KR20230153873A - Propellant for fluid injection - Google Patents

Abstract

The present invention relates to a propellant for fluid injection. A fluid pressurizing part is installed in a pipe connected to a nozzle, and a steel wire for fluid rotation is provided on the inner circumferential surface of the nozzle's injection hole to pressurize the fluid supplied through a hose from a fluid supply source on the ground or water. and for spraying by rotating.
To this end, the present invention is a propellant that generates propulsion by high-pressure injection of fluid supplied through a fluid transfer unit from a fluid source on land or water, in which fluid flows in from the lower part of the main pipe and branches out radially through each branch pipe. It is detachably coupled to the sending propellant body and the end of each branch pipe, and forms an orifice part whose pipe diameter is reduced and expanded in the middle of the pipe. An orifice nozzle unit for spraying, a fluid pressurizing unit that is installed at the front end of the orifice nozzle unit on each branch pipe and whose operation is controlled by a motor control signal transmitted from the control unit to pressurize and deliver or block the fluid in the pipe, and the main pipe of the propellant body. It is provided at the top and includes a control unit that controls the propellant body to move according to the pilot's will by adjusting the motor control signal to control the fluid pressurization delivery or blocking operation of the fluid pressurization unit, so that it can be used as a thrust reinforcement or a stand-alone propellant for the drone. let it be

Description

Propellant for fluid injection}

The present invention relates to a propellant for fluid injection. More specifically, a fluid pressurizing part is installed in a pipe connected to a nozzle, and a rifling for rotating and pressurizing the fluid is formed on the inner circumferential surface of the nozzle to spray fluid on land or water. By pressurizing and rotating the fluid supplied through the hose from the fluid source to spray it, it can be used as a thrust reinforcement when attached to a drone or as a propellant for independent flight, and has elastic support, buffering, and flotation. By providing a part, it is possible to prevent damage or loss due to collision or impact with an external object when landing on the ground or water, and to allow chemical liquids such as chemicals or soap solution to be automatically mixed into the nozzle and sprayed mixed with the fluid. This relates to a fluid injection propellant that can be used in disaster prevention drones or performance drones.

In general, an unmanned vehicle or drone (hereinafter collectively referred to as 'unmanned vehicle') has an even number (2, 4, 6, By rotating the wings (8, etc.) clockwise or counterclockwise, the lift and propulsion force necessary for flight are generated, and the rotation speed of these wings is adjusted to achieve hovering, yawing, and rising/falling. ), pitching, and rolling (rolling left/right) can be controlled.

As the spread of these unmanned vehicles has recently expanded, control technology using mobile communication terminals such as smartphones is gradually being developed, including high-altitude video and photo shooting and delivery, weather information collection, fire suppression, pesticide spraying for pest control, and decontamination. , It is used in various fields such as quarantine work to prevent the spread of infectious diseases.

In particular, in fire suppression, quarantine, and pest control work, when a large fire or forest fire breaks out, or when pesticides or disinfectants are sprayed on large areas of farmland or infected areas, quick and accurate work is possible only when the fluid can be sprayed continuously. The unmanned navigation vehicle used at this time must be able to continuously inject a large amount of fluid.

However, conventional conventional unmanned vehicles obtain flight power by rotating rotor blades to generate lift and propulsion, and transporting heavy fluids consumes a lot of fuel, making it difficult to continuously spray fluids.

In order to solve this problem, Republic of Korea Patent No. 10-1694132 (registered on January 3, 2017; hereinafter abbreviated as 'Patent Document 1') proposes a device that can be moved by using the force generated when high-pressure fluid is discharged as thrust. Technology related to navigation vehicles is known.

According to Patent Document 1, since high-pressure fluid is used as a propellant, a separate power source is not required, thereby reducing fuel consumption and enabling continuous spraying of a large amount of fluid.

However, since multiple drivers and power transmission members for fluid injection are additionally attached to each nozzle, the configuration is not only complicated, but also fuel consumption increases, which has the disadvantage of shortening flight time. There is a need for an unmanned aerial vehicle flight system for fire suppression, quarantine, or disaster prevention that can work efficiently for long periods of time.

KR 10-1694132 B1 2017.01.03. registration

Therefore, the present invention was devised to solve the above problems, and the technical problem to be solved by the present invention is to install a fluid pressurization part in the pipe connected to the nozzle and provide a steel wire for fluid rotation on the inner circumferential surface of the nozzle to The object is to provide a propellant for fluid injection that can generate propulsion by pressurizing and rotating fluid supplied through a hose from an aqueous fluid source and spraying it.

Another technical problem of the present invention is to provide a drone detachable part so that it can be attached and detached to the drone body, so that when attached to the drone body, it can be used as a thrust reinforcement for the drone, contributing to stabilizing the flight attitude of the drone, or used as a propellant for independent flight. The goal is to provide a propellant for fluid injection that allows.

