WO2022019749A1

WO2022019749A1 - Unmanned firefighting drone

Info

Publication number: WO2022019749A1
Application number: PCT/MY2021/050020
Authority: WO
Inventors: Amin BIN HALIM RASIP
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-07-20
Filing date: 2021-03-31
Publication date: 2022-01-27
Anticipated expiration: 2023-01-20
Also published as: MY201218A; AU2021313699A1

Abstract

The invention discloses an unmanned, firefighting drone (100) comprising at least one propulsion unit (101), and a gyroscopic frame (200) which frame (200) carries a launching unit (300), wherein the launching unit (300) is adapted to receive fire retarding material, and is rotatable, in use, independently of the propulsion unit (101) to aim and discharge fire retarding material at an intended target.

Description

UNMANNED FIREFIGHTING DRONE

FIELD OF INVENTION

The present invention relates to an unmanned firefighting drone. More particularly, the present invention relates to an unmanned firefighting drone that is capable of extinguishing extreme cases of fire within an affected area with minimal assistance and risks of endangering human lives.

BACKGROUND OF THE INVENTION

Natural disasters or unforeseen accidents continue to occur occasionally despite society’s advancements and growth. One of the most devastating elements of nature is fire, with its ability to spread quickly and engulf an entirety of forests and buildings alike rapidly, making it one of nature’s deadliest forces. With the recent wildfires that has been occurring throughout the world, there is an increasing demand of industrial technologies designed for fighting fires and extinguishing them in rapid succession. Trained firefighters are often deployed to the scene of a fire along with conventional fire trucks and fire hoses to handle the hazardous situation. For fires that break out in areas that are inaccessible by conventional means, aerial fire fighting units such as planes and helicopters carry a predetermined amount of water or fire retardant chemicals to extinguish the fire before having to return to resupply the payload. In the recent years, there has been a surge of technologies employing unmanned aerial vehicles (UAV) or drones to undergo such operations.

Many technologies related to firefighting drones have been proposed to further improve this application. For example, South Korea patent with publication no. KR101741578B1 discloses fire suppression drones capable of emitting fire extinguishers include a fire tracing unit for tracking fire origin based on thermal imaging data of a built-in thermal imaging camera and heat sensing data of a heat sensing sensor unit. According to this document, it also includes a throwing unit for adjusting the angle of fire and the firing distance of the fire extinguisher based on the tracking result of the fire tracing unit, and a moving unit including a plurality of propellers and adjusting the moving direction. This configuration disposes a throwing unit capable of adjusting the angle of rotation of the drone in connection with a thermal sensor unit for discharging the fire extinguishing material. This is undesirable as the accuracy of the drone is heavily affected by natural factors such as strong wind. Another technology as disclosed in South Korean patent with publication no. KR101437323B1 recites an unmanned aerial vehicle for fire fighting that is suitable for quickly putting out fires at fire sites where firefighters have difficulty in accessing. The configuration disposes multiple launchers in the drone whereby the launchers are separated in two sections; the upper section launches a plurality of fire extinguishing pellets using compressed air, and the lower section releases the fire extinguishing pellets through an opening on the lower surface of the launcher. United States patent with publication no. US10413763B2 discloses a fire extinguishing firefighting drone which, in case of a fire in a house, a structure, a building, or the like, can be rapidly introduced to extinguish a fire in an early stage of the fire, and can be remotely operated in an unmanned manner through connection with a central control system. The fire extinguishing firefighting drone includes a flight unit configured to include propeller units, a disaster prevention turret unit configured to spray a fire extinguishing chemical, a plurality of movement units configured to move a body unit, and a disaster prevention means unit configured to be provided with items adapted to spray a fire extinguishing chemical, to launch a fire extinguishing bomb, or to save lives.

