KR20150090539A - Vertical takeoff and landing aircraft for fire control - Google Patents

Abstract

The present invention relates to a vertical takeoff and landing aircraft for fire control, comprising: a body part; a control part combined with the body part; a pair of frames whose one end is combined with the body part and radially extended from the center of the body part; a propulsion unit including an engine combined with the other end of the frame and driven by receiving a signal from the control part, and a propeller combined with one end of the engine and rotated by the engine to generate a thrust in a vertical direction; a fuel supply unit including a fuel container installed in the body part, and a fuel line fixed to the frame to supply fuel to each engine; a fire control unit installed in the body part to collect and transmit video and audio of a disaster area; and a ground control unit to transmit a flying signal to the control part and to wirelessly control a vertical takeoff and landing aircraft. The present invention improves capacity and mileage, provides high stability using multiple propellers, and reduces failure due to a simple structure.

Description

{Vertical takeoff and landing aircraft for fire control}

BACKGROUND OF THE INVENTION 1. Field of the Invention [0002] The present invention relates to a vertical take-off and landing aircraft for a fire control system, and more particularly, to a vertical take-off and landing aircraft for a fire control system having a large number of engines and propellers.

A helicopter is an aircraft with lift and propulsive force generated by turning a rotating wing, called a rotor, to the engine. Vertical takeoff and landing and air stopping are possible, and the rotary wing controls the angle so that it can move forward, backward, and horizontally.

Helicopters are available for a variety of purposes such as police service, lifeguarding, fire suppression, aerial photographing, and the ability to take off and land on a small area, fly at slow speed along complicated terrain, and stay in one place. In addition, a helicopter may be used as an unattended person without being carried directly by the user when used in aerial photography, pesticide application, or the like.

However, since the conventional helicopter is composed of the main rotor and the sub rotor two wings, even if a single wing is damaged or obstructed, the unmanned helicopter crashes, and at the same time, the side is gentle and flat, I have a problem.

Recently, a multi-copter with a number of electric motors and propellers has been developed that uses a battery to operate as an electric motor. The multi-copter is a type of helicopter capable of vertical takeoff and landing, . Most multi-copters have an even number of rotor blades in the form of two pairs (quadrocopter, X-copter), three pairs (hexacopter, Y-6) and four pairs (octocopter) In the case of -6, it is placed on the two lower planes. However, the multi - copter has a limited take - off load due to the use of electricity from the battery, which limits the flight time.

In particular, unmanned aerial vehicles can be put into a disaster situation where firefighting personnel are inaccessible, such as fire, toxic gas generation, nuclear accident, CBRN terrorism, floods due to abnormal climate or floods. It is necessary to develop the unmanned aerial vehicle technology that can promptly control and control the situation of the damage site to the firefighting officer and the command and control room and safeguard the safety of firefighting personnel.

As a conventional technique, Patent Document 1 proposes a rotary wing unmanned reconnaissance aircraft having four wing structures, but it has a disadvantage in that it can not fly for a long time like a vertical takeoff aircraft for a fire control system of the present invention and the load load is not large.

1. Korean Published Patent No. 10-2008-0099839

SUMMARY OF THE INVENTION The present invention has been made in view of the above-mentioned needs, and it is an object of the present invention to provide a multi-copter which can operate with a battery and an electric motor, And a vertical take-off and landing gear for a fire control system equipped with an engine and a propeller.

According to another aspect of the present invention, there is provided a vertical take-off device for a firefighting control system, comprising: a body part; a control part coupled to the body part; one end coupled to the body part and extending radially from the center of the body part, An engine that is coupled to the other end of the frame and receives signals from the control unit and drives the engine; and a propeller that is coupled to one end of the engine and rotates by the engine to generate a vertical thrust A fuel supply unit which is installed on the body part and which is fixed to the frame and supplies a fuel to each of the engines; A firefighter unit and a control signal to the control unit to wirelessly transmit the vertical take- It characterized in that it comprises a control unit that controls the ground.

In an embodiment of the present invention, the fire-fighting unit may include a gimbal installed at the lower end of the body part to rotate about two axes, a thermal imager installed on the gimbal and capturing an image, a sound recorder for recording voice, A speaker for transmitting sound transmitted from the ground control unit, and an illumination device for illuminating the front and rear sides.

