KR101483064B1

KR101483064B1 - Portable launch control apparatus and operating method for guided air vehicle launch system

Info

Publication number: KR101483064B1
Application number: KR1020140020391A
Authority: KR
Inventors: 이재은
Original assignee: 엘아이지넥스원 주식회사
Priority date: 2014-02-21
Filing date: 2014-02-21
Publication date: 2015-01-21

Abstract

Releases portable launch control equipment for an induction vehicle launch system. The present invention relates to a display unit for displaying engagement information related to shooting of an object to be guided, which is calculated based on image information of the target and the image information; A control unit for generating firing information for firing the guided vehicle according to an operation of an operator based on the firing information displayed on the display unit and providing the firing information to the firing unit; And a strap coupled to a housing for receiving the engagement information from the launch device to receive the display device and the control device to control the launch device from a remote location and to wear the housing on the wrist or arm of the user; .

Description

Technical Field [0001] The present invention relates to a portable launch control apparatus and an operating method for an induction vehicle launch system,

The present invention relates to a portable launch control device, and more particularly, to a portable launch control device and method for controlling an induction vehicle by outputting information collected from the outside to an image and interfacing with a launch device based on an output image.

Inductive flight system is a system that controls a series of procedures related to the launch of an induction vehicle in an induction system. In addition, the guidance vehicle launch system creates a mission plan and controls the launch control equipment and the launch device according to the generated mission plan, and executes the launch procedure for the guidance vehicle.

Inductive vehicles in an induction vehicle launch system are rocket propulsion vehicles that can be guided to a target by command. When the direction and distance to the target are calculated according to the inertial induction method or the tracking induction method, the guided vehicle is guided to the target by controlling the flight characteristics according to the calculated direction and distance.

These guided vehicles are launched from the launch control equipment to the target. Launch control equipment is a device that receives information of targets collected from an unmanned airplane and outputs information to a display device such as LCD. It is a device that acts as a brains of an induction vehicle launching system. It is largely composed of engagement planning, engagement control, It is in charge of functions such as target selection and status display.

Conventional launch control equipment is composed of a large number of computers and communication equipment, which is bulky and heavy, which is not easy to carry and requires a separate external power supply to supply power to the computer and communication equipment. .

In addition, since the conventional launch control equipment has many functions, the number of parts is large and the heat radiation path is complicated. Therefore, launch control equipment needs to be reduced in weight by applying an effective heat dissipation system for easy portability.

Japanese Laid-Open Patent Application No. 10-2011-0126898 discloses a launch control system for a mobile launch system. The launch control system includes input / output means for inputting various commands for controlling and proceeding a launch procedure and for checking the status of an induction vehicle It is possible to increase the mobility of the control equipment by operating the launch control equipment on a portable vehicle.

However, since the launch control device is an invention that is mounted on a mobile vehicle and is easy to move, there is a difference from the present invention in which an operator can operate the launch control device.

Accordingly, it is an object of the present invention to provide a launch control device for controlling an induction vehicle in cooperation with a launch device in an induction vehicle launch system, which includes a strap portion and can be worn on an operator's wrist or an arm To provide portable launch control equipment.

However, the objects of the present invention are not limited to those mentioned above, and other objects not mentioned can be clearly understood by those skilled in the art from the following description.

According to an aspect of the present invention, there is provided a portable launch control system for an induction vehicle launch system, including: a display unit for displaying engagement information related to launching of an induction vehicle based on image information of a target and image information; part; A control unit for generating firing information for firing the guided vehicle according to an operation of an operator based on the firing information displayed on the display unit and providing the firing information to the firing unit; And a strap coupled to a housing for receiving the engagement information from the launch device to receive the display device and the control device to control the launch device from a remote location and to wear the housing on the wrist or arm of the user; .

Wherein the control device receives the image information from the unmanned airplane, transmits the image information to the launch device to request the engagement information, receives the engagement information from the launch device, and displays, based on the engagement information, The launching information is generated and transmitted to the launching device, wherein the launching information is attachable to and detachable from the side of the housing.

Said strap including a strap surrounding a portion of a hand of an operator; A winding portion located on both sides of the housing and connected to both ends of the strap to couple the strap to the housing; And a support member positioned on both sides of the housing to support the strap, wherein the strap is separable from the center point.

The winding unit has a spring having an elastic force, and when the center point of the strap is separated, the winding unit is rotated by the spring to pull the strap and wind it inside the housing.