There exists a need to provide an unmanned firefighting drone, in which the drone provides a gyroscopic frame which allows for freedom of rotation for the mounted launching units. More particularly, the launching unit of the drone is able to rotate independently to the body of the drone during the firefighting operation. SUMMARY OF INVENTION

The present invention discloses an unmanned, firefighting drone comprising at least one propulsion unit, and a gyroscopic frame which the frame carries a launching unit, wherein the launching unit is adapted to receive fire retarding material, and is rotatable, in use, independently of the propulsion unit to aim and discharge fire retarding material at an intended target.

Preferably, the propulsion unit comprises at least one propeller unit for enabling flight, mounted onto a body of the drone.

Preferably, the gyroscopic frame is configured to mount at least one launching unit, such that the launching unit is able to independently rotate along 3 axes of the gyroscopic frame.

Preferably, the launching unit comprises a rotatable magazine housing a plurality of projectile units containing the fire retarding material.

Preferably, each projectile unit comprises a plastic enclosure with a hollow interior for containing the fire retarding material to be launched at the designated target.

Preferably, each plastic enclosure of the projectile unit comprises two separable parts fitted together.

Preferably, the launching unit utilizes a solenoid and at least one spring mechanism in connection with a piston for discharging the projectile units, such that the solenoid and spring mechanism function from power provided from an electrical supply in the drone connected to the launching unit. Preferably, the fire retarding material includes liquid nitrogen.

Preferably, the drone includes wireless communication means for controlling the flight of the drone.

One skilled in the art will readily appreciate that the present invention is well adapted to carry out the objects and obtain the ends and advantages mentioned, as well as those inherent therein. The embodiment described herein is not intended as limitations on the scope of the invention.

BRIEF DESCRIPTION OF THE DRAWINGS

For the purpose of facilitating an understanding of the invention, there is illustrated in the accompanying drawing the preferred embodiments from an inspection of which when considered in connection with the following description, the invention, its construction and operation and many of its advantages would be readily understood and appreciated.

FIG. 1 illustrates a side elevation view of an unmanned, firefighting drone according to the present invention.

FIG. 2 illustrates a top elevation view and front elevation view of the unmanned firefighting drone according to the present invention.

FIG. 3 illustrates a side elevation view of a preferred embodiment of a launching unit according to the present invention.

FIG. 4 illustrates a cross section view of the launching unit assembly according to the present invention. FIG. 5 illustrates an enlarged cross section view of a magazine body and a launching barrel according to the present invention.

FIG. 6 illustrates a cross section view of a projectile unit according to the present invention.

DETAILED DESCRIPTION OF THE INVENTION

Hereinafter, the invention shall be described according to the preferred embodiments of the present invention and by referring to the accompanying description and drawings. However, it is to be understood that limiting the description to the preferred embodiments of the invention is merely to facilitate discussion of the present invention and it is envisioned that those skilled in the art may devise various modifications without departing from the scope of the appended claim.

The present invention will be now described in greater detail with reference to the drawings.

FIG. 1 illustrates an assembly of an unmanned, firefighting drone 100 constructed in accordance to the invention. In its preferred form, the drone 100 comprises at least one propulsion unit 101, wherein the propulsion unit 101 further comprises at least one propeller unit 101a, 101b, 101c & lOld for enabling flight, and wherein the propeller units 101a, 101b, 101c & lOld may be aftermarket propeller units 101a, 101b, 101c & lOld or 3D printed propeller units 101a, 101b, 101c & lOld to accommodate for the size of the drone 100. Preferably, the size of the propeller units 101a, 101b, 101c & lOld corresponds to the amount of load that the drone 100 will have to lift during operation. Further, the propeller units 101a, 101b, 101c & lOld are connected to motors 103 fitted onto multiple elongated arms 102 extending from the body of the drone, wherein the motors 103 may be brushless Direct Current (DC) electric motors commonly used in electrical equipment which operates by converting supplied electrical energy into mechanical energy. By way of example but not limitation, the body of the drone 100 may include compartments for housing a power supply unit, an electronic speed controller unit, a flight controller unit, and a wireless transceiver, wherein the power supply unit may be any type of battery such as rechargeable lithium polymer batteries, lithium ion batteries or the likes, configured to supply power to the motors 103, launching unit 300, electronic speed controller unit, flight controller unit and wireless transceiver therewith. The wireless transceiver may be a wireless module capable of transmitting and receiving signals via a wireless protocol cloud such as Long Term Evolution (LTE) cloud, Code Division Multiple Access (CDMA) and its derivatives, Enhanced Data Rates for GSM Evolution (EDGE), 3G protocol, High Speed Packet Access (HSPA), 4G protocol, 5G protocol, Bluetooth and the likes, in accordance to the advancement of wireless technology with time. The flight controller unit operates as the motherboard of the drone 100 by issuing commands received from a control centre or drone 100 operator through the wireless transceiver, wherein functions such as regulating motor speeds, controlling autopilot mode and other autonomous functions are further controlled by the flight controller unit. Further, the electronic speed controller unit operates by monitoring and varying the speed of the drone 100 during flight, and is responsible for the direction of flight of the drone 100 therewith. Optionally, the drone 100 may be fitted with an integrated video capturing device, such as a thermal imaging camera, digital camera or action camera capable of providing a real-time video feed to a drone operator. Preferably, the plurality of electronic components housed in the body of the drone 100 communicate with one another to form an interconnected communication network.

