KR101483063B1 - Operating method of portable launch apparatus for guided air vehicle launch system - Google Patents

Abstract

Discloses a method for operating a portable launch device for an induction vehicle launch system. The present invention relates to a method and system for generating engagement information including information related to an engagement plan for a target using image information including a position, a size, and a movement of a target provided from a launch control device; Transmitting the generated engagement information to the launch control device; And controlling firing of the guide vehicle mounted on the launching platform according to the firing information and the previously generated firing information when the firing information for firing the flight vehicle guided to the target is received from the firing control device; .

Description

Technical Field [0001] The present invention relates to an operation method of a portable launch device for an induction vehicle launch system,

The present invention relates to a method of operating a portable launching apparatus, and more particularly, to a method of operating a portable launching apparatus for an induction vehicle launching system for preventing exposure of an operator's position in launching an induction vehicle to a target.

Inductive flight system is a system that controls a series of procedures related to the launch of an aircraft 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 mounted on various types of launch devices. Conventional launch devices are ground-mounted launchers that are fixed in non-portable sites, vehicle-mounted launchers that are somewhat bulky, portable and non-operational due to noise and maneuverability, towing and towing vehicles Type launch device, an armored vehicle-mounted launch device, or an anti-charger launch device. Most of these launchers are fired at fixed sites, which are large in size and integral with launch control equipment. Also, in case of a fixed launch device, the position is exposed to the opponent at the normal time and can be a target of surveillance, and motion can be captured even just before the launch of the guidance vehicle, so that the opponent can respond immediately.

In the conventional domestic patent registration No. 10-0985155, as an approach for solving such a problem, there is disclosed an airborne launch device for launching a vehicle mounted on a vehicle or portable, that is, A target position searching unit for searching the position of the target from the generated image and an input unit for inputting a signal for emitting the flying object once the position of the target is determined from the search result, do.

However, since such a conventional airborne launcher also needs to be operated by an operator, there is a problem that the risk of exposure of the operator's location is accompanied when the airborne object is launched.

SUMMARY OF THE INVENTION Accordingly, it is an object of the present invention to provide a portable launch device for preventing exposure of an operator's position when an induction air vehicle is fired by an operator operating a launch control device and a launch device in an induction vehicle launch system And to provide a method of operation.

According to another aspect of the present invention, there is provided a method of operating a portable launching device for an induction vehicle launching system, comprising: receiving image information including a position, a size, and a movement of a target from an unmanned airplane; Generating launch information for launching the guidance vehicle guided to the target on the basis of the engagement information including information related to the engagement plan for the target calculated from the received image information of the launch control device; And launching the guidance vehicle in accordance with the launch information provided by the launch device and the launch information provided from the launch control device, wherein the launching control device is configured to separate the launch device from the launch device by a predetermined distance To the launch device.

Wherein the generating of the launch information comprises: when the launch device receives the image information from the launch control device, transmitting the engagement information generated using the received image information to the launch control device, The firing information is generated based on the firing information, and the firing information is fired on the basis of the firing information and the generated firing information.

According to an aspect of the present invention, there is provided a method of operating a portable launch device for an induction vehicle launch system, the method comprising the steps of: Generating engagement information including information related to an engagement plan; Transmitting the generated engagement information to the launch control device; And controlling firing of the guide vehicle mounted on the launching platform according to the firing information and the previously generated firing information when the firing information for firing the flight vehicle guided to the target is received from the firing control device; .

Wherein the step of controlling the launching of the guided vehicle further includes the step of, when receiving the launch information for launching the air vehicle guided to the target from the launch control equipment, The guidance vehicle is ignited, and the guidance vehicle is fired toward the target.

Wherein the engagement information includes coordinate information including coordinates indicating a position of the target; And predicted time information for estimating a time required until the guidance vehicle arrives at the target located in the coordinate information.

Accordingly, the present invention allows the operator to carry the launch device and the launch control device at the same time, but the launch device and the launch control device can be operated at a distance from each other, thereby preventing exposure of the operator's position There is an effect.

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 showing the configuration of a launch device according to an embodiment of the present invention.
3 is a schematic view illustrating a structure of a launch device according to an embodiment of the present invention.
4 is a first diagram illustrating an external configuration of a launch device according to an embodiment of the present invention.
5 is a second diagram illustrating an external configuration of the launch device according to an embodiment of the present invention.
6 is a flowchart illustrating a method of launching an induction vehicle 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 vehicle 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 capable of operating simultaneously by an operator, and a launch device 300 do.