And a heat spreader disposed between the display unit and the control unit and formed in the same shape as the housing to protect the display unit from external impacts and to allow heat generated from the display unit and the control unit to contact outside air, .

And a laser induction device for designating a target point of the guidance vehicle when the target is identified by the operator's eyes.

And a voice input / output unit configured by a microphone for inputting voice of the operator and a speaker for outputting voice of the external personnel for a voice communication mode in which the operator can communicate with external personnel by voice, do.

And a terminal unit for updating the software of the control device and connecting the software to external devices for checking whether there is an abnormality in the software.

Further comprising an input unit configured by a plurality of input buttons for receiving commands for a plurality of functions, wherein the input button includes a first function button for receiving a command to display the image information and the engagement information on the display unit; A launch button for receiving a launch command of the guidance vehicle; A second function button for receiving a command for correcting the flight path of the guidance vehicle; A safety arming button for stopping the function of the fire button; An induction button for receiving a command to operate the laser induction device; And a mode change button for inputting a command for changing to the voice communication mode.

According to an aspect of the present invention, there is provided a method of operating a portable launch control device for an induction vehicle launch system, the method comprising: receiving engagement information relating to launch of an induction vehicle calculated based on image information of a target; Displaying the image information and the engagement information; And generating firing information for firing the guided vehicle according to an operation of an operator at a position spaced a predetermined distance from the firing device on the basis of the displayed image information and the firing information, and transmitting the generated firing information to the launching device.

The step of receiving the engagement information comprises: receiving the image information from an unmanned air vehicle; And transmitting the image information to the launch device and receiving the engagement information calculated based on the image information from the launch device.

Accordingly, the present invention has the effect of increasing the portability by incorporating the function of generating engagement information, which is the function of the launch control device, in the launch device and combining the strap portion with the lightened launch control device.

In addition, the present invention has the effect of simplifying the heat dissipation structure in accordance with the lightened launch control equipment, thereby reducing weight and volume.

In addition, since the launch control device having the strap portion can be mounted on the wrist or the arm of the operator, the launch device can be controlled remotely from a position distant by a certain distance, thereby preventing the exposure of the operator's position .

1 is a block diagram schematically showing a configuration of an induction vehicle launch system according to an embodiment of the present invention.
2 is a block diagram schematically illustrating the configuration of the launch control device 200 according to an embodiment of the present invention.
3 is a first view of the launch control equipment according to an embodiment of the present invention.
4 is a second view of the launch control equipment according to an embodiment of the present invention.
FIG. 5 is a side view illustrating a combination of launch control equipment according to an embodiment of the present invention. Referring to FIG.
6 is a view illustrating an internal heat dissipation structure of the launch control device according to an embodiment of the present invention.
7 is a flowchart illustrating a method of operating a launch control device according to an embodiment of the present invention.

In order to fully understand the present invention, operational advantages of the present invention, and objects achieved by the practice of the present invention, reference should be made to the accompanying drawings and the accompanying drawings which illustrate preferred embodiments of the present invention.

Hereinafter, the present invention will be described in detail with reference to the preferred embodiments of the present invention with reference to the accompanying drawings. However, the present invention can be implemented in various different forms, and is not limited to the embodiments described. In order to clearly describe the present invention, parts that are not related to the description are omitted, and the same reference numerals in the drawings denote the same members.

Throughout the specification, when an element is referred to as " including " an element, it does not exclude other elements unless specifically stated to the contrary. The terms "part", "unit", "module", "block", and the like described in the specification mean units for processing at least one function or operation, And a combination of software.

1 is a block diagram schematically showing a configuration of an induction vehicle launch system according to an embodiment of the present invention.

Referring to FIG. 1, an induction object launch system according to an embodiment of the present invention includes an unmanned air vehicle 100 having an image acquisition means, a launch control device 200, and a launch device 300.

The unmanned airplane (100) refers to an aircraft that is controlled by the ground and operated by the pilot, not directly by the pilot. Such an unmanned airplane (100) has a possibility of loss of life, such as an attack using a missile on a target, a reconnaissance activity on a target in a battle situation, etc., and is operated more efficiently, stably, and at a low cost than a manned aircraft in a dangerous operation can do.