In one embodiment of the present invention, the terrestrial control unit may include a display for displaying images transmitted by the firefighter unit or a control screen for controlling the vertical takeoff and landing, a sound recorder for recording voice and transmitting the sound to the firefighter unit, And a speaker for transmitting the voice transmitted from the first unit.

As an embodiment of the present invention, the navigation system further includes a GPS installed in the body portion and confirming the position of the vertical take-off and landing device and transmitting the position to the ground control unit. The ground control unit displays the received real- It is capable of remote control flight or automatic flight, and is characterized by automatic return to the starting point when low voltage or communication is lost.

According to an embodiment of the present invention, the controller controls a throttle valve that controls a fuel injection amount of the engine to control a rotational speed of the propeller, thereby controlling a posture and a thrust of the vertical take-off and landing device.

As an embodiment of the present invention, The propulsion unit is characterized in that the propeller rotating in the clockwise direction and the propeller rotating in the counterclockwise direction are paired.

 In one embodiment of the present invention, the propulsion unit includes a starter connected to the engine shaft in an opposite direction to which the propeller is connected, and the control unit receives a start signal from the ground control unit and outputs a current signal to the starter And activates the engine by the electric motor of the starter.

The present invention has a large maximum load and a long flying time as compared with a multi-copter in which a fuel cell is disposed at the center and a plurality of engines and a propeller are used for a battery and an electric motor.

In addition, it is equipped with a large number of propellers, and has high stability.

In addition, vertical landing and landing is possible on any terrain, and it can be mounted on a small vehicle.

1 is a perspective view showing a vertical take-off and landing aircraft for fire control using a plurality of engines and propellers according to the present invention.
2 is a plan view of a vertical take-off and landing aircraft for fire fighting control according to the present invention.
3 is a view showing a propulsion unit of a vertical take-off and landing aircraft for fire control according to the present invention.
4 is a side view of a vertical take-off and landing aircraft for fire control according to the present invention.

Hereinafter, embodiments of the present invention will be described with reference to the drawings. The drawings illustrate only the essential features of the invention in order to facilitate clarity of the invention and are not to be construed in a limiting sense since they are not shown in the accompanying drawings.

FIG. 1 is a perspective view of a vertical take-off and landing aircraft for fire control using a plurality of engines and propellers according to the present invention. FIG. 2 is a plan view of a vertical take- A control unit 200, a frame 300, a propulsion unit 400, a fuel supply unit 500, a firefighting unit 600, and a ground control unit 700. [

The body part 100 may further include landing means for supporting the vertical take-off and landing device so as to be spaced apart from the ground at a predetermined height.

The controller 200 may be coupled to the body 100. The control unit 200 controls the propulsion unit 400 and the fuel supply unit 500 to stably control the flight of the vertical take-off and landing aircraft.

The frame 300 has one end coupled to the body 100 and extending radially from the center of the body 100, and may be formed of two or more pairs. The conventional helicopter has two wing structures and is low in stability and is likely to fall when one wing is damaged. However, the frame 300 according to the present invention extends radially to the body 100 and is formed as a pair The stability of flight can be improved.

3, the propulsion unit 400 is coupled to the other end of the frame 300, receives a signal from the control unit 200, And a propeller 420 coupled to one end of the engine 410 and rotated by the engine 410 to generate a thrust in the vertical direction. The vertical take-off and landing according to the present invention has a large number of engines 410 and a propeller 420 and has a large maximum load and a long flight time as compared with a multi-copter using a battery and an electric motor. Engine 410 may be a nitro engine, two-stroke or four-stroke gasoline engine. In addition, since a plurality of propellers 420 are provided, the flight stability is excellent, and even if a single wing is damaged due to a simple structure, it is possible to fly. At present, the unmanned helicopter is two months in pilot training period, but the vertical take-off and landing aircraft according to the present invention composed of four engines and propellers is very easy to operate and can be operated after two days of training. In addition, the propeller 420 may include a cylindrical duct on its outer periphery to support and protect the propeller 420 while improving the propulsion efficiency.

