically arranged with respect to the central axis of the discharge pipe. It is configured to include a wheel and a motor driving means for providing a rotational force to each of the acceleration wheels.

The aircraft equipped with the launch device of the present invention as described above is configured so that the propeller included in the air flow means is not exposed to the outside, and there is an advantage that it can safely approach the building for purposes such as fire suppression or rescue.

In addition, the aircraft equipped with the launch device of the present invention is equipped with a launch device capable of launching a projectile for breaking a building window in the lateral direction, thereby effectively providing a suppression function for fire inside a building or a rescue function for people inside the building. There is this.

In addition, the aircraft equipped with the launch device of the present invention is provided with a device for discharging the extinguishing agent in one direction of the main body portion, so that it can easily access high-rise fire sites where it is difficult for a fire engine to approach and provide a fire suppression function. have.

1 is a perspective view of an aircraft according to an embodiment of the present invention;
Figure 2 is a bottom direction perspective view of an aircraft according to an embodiment of the present invention;
3 is a partial excerpt cross-sectional view of an aircraft according to an embodiment of the present invention;
4 is a partial excerpt cross-sectional view of an aircraft according to an embodiment of the present invention;
5 is a partial cross-sectional view of an aircraft according to an embodiment of the present invention;
6 is a perspective view of a partial excerpt of an aircraft according to an embodiment of the present invention;
7A is a partial cross-sectional view of an aircraft according to an embodiment of the present invention;
7B is another partial cross-sectional view of an air vehicle according to an embodiment of the present invention;
8 is a partial cross-sectional view of an aircraft according to an embodiment of the present invention;
9 is a bottom side perspective view of an aircraft according to another embodiment of the present invention;
10 is a control configuration diagram of an aircraft according to an embodiment of the present invention.

The present invention may be embodied in various other forms without departing from its technical spirit or main characteristics. Accordingly, the embodiments of the present invention are merely illustrative in all respects and should not be construed as limiting.

The terms 1st, 2nd, etc. are used only for the purpose of distinguishing one component from another component. For example, without departing from the scope of the present invention, a first component may be referred to as a second component, and similarly, a second component may also be referred to as a first component.

When a component is referred to as being “connected” or “connected” to another component, it may be directly connected or connected to the other component, but another component may exist in between.

As used herein, the singular expression includes the plural expression unless the context clearly dictates otherwise. In the present application, terms such as "comprises" or "comprising", "have" and the like are intended to represent the presence of elements or combinations thereof described in the specification, and the possibility that other elements or features may be present or added. It is not precluded.

Hereinafter, preferred embodiments according to the present invention will be described in detail with reference to the accompanying drawings.

Figure 1 is a perspective view of an aircraft according to an embodiment of the present invention, Figure 2 is a bottom direction perspective view of an aircraft according to an embodiment of the present invention, Figure 3 is a partial excerpt sectional view of an aircraft according to an embodiment of the present invention, Figure 4 is this view It is a partial excerpt cross-sectional view of an aircraft according to an embodiment of the invention.

In the aircraft (F) of this embodiment, the main body portion 10 and the outer body portion 20 forming a ring shape surrounding the outer side are coupled through the connection frame portion 30 . Preferably, the body portion 10, the outer body portion 20 and the connecting frame portion 30 may be made of a lightweight elastic synthetic resin material, and in particular, the outer body portion 20 is close to the building during the flight of the aircraft (F). In consideration of the possibility of colliding with a building wall or the like when entering the space between buildings or building interior space, it is recommended to be made of a synthetic resin material with good impact resistance and elasticity.

For example, the body portion 10 may be formed in a cylindrical shape or a disk shape, but is not limited thereto.

The outer body portion 20 forms a ring shape surrounding the outer side 10a of the main body portion 10 and is disposed to have a gap with the outer side 10a of the main body portion 10 .

The connection frame part 30 connects the main body part 10 and the outer body part 20 to be integrally coupled, and is configured to allow air flow in the vertical direction (U-D).

The plurality of air flow means 40 is centered on the main body 10 in the ring-shaped space S formed between the outer 10a of the main body 10 and the inner 20a of the outer body 20 . is symmetrically placed. 1 and 2, a case in which a total of six air flow means 40 are installed is illustrated. In the case of the embodiment of Fig. 9, a case in which a total of eight air flow means 40 are installed as a modification is illustrated.