In the present invention, the UAV 100 includes image acquisition means such as an optical (EO) camera, an infrared ray (IR) camera and a CCD (Charge-coupled Device) camera to determine the position, It is possible to obtain the image information. In addition, the UAV 100 includes the wireless transceiver and transmits acquired image information to the fire control equipment 110. Here, the UAV 100 may be replaced by various types of reconnaissance equipment capable of performing a reconnaissance function for a target and capable of wired / wireless communication.

The launch control device 200 receives the image information from the UAV 100 and transmits the received image information to the launching device so that the launch control device 200 can receive the engagement information in response thereto. Also, the launch control device 200 can receive the launch information about the target from the operator based on the received engagement information, and direct the launch of the guide flight vehicle mounted on the launch device 300. At this time, the launch control device 200 can display and display the image information on a display device such as an LCD, an LED, and a flexible display so that the operator can easily confirm the image with the naked eye.

The launch device (300) is a device that performs various operations according to various signals transmitted from the launch control device (200).

The launch device (300) analyzes the image information received from the launch control device. Here, the launch device 300 receives image information from the launch control device 200 and calculates engagement information for the target from the received image information. The launch device 300 is equipped with a program for calculating engagement information using image information. The engagement information includes an engagement plan, target selection, and evaluation of the threat of the target, which are information necessary for the determination of the launch of the guided vehicle toward the target.

At this time, the engagement plan may include whether or not the guided vehicle is fired and the expected time in the target. Whether the guidance vehicle is fired includes whether there is an obstacle during the flight of the guidance vehicle through the image information received from the UAV, whether it is located within the flying distance of the guidance vehicle, and whether there is difficulty in setting the coordinates because the movement of the target changes rapidly can do. If it is determined that the guidance vehicle can reach the target, the launching device 300 calculates the estimated time required for the guidance vehicle to arrive at the target.

The launching device 300 can calculate the predicted time based on the coordinate information of the target, the launch preparation time, and the flight time of the guided vehicle. Here, the coordinate information of the target refers to the coordinates of the point where the target is located. The launch preparation time may include the time required for the determination of the engagement and the preparation time from the moment of the engagement decision to the take-off of the guided vehicle. The flight time of the guided vehicle refers to the time required for flying toward the target with the optimal trajectory.

An evaluation of the threat of a target can be said to rank the hit for that target when there is an element in which any one of two or more targets is more threatening to the friendly than all other targets.

The target selection is to select the target with the highest hit rank among the many targets that would be a threat to this alliance.

In addition, the launch device 300 receives the launch information from the launch control device 200, and launches an induction air vehicle mounted on the launch device 300. The launch device (300) receiving the launch information can automatically fire the guide air vehicle toward the target after the automatic switch to the target direction.

Here, wired communication or wireless communication is used between the launch control device 200 and the launch device 300, for example, short-range wireless communication, Ethernet, and optical communication. The present invention preferably uses wireless communication.

At this time, the engagement information obtained by analyzing the image information by the launch device 300 is stored in a storage medium such as an SSD applied to the launch device 300. [ The engagement information can be confirmed later through the check port of the launch control device 200 or the launch device 300. It is also possible that the engagement information is stored in the storage medium of the UAV 100 in cooperation with the UAV 100.

The launch control device 200 and the launch device 300 of the present invention can be carried and operated by an operator at the same time. The launch control device 200 controls the position, size and movement of the target from the unmanned airplane And the like. The launch control device 200 transmits the image information to the launch device 300 to calculate engagement information for responding to the target through the image information. The launch device 300 can obtain the engagement information for the target using the image information in a predetermined manner.

The launch device (300) transmits the engagement information to the launch control device (200). Then, the launch device 300 is installed on the ground within a flight distance of the guided vehicle by the operator according to the engagement information, the distance between the launch device 300 and the target. The operator operates the launch control device 200 at a distance from the launch device 300 in order to prevent positional exposure during the launch of the guidance vehicle. That is, the launch device 300 and the launch control device 200 are disposed apart from each other by a predetermined distance.

The launch control device (200) transmits the launch information for launching the induction vehicle to the launch device (300) according to the engagement information. The launch device (300) receiving the launch information ignites the thermocouple of the guided air vehicle after automatically switching to the target direction, and fires the guided air vehicle toward the target.

Therefore, the portable launch device 300 of the present invention can remotely control an induction flight in the launch device 300 by using the launch control device 200 after a certain distance from the launch control device 200 and the launch device 300 Since launching, the guidance vehicle launch point is exposed, but the exposure of the operator can be prevented.