Another technical problem of the present invention is to provide a buffer with elastic support, buffering power, and flotation to surround and protect the propellant body and nozzle, so that when the thrust reinforcement or propellant lands on the ground, the elastic support of the buffer and The shock is alleviated by the buffering force to protect the propellant body and nozzle from collision or impact with external objects, and when landing on the water, the nozzle buffer's elastic support, buffering force, and buoyancy force prevent collisions or shocks with external objects. The aim is to provide a propellant for fluid injection that can protect the propellant body and nozzle from impacts, etc., while allowing it to float on water to prevent damage or loss.

Another technical problem of the present invention is to install auxiliary pipes in parallel on one side of the pipe connected to the nozzle, and install a chemical liquid container and an opening/closing valve in which chemical liquid such as medicine or soap solution is stored on the auxiliary pipe to operate the fluid pressurization unit. The purpose is to provide a propellant for fluid injection that can be used in disaster prevention drones or performance drones by allowing chemical liquids such as medicine or soap solution to be automatically mixed into the nozzle and sprayed together with the fluid due to the pressure difference within the city pipe. .

An embodiment of the present invention for achieving the above object is a propellant that generates propulsion by spraying high pressure fluid supplied through a fluid transfer unit from a fluid source on the ground or on the water, and the upper end is closed and the side of the main pipe is vertically arranged. It is a piping body in which a plurality of branch pipes are radially branched, and the fluid flows in from the lower part of the main pipe. The propellant body part branches and discharges the fluid radially through each branch pipe, and is detachably attached to the end of each branch pipe, respectively. An orifice nozzle part that sprays fluid by controlling the flow rate and flow rate inside the pipe by the pressure difference before and after the orifice part by forming an orifice part whose pipe diameter is reduced and expanded in the middle of the pipe is installed at the front end of the orifice nozzle part on each branch pipe. A fluid pressurization unit, the operation of which is controlled by a motor control signal transmitted from the control unit, to pressurize and deliver or block the fluid in the pipe, and a motor control provided at the upper part of the main pipe of the propellant body to control the fluid pressurization delivery or blocking operation of the fluid pressurization unit. It is a propellant for fluid injection, including a control unit that adjusts signals to control the propellant body to move according to the pilot's will.

According to the present invention, a fluid pressurizing part is installed in the pipe connected to the nozzle, and a steel wire for fluid rotation is provided on the inner circumferential surface of the nozzle to pressurize and rotate the fluid supplied through the hose from a fluid source on the ground or water to spray it. Therefore, it is possible to reinforce the propulsion force by fluid injection, providing an advantage that can contribute to stabilizing the flight attitude of the propellant.

In addition, according to the present invention, the drone is provided with a detachable part so that it can be attached to the drone and used as a thrust reinforcement, or separated and used as an independent propellant. Therefore, when attached to the drone, it can be used as a thrust reinforcement of the drone, contributing to stabilizing the flight attitude of the drone. It provides the advantage of being able to be freely used as a propellant or independently flying propellant.

In addition, according to the present invention, by using a buffer having elastic support, buffering force, and flotation, it is possible to elastically land on the ground or water or float on the water, thereby preventing damage or damage due to collision or impact with an external object. This provides the advantage of preventing loss, etc.

In addition, according to the present invention, the chemical liquid such as medicine or soap solution is automatically mixed with the nozzle and can be mixed and sprayed with the fluid, thereby providing the advantage of being able to be used in a drone for disaster prevention or a drone for performance.

Figure 1 is a perspective view illustrating the simplest implementation of the fluid injection propellant according to the present invention.
Figures 2 (a) and (b) are reference diagrams comparing an impeller with water turbine blades in a first direction and an impeller with water turbine blades in a second direction.
Figure 3 is an enlarged cross-sectional view of the impeller and orifice nozzle portion of Figure 1.
Figure 4 is a perspective view illustrating a state in which the fluid pressurizing part is implemented as a pressurizing pump in the fluid injection propellant according to the present invention.
Figure 5 is a perspective view illustrating a form in which a chemical liquid mixing part is added to the fluid injection propellant of Figure 1.
Figure 6 is a detailed cross-sectional view illustrating the impeller, orifice nozzle part, and chemical liquid mixing part of Figure 5 on an enlarged scale.
Figure 7 is a bottom view illustrating an excerpt of a buffer part that can be fastened to a propellant for fluid injection according to each embodiment of the present invention.
Figure 8 is a perspective view illustrating a form in which the fluid pressurizing part is implemented with an impeller and a pressurizing pump and a chemical liquid mixing part is added in the fluid injection propellant according to the present invention.