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, and receives the engagement information in response to the received image information. 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 or an LED, 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 fires an induction air vehicle mounted on the launch device. 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 is stored in a storage medium such as an SSD applied to the launch device. 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 can be operated by the operator simultaneously with the launch control device 200 and the launch device 300 of the present invention. The launch control device 200 controls the position of the target from the unmanned airplane 100, Size, motion, and so on. 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 equipment at a distance from the launching device to prevent positional exposure during the launch of the pilot 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 showing the configuration of a launch device according to an embodiment of the present invention.

2, the launch device 300 includes a control device 310, a launch pad 320, and an elevation control device 330. The controller 310 may include a communication module 311, a control module 312, a power module 313, a simulation module 314, an elevation drive module 315, and an interlocking module 316.

The launch device 300 configured to fire the guided vehicle is not only capable of launching the guided vehicle but also generates the engage information necessary to guide the guided vehicle to the target.

The communication module 311 receives image information about the target from the launch control device 200. [ The communication module 311 is responsible for receiving and transmitting various signals between the launch control device 200 and the launch device 300 and receiving information about the flight to the target after launching the induction vehicle from the navigator of the guidance flight vehicle.

The control module 312 receives the image information from the communication module 311 and analyzes the provided image information in a predetermined manner to calculate engagement information for the target. The engagement information calculated by the control module 312 is transmitted to the launch control device 200 through the communication module.

Then, the control module 312 receives the launch information for launching the guidance vehicle through the communication module 311 from the launch control device 200. The control module 312 controls the simulation module 314, the high angle driving module 315, the interlocking module 316, the launching platform 320, the high angle adjusting device 330, and the power source And controls the module 313.

The simulation module 314 is a device that simulates a function of a certain device. The simulation module 314 of the present invention simulates the operation of the guidance vehicle mounted on the launch device 300 to check whether the guidance vehicle can be fired. If there is no fault in the guided vehicle, the guided flight continues. If there is a problem with the launch of the guidance vehicle, the guidance vehicle must be reinstalled by the operator.

The high angle drive module 315 controls the high angle adjustment device to adjust the angle in the vertical direction with respect to the ground.

The interlocking module 316 controls the launching platform according to the launch information to ignite the thermal battery of the induction flight vehicle.

The launching platform 320 may be a place where an induction air vehicle is mounted inside and an advance air vehicle of the induction air vehicle waits. The launcher 320 transmits power supplied from the power module 313 to the induction flight body under the control of the interlocking module 316, and ignites the thermocouple of the induction flight body to assist in launching the induction flight body.

The elevation angle adjusting device 330 is a device for adjusting the elevation angle of the launching platform 320 in the vertical direction and is automatically driven by a motor so as to minimize the flying distance of the flying object in order to effectively remove the target. The high angle adjusting device 330 is controlled by the high angle driving module 315, and the elevation angle can be adjusted from 0 to 89.5 degrees. Of course, the high angle adjusting device 330 may further include a rotation driver and be rotatable 360 degrees in the horizontal direction.

The launch device 300 can rotate in the direction of the target even if it is installed in a direction different from the direction of the target according to the operation of the high angle adjusting device. In addition, the launch device 300 having the elevation control device 330 can wirelessly adjust the direction of the launch device 300 even when the operator is away from the launch device 300, which is effective in preventing position exposure of the operator.

The power supply module 313 is connected to each of the devices of the launch device, i.e., the communication module 311, the control module 312, the simulation module 314, the elevation drive module 315, the interlocking module 316, And supplies power to the elevation control device 330. In particular, the control module 312 supplies or cuts off the power to the guidance vehicle by a control command.

3 is a diagram illustrating the structure of a launch device 300 according to an embodiment of the present invention.

3 (a) shows the combined state of the controller 310 and the launching platform 320. FIG. The control device 310 is configured as a combination of the respective modules 311 to 316. Each of the modules 311 to 316 of the launch device 300 is physically separated according to functions. The modules 311 to 316 are of a removable type, and any specific module can be easily added or deleted.

Also, a heat sink 317 formed by gear machining for heat dissipation of the modules 311 to 316 can be attached to the side of each of the modules 311 to 316.