The plurality of air flow means 40 are installed based on the connection frame part 30, and are configured so that the air introduced from the upper part is pressurized and discharged to the lower part using the propeller 46 driven by the motor 44. .

For example, the connection frame part 30 includes a plurality of first connection frames 31 arranged to connect the outer side 10a of the main body 10 and the inner side 20a of the outer body unit 20 and , is configured to include a plurality of second connection frames 32 connecting the adjacent first connection frames 31 .

In more detail, the connection frame unit 30 includes a plurality of upper first connection frames 31 arranged to connect the outer side 10a of the main body 10 and the inner side 20a of the outer body unit 20 . -1), a plurality of second connection frames 32 connecting the adjacent upper first connection frames 31-1, and the outer portion 10a of the main body 10 and the outer body portion 20 It is arranged to connect the inner side 20a and is configured to include a plurality of lower first connecting frames 31 - 2 arranged to have a gap under the upper first connecting frame 31-1.

For example, the air flow means 40 is installed based on the lower first connection frame 31 - 2 .

Through this configuration, in the aircraft (F) of this embodiment, since the air flow means 40 is not directly exposed to the side through the outer body part 20, it is close to the building during the flight of the aircraft (F) or the space between buildings or When entering the building interior space, the propeller 46 of the air flow means 40 collides with the wall of the building and prevents the risk of damage.

In addition, in the aircraft (F) of this embodiment, since the air flow means 40 is not directly exposed to the upper or lower side through the connection frame part 30, when approaching or entering the building during the flight of the aircraft (F) The propeller 46 of the air flow means 40 prevents the risk of being damaged by colliding with various structures protruding from the ceiling or wall of the building. Reference numeral 11 denotes a landing leg of the aircraft (F).

The vehicle (F) of this embodiment is configured to include a launch device (300).

The launch device 300 is capable of firing a projectile 320 for destroying a building window loaded in a launch tube 310 installed on one side of the main body 10 in the lateral direction.

The launch device 300 includes a launch tube 310 , a projectile 320 , and a launch manipulation mechanism 330 .

One or two or more of the launch tubes 310 are installed on one side of the main body 10 , and are installed toward the front side of the aircraft F so as to be able to fire toward the glass window of a building where a fire has occurred. In addition, it is preferable that the installation direction of the firing tube 310 and the installation direction on the discharge side of the above-described injection tube 106 and the second discharge tube 204 coincide with each other. Through this configuration, the projectile 320 fired from the firing tube 310 before discharging the extinguishing agent through the injection pipe 106 or the second discharge pipe 204 destroys the building glass window, so that the extinguishing agent can be injected into the building. have.

The projectile 320 has an arrow shape with a collision body 322 on the front side and a gas container 324 on the rear side, and the gas container 324 in a state loaded inside the launch tube 310 When the through-hole 324a is formed in the rear end 324-1 of the through-hole 324a by an external force, it is fired toward the front side of the canister 310 by the gas pressure ejected through the through-hole 324a.

In the projectile 320 , at least the colliding body 322 is made of a metal material or a synthetic resin material having hardness and weight so as to give a sufficient impact force to the building glass window.

The firing operation mechanism 330 is installed on the rear side of the projectile 320 and forms a through hole 324a by applying an external force to the rear end 324-1 of the gas container 324 when a control signal is input.

In more detail, the firing operation mechanism 330 includes an electromagnet 332 installed at the rearmost side of the firing tube 310, and is located in front of the electromagnet 332 and receives a repulsive force from the electromagnet 332. and a permanent magnet 334 capable of moving forward in the canister 310 .

In addition, the firing operation mechanism 330 is provided on the front side of the permanent magnet 334 and applies an external force to the rear end 324-1 of the gas container 324 when the permanent magnet 334 moves forward. and an aperture needle 336 configured to apply the aperture 324a.

Referring to FIG. 4 , a through-hole 310a is formed in the internal partition of the firing tube 310 so that a through-hole needle 336 passes to apply an external force to the rear end 324-1 of the gas container 324. has been

In the state of Figure 4 (a), the permanent magnet 334 maintains a state adjacent to the electromagnet 332 by the initial setting. When the power of the battery 350 is applied to the electromagnet 332 by the operation of the switch means 360, a magnetic force is generated in the electromagnet 332, and a permanent magnet 334 installed to receive a repulsive force by the magnetic force of the electromagnet 332. moves in the direction (forward) of the inner bulkhead of the launch tube 310 . The operation of the switch means 360 may be performed by a control signal of the control unit 2 to be described later.