2 is a block diagram schematically illustrating the configuration of the launch control device 200 according to an embodiment of the present invention.

2, the launch control device 200 includes a display unit 210, a control unit 220, a strap unit 230, a laser induction unit 240, an input button 250, an antenna 260, a voice input / (270), a terminal portion (280), and a housing (290).

The display unit 210 displays image information and engagement information for the target. In the above description, the image information includes a position, a scale, and the like with respect to the target, and the engagement information includes a threat evaluation required for selecting a target and a flight expected time required for the target to reach the target.

In addition, the display unit 210 may display the forward situation and the state of the guidance vehicle acquired through the reconnaissance camera built in the guidance vehicle while the guidance vehicle is flying toward the target. The display unit 210 may be an image display device for controlling the guided vehicle based on the image displayed by the operator.

The control device 220 transmits and receives various information in cooperation with the launch device 300. Various information includes image information, engagement information, and launch information.

Also, the control device 220 generates firing information according to the operation of the operator and transmits the generated firing information to the launch device 300. The operation of the operator may be an operation of pressing the launch button based on the image displayed on the display unit 210. [ In one embodiment, the operator basically presses the firing button at a position spaced a certain distance from the launch device. This is to prevent exposure of the operator's position. The launch information may include igniting thermocouples of the guidance vehicle mounted on the launch device 300.

The strap portion 230 is an apparatus for enhancing the portability of the launch control device 200 and is coupled to the housing 290 so that the launch control device 200 can be worn on the operator's wrist or arm. This is to make it easier for the operator to operate the launch control device 200. In addition, the strap 230 may be electrically connected to the controller 220 and may include a sensor for informing an external person of the existence of the operator.

In one embodiment, the sensor is preferably located near a midpoint of the strap so that biometric information including a pulse of the operator can be sensed. Such a sensor can be made of a current sensing survival measurement sensor using a piezoelectric element. The biometric information of the operator detected by the sensor is transmitted to the senior unit or the surrounding operational personnel so that it can be used to check whether the operator is alive or not in real time.

The laser induction device 240 is a device for guiding an induction vehicle to a target using a laser. The laser induction device 240 is activated by the guidance button 256 of the fire control equipment 200 to fire the laser toward the target. The target designated by the laser induction device 240 becomes the guiding point of the guided vehicle. Therefore, the laser induction apparatus 240 has an effect of shortening an induction flight time for a target with a short distance.

The input button 250 is a means for receiving a command for performing various functions of the launch control device. The input button 250 may supply power to the launch control device to operate the function and direct the launch of the guidance vehicle mounted on the launch device. Also, the input button 250 may instruct to display a map of a target or a surrounding area. The input button 250 may comprise a plurality of buttons for performing various functions of the launch control device.

The antenna 260 is for transmitting and receiving various information in cooperation with a senior unit, an unmanned aerial vehicle, and the launch device 300 in the tactical command automation system. In addition, the antenna 260 is an element for wirelessly transmitting core commands such as firing, stopping of the firing, and emergency explosion. Preferably, the antenna 260 uses an omnidirectional antenna that does not generate a blind spot due to a signal in various directions.

In one embodiment, the antenna 260 may use a directional antenna that changes the direction of the signal, as the case may be. Directional antennas are radio signals only in one direction, so signals are more than omnidirectional signals. However, the other directions except for the direction of radio signals are blind zones. . To overcome this problem, a directional antenna having a waveguide and a reflector can be used.

The voice input / output unit 280 includes a microphone and a speaker, and enables voice communication in the voice communication mode of the launch control device 200. In the voice communication mode, the operator can communicate with a person who wants to communicate with the microphone of the voice input / output unit 280 through a speaker and voice. This makes it unnecessary for the operator to have a separate radio apparatus for communication, which can simplify the arming of the operator.

The terminal unit 270 is a terminal for manually inputting the software upgrade and operation information of the launch control device 200 and for connecting the external device for checking the operation of each device of the software inspection and launch control device 200 to be.

The housing 290 includes a display unit 210, a control unit 220, a laser guide unit 240, an input button 250, an antenna 260, a terminal unit 270 and a voice input / output unit 280, . This housing (290) engages with the strap portion (230). The housing 290 may be a substantial element that an operator wears on the wrist or arm.