The launching platform 320 may comprise a launch tube 321 and a gas outlet 322. The launching platform 320 may be formed of at least one launching tube as a part for fixing the guide body 400. The launching platform 320 is made of a heat resistant metal such as a ceramic alloy, a ceramic coating, or nickel, so that the influence of high heat generated when the guidance flight vehicle 400 is fired can be reduced.

Also, the launch pad outer wall 323 is essentially closed to obtain an effective initial thrust. However, if the heat generated by the launching of the guidance vehicle affects the modules, a plurality of small holes may be formed to allow air inflow. This is to reduce the high temperature of heat generated by the launch vehicle.

Figure 3 (b) shows the front and back of each module of the launch device 300.

Referring to FIG. 3 (b), the module mounts the signal connector 319 and the power connector 318. The signal connector 319 and the power connector 318 are of a mounting connector type that directly engages the connector of the launching base without any additional device. This can simplify disassembly and assembly, and reduce the weight of the launch device.

3C is a view for showing an internal configuration of the launch pad 320. As shown in FIG.

3 (c) shows the inside of the launching platform 320, in which the guide flight vehicle 400 is installed inside the launching pipe 321. In the launch tube 321, a holder 325 for holding an induction body, and a connector 324 for maintaining and releasing an electrical connection with an induction body to be launched within the tube pipe 321 are formed.

The guide body 400 is mounted on a cradle 325 formed inside the launch tube 321 when the cradle 320 is mounted on the launching platform 320 and is connected to the connector 324 to receive a control command of the controller 310. The guided vehicle 400 is powered by the connector 322, and when the thermal battery is ignited by the firing information, the guided vehicle 400 is driven toward the target.

At this time, the gas generated at the time of launching the guided vehicle 400 is discharged through the gas outlet 322 in the same direction as the direction of emission of the guide body 400. The reason why the gas discharge port 332 is directed toward the guidance flight body 400 is to prevent the reaction force from being applied to the bottom of the launching platform 320 so that the induced flight body is not released by the reaction force during the launch. The tube inner wall 326 is made of a heat-resistant material. This is to withstand the high heat of the gas generated by the launch vehicle.

4 is a first diagram illustrating an external configuration of a launch device according to an embodiment of the present invention.

The launch device 300 may include an antenna 340 for wirelessly communicating essential commands such as control of the launch control device 200 with the launch control device 200, launch, stop of launching, and emergency demolition. The antenna 340 is basically a non-directional antenna, and other antennas may be used depending on the frequency of use.

The elevation angle adjusting device 330 is a device for adjusting the direction of the launch device 300 in order to launch the guidance object in the target direction and includes a control device 310 and a launch device 300 for locating the launch device 320 therein And is composed of an upper frame 331, an elevation adjuster 332, a lower frame 333, and a fixed frame 334 mounted on one side of the body.

The upper frame 331 is mounted on one side of the body of the launcher 300 to support the launcher of the launcher. The lower frame 333 is positioned on the ground and serves to fix the launch device.

The fixed frame 334 is connected to the lower frame 333 and serves to further fix the lower frame 333 on the ground. The fixed frame 334 is fixed to the ground by an operator as a form for fixing to the ground. At this time, the operator can use a tool such as a hammer to fix the fixed frame to the ground.

The elevation adjuster 332 is connected to the upper frame 331 and the lower frame 333 to control the angle between the lower frame and the upper frame with reference to the lower frame.

In one embodiment, when the launching device 300 is fixed to the ground by the fixed frame 334 and the lower frame 333, the operator may use the launch control device 300 to fire the guided vehicle with the launch control device 300, And moves to a position a certain distance away. The launch device 300, which receives the guidance vehicle launch information from the mobile operator, controls the elevation controller 332 to adjust the direction of the launcher in accordance with the received launch information and the pre-calculated engagement information.

The launch device 300, which determines the direction of the launch pad by the high angle control device 330, fires the guidance flight object according to the guidance information input from the operator.

5 is a second diagram illustrating an external configuration of a launch device according to an embodiment of the present invention.

Referring to FIG. 5, the launch device 300 of the present invention is a compact form and a bag-shaped launch device 300 that is easy to carry. The launch device 300 may include a wear part composed of a shoulder strap 362 and a back part 361 on one side of the body 350 of the launch device for positioning the control device and the launcher therein. The launching apparatus 300 having the wearer can basically move the operator on his back. When the operator carries the operation device 300 for a long time, the shoulder strap and the back of the operator may be made of a material such as leather or fabric to protect the health of the operator.