Hereinafter, the configuration and operation of the propellant for fluid injection according to the present invention and its effects will be described in detail with reference to the accompanying drawings.

The terms or words used in this specification and claims are not to be construed limited to their ordinary or dictionary meanings, and the inventor can appropriately define the concept of terms in order to explain his or her invention in the best way. It must be interpreted based on the meaning and concept consistent with the technical idea of the present invention. Therefore, it is understood that the embodiments described in this specification and the configurations shown in the drawings are only one of the most preferred embodiments of the present invention, and that there may be various equivalents and modifications that can replace them at the time of filing the present application. shall.

Figure 1 is a perspective view illustrating the simplest implementation of the fluid injection propellant according to the present invention, and Figures 2 (a) and (b) show an impeller with water turbine blades in the first direction and a water turbine in the second direction. It is a reference diagram illustrating a comparison of impellers with wings, and Figure 3 is an enlarged cross-sectional view illustrating the impeller and orifice nozzle part of Figure 1, and Figure 4 is a fluid pressurizing part implemented as a pressurizing pump in the fluid injection propellant according to the present invention. As a perspective view illustrating the state, the propellant for fluid injection of the present invention may be composed in the simplest form including a propellant body portion 110, an orifice nozzle portion 120, a fluid pressurizing portion 130, and a control portion 140. You can. The fluid injection propellant of the present invention is provided with a drone attachment/detachment part 113 on the upper part of the propellant body 110 to be detachably coupled to the drone body, so that it can be used as a thrust reinforcement for a drone or as a propellant for independent flight. It may be implemented in an enabling embodiment.

Figure 5 is a perspective view illustrating a chemical liquid mixing part added to the fluid injection propellant of Figure 1, and Figure 6 is an enlarged cross-sectional view illustrating the impeller, orifice nozzle part, and chemical liquid mixing part of Figure 5, each embodiment of the present invention. The propellant for fluid injection according to can be implemented in another embodiment by providing a chemical liquid mixing part 150 on one side of the orifice nozzle part 120, and in this case, the chemical or soap solution of the chemical liquid mixing part 150 The chemical solution can be automatically mixed with the nozzle and mixed with the fluid to be sprayed, so that it can be used in a disaster prevention drone or performance drone.

Figure 7 is a bottom view illustrating an excerpt of a buffer part that can be fastened to a fluid injection propellant according to each embodiment of the present invention. The fluid injection propellant according to each embodiment of the present invention includes a fluid transfer portion 10 and a propellant body portion. It is further provided with a buffer part 160 that is assembled or separated from (110), so that it can elastically land when landing on the ground or water or float on the water due to the elastic support, buffering force, and flotation force of the buffer part 160. It can also be implemented in an embodiment that prevents damage or loss due to collision or impact with an external object.

Figure 8 is a perspective view illustrating a form in which the fluid pressurizing part is implemented with an impeller and a pressurizing pump and a chemical liquid mixing part is added in the fluid injection propellant according to the present invention. The fluid injection propellant according to each embodiment of the present invention has an impeller (131). ) and the pressurization pump 133, each fluid pressurization unit 130 is configured to include both, and when attached to the drone and used as a thrust reinforcement, the drone is doubly powerful by the impeller 131 and the pressurization pump 133. It can be implemented to reinforce the thrust or to generate a double strong thrust by the impeller 131 and the pressure pump 133 when used as a solo flying propellant.

Each embodiment of the present invention as described above can be implemented by applying to a propellant that generates propulsion by high-pressure injection of fluid supplied through the fluid transfer unit 10 from a fluid source on land or water.

In order to implement the propellant for fluid injection of the present invention, first, the fluid transfer unit 10 is a part whose one end is connected to a fluid supply source on the ground or water and serves to continuously supply fluid to the propellant of the present invention through a hose. As illustrated in FIG. 1, it consists of a hose 11 and a connecting member 12 for transferring fluid. The fluid is pressurized using a pump, etc. on the ground or on the water, and the hose 11 and the connecting member 12 are used. It is configured to supply fluid to the propellant body portion 110 through. This fluid transfer unit 10 may be connected to a fluid supply source such as a high-pressure water spray on the ground, a vehicle for quarantine or firefighting, or a vessel on the water.