3 is a first view of the launch control equipment according to an embodiment of the present invention.

3, the display unit 210 is located on the front of the fire control equipment 200, and displays information for launching an induction vehicle. Through the displayed information, the operator can judge whether or not the guidance vehicle is fired on the target. The display unit 210 is applicable as a flexible display for saving power and lightening of the launch control device 200. [ LCDs, LEDs, and OLED displays can also be used as needed.

The strap portion 230 is located on the opposite side where the display portion 210 is located. This is for viewing an image that appears through the display unit 210 while the operator wears the wrist or the arm. The components of the strap portion 230 will be described later in Fig.

The power button 251 is a button for supplying power to the launch control device 200 and operating the same.

The launch button 252 is a button for launching the guidance vehicle.

The launch stop button 253 is a button for stopping the flight of an induction vehicle in an emergency situation during an induction flight.

The emergency explosion button 254 is a button for manually blowing the guidance vehicle after the guidance vehicle is launched.

The function buttons 255 are basically provided with 12 buttons composed of F1 to F12. Here, the function buttons 255 may be further added or deleted as needed. Each button is a button that allows quick access to various functions incorporated in the launch control device 200. The built-in functions include a function to display image information and engagement information, a function to show the position and route of the personnel located within the scope, an ability to show the map of the route, the route modification function of the guidance vehicle, And a function of acquiring thermal image information using a camera of an induction vehicle.

The voice input / output unit 280 is provided on the left front side of the launch control device 200 to enable voice communication in a voice communication mode. Since the voice input / output unit 280 is located inside the launch control device, portability can be enhanced.

4 is a second view of the launch control equipment according to an embodiment of the present invention.

4, the control device 220 may be located inside the launch control device 200 in the form of a card constituting a circuit. The control device 220 includes a control module 221, a communication module 222, and a power module 223.

The control module 221 receives an instruction according to an operator's operation and controls the display unit 220 to display an image or control the communication module 222 to transmit and receive various information.

The communication module 222 performs a function of interworking with a senior unit, an unmanned aerial vehicle, and the launch device 300.

The power module 223 is a battery that supplies power to the fire control equipment 200 and is attached to the back surface of the control unit 220 and exposed to the outside. In order to protect such power module 223, the fire control equipment 200 may have a battery cover 224. The battery cover 224 may be a cover that not only protects the power module 223 but also covers the rear surface of the firing control equipment.

The laser induction device 240 is not shown in the drawing but is located inside the right side of the launch control device 200. The laser induction device 240 is located inside the emission control device, so that a separate device is not required additionally, so that the portability can be improved.

The guidance button 256, the mode change button 257 and the safety arming button 258 may be located on the upper side of the fire control equipment 200 so as not to overlap the terminal portion 270, .

The guidance button 256 is a button for activating the laser induction device 240 of the fire control equipment 200. The launch control device 200 in which the laser induction device 240 is activated by the guidance button 256 can drive the launch device 300 without any additional communication so that the target can be quickly hit and batched.

The mode change button 257 is a button for switching to the voice communication mode of the launch control device 200. The voice communication mode refers to a mode in which the launch control device 200 can communicate with the outside by voice. The mode change button 257 can be changed from the communication mode to the normal mode. The normal mode is a mode for performing all the functions other than the function of communicating with the outside by voice. If necessary, the normal mode and the communication mode may be simultaneously implemented.

The safety arming button 258 is a button for activating or deactivating the launch control equipment 200. The launch control device 200 deactivated by the safety arming button 258 may stop all functions of the input button 250. Or the safety arming button 258 may be changed to stop the function of the launch button only if necessary. Having such a safety arming button 258 is intended to prevent inadvertent firing of the guidance vehicle.

The antenna 260 is mounted on the side of the launch control equipment. The volume of the antenna 260 may be reduced according to the development of the technology, and the size of the launch control device may be further reduced if the antenna 260 is positioned inside the launch control device.

The terminal portion 270 is composed of a USB terminal 271 and a check terminal 272 and may be located on the upper side of the launch control device 200. The terminal portion 270 can be normally protected by an outer cover.

The USB terminal 271 is a terminal for connecting an external device for manually inputting software upgrade and operation information of the launch control device 200. [

The check terminal 272 is a terminal for connecting with an external device for checking software of the launch control device 200 and checking whether operation of each device of the launch control device 200 is abnormal.