As in the state of FIG. 4 (b), the through-hole needle 336 installed on the front side of the permanent magnet 334 passes through the through-hole 310a to apply an external force to the rear end 324-1 of the gas container 324. When the through hole 324a is formed by applying , the projectile 320 is fired toward the front side of the canister 310 by the gas pressure ejected through the through hole 324a.

The glass window of the building may be destroyed by the projectile 320 fired to the front side, and then the extinguishing agent may be injected into the building.

The projectile 320 may be launched for purposes other than injecting the extinguishing agent. For example, the projectile 320 may be launched to allow lifesaving equipment to enter a building for the purpose of saving lives, or to allow people in the building to access lifesaving equipment outside the building.

Preferably, the vehicle (F) of this embodiment is configured to include a camera (60).

The camera 60 is installed on the upper side of any one of the main body 10 or the connection frame 30 .

The camera 60 may be a well-known digital camera, preferably a PTZ (Pan Tilt Zoom) camera capable of controlling a shooting angle.

The camera 60 executes a photographing operation under the control of the control unit 2, and when the aircraft F of this embodiment approaches the building and executes a fire suppression function, it is photographed and transmitted to the remote control system 1000 can

Preferably, the aircraft (F) of this embodiment is installed on the upper side of any one of the main body part 10 or the connection frame part 30 and a distance measuring sensor 62 disposed toward a preset one direction. is comprised of As a modification, the distance measuring sensor 62 may be integrally installed with the camera 60 .

The distance measuring sensor 62 may be a variety of known sensors, for example, any one of an ultrasonic sensor, an infrared sensor, a LIDAR sensor, a radar (RADAR) sensor, or a camera sensor (Passive Sensor) can be used An appropriate sensor may be selected in consideration of a required measuring distance and a measuring environment.

The distance measurement sensor 62 performs distance measurement under the control of the controller 2, and measures the proximity distance to the building when the vehicle F of this embodiment approaches the building, and the vehicle F and the building The control unit 2 provides information for executing direction/speed control of the air flow means 40 to keep the proximity distance to the required distance. As a modification, the control unit 2 by transmitting information about the measured distance to the remote control system 1000 and receiving control information for controlling the direction/speed of the air flow means 40 from the remote control system 1000 It is also possible to perform direction/speed control of the false air flow means 40 .

Preferably, the vehicle (F) of this embodiment is configured to include a warning light (90). The warning light 90 provides a function of notifying the surroundings of this state when the aircraft F of this embodiment operates in a fire suppression operation.

5 is a partial cross-sectional view of an aircraft according to an embodiment of the present invention, FIG. 6 is a partially extracted perspective view of an aircraft according to an embodiment of the present invention, FIG. 7A is a partial cross-sectional view of the aircraft according to an embodiment of the present invention, FIG. Another partial cross-sectional view of the vehicle according to the embodiment of the present invention, Figure 8 is a partial cross-sectional view of the vehicle according to the embodiment of the present invention, Figure 9 is a bottom direction perspective view of the vehicle according to another embodiment of the present invention.

The aircraft F of this embodiment is provided with devices 100 and 200 for discharging the extinguishing agent in one direction of the main body 10, and in particular, a device for discharging the extinguishing agent in the firing direction of the projectile 320 ( 100,200) are provided.

For example, the device for discharging the fire extinguishing agent pressurizes the liquid fire extinguishing agent (LE) inside the storage container 102 installed in the main body 10 with a pump 104 to one side of the main body 10 . It may be a spray-type fire extinguishing device 100 that can be sprayed and discharged in the lateral direction through the injection pipe 106 extended to the . The length of the injection pipe 106 may be appropriately set in consideration of the accessible distance to the building where the fire has occurred, the firing distance of the extinguishing agent, and the like. For example, the storage container 102 may be manufactured in the form of a tank capable of refilling the liquid extinguishing agent (LE), but is not limited thereto. Reference numeral 101 of FIG. 5 denotes a suction pipe of the liquid extinguishing agent (LE).