As illustrated in FIG. 1, the propellant body portion 110 has a main pipe 111 that is closed at the upper end and open at the lower end and is arranged vertically up and down to form the center of gravity of the propellant body portion, and a plurality of radial pipes in the main pipe 111. The branch pipe 112 is made of an It is configured to allow fluid to flow from the fluid transport unit 10, and the end of each branch pipe 112 is bent downward for downward transport of the fluid, and the end part has a nozzle coupling portion 112a for coupling or separating the nozzle. is formed. In addition, this propellant body portion 110 may be further provided with a drone attachment/detachment portion 113 on the upper part of the body to be detachably coupled to or detachable from the drone body, whereby the propellant body portion 110 is attached to the drone attachment/detachment portion 113. ) can be used to attach to the lower part of the drone body so that it can be used as a thrust reinforcement for the drone, thereby contributing to stabilizing the drone's flight posture. Additionally, if this propellant body portion 110 is not attached to the drone body, it can be used as a propellant that flies independently.

Here, the main pipe 111 has a guide wall formed therein to guide the fluid flowing in from the fluid transfer unit 10 to each branch pipe 112 to easily guide the fluid to be branched and transferred to each branch pipe 112. It may be configured. Additionally, the branch pipe 112 may be formed by equally spaced branches, for example, into 4 branches (quadcopter type or X type), 6 branches (hexacopter type), or 8 branches (octacopter type).

The orifice nozzle part 120 is detachably coupled to the nozzle coupling part 112a at the end of each branch pipe 112, and forms an orifice part 121 whose pipe diameter (internal diameter) is reduced and expanded in the middle of the pipe. It is provided with a nozzle injection port 122 to control the flow rate and flow rate inside the pipe by the pressure difference before and after the orifice unit 121 to inject fluid through the nozzle injection port 122 at the end. A steel wire (Rifling) 122a is formed on the inner peripheral surface of the nozzle injection hole 122 of the orifice nozzle unit 120 to generate rotational force in the fluid injected from the injection hole, so that the fluid can be rotated and sprayed. Additionally, in this orifice nozzle part 120, an inlet hole 121a through which fluid can flow from the chemical liquid mixing part 150, which will be described later, may be formed on one side of the nozzle body forming the orifice part 121.

The fluid pressurizing unit 130 is installed at the front end of the orifice nozzle unit 120 on each branch pipe 112, and its operation is controlled by a motor control signal transmitted from the control unit 140 to pressurize or deliver the fluid in the pipe. Block it. This fluid pressurizing unit 130 may be implemented as either an impeller 131 and an impeller driving motor 132, or a pressurizing pump 133 and a pump driving motor 134.

An example in which the fluid pressurizing unit 130 is composed of an impeller 131 and an impeller driving motor 132 is illustrated in FIGS. 1 to 3. The impeller 131 is rotatably fixed and integrally attached to the power transmission shaft 132a connected to the impeller drive motor 132, is inserted and installed inside each branch pipe 112, and is installed on the pipe by rotating inside the pipe. The fluid is rotated and pressurized to supply or block the fluid to the orifice nozzle unit 120. In this impeller 131, as illustrated in (a) of FIG. 2, a plurality of water turbine blades 131c for rotating and pressurizing fluid in the first direction may be formed on the outer peripheral surface of the drum, which is the center of the rotation axis of the impeller. , as illustrated in (b) of FIG. 2, a plurality of water turbine blades 131d for rotating and pressurizing the fluid in the second direction opposite to the first direction may be formed on the outer peripheral surface of the drum, which is the center of the rotation axis of the impeller. there is. In addition, the impeller 131 may be composed of multi-stage impellers 131a and 131b arranged at regular intervals in the longitudinal direction along the power transmission shaft 132a of the impeller drive motor 132, as illustrated in FIG. 3. there is. In this case, it is preferable that each impeller (131a, 131b) is composed of an impeller with water turbine blades in the same direction. In particular, it is preferable that the impeller 131 of the fluid pressurizing part 130 installed in any one branch pipe 112 is installed with an impeller having water turbine blades in the opposite direction to the impeller installed in the other branch pipe adjacent to it. . For example, in the case of a quadcopter-type branched propellant, if an impeller with a water turbine blade twisted in a first direction is installed in one branch pipe, a water turbine blade twisted in a first direction is also installed in a diagonal branch pipe. An impeller with a is installed, and an impeller with water turbine blades twisted in a second direction opposite to the first direction is installed in the branch pipes on both sides adjacent to the branch pipe. In this way, installing an impeller in which the water turbine blades are twisted in the first or second direction is, for example, in a quadcopter-type unmanned navigation vehicle equipped with four propellers, the first and third propellers are twisted in the first direction. This is based on the principle of generating thrust by rotating the second and fourth propellers in a second direction opposite to the first direction.

The impeller drive motor 132 is driven or stopped by a motor control signal from the control unit 140, and has a power transmission shaft 132a, where the end of the power transmission shaft 132a penetrates the body of the branch pipe 112. It is directly connected to the drum, which is the rotation center of the impeller 131, and is configured to directly transmit the power of the motor to the impeller.