A gyroscope is generally known as a device consisting of a wheel or disc mounted so that it can spin rapidly about an axis which is itself free to alter in direction, wherein an orientation of the axis is not affected by tilting of a specific mounting. In a particular embodiment, the gyroscopic frame 200 comprises a cylindrical tube, configured to form an external circular frame 200a, mounted on at least two pivoted support points on at least one elongated arm 104 angularly extended upwards to the body of the drone 100 therewith which allows a rotation of the external circular frame 200 about a single axis, wherein the cylindrical tube may be constructed with a lightweight metal alloy or synthetic plastics such as polyvinyl chloride (PVC) or the likes. Preferably, at least one or more circular frames 200b & 200c are thusly connected internally to the external circular frame 200a, acting as added gimbal sets to allow additional degrees of rotational freedom for the launching unit 300. By way of example, at least one launching unit 300 is mounted onto the centre of the gyroscopic frame 200 on an elongated cylindrical tube 201 connected horizontally to the middle points of the gyroscopic frame 200, which will be discussed further herein.

In one particular embodiment, the launching unit 300 comprises a main body, configured to house at least one spring mechanism 304 coupled with a solenoid, a reloading mechanism, a trigger mechanism, a magazine body 302 and a launching barrel 301 thusly connected to the main body of the launching unit 300. Preferably, the main body, launching barrel and the magazine body are made out of lightweight synthetic plastic such as polyvinyl chloride (PVC) to maintain an overall lightweight architecture, wherein the launching unit is required to withstand a high recoil during operation due to the backwards momentum caused by launching the projectile unit. The spring mechanism 304 in the launching unit further comprises at least one pairing of springs 304a & 304b in tension, whereby the springs are attached to metal plates 309 at each ends to be attracted and repelled by at least one solenoid 306, as illustrated further in FIG. 3. Particularly, the solenoid 306 may include a spool of metallic wire, often made of iron, coiled therealong, and is powered by the power supply unit in the body of the drone. The solenoid 306 functions by generating a magnetic field when electric current passes through the wire, which then could be switched on and off by the application and removal of electric current. In a preferred embodiment, the magazine body 302 housing the plurality of projectile units 400 are rotatable along the launching barrel 301, wherein the magazine body 302 functions similarly to rotary magazines found in antique firearms. The magazine body 302 may contain a spring at one end of the magazine body for loading the projectile units 400 into the magazine body 302, similarly to a firearm magazine, whereby the spring is compressed when the magazine body is fully loaded and subsequently pushes the projectile units 400 into the reloading cartridge 303 during operation. In a particular embodiment, the reloading cartridge 303 operates by inserting the projectile unit 400 from the magazine body 302 into the launching barrel 301 whereby the piston 306 will subsequently launch the projectile unit 400 thereafter when the trigger mechanism 305 is pulled. Preferably, the reloading cartridge 303 may be a hollow cartridge large enough to fit at least one projectile unit at a time.