For example, water may be used as the liquid extinguishing agent (LE). Water has a high cooling effect, and when sprayed in the form of a spray, it has a fire extinguishing effect that blocks air. When water is used as the liquid extinguishing agent (LE), the water introduced into the storage container 102 is pressurized with the pump 104 and sprayed in the lateral direction through the injection pipe 106 extended on one side of the main body 10. .

As another example, an aqueous solution of an extinguishing agent component may be used as the liquid extinguishing agent (LE). For example, if an aqueous solution of aluminum sulfate and an aqueous solution of sodium bicarbonate are mixed just before use, carbon dioxide, sodium sulfate, and aluminum hydroxide are produced by reaction, and they are released as foam together with water, so there is a fire extinguishing effect. To this end, in the configuration of the storage container 102, a storage space for storing an aqueous aluminum sulfate solution and a storage space for storing an aqueous sodium hydrogen carbonate solution are separately configured, and an aqueous solution mixing section is configured in the middle of the injection pipe or the suction pipe to form sulfuric acid The aqueous aluminum solution and the aqueous sodium bicarbonate solution may be mixed during the spraying process.

On the other hand, the device for discharging the fire extinguishing agent discharges the ball type fire extinguishing agent (BE) accommodated in the discharge pipe 204 installed to have a side discharge direction of the main body 10 as a discharge control mechanism. It may be a ball-type fire extinguishing agent discharging device 200 that can be discharged through the control of 210 .

The aircraft (F) of this embodiment effectively suppresses the building fire by using the discharge pipe 204 installed to have a side discharge direction together with the launch device 300 capable of firing the building window destruction projectile 320 in the side direction. can do.

The ball type fire extinguishing agent discharging device 200 illustrated in this embodiment has a first discharge pipe 202 discharging the ball type fire extinguishing agent (BE) in the lower direction and a second discharge pipe discharging the ball type fire extinguishing agent (BE) in the lateral direction ( 204), in particular, the second discharge pipe 204 throws a ball-type fire extinguishing agent (BE) into the building through the building window in which the glass window is destroyed by the launch device 300 of the discharge pipe 204 of have a function In consideration of this, hereinafter, the discharge pipe 204 of the present embodiment will be described with a focus on the second discharge pipe 204 .

A ball-type fire extinguisher (BE) is a type of fire extinguisher for throwing, and may be understood as an extinguishing agent manufactured in the form of a ball. Throwing fire extinguishers are also called fire extinguishers.

Throwing fire extinguishers are of a type using a liquid extinguishing agent and a type using a powder extinguishing agent. Throwing fire extinguishers that use liquid extinguishers extinguish the fire while removing oxygen as the case (eg, glass or synthetic resin such as vinyl chloride) is broken and the extinguishing agent vaporizes when it is thrown into a fire. In this process, the cooling action by the extinguishing agent and the oxygen blocking action by the aqueous film foaming agent are performed simultaneously. Throwing fire extinguishers that use powder extinguishers extinguish the fire in such a way that, when thrown into a fire, the case is broken by the action of the ignition wire at the time of impact or flame contact, and the powder type extinguishing agent scatters. The ball type fire extinguishing agent (BE) of this embodiment is a ball-shaped case of a throwing fire extinguisher, and various commercial products are known.

The aircraft F of this embodiment can control the discharge of the ball-type extinguishing agent BE by using the ball-type extinguishing agent discharging device 200 .

Preferably, the ball-type extinguishing agent discharging device 200 is installed inside the main body 10 and accommodates one or more ball-type extinguishing agents (BE) therein, and the ball-type extinguishing agent (BE) is at least by its own weight. It includes one or more discharge pipes 202 and 204 installed so as to be discharged in a lower direction or a side direction of the main body 10 .

In addition, the ball-type fire extinguishing agent discharging device 200 is installed on the discharge side of the discharge pipes 202 and 204 and is blocked or discharged to control the discharge of the ball type fire extinguishing agent (BE) accommodated in the discharge pipes 202 and 204. It includes an emission control mechanism 210 that operates.

Preferably, the discharge control mechanism 210 includes a first locking piece 211 , a second locking piece 212 and a driving mechanism 220 .

The first locking piece 211 is a first protruding into the interior of the discharge pipes 202 and 204 to perform a discharge locking operation to prevent movement of the ball-type fire extinguishing agent BE by its own weight at one point of the discharge pipes 202 and 204. It is possible to convert to the second state retracted from the inside of the discharge pipes 202 and 204 to perform a discharge release operation capable of movement by the state and the weight of the ball-type fire extinguishing agent (BE).