An example in which the fluid pressurizing unit 130 is comprised of a pressurizing pump 133 and a pump driving motor 134 is illustrated in FIG. 4 . The pressurization pump 133 is installed by cutting each branch pipe 112 and tightly inserting it into the middle part using a pipe joint method, and is directly driven by the pump drive motor 134 controlled by the motor control signal from the control unit 140. By pumping the fluid on the pipe to the outlet side using a pressurized pumping method, the fluid flow, such as the flow rate or flow rate, within each branch pipe 112 is controlled through this pumping operation, and the fluid is pumped from the orifice nozzle portion 120 at the end of each branch pipe 112. It is possible to increase or decrease the rotational injection speed and pressure of the injected fluid.

The control unit 140 is installed on the upper part or one side of the propellant body 110 and receives an impeller drive motor 132 control signal or a pump drive motor ( 134) By outputting a control signal to adjust the injection amount or injection pressure of the fluid injected from the orifice nozzle unit 120, the propellant body unit 120 is controlled to move according to the pilot's will. In addition, this control unit 140 provides a chemical solution mixing unit 150 to be described later along with an impeller drive motor 132 control signal or a pump drive motor 134 control signal for controlling the fluid pressurization or blocking operation of the fluid pressurization unit 130. By outputting a control signal from the opening/closing valve 151 and adjusting the injection amount or injection pressure of the fluid injected from the orifice nozzle unit 120, the propellant body unit 120 is controlled to move according to the operator's will, and the chemical liquid mixing unit 150 is controlled. The chemical liquid is automatically introduced into the nozzle through the inlet hole 121a by the pressure difference before and after the orifice unit 121 in the orifice nozzle unit 120, thereby allowing the fluid mixed with the chemical liquid to be injected.

As illustrated in FIGS. 5 and 6, the chemical liquid mixing unit 150 is installed between the branch pipe 112 of the propellant body 110 and the inlet hole 121a of the orifice nozzle unit 120, and contains chemicals or soap. One of the chemicals is supplied to the orifice nozzle unit 120. For this purpose, there is an auxiliary pipe 114 between the branch pipe 112 of the propellant body 110 and the inlet hole 121a of the orifice nozzle part 120 through which the fluid flowing into the branch pipe 112 can be bypassed. It is formed by branching from the branch pipe 112, and on this auxiliary pipe 114, there is an opening/closing valve 151 for opening and closing the pipe of the auxiliary pipe 114 by a control signal from the control unit 140, and a medicine or soap solution. A chemical liquid container 152 in which one chemical liquid is stored is installed. The terminal end of the auxiliary pipe 114 is connected to the inlet hole 121a of the orifice nozzle part 120, and is connected to the front and rear of the orifice part 121 generated when the opening and closing valve 151 is opened and the orifice nozzle part 120 is operated. Due to the pressure difference, the fluid in the pipe of the auxiliary pipe 114 is automatically introduced into the nozzle through the inlet hole 121a of the orifice nozzle part 120 and mixed and sprayed through the nozzle injection hole 122.

As illustrated in FIG. 7, the buffer unit 160 is sized to surround the propellant body 110 and is detachably coupled to the fluid transfer unit 10 and the propellant body 110 to form a bond between the fluid transfer unit 10 and the propellant body 110. (110) and the orifice nozzle part 120 are elastically supported, and are equipped with a buffering force and flotation force to absorb external shock, so that when landing on the ground or water, the fluid transfer part 10, the propellant body part 110, and the orifice nozzle The part 120 is wrapped and protected. For this purpose, the shock absorber 160 has a wheel 161 on the inner periphery forming the main frame, and the inner periphery is supported by the wheel 161, and air is injected to add elastic support, buffering force, and flotation force, thereby fixing the shape. A tubular body 162 made of a flexible material forms the outer peripheral surface. In the inner central part of the wheel 161, a hose fixing groove 163 for fixing the hose of the fluid transfer unit 10 is formed by being supported by a plurality of holders 164, and is formed on one side of the space separated by each holder 164. A plurality of pipe fixing grooves 165 are formed to support and fix the propellant body 110, that is, the bent end of the branch pipe 112 by inserting it, so that the fluid transfer part 10, the propellant body 110, and the orifice are formed. It is configured to protect the nozzle unit 120 from external shock.

The overall operation and effect of the fluid injection propellant of the present invention configured as above will be described as follows.

First, the fluid transfer unit 10 is connected to a fluid supply source such as a high-pressure water spray on the ground, a quarantine or firefighting vehicle, or a ship on the water, and the connecting member 12 installed at the end of the hose 11 is connected to the propellant body portion ( It is closely connected to the hose coupling portion 111a formed in the main pipe 111 of 110).