The propelling unit 400 can control a posture and a thrust of the vertical take-off and landing device by a pair of a propeller 420 rotating in a clockwise direction and a propeller 420 rotating in a counterclockwise direction. A control unit 200 at the center, and an internal combustion engine engine 410 composed of four or more even numbers, and a propeller 420 corresponding to the engine 410 is formed at an upper portion of the engine 410. Half of the even number of engine 410 and propeller 420 rotate in the clockwise direction and the other half in the counterclockwise direction and the forward rotation engine is rotated at a constant pitch so that the propeller 420 generates a downward air flow, The rotating engine may have an inverse pitch. In the case of a quad rotor equipped with four propellers 420, the front and rear propellers 420 rotate in a clockwise direction, and the left and right propellers 420 rotate counterclockwise. The same number of propellers 420 are turned counterclockwise to cancel the torque. In order to ascend or descend, the entire rotational speed may be increased or decreased. To tilt leftward, the rotational speed of the left propeller 420 may be lowered and the rotational speed of the right propeller 420 may be increased. Forward and reverse can be done in the same way.

The controller 200 controls the throttle valve 412 to adjust the fuel injection amount of the engine 410 to control the rotational speed of the propeller 420 to control the posture and the thrust of the vertical take-off and landing device. The rotation servo 411 receives the pulse width modulation (PWM) signal received from the control unit 200 and interlocks the rotation servo 411 and the throttle valve 412 of the vaporizer of the engine 410 to move the rotation servo 411 And adjusts the angle of the throttle valve 412 corresponding thereto. The controller 200 may control the rotation speed of the engine 410 by adjusting the angle of the throttle valve 412 to increase or decrease the fuel injected or drawn into the engine 410. The control unit 20 controls the engine 410 and controls the rotational speed of the propeller 420 provided in each engine 410 to control the ascending, descending, and flying directions of the vertical take-off and landing aircraft.

The throttle valve 412 may correspond to 0 to 90 degrees from 360 degrees (0 to 100%) of the rotation servo 411 and the throttle valve 412 may control the response characteristic of the rotation servo 411 But it is possible to make 0 to 50% of the movement of the rotary servo 411 correspond to 0 to 90 degrees of the valve. The throttle valve 412 has a butterfly valve structure so that when it is fully opened, it is horizontally positioned with respect to the fluid flow so that it can not rotate anymore.

In addition, the propulsion unit 400 includes a starter. A starter may be provided in the opposite direction to the axis of the engine 410 and connected to the propeller. The control unit 200 receives a start signal from the ground control unit 700 and transmits a current signal to the starter to activate the engine 410 by the electric motor of the starter. The starter is connected to an axis behind the engine 410 to operate electrically.

4 is a side view of a vertical take-off and landing aircraft for fire fighting control according to the present invention. The fuel supply unit 500 includes a fuel tank 510 installed in the body 100 and a fuel tank 510 fixed to the frame 300, And a fuel line 520 for supplying fuel to the fuel lines 410. The fuel tank of the fuel supply unit 500 is installed in the body 100 and supplies fuel to each engine 410 through the fuel line 520. The fuel cell 510 is disposed at the center of the multi-copter and the fuel is supplied to drive the plurality of engines 410 and the propeller 420, thereby increasing the flight time of the vertical take- The maximum loadable weight can be increased. By increasing the loading weight, it is possible to fly for a long time, and the efficiency of the control work in the disaster area such as fire can be improved.

The fire fighting unit 600 may be installed in the body 100 to collect images and sounds of the disaster area and transmit the images and sounds. The firefighting unit 600 includes a gimbal 610 installed at the lower end of the body 100 so as to rotate about two axes, a thermal imager 620 mounted on the gimbals 610, A sound recorder 630 for recording voice, a speaker 640 for transmitting a warning sound or voice transmitted from the ground control unit, and a lighting device 650 capable of guiding persons to illuminate front and rear.

The two-axis gimbal camera 620 can control the shooting direction and control the tilt axis and the roll axis of the image in a stable manner, and one operator can control the flight and the image at the same time. Further, the camera 620 mounted on the gimbals 610 can be mounted according to the situation of a disaster area, such as a general camera or a thermal imaging camera. A sound recorder 630 and a speaker 640 to record a sound such as a request for a rescue site as well as an image of a scene at a disaster site and transmit the announcement message to the speaker 640 for safely guiding the life of the commander or the firefighter . In addition, the lighting device 650 can be installed at night or in a dark place with toxic gas to enable field verification and induction of life with powerful illumination.

The terrestrial control unit 700 may transmit the control signal to the controller 200 to wirelessly control the vertical landing and landing aircraft. Also, the ground control unit 700 includes a display 710 displaying an image transmitted by the firefighter unit 600 or a control screen for controlling the vertical take-off and landing device, a sound recording unit 710, And a speaker 730 for transmitting voice transmitted from the firefighter unit. The ground control unit 700 includes not only a flight of a vertical take-off and landing device but also a video shooting, a voice transmission / reception, a lighting device 650 Can be controlled remotely.