The body 350 of the launch device for locating the control device and launcher therein may be made of aluminum or glass reinforced plastic to improve portability. Inside the body 350, a damper damper is attached to the corner to mitigate the impact of the control device and the launching platform.

5, the launch device 300 may further include an upper lid 371 and a lower lid 372 for preventing inflow of water and impact from the outside. The upper lid 371 and the lower lid 372 include sealing and gaskets for waterproof and electromagnetic interference (EMI) shielding in contact with the body 350 of the launch device 300. The upper lid 371 and the lower lid 372 may be fixedly coupled to the body 350 by a compression latch 380.

The compression latch 380 serves to fix the upper cover and the lower cover to the body and then fix it, and the compression latch 380 is basically driven manually but may be automatically driven in the future. When the compression latch 380 is automatically implemented, the launch device can protect the guide body with a cover until the launch, thereby minimizing external influences on the guide body.

6 is a flowchart illustrating a method of launching an induction vehicle according to an embodiment of the present invention.

Referring to FIG. 6, the UAV 100 mounts a reconnaissance camera to acquire image information including a position, a size, and a motion of the target (S601), and transmits the acquired image information to the launch control equipment (S603)

The launch control device 200 receives the image information from the UAV 100 and transmits the received image information to the launch device (S605)

The launch device 300 calculates the engagement information for the target using the received image information. (S607) At this time, the launch device 300 is operated at an arbitrary point to fire the guidance vehicle by the operator in accordance with the engagement information (S609)

The launch device 300 transmits the calculated engagement information to the launch control device (S611)

The launch control device 200 generates launch information for launching an induction vehicle based on the image information and the engagement information at a position separated by a certain distance from the launch device 300 (S613) And transmits the firing information to the launch device 300. (S617)

The launch device 300 receives the launch information and controls the elevation control device according to the engagement information and the launch information to change the direction of the launching platform toward the target and launch the guided vehicle (S619)

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
310: Control device
311: Communication module 312: Control module
313: Power module 314: Simulation module
315: high angle drive module 316: interlocking module
320: Launcher
330: High angle adjustment device

Claims (5)

The launch control device receiving image information including the location, size, and movement of the target from the unmanned aerial vehicle;
Generating launch information for launching the guidance vehicle guided to the target on the basis of the engagement information including information related to the engagement plan for the target calculated from the received image information of the launch control device; And
Launching the guidance vehicle according to the engagement information and the launch information provided from the launch control device;
Wherein the generating step transmits the launch information to the launch device at a position spaced apart from the launch device by a predetermined distance,
Wherein the generating of the launch information comprises: when the launch device receives the image information from the launch control device, transmitting the engagement information generated using the received image information to the launch control device, When the launching information is generated based on the engagement information, the guidance information is fired on the basis of the provided launch information and the created engagement information. How to operate. delete Generating engagement information including information related to an engagement plan for the target using image information including the position, size, and movement of the target provided from the launch control device;
Transmitting the generated engagement information to the launch control device; And
Controlling firing of the guided vehicle mounted on the launching base according to the firing information and the generated firing information when receiving firing information for firing a flying body guided to the target from the firing control equipment;
Wherein the step of controlling the launching of the guidance vehicle comprises the steps of: when receiving the image information from the launch control device, transmitting the engagement information generated using the received image information to the launch control device; And the launch vehicle is fired on the basis of the launch information and the generated engage information when the launch information generated based on the engage information is received from the control equipment. How to operate the device. 4. The method of claim 3, wherein the step of controlling the launch of the guidance vehicle
Wherein the control unit controls the launching unit to rotate in the direction of the target according to the launch information and the generated engagement information when the launch control unit receives the launch information for launching the airplane guided to the target,
And the guidance flight body is ignited to fire the guidance flight body toward the target, and the method for operating the portable launching apparatus for the guidance flight vehicle launching system. 4. The method according to claim 1 or 3,
Coordinate information including coordinates indicating a position of the target; And
Estimated time information for estimating a time required until the guidance vehicle arrives at the target located in the coordinate information;
Wherein the control unit is configured to control the operation of the portable launch device.

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