As described above, when the fluid transfer unit 10 and the propellant body 110 are connected, the fluid can be continuously supplied to the main pipe 111 of the propellant body 110 by pressurizing the fluid from the fluid transfer unit 10 with a pump, etc. When fluid flows into the main pipe 111, the fluid flowing into the main pipe is guided by the guide wall and supplied to each branch pipe 112.

In this way, when the fluid is branched and supplied to each branch pipe 112, the operation of the impeller 131 or the pressurizing pump 133 of the fluid pressurizing unit 130 is controlled by the motor control signal transmitted from the control unit 140 to form an orifice. It is possible to pressurize or block the fluid in the pipe delivered to the nozzle unit 120. At this time, as illustrated in FIG. 2, the impeller 131 of the fluid pressurizing unit 130 has a plurality of water turbine blades 131c and 131d formed on the outer peripheral surface of the drum, which is the center of the rotation axis, to direct the fluid in the pipe in the first direction, or It is possible to rotate and pressurize in a second direction opposite to the first direction, and as illustrated in FIG. 3, when the impeller 131 is composed of multi-stage impellers 131a and 131b, the rotation and pressurizing force can be reinforced. do.

Here, when the fluid pressurization unit 130 is composed of the pressurization pump 133 and the pump drive motor 134, the pump drive motor 134 and the pressurization pump 133 are directly driven by the motor control signal from the control unit 140. By pumping the fluid on the pipe to the outlet side using a pressurized pumping method, the fluid flow such as flow rate or flow rate within each branch pipe 112 is controlled to rotate the fluid sprayed from the orifice nozzle portion 120 at the end of each branch pipe 112. It is possible to increase or decrease the injection speed and pressure.

Accordingly, the fluid injection propellant of the present invention sprays the fluid supplied through the fluid transfer unit 10 and the propellant body 110 from a fluid source on the ground or on the water by pressurizing and rotating the fluid through the orifice nozzle unit 120 to provide propulsion. It occurs.

Meanwhile, in the fluid injection propellant according to the present invention, the orifice nozzle portion 120 is configured to be detachably coupled or separated from the nozzle coupling portion 112a of each branch pipe 112, and is configured to be detachably coupled or separated from the pipe diameter (internal diameter) in the middle of the pipe. This shrinking and expanding orifice portion 121 is formed so that the fluid can be sprayed by adjusting the flow rate and flow rate inside the pipe by the pressure difference before and after the orifice portion. Therefore, when the orifice nozzle part 120 is coupled to the nozzle coupling part 112a of each branch pipe 112, the fluid injection propellant of the present invention is used by the impeller 131 of the fluid pressurizing part 130 or the pressurizing pump ( 133), the pressure difference within the pipe before and after the orifice portion 121 of the orifice nozzle portion 120, and the fluid due to the steel wire 122a formed on the inner peripheral surface of the nozzle injection port 122. The fluid can be pressurized and rotated to high pressure by rotational force and pressing force and injected through the nozzle injection hole 122.

On the other hand, when the orifice nozzle part 120 is not coupled to the nozzle coupling part 112a of each branch pipe 112, the fluid injection propellant of the present invention is used to force the fluid in the pipe by the fluid pressurizing part 130. By pressurizing and rotating the fluid through rotation and pressing operations, the fluid can be sprayed directly from the end of each branch pipe 112.

Meanwhile, in a state in which the orifice nozzle part 120 is coupled to the nozzle coupling part 112a of each branch pipe 112, the branch pipe 112 of the propellant body part 110 and the inlet hole of the orifice nozzle part 120 As illustrated in FIGS. 5 and 6, an auxiliary pipe 114 through which fluid is bypassed is installed between (121a), and the auxiliary pipe 114 is controlled by a control signal from the controller 140 on the auxiliary pipe 114. A chemical liquid mixing unit 150 consisting of an opening/closing valve 151 for opening and closing the pipe and a chemical liquid container 152 in which either chemical liquid or soap liquid is stored is installed, and the inlet hole of the orifice nozzle portion 120 ( When connected to 121a), when the opening/closing valve 151 is opened by the control unit and the orifice nozzle unit 120 is operated, the fluid injection operation generated from the nozzle injection port 121 causes the orifice unit 121 to move forward and backward. A pressure difference occurs within the pipe, and the pressure difference allows the fluid within the pipe of the auxiliary pipe 114 to automatically flow into the inlet hole 121a of the orifice nozzle portion 120. Due to this automatic inflow operation, the orifice nozzle unit 120 can mix either the chemical liquid or the soap liquid in the chemical liquid container 152 with the fluid rotated and pressurized and discharged from the fluid pressurizing unit 130 and spray it at high pressure. There will be.