In another preferred embodiment, the launching unit 300 presents an additional feature of automatically reloading the projectile units 400 into the launching barrel 301 by employing a reverse motion linkage 308 between the trigger mechanism 305 and the reloading mechanism 303. Reverse motion linkage levers 308 are typically used to make things move in opposite directions, wherein the output movement will be same as the input movement but in the opposite direction if the pivot point of the reverse motion linkage lever 308 is at the centre of the connecting lever. During operation, the reverse motion linkage lever 308 functions by locking the reloading cartridge 303 when the trigger mechanism 305 is pulled, and unlocking the reloading cartridge 303 when the trigger mechanism 305 is at rest, which will be discussed further herein.

Referring to FIG. 2, the assembly of the drone 100 is shown in a top elevation view and front elevation view for a clearer illustration of the gyroscopic frame 200 and the mounted launching units 300 therewith. By way of example, at least one launching unit 300 is attached to the gyroscopic frame 200 of the drone 100, wherein the launching unit 300 is rotatable in 3 axes independent to the body of the drone, as illustrated by FIG. 1 and FIG. 2 respectively. The side view as illustrated in FIG. 1 shows the launching unit 300 being able to rotate along the X-axis and Z-axis, whereas FIG. 2 illustrates the rotation of the launching unit along the Y-axis and Z-axis from the front view, and along the X-axis and Y-axis if viewed from a top elevation. The rotation of the launching unit 300 along the 3 axes can either be remotely controlled by the drone 100 operator from a safe distance or programmed into the flight controller unit in the drone 100 prior to the operation.

FIG. 3 illustrates a preferred embodiment of the launching unit 300 in operation. Prior to launching, the projectile unit 400 is loaded into the reloading mechanism 303, wherein the reloading mechanism 303 is unlocked by a reloading pin 311 for the projectile unit 400 to travel through. Concurrently, the activated solenoid 306 repels the metal plate 309 attached to the ends of the springs 304, causes one pair of the springs 304 to be in a compressed 304b state, and the other pair of the springs 304 to be in a stretched 304a state. The metal plate 309 is then locked in place by the trigger mechanism 305 to prevent misfires from occurring. When the trigger mechanism 305 is pulled, the solenoid 306 is subsequently turned off and the metal plate 309 is released from its position, pushing towards the piston 307. The piston 309 is then flung towards the projectile unit 400, pushing naturally compressed air to the projectile unit 400, causing the projectile unit 400 to be forcefully launched out of the launching barrel 301. Concurrently, the pulling of the trigger mechanism 305 causes the reverse motion linkage lever 308 to move in the opposite direction of the trigger mechanism 305, causing the reloading pin 311 to lock the reloading mechanism 303, thus preventing the projectile unit 400 from being loaded into the launching barrel 301.

FIG. 4 illustrates an exemplary embodiment of a cross section view of the magazine launching unit 300 assembly, wherein A represents an enlarged view of the cross section of the magazine body 302 and launching barrel 301 which is illustrated respectively in FIG. 5. In this particular embodiment, the magazine body 302 comprises a cylindrical tube 314 with at least one aperture 313 for loading the projectile units 400 into the magazine body 302, wherein the magazine body 302 is surrounding the launching barrel 301 of the launching unit 300. By way of example, the projectile units 400 are loaded into the reloading cartridge 303 through an entry 312 into the inner chamber 315 of the launching barrel where it will be disposed until launched during operation. During operation, the piston 307 is pushed through an aperture 314 in the launching barrel 301 where it will make contact with the projectile unit 400 and subsequently launch the projectile unit 400 out of the launching unit 300. The magazine body 302 further shows a circular enclosure 317 for securing the projectile units 400 in place. Optionally, the mouth of the launching barrel 301 may employs ridges 318 therealong for strengthening the structural integrity of the launching barrel 300.