The second locking piece 212 is, at another point in the longitudinal direction of the discharge pipes 202 and 204, the inside of the discharge pipes 202 and 204 to perform a discharge locking operation to prevent the movement of the ball-type fire extinguishing agent BE by its own weight. It is possible to convert the first state protruding to the furnace and the second state retracted from the inside of the discharge pipes 202 and 204 to perform a discharge release operation capable of movement by the weight of the ball-type fire extinguishing agent BE. The length direction may be any one of a straight length or a curved length.

The driving mechanism 220 alternately changes the first locking piece 211 and the second locking piece 212 into a first state or a second state, respectively.

In the case of FIG. 7A , the first locking piece 211 is in a first state and the second locking piece 212 is in a second state. In the case of FIG. 7B , the first locking piece 211 is in a second state, and the second locking piece 212 is in a first state.

In more detail, the driving mechanism 220 includes a movable rod 222 and a driving means 224 .

The movable rod 222 may be formed, for example, in a substantially “T” shape, and one end 222a is coupled through the hole H formed in the first locking piece 211 to allow relative movement. and the other end 222b is coupled through the hole H formed in the second locking piece 212 in a relatively movable form, and rotates in one direction RR1 around the rotation shaft 222c located in the center. At the time of making the first locking piece 211 into a first state and also making the second locking piece 212 into a second state, when rotating in the other direction RR2 about the rotation shaft 222c It is configured to make the first locking piece 211 into a second state and also to make the second locking piece 212 into a first state. The first locking piece 211 and the second locking piece 212 are installed to be slidably movable inside the guide hole SH formed to extend to the outside on one side of the discharge pipes 202 and 204, and protrude or retreat into the discharge pipes 202 and 204. can do. Reference numerals 227a and 227b in FIG. 6 denote casing parts for constituting the guide hole SH, and reference numeral 229 denotes a support part for supporting the rotation shaft 222c.

The driving means 224 rotates the movable rod 222 in the one direction RR1 or the other direction RR2.

Preferably, the driving means 224 is connected to the movable piece 224a through a movable piece 224a extending from the center of the movable rod 222 and one or more link members 224c and 228 to the movable piece 224a. It is configured to include a motor 224b configured to be able to rotate the movable piece 224a in one direction RR1 or the other direction RR2.

6 to 7b, when the motor shaft 224d of the motor 224b rotates in the RR3 direction, the link member 224c integrally connected to the motor shaft 224d rotates counterclockwise, and one end 228a of the link member 224c rotates in a rotatable state. Another linked link member 228 moves. When the other link member 228 moves, the other end 228b rotates the movable piece 224a counterclockwise around the rotation shaft 222c. Accordingly, while the movable rod 222 rotates in the RR2 direction about the rotation shaft 222c, the first locking piece 211 is placed in the second state and the second locking piece 212 is placed in the first state.

On the contrary, when the motor shaft 224d of the motor 224b rotates in the RR4 direction, the link member 224c integrally connected to the motor shaft 224d rotates clockwise, and as the operation in the opposite direction to the operation proceeds, the first locking piece 211 is moved to the first and make the second locking piece 212 into the second state. The operation of the motor 224b is controlled by a control unit 2, which will be described later.

Through this operation, the driving mechanism 220 alternately converts the first locking piece 211 and the second locking piece 212 into a first state or a second state, respectively.

According to this alternating state change, the discharge of the ball type extinguishing agent (BE) can be effectively controlled.

Referring to FIG. 7A , a plurality of ball-type fire extinguishing agents BE are charged inside the discharge pipe 204, and the ball-type fire extinguishing agent BE1 located at the most front part is discharged by the first stopping piece 211 in the first state. has been manipulated. When the driving mechanism 220 is operated in this state, the first locking piece 211 is in the second state and the second locking piece 212 is converted to the first state, and is initially discharged by the first locking piece 211 . The ball-type fire extinguishing agent BE1 in the jammed state moves toward the outlet side of the discharge pipe 204 . The ball-type extinguishing agent BE1' of FIG. 5A illustrates a state in which the ball-type extinguishing agent BE1 has moved toward the outlet side of the discharge pipe 204 .