A display 710 is provided to check the real-time image and the flight control screen transmitted by the firefighter's unit 600 at one time, which is advantageous for ground control. In addition, a high-brightness display can be used so that the received image and the control image can be checked even in the bright outdoor. Also, the ground control unit 700 can transmit and receive video and audio using the LTE network, and can confirm and direct the disaster scene in real time.

The vertical take-off and landing device further includes a GPS installed on the body part 100 and confirming the position of the vertical take-off and landing device and transmitting the position to the ground control unit 700. The ground control unit 700 receives the received real- The GPS position can be displayed on the display 710 for remote pilot flight or automatic flight, and can be automatically returned to the starting point when low voltage or communication is lost. GPS equipped with a digital map, you can check the real time location of the vertical takeoff and landing, you can set the arrival point to fly by automatic flight. Also. If a flight obstacle occurs, return to the starting position is possible.

The vertical takeoff and landing aircraft according to the present invention has a fuel tank at the center, a plurality of engines and a propeller, and has a large maximum load and a long flight time as compared with a multi-copter using a battery and an electric motor. It has high stability with many propellers and can be used stably when it is put into a disaster situation due to its simple structure. It can be vertically landed and landed on any terrain, and can be mounted on a small vehicle. It can be put into real-time in a disaster scene such as a fire, so that quick and efficient command control is possible. In addition, it is possible to enhance the rescue ability of the damaged area by supporting the safety and suppression of firefighting personnel.

While the present invention has been particularly shown and described with reference to exemplary embodiments thereof, it will be understood by those skilled in the art that various changes and modifications may be made therein without departing from the spirit and scope of the invention as defined in the appended claims. It will be possible.

100: body part 200:
300: frame 400: propelling unit
410: engine 411: rotation servo
412: Throttle valve 420: Propeller
500: fuel supply unit 510: fuel tank
520: Fuel line 600: Firefighter unit
610: Gimbal 620: Thermal camera
630: Recorder 640: Speaker
650: Lighting device 700: Ground control unit
710: Display 720: Sound Recorder
730: Speaker

Claims (7)

A body portion;
A control unit coupled to the body portion;
A frame, one end of which engages with the body and extends radially from the center of the body, wherein the frame is formed in two or more pairs;
A propulsion unit coupled to the other end of the frame and configured to receive and drive signals from the control unit and a propeller coupled to one end of the engine and rotated by the engine to generate a vertical thrust;
A fuel supply unit comprising a fuel tank installed in the body and a fuel line fixed to the frame and supplying fuel to each of the engines;
A firefighter unit installed in the body and collecting and transmitting images and sounds of the disaster area; And
And a ground control unit for wirelessly controlling the vertical take-off and landing device by transmitting a control signal to the control unit. The fire fighting apparatus according to claim 1,
A gimbal installed at the lower end of the body to rotate about two axes;
An infrared camera mounted on the gimbals and capturing an image;
A voice recorder;
A speaker for transmitting a warning sound or a sound transmitted from the ground control unit; And
And a lighting device capable of guiding the person to the front and rear of the vehicle. 2. The apparatus of claim 1, wherein the ground control unit
A display for displaying images transmitted by the firefighter unit or a control screen for controlling the vertical takeoff and landing;
A sound recorder for recording the voice and transmitting the sound to the fire fighting unit; And
And a speaker for transmitting sound transmitted from the firefighter unit. The method of claim 3,
Further comprising: a GPS installed in the body portion and confirming the position of the vertical take-off and landing device and transmitting the position to the ground control unit,
Wherein the ground control unit displays the received real time GPS on the display to enable remote control flight or automatic flight and automatically return to the starting point when low voltage or communication is lost. The method according to claim 1,
Wherein the controller controls a throttle valve for controlling the fuel injection amount of the engine to control the rotational speed of the propeller to control the posture and the thrust of the vertical take-off and landing device. The method according to claim 1,
Wherein the propulsion unit comprises a pair of a propeller rotating in a clockwise direction and a propeller rotating in a counterclockwise direction. The method according to claim 1,
The propulsion unit includes a starter connected to the engine shaft in the opposite direction to which the propeller is connected. The control unit receives a start signal from the ground control unit and transmits a current signal to the starter, Wherein said engine is activated by said control means.

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