FIG. 5 is a side view illustrating a combination of launch control equipment according to an embodiment of the present invention. Referring to FIG.

5, the launch control device 200 is configured by coupling a strap portion 230 to a housing 290 that accommodates the display portion 210 and the control device 220.

The display unit 210 is disposed on the inner side of the housing 290 and is located on the opposite side of the strap 230 so that the operator can easily see the wrist when worn. In one embodiment, the display portion 210 may be planar, but may later be made of a flexible display so that the housing 290 may be more closely attached to an operator's wrist or arm.

The control device 220 can be detached and attached to the side surface of the housing 290. This control device 220 is a possible form by implementing the functions of the conventional launch control device in the launch device 300. [ The functions of the conventional launch control device 200 include threat evaluation for a target, selection of a target according to threat evaluation, and establishment of an engagement plan for a target.

This type of control device 220 may be easily detachable and easy to separate from the launch control device 200 and limit the function of the launch control device 200 under special circumstances.

The housing 290 is hollow so that the display unit 210 and the control unit 220, which are components of the launch control equipment 200, can be accommodated. The housing 290 is an element that is combined with the strap portion 230 to be worn by the operator.

The strap portion 230 includes a winding portion 232 positioned on both sides of the housing 290, a strap 231 having both ends connected to the winding portion 232 and a strap 231 positioned on both sides of the housing 290, And a supporting base 233 for supporting.

The strap 231 may have a wide width corresponding to the entire length of the housing 290, in the form of wrapping a part of the hand including the wrist of the operator. In one embodiment, the strap 231 is preferably made of a material having a thickness of less than 1 mm and capable of being accommodated in the launch control device 200 and having a high rigidity to bear the weight.

The winding portion 232 is positioned on both sides of the housing 290 and serves to couple the strap 231 to the housing 290. [

In an embodiment, the winding unit 232 includes a torsion spring having an elastic force, and the strap 231 is pulled by the torsion spring and wound around the inside of the housing 290. When the center point of the strap 231 is separated, the winding section 232 is rotated by the torsion spring to pull the strap 231. The strap 231 pulled by the elastic force of the torsion spring is accommodated in the housing 290 in a rolled shape and is protected by the housing 290 at normal times. Also, the strap 231 of the winding unit 232 can be worn by the operator in a tight contact with the launch control equipment due to the pulling force of the winding unit 232, thereby preventing shaking.

The support 233 supports the strap 231 to allow the operator to feel comfort when the launch control device 200 is worn on the wrist or arm. The support 233 also functions to allow the strap 231 to be smoothly inserted into the housing 290 when the strap 231 is detached.

6 is a view illustrating an internal heat dissipation structure of the launch control device according to an embodiment of the present invention.

6 (a), the fire control equipment 200 includes a heat spreader 292 for effectively dissipating heat of the fire control equipment 200, which is lightened inside the housing 290.

6 (a) shows a form in which the heat spreader 292 is positioned inside the fire control equipment 200. As shown in FIG. The heat spreader 292 is formed in the same shape as the housing 290 to protect the launch control device 200 from external impacts. The heat spreader 292 may be made of aluminum, but may further be formed by sintering the carbon nanotube powder. The heat spreader 292 not only withstands an external impact but also has high thermal conductivity and is effective for heat dissipation.

6 (b) shows a path through which heat generated from the components of the fire control equipment 200 equipped with the heat spreader 292 moves. The heat spreader 292 is positioned between the display unit 210, which is a main heat source, and the control unit 220, and receives heat. The transferred heat moves inside the heat spreader 292 and comes into contact with the outside air. The heat in contact with air can be cooled by air. The launch control device 200 equipped with the heat spreader 292 is effective in reducing weight because it is not necessary to install a device for heat radiation for each heat emitting element.

7 is a flowchart illustrating a method of operating a launch control device according to an embodiment of the present invention.

Referring to FIG. 7, the launch control device 200 receives image information including the location and scale of the target from the UAV 100 in step S701, and transmits the received image information to the launch device 300 (S703)

The launch control device 200 receives the engagement information related to the launch of the guidance object calculated based on the image information from the launch device in step S705, and displays the received engagement information and the received image information in step S707.

Based on the displayed image information and the engagement information, the launch control device 200 receives a command related to launching an induction vehicle from an operator at a position distant from the launch device at step S709.