In this process, another ball-type extinguishing agent BE2 is moved and located in the space where the ball-type extinguishing agent BE1 is discharged, and the discharge is caught by the second locking piece 212 converted to the first state as shown in FIG. 5B. become in a state of being

After that, when the first and second locking pieces 211 and 212 are alternately converted to the first or second states, respectively, another ball-type fire extinguishing agent BE2 at the position of FIG. 5B is moved to the position of the ball-type fire extinguishing agent BE1 of FIG. 5A and is located in a dischargeable state.

By this mutually alternating conversion structure of the first locking piece 211 and the second locking piece 212, the ball-type fire extinguishing agent discharging device 200 of this embodiment releases a plurality of ball-type fire extinguishing agents BE. It can be effectively separated and discharged one by one.

Meanwhile, from another point of view, the ball-type extinguishing agent discharging device 200 includes a first discharge pipe 202 , a second discharge pipe 204 , and an accelerated discharge means 230 .

The first discharge pipe 202 is installed so that the ball-type fire extinguishing agent (BE) is put in through the upper opening 202a, stored therein, and can be discharged through the lower opening 202b, and the discharge control mechanism ( 210) is provided. The first discharge pipe 202 is suitable for dropping and throwing a ball-type extinguishing agent (BE) from the top of a building where a fire has occurred or at a forest fire site.

The second discharge pipe 204 is installed so that the ball-type fire extinguishing agent (BE) is put in through the upper opening 204a, stored therein, and discharged through the side opening 204b, and the discharge control mechanism 210 ) is provided. The second discharge pipe 204 is suitable for throwing the ball type fire extinguishing agent (BE) into the building through an open or destroyed window at the side of the building where the fire occurs.

The second discharge pipe 204 further accelerates the ball-type fire extinguishing agent (BE) discharged by the discharge release operation of the discharge control mechanism 210 so that it is discharged through the side opening 204b. ) is provided.

For example, the accelerated discharge means 230 is capable of transmitting rotational force while in press contact with the surface of the ball-type fire extinguishing agent (BE) passing through the inside of the second discharge pipe 204, and the second discharge pipe 204 ) with respect to the central axis 204x of at least two acceleration wheels 232 symmetrically arranged, and a motor driving means 234 for providing a rotational force to each of the acceleration wheels 232. . For example, the acceleration wheel 232 may be manufactured by covering the outer circumferential surface of the metal or synthetic resin wheel with a material having elasticity and frictional force (eg, rubber), and in a state of pressurized contact with the surface of the ball type fire extinguishing agent (BE). It accelerates the rotation by transmitting frictional force.

The motor driving means 234 may be installed on the outer surface of the second discharge pipe 204 or the lower surface of the main body 10 , and the accelerator wheel 232 is connected to the driving shaft of the motor driving means 234 and installed in the first 2 Through the through hole 204h formed through the side of the discharge pipe 204, the second discharge pipe 204 may come into contact with the ball-type fire extinguishing agent (BE) moving in the inside to impart a rotational force.

10 is a control configuration diagram of an aircraft according to an embodiment of the present invention.

The vehicle F of this embodiment includes a control unit 2 and a communication unit 4, and although not shown, a charging/discharging battery for power supply, a GPS module for obtaining flight location information, and an altitude sensor for obtaining flight altitude information , and a gyro sensor for obtaining flight attitude information may be provided. The control unit 2 and the communication unit 4 may be installed in the body unit 10 .

The control unit 2 includes a CPU and a memory and may be understood as a computing means in which computer software for vehicle control is driven. The control unit 2 may wirelessly communicate with the remote control system 1000 through the communication unit 4 , and receives control information including flight control information and fire suppression control information from the remote control system 1000 . Alternatively, image information captured by a camera, distance measurement information, flight location information, and flight posture information may be transmitted to the remote control system 1000 .

In addition, the control unit 2 controls the direction/speed of the air flow means 40 installed in the aircraft F based on the control logic preset in the memory or the control command received from the remote control system 1000, and the injection type fire extinguishing device Operation control of 100 , operation control of the ball-type fire extinguishing agent discharging device 200 , and operation control of the launch device 300 may be executed.

In addition, the control unit 2 executes generation of image information using the camera 60 and generation of distance measurement information using the distance measurement sensor 62, and uses each information to control flight or fire suppression operation, etc. can run

For example, the remote control system 1000 may be a computing means in which computer software for vehicle control/monitoring is driven and wireless information transmission and reception is possible.