Meanwhile, the propellant for fluid injection of the present invention in each of the above-described embodiments can function as an independent propellant when the propellant body portion 110 is used alone without being attached to the drone body. In this case, the propellant When the body portion 110 is attached to the drone body through the drone attachment/detachment portion 113, the fluid injection propellant of the present invention can be used as a thrust reinforcement for the drone, contributing to stabilizing the drone's flight attitude.

Lastly, in the propellant for fluid injection of the present invention, as illustrated in FIG. 7, a buffer portion 160 of a size surrounding the propellant body 110 is detachably coupled to the fluid transfer portion 10 and the propellant body 110. In addition, the hose of the fluid transfer unit 10 is fixed by inserting it into the hose fixing groove 163 formed in the inner center of the wheel 161 forming the main frame, and a plurality of pipes formed in the space separated by each holder 164 are fixed. After inserting the bent end of each branch pipe 112 into the groove 165 to support and fix it, when air is injected into the tubular body 162 formed on the outer peripheral surface of the wheel 161, the buffer portion 160 is elastically formed. It is possible to add support, buffering, and flotation. When the fluid injection propellant of the present invention is operated in this state, the tubular body 162 is connected to the fluid transfer part 10, the propellant body part 110, and the orifice nozzle part 120 when landing on the ground or water during operation. Because it can be wrapped and protected, the propellant can cushion the impact when landing on the ground, allowing it to land elastically, and when landing on the water, it can float on the water instead of sinking in the water, preventing damage from collisions or shocks with external objects. Damage or loss can be prevented.

As described above, although the present invention has been described with reference to limited examples and drawings, the present invention is not limited to the above examples, nor is it limited to using a single or separate supply pipe, which is the field to which the present invention pertains. Those skilled in the art can make various modifications and variations from this description. Accordingly, the spirit of the present invention should be understood only by the scope of the patent claims described below, and all equivalent or equivalent modifications thereof shall fall within the scope of the spirit of the present invention.

10: fluid transfer unit 11: hose
12: connecting member 110: propellant body part
111: main pipe 111a: hose joint
112: branch pipe 112a: nozzle joint
113: Drone attachment/detachment part 114: Auxiliary piping
120: Orifice nozzle part 121: Orifice part
121a: inlet hole 122: nozzle injection hole
122a: steel wire 130: fluid pressurization unit
131: Impeller 131a, 131b: Multi-stage impeller
131c, 131d: Waterwheel blade 132: Impeller drive motor
132a: Power transmission shaft 133: Pressurization pump
134: pump driving motor 140: control unit
150: Chemical liquid mixing unit 151: Open/close valve
152: Medicine container 160: Buffer part
161: wheel 162: tubular body
163: Hose fixing groove 164: Holder
165: Piping fixing groove

Claims (14)