The launch control device 200 generates launch information for launching the guidance vehicle in accordance with the received command, and transmits the generated launch information to the launch device 300 in step S713. do.

The method according to the present invention can be implemented as a computer-readable code on a computer-readable recording medium. A computer-readable recording medium includes all kinds of recording apparatuses in which data that can be read by a computer system is stored. Examples of the recording medium include a ROM, a RAM, a CD-ROM, a magnetic tape, a floppy disk, an optical data storage device, and the like, and a carrier wave (for example, transmission via the Internet). The computer-readable recording medium may also be distributed over a networked computer system so that computer readable code can be stored and executed in a distributed manner.

While the present invention has been particularly shown and described with reference to exemplary embodiments thereof, it is evident that many alternatives, modifications and variations will be apparent to those skilled in the art.

Accordingly, the true scope of the present invention should be determined by the technical idea of the appended claims.

100: Unmanned aircraft
200: Launch control equipment
300: launch device
210:
220: Control device
221: Control module
222: communication module
223: Power module
230: Strap portion
231: Strap
232:
233: Support
240: laser induction device
250: Input Button
260: antenna
270: terminal portion
280: Voice input / output unit
290: Housing
292: Heat spreader

Claims

A display unit for displaying image information about a target and engagement information related to shooting of the guidance object calculated based on the image information;
A control unit for generating firing information for firing the guided vehicle according to an operation of an operator based on the firing information displayed on the display unit and providing the firing information to the firing unit; And
A strap part coupled to a housing for receiving the engage information from the launch device and accommodating the display part and the control device so that the launch device can be controlled at a long distance, and the housing is worn on the wrist or arm of the operator;
, Wherein the control device
Receiving the image information from the unmanned airplane, transmitting the image information to the launch device to request the engagement information, receiving the engagement information from the launch device, and generating the launch information based on the operation of the operator based on the engagement information Wherein the portable device is of a type capable of being detached and detached from the side of the housing.

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2. The apparatus of claim 1, wherein the strap portion
A strap surrounding a portion of the operator's hand;
A winding portion located on both sides of the housing and connected to both ends of the strap to couple the strap to the housing;
A support positioned on both sides of the housing to support the strap;
Wherein the strap is separable at a central point. &Lt; RTI ID = 0.0 > A < / RTI > portable launch control system for an induction vehicle launch system.

The guidance system according to claim 3, wherein the winder comprises a spring having an elastic force, and when the central point of the strap is separated, the winder rotates by the spring to pull the strap and wind it in the housing. Portable launch control equipment for.

[2] The apparatus of claim 1, further comprising: a housing disposed between the display unit and the control unit and formed in the same shape as the housing to protect the display unit and the controller from external impact, Heat spreader
Wherein the portable launch control system further includes a portable launch control system for the guidance vehicle launch system.

The apparatus according to claim 1, further comprising: a laser induction device for designating a target point of the guidance vehicle when the target is visually recognized by the operator;
Wherein the portable launch control system further includes a portable launch control system for the guidance vehicle launch system.

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The terminal device according to claim 1, further comprising: a terminal unit for updating the software of the control device and connecting the external device to the external device for checking whether the software is abnormal;
Wherein the portable launch control system further includes a portable launch control system for the guidance vehicle launch system.

9. The apparatus according to any one of claims 1 to 8, further comprising input means comprising a plurality of input buttons for receiving commands for a plurality of functions,
A first function button for receiving a command for displaying the image information and the engagement information on the display unit;
A launch button for receiving a launch command of the guidance vehicle;
A second function button for receiving a command for correcting the flight path of the guidance vehicle;
A safety arming button for stopping the function of the fire button;
An induction button for receiving a command for operating the laser induction device; And
A mode change button for inputting a command for changing to a voice communication mode;
Wherein the portable launch control system is adapted for use with a launch vehicle control system.

Receiving engagement information related to the launch of the guidance vehicle calculated based on the image information about the target;
Displaying the image information and the engagement information; And
Generating launch information for launching the guided vehicle according to an operation of an operator at a position spaced a predetermined distance from the launch device based on the displayed image information and the engage information, and transmitting the generated launch information to the launch device;
Wherein the step of receiving the engagement information comprises:
Receiving the image information from an unmanned aerial vehicle; And
Transmitting the image information to the launch device and receiving the engagement information calculated based on the image information from the launch device;
Wherein the method comprises the steps of: (a)

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