Although the present invention has been mainly described with reference to the accompanying drawings, it will be apparent to those skilled in the art that many various and obvious modifications can be made therefrom without departing from the scope of the present invention. Accordingly, the scope of the present invention should be construed by the appended claims to cover many such modifications.

10: body part
20: outer body part
30: connection frame part
31: first connection frame
32: second connection frame
40: air flow means
44: motor
46: propeller
60: camera
62: distance measuring sensor
100: injection type fire extinguishing system
102: storage container
104: pump
106: injection pipe
200: ball type extinguishing agent discharge device
202: first discharge pipe
204: second discharge pipe
210: emission control mechanism
211: first jamming piece
212: second hook piece
220: drive mechanism
222: movable bar
224: driving means
224a: movable piece
224b: motor
224c: link missing
230: accelerated discharge means
232: accelerator wheel
234: motor driving means
300: launcher
310: launch tube
320: projectile
322: Collider
324: gas container
324a: through hole
330: fire control mechanism
332: electromagnet
334: permanent magnet
336: hollow needle
BE: Ball type extinguishing agent
F: aircraft
LE: liquid extinguishing agent
S: Ring-shaped interspace

Claims (10)

body part;
an outer body portion forming a ring shape surrounding the outer side of the main body portion and disposed in a state having a gap with the outer side of the main body portion;
a connecting frame unit configured to connect and integrally combine the main body and the outer body and allow air to flow in an up-down direction;
It is symmetrically disposed in the ring-shaped space between the outer side of the main body and the inner side of the outer body part, is installed based on the connection frame part, and uses a propeller driven by a motor to move air introduced from the upper part to the lower part. a plurality of air flow means configured to be pressurized; and
It includes; a launch device capable of firing a projectile for destroying a building window loaded in a launch tube installed on one side of the main body in the lateral direction;
The launch device is
a launch tube installed on one side of the main body;
It has an arrow shape with a collision body provided on the front side and a gas container on the rear side, and the gas pressure ejected through the through hole when the through hole is formed by an external force in the rear end of the gas container in a state loaded in the canister A projectile fired toward the front side of the launch tube by
Aircraft equipped with a launch device, characterized in that it is installed on the rear side of the launch vehicle and comprises a launch operation mechanism for forming a through hole by applying an external force to the rear end of the gas container when a control signal is input.
delete According to claim 1,
The firing operation mechanism is
an electromagnet installed on the rearmost side of the launch tube;
a permanent magnet positioned in front of the electromagnet and capable of moving forward in the canister when receiving a repulsive force from the electromagnet;
Aircraft having a launch device, characterized in that it is provided on the front side of the permanent magnet and is configured to include a needle for a hole configured to form a hole by applying an external force to the rear end of the gas container when the permanent magnet moves forward .
According to claim 1,
An aircraft having a launch device, characterized in that it is provided with a device for discharging a fire extinguishing agent in the firing direction of the projectile.
5. The method of claim 4,
The device for discharging the fire extinguishing agent,
Aircraft having a launch device, characterized in that it is an injection-type fire extinguishing device that can be sprayed and discharged in the lateral direction through an injection pipe extending on one side of the body by pressing the liquid extinguishing agent inside the storage container installed in the main body with a pump.
5. The method of claim 4,
The device for discharging the fire extinguishing agent,
Aircraft having a launch device, characterized in that it is a ball-type fire extinguishing agent discharge device capable of discharging the ball type fire extinguishing agent stored in the discharge pipe installed to have a side discharge direction of the main body through the control of the discharge control mechanism.
7. The method of claim 6,
The ball type fire extinguishing agent discharging device,
a discharge pipe installed inside the main body and accommodating one or more ball-type fire extinguishing agents therein, and installed so that the ball-type fire extinguishing agent can be discharged in a lateral direction of the main body by at least its own weight;
Aircraft equipped with a launch device, characterized in that it is installed on the discharge side of the discharge pipe and comprises a discharge control mechanism for controlling the discharge of the ball-type fire extinguishing agent accommodated in the discharge pipe, or for releasing the discharge operation.
body part;
an outer body portion forming a ring shape surrounding the outer side of the main body portion and disposed in a state having a gap with the outer side of the main body portion;
a connecting frame unit configured to connect and integrally combine the main body and the outer body and allow air to flow in an up-down direction;