In the propellant that generates propulsion by high-pressure injection of fluid supplied through the fluid transfer unit 10 from a fluid source on the ground or on the water,
It is a pipe body with a closed upper end and a plurality of branch pipes 112 radially branched from the side of the vertically arranged main pipe 111. Fluid flows in from the lower part of the main pipe 111 and flows through each branch pipe 112. A propellant body portion 110 that diverges and discharges fluid radially;
It is detachably coupled to the end of each branch pipe 112 and forms an orifice portion 121 whose pipe diameter is reduced and expanded in the middle of the pipe to control the flow rate and flow rate inside the pipe by the pressure difference before and after the orifice portion. An orifice nozzle unit 120 that sprays fluid;
A fluid pressurization unit ( 130); and
It is provided on the upper part of the main pipe 111 of the propellant body 110, and controls the propellant body 120 by adjusting a motor control signal for controlling the fluid pressure delivery or blocking operation of the fluid pressurization part 130. A propellant for fluid injection, characterized in that it includes a control unit 140 that controls the movement according to. The method of claim 1, wherein the propellant body portion 110,
A hose coupling portion (111a) is formed at the lower end of the main pipe 111 to couple or separate the fluid conveying portion 10 to allow fluid to flow in from the fluid conveying portion 10, and the ends of each branch pipe 112 is formed by bending downward to transport the fluid downward, and a nozzle coupling portion 112a is formed at the end thereof for coupling or separating the nozzles, so that the orifice nozzle portion 120 is detachably coupled. Propellant for fluid injection. The method of claim 1, wherein the orifice nozzle unit 120,
A propellant for fluid injection, characterized in that a steel wire (122a) for generating rotational force of the fluid is formed on the inner peripheral surface of the nozzle injection hole (122) and is configured to rotate and inject the fluid. The method of claim 1, wherein the fluid pressurizing unit 130,
An impeller (131) that is rotatably inserted and installed inside each branch pipe (112) and rotates and pressurizes the fluid in the pipe by rotating inside the pipe to supply or block the fluid to the orifice nozzle portion (120); and
It is driven or stopped by a motor control signal from the control unit 140, and has a power transmission shaft 132a, where the end of the power transmission shaft 132a penetrates the body of the branch pipe 112 to form the impeller 131. A propellant for fluid injection, characterized in that it includes an impeller drive motor 132 that is directly connected to the drum, which is the center of rotation, and transmits the power of the motor to the impeller. The method of claim 4, wherein the impeller 131 is,
A propellant for fluid injection, characterized in that a plurality of water turbine blades (131c) are formed on the outer peripheral surface of the drum forming the center of the rotation axis to rotate and pressurize the fluid in the pipe in a certain direction. The method of claim 4, wherein the impeller 131 is,
A fluid that is supported by the power transmission shaft 132a and rotatably installed as a whole, and is composed of multi-stage impellers 131a and 131b arranged at regular intervals along the longitudinal direction of the power transmission shaft 132a. Propellant for injection. The method of claim 6, wherein the multi-stage impellers (131a, 131b),
A propellant for fluid injection equipped with a fluid pressurizing part and a steel wire, characterized in that it is an impeller with water turbine blades in the same direction. The method of claim 5, wherein the impeller 131 installed in each branch pipe 112 is,
A propellant for fluid injection, characterized in that an impeller with water turbine blades in the opposite direction to an impeller installed in a neighboring branch pipe is installed. The method of claim 1 or 4, wherein the fluid pressurizing unit 130,
A pressure pump 133 that is closely inserted and installed in the middle of each branch pipe 112 through a pipe joint and pressurizes the fluid in the pipe using a pressure pumping method to supply or block the fluid in the pipe to the orifice nozzle portion 120; and
It is driven or stopped by a motor control signal from the control unit 140, and is installed to be exposed to the outside of the branch pipe 112, but is configured to include a pump drive motor 134 that directly drives the pressurization pump 133. A propellant for fluid injection, characterized in that. The method of claim 1, wherein the propellant body portion 110,
A drone attachment/detachment portion 113 for coupling or separation from the drone body is provided on the upper part of the main pipe 111, and is coupled to the drone body through the drone attachment/detachment portion 113 to be used as a thrust reinforcement for the drone, or the drone attachment/detachment portion 113 ) A propellant for fluid injection, characterized in that it can be separated from the drone body and used as a propellant that flies independently. The method of claim 1, wherein the orifice nozzle unit 120,
An inlet hole 121a through which fluid can flow in from the outside is formed on one side of the nozzle body forming the orifice portion 121,
Between the branch pipe 112 of the propellant body 110 and the inlet hole 121a of the orifice nozzle 120, there is a space for supplying either a chemical or a soap solution to the orifice nozzle 120. A propellant for fluid injection, characterized in that a chemical liquid mixing unit (150) is installed. The method of claim 11, wherein the propellant body portion 110,
An auxiliary pipe 114 through which fluid flowing into the branch pipe 112 can be bypassed is formed by branching from the branch pipe 112, and the end of the auxiliary pipe 114 is coupled to the branch pipe 112 by the orifice nozzle. It is formed to be connected to the inlet hole 121a of the part 120,
The chemical liquid mixing unit 150,
An opening/closing valve 151 installed on the auxiliary pipe 114 to open and close the piping of the auxiliary pipe 114 by a control signal from the control unit 140, and a storage device for storing either a chemical solution or a soap solution. It consists of a chemical liquid container (152),
Fluid in the pipe of the auxiliary pipe 114 flows into the orifice nozzle part 120 due to the pressure difference before and after the orifice part 121 that occurs when the opening and closing valve 151 is opened and the orifice nozzle part 120 is operated. A propellant for fluid injection, characterized in that it is configured to automatically flow into the nozzle through the ball (121a). According to paragraph 1,
It has a size that surrounds the circumference of the propellant body 110 and is detachably coupled to the fluid transfer unit 10 and the propellant body 110 to connect the fluid transfer unit 10, the propellant body 110, and the orifice nozzle unit 120. A buffer unit ( 160); A propellant for fluid injection, characterized in that it further comprises a. The method of claim 13, wherein the buffer unit 160 is,
A wheel 161 on the inner periphery forming the main skeleton, and a tubular body 162 made of a flexible material to which elastic support, buffering and flotation are added by injecting air, form the outer periphery,
In the inner central part of the wheel 161, a hose fixing groove 163 for inserting, supporting and fixing the hose of the fluid transfer unit 10 is formed by being supported by a plurality of holders 164 and separated by each holder 164. A propellant for fluid injection, characterized in that a plurality of pipe fixing grooves (165) are formed in the space where the orifice nozzle portion (120) can be inserted and supported.