FIG. 6 illustrates an enlarged view of the cross section of the projectile unit 400. In this particular embodiment, the projectile unit 400 comprises two halves 401a & 401b of a spherical shell 401 fitted together, wherein the present invention may utilize a lightweight, low density and rigid plastic polymer, metal alloy, or the likes. In a preferred embodiment, each half 401a & 401b of the spherical shell 401 may be moulded with a plurality of grooves 403 or apertures for fitting a plurality of connector pins 405, permitting a single moulding to be used for both sides of the spherical shell 401 with a secure joint between them. Preferably, the connector pins 405 employed for holding the two halves 401a & 401b of the spherical shell 401 together may be shear pins, whereby the shear pins function as a mechanical safeguard designed to break once a predetermined force is applied onto the shear pins. In another preferred embodiment, the spherical shell 401 of the projectile unit comprises an outer 402a & 402b and inner chamber 404 containing fire retarding materials, wherein the inner chamber 404 is filled with a primary fire retarding material and the outer chamber 402a & 402b may be filled with a secondary fire retarding material or left empty to act as a means of insulation for the primary fire retarding material. Preferably, the primary fire retarding material contained in the inner chamber 404 is liquid nitrogen, which is commonly utilized as coolants for superconductors and various mechanical equipment, and also freezing and transporting of food products. Generally, nitrogen gas turns into liquid state at -160°C and has very low pressure in this state, thus the projectile unit 400 containing the liquid nitrogen has to be kept below this temperature to ensure it maintains its state. In operation, the projectile unit 400 which is launched at the intended target area will be exposed to extreme heat, which in turn will cause the internal temperature and pressure of the projectile unit 400 to increase rapidly due to the thermodynamic nature of liquid nitrogen. Subsequently, the rapid increase in internal pressure will increase the shear force applied onto the connector pins 405 holding the spherical shell 401 together, causing them to break and further releases the encapsulated liquid nitrogen onto the intended target area. The liquid nitrogen will then further undergo rapid expansion upon exposure to the surrounding heat in the environment, subsequently enveloping the intended target area and successfully extinguish the fire present.

The present disclosure includes as contained in the appended claims, as well as that of the foregoing description. Although this invention has been described in its preferred form with a degree of particularly, it is understood that the present disclosure of the preferred form has been made only by way of example and that numerous changes in the details of construction and the combination and arrangements of parts may be resorted to without departing from the scope of the invention.

Claims

1. An unmanned, firefighting drone ( 100) comprising at least one propulsion unit, and a gyroscopic frame (200) which the frame (200) carries a launching unit (300), wherein the launching unit (300) is adapted to receive fire retarding material, and is rotatable, in use, independently of the propulsion unit (101) to aim and discharge fire retarding material (404) at an intended target.

2. The drone according to Claim 1, wherein the propulsion unit (101) comprises at least one propeller unit for enabling flight, mounted onto a body of the drone.

3. The drone according to Claim 1 or Claim 2, wherein the gyroscopic frame (200) is configured to mount at least one launching unit (300), such that the launching unit is able to independently rotate along 3 axes of the gyroscopic frame (200).

4. The drone according to any of the preceding claims, wherein the launching unit (300) comprises a rotatable magazine (302) housing a plurality of projectile units (400) containing the fire retarding material.

5. The drone according to Claim 4, wherein each projectile unit (400) comprises a plastic enclosure (401) with a hollow interior for containing the fire retarding material to be launched at the designated target.

6. The drone according to any one of Claim 5, wherein each plastic enclosure (401) of the projectile unit (400) comprises two separable parts fitted together.

7. The drone according to any of the preceding claims, wherein the launching unit (300) utilizes a solenoid (306) and at least one spring mechanism (304) in connection with a piston (307) for discharging the projectile units (400), such that the solenoid (306) and spring mechanism (307) function from power provided from an electrical supply in the drone (100) connected to the launching unit (300).

8. The drone according to any of the preceding claims, wherein the fire retarding material includes liquid nitrogen.

9. The drone according to any of the preceding claims, wherein the drone (100) includes wireless communication means for controlling the flight of the drone (100).