It is symmetrically disposed in the ring-shaped space between the outer side of the main body and the inner side of the outer body part, is installed based on the connection frame part, and uses a propeller driven by a motor to move air introduced from the upper part to the lower part. a plurality of air flow means configured to be pressurized; and
A launch device capable of firing a projectile for destroying a building window loaded in a launch tube installed on one side of the main body in the lateral direction;
A device for discharging a fire extinguishing agent in the firing direction of the projectile is provided;
The device for discharging the fire extinguishing agent,
It is a ball-type fire extinguishing agent discharging device capable of discharging the ball-type fire extinguishing agent stored in the discharge pipe installed to have a lateral discharge direction of the main body through the control of the discharge control mechanism,
The ball type fire extinguishing agent discharging device,
A discharge pipe installed inside the main body and accommodating one or more ball-type fire extinguishing agents therein, and installed so that the ball-type fire extinguishing agent can be discharged in the lateral direction of the main body by at least its own weight, and installed on the discharge side of the discharge pipe, inside the discharge pipe and a discharge control mechanism that performs a discharge locking or discharge release operation to control discharge of the ball-type fire extinguishing agent stored in the
The emission control mechanism,
At one point of the discharge pipe, the first state protruding into the interior of the discharge pipe so as to be a discharge jamming operation that blocks movement by its own weight of the ball-type fire extinguishing agent, and a discharge release operation that allows movement by its own weight of the ball-type fire extinguishing agent A first engaging piece that can be converted to a second state retracted from the inside of the discharge pipe, and
At another point in the longitudinal direction of the discharge pipe, the first state protruding into the interior of the discharge pipe so as to be a discharge jamming operation that prevents movement by its own weight of the ball type fire extinguishing agent, and the ball type fire extinguishing agent can be moved by its own weight A second locking piece that can be converted to a second state retracted from the inside of the discharge pipe so as to be a discharge release operation;
Aircraft with a launch device, characterized in that it comprises a drive mechanism for converting the first and second locking pieces to the first state or the second state alternately, respectively.
body part;
an outer body portion forming a ring shape surrounding the outer side of the main body portion and disposed in a state having a gap with the outer side of the main body portion;
a connecting frame unit configured to connect and integrally combine the main body and the outer body and allow air to flow in an up-down direction;
It is symmetrically disposed in the ring-shaped space between the outer side of the main body and the inner side of the outer body part, is installed based on the connection frame part, and uses a propeller driven by a motor to move air introduced from the upper part to the lower part. a plurality of air flow means configured to be pressurized; and
A launch device capable of firing a projectile for destroying a building window loaded in a launch tube installed on one side of the main body in the lateral direction;
A device for discharging a fire extinguishing agent in the firing direction of the projectile is provided;
The device for discharging the fire extinguishing agent,
It is a ball-type fire extinguishing agent discharging device capable of discharging the ball-type fire extinguishing agent stored in the discharge pipe installed to have a lateral discharge direction of the main body through the control of the discharge control mechanism,
The ball type fire extinguishing agent discharging device,
A discharge pipe installed inside the main body and accommodating one or more ball-type fire extinguishing agents therein, and installed so that the ball-type fire extinguishing agent can be discharged in the lateral direction of the main body by at least its own weight, and installed on the discharge side of the discharge pipe, inside the discharge pipe and a discharge control mechanism that performs a discharge locking or discharge release operation to control discharge of the ball-type fire extinguishing agent stored in the
The exhaust pipe is
The ball-type extinguishing agent is put in through the upper opening, stored inside, and installed to be discharged through the side opening, and the ball-type extinguishing agent discharged by the discharge release operation of the emission control mechanism is further accelerated to further accelerate the side opening Aircraft equipped with a launch device, characterized in that provided with an acceleration discharge means to be discharged through the.
10. The method of claim 9,
The accelerated discharge means,
An acceleration wheel capable of transmitting rotational force in a pressurized contact with the surface of the ball-type fire extinguishing agent passing through the interior of the discharge pipe and symmetrically disposed with respect to the central axis of the discharge pipe,
An aircraft having a launch device, characterized in that it comprises a motor driving means for providing a rotational force to each of the acceleration wheels.

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