Patent ID: 12235081

DETAILED DESCRIPTION OF EXEMPLARY EMBODIMENTS

Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings. Various advantages and features of the present invention and methods accomplishing the same will become apparent from the following detailed description of embodiments with reference to the accompanying drawings. However, the present invention is not limited to embodiments to be disclosed below, but may be implemented in various different forms, these embodiments will be provided only in order to make the present invention complete and allow one of ordinary skill in the art to which the present invention pertains to completely recognize the scope of the present invention, and the present invention will be defined by the scope of the claims. Throughout the specification, the same components will be denoted by the same reference numerals.

Unless defined otherwise, all the terms, including technical and scientific terms, used herein have the same meaning as meanings commonly understood by one of ordinary skill in the art to which the present invention pertains. In addition, the terms defined in generally used dictionaries are not ideally or excessively interpreted unless they are specifically defined clearly. As used herein, the terms are for describing embodiments rather than limiting the present invention. Unless explicitly described to the contrary, a singular form includes a plural form in the present specification.

Hereinafter, in this specification, a laser device for aircraft defense may be referred to as a laser device or a laser scanner.

FIG.1is an exemplary diagram of a laser device for aircraft defense according to an embodiment of the present invention.

Referring toFIG.1, the laser device may include a laser oscillator32, a beam transmission optical system40, and a rotating mirror unit20.

The laser oscillator32according to an embodiment of the present invention may generate a high-power beam for destroying an object, for example, aircraft such as a drone.

According to an embodiment, the laser oscillator32may generate a laser beam irradiation surface44having an energy density equal to or greater than a preset threshold in a laser beam irradiation area45ofFIG.1.

In another embodiment, the laser oscillator32may generate a beam of output for at least disabling an optical sensor of the drone. When the optical sensor is disabling, the drone loses controllability. In addition, when a motor or a propeller is destroyed, the power of the drone is lost, so the flight capability of the drone is lost.

In another embodiment, the laser oscillator32may generate a beam of output for scanning drone's emergence, a drone's flight direction, a drone's flight speed, etc., in a predetermined area.

The beam transmission optical system40according to an embodiment may be an infinite focus optical system.

The beam transmission optical system40according to another embodiment may be a condensing optical system.

Alternatively, according to an embodiment of the present invention, the beam transmission optical system40may include an optical system in which an infinite focus optical system and a condensing optical system are combined in a composite manner.

The infinite focus optical system and the condensing optical system may each be a reflective mirror or a transmissive lens.

The rotating mirror unit20may be, for example, a polygonal mirror, but the embodiment of the present invention is not limited thereto.

Referring toFIG.1, a laser beam16generated by the laser oscillator32is transmitted to the rotating mirror unit20through the beam transmission optical system40.

In this case, the rotating mirror unit20rotates at high speed around a rotation axis and performs x-axis scanning on a focal length of the rotating mirror unit20.

According to an embodiment of the present invention, the rotating mirror unit20generates a reflection angle34of a mirror surface by performing a tilting or reciprocating rotational movement of the rotation axis, and the y-axis scanning may be performed on the focal length of the rotating mirror unit20by this reflection angle34.

For example, when the beam transmission optical system40is the infinite focus optical system or the condensing optical system, the laser beam16of the laser oscillator32is transmitted to the rotating mirror unit20and the focus of the beam changes to infinity or is condensed at a required location.

Next, the transmitted laser beam16may be scanned along the x-axis and y-axis by the rotating mirror unit20.

As described above, by the x-axis scanning and y-axis scanning of the rotating mirror unit20, a laser beam irradiation surface44may be generated on the focal length of the laser beam16from the rotating mirror unit20.

The laser beam irradiation surface44may be, for example, a virtual surface of laser energy limit required for destroying or disabling aircraft.

For convenience of description, the laser beam irradiation surface44ofFIG.1is depicted as a two-dimensional plane, and in reality, there is an area having a similar concentration and may have a predetermined thickness.

That is, in this specification, the location where the focus of the laser beam is formed has the highest energy and the best destruction efficiency for the aircraft, which is expressed as ‘laser irradiation surface44’ for convenience. In reality, however, the location is an area having a predetermined thickness, not a surface.

According to an embodiment, the laser beam irradiation area45may be a three-dimensional space from a launching point of the mirror surface of the laser device or the rotating mirror unit20to the laser beam irradiation surface44, and may be a square pyramid-shaped space as illustrated inFIG.1.

The entire area of the laser beam irradiation area45is an effective range for hitting aircraft, and is a space where aircraft located on the laser beam irradiation area45may be hit with the laser beam16.

Although not illustrated, the laser device may include a controller that controls the overall operation of each component of the laser device and controls to generate the laser beam irradiation area45. Meanwhile, according to an embodiment of the present invention, the rotating mirror unit20and the laser oscillator32may be combined in plural numbers. When the number of laser oscillators32is plural, the laser oscillators32may be arranged vertically, but the embodiment of the present invention is not limited thereto.

FIG.2is an exemplary diagram illustrating an example of one-axis scanning of the laser device for aircraft defense ofFIG.1.FIG.2is an example of the simplest configuration of the laser device ofFIG.1, and is an example of a one-dimensional scan configuration in which the laser beam16is irradiated only in one axis, x-axis, direction.

Referring toFIG.2, the laser beam16may be output by the laser oscillator32and transmitted to the rotating mirror unit20through the beam transmission optical system40. In this case, the rotating mirror unit20rotates and performs the one-axis, x-axis, scan by reflecting and scanning the laser beam16.

FIG.2is an example of a case where the laser device ofFIG.1does not tilt the rotating mirror unit20, and when the rotation axis of the rotating mirror unit20is tilted in a reciprocating rotational movement manner, the laser device generates the reflection angle34of the mirror surface of the rotating mirror unit20as illustrated inFIG.1.

FIG.3is an exemplary diagram showing an example of scanning using a condensing optical system to the laser device for aircraft defense ofFIG.1.

Referring toFIG.3, the laser device performs the one-axis, x-axis, scan, and irradiates the laser beam in a straight line300in a direction of an arrow from the left to the right.

In this case, the tilting of the rotating mirror unit20generates a plurality of arrow straight lines in a y-axis direction that is horizontal to an arrow straight line300by the reflection angle34of the mirror surface, so a predetermined laser beam irradiation surface is generated.

The arrow straight line300constituting the laser beam irradiation surface is expressed as the straight line300for convenience, but may be an area having a thickness301with a similar concentration located at the focal length of the laser beam16of the laser device.

InFIG.3, the laser beam irradiation surface at a location where the energy density of the laser beam16is high and the destruction efficiency is high is illustrated as an example.

FIGS.4A to4Care exemplary diagrams illustrating an example of generating the laser beam irradiation area of the laser device for aircraft defense ofFIG.1.

InFIG.4A, the laser oscillator32generates a high-power beam.

The rotating mirror unit20performs the x-axis scanning through the rotational movement, and performs the y-axis scanning by vertical movement, that is, reciprocating tilting of the rotation axis of the rotating mirror unit20. InFIG.4A, the high-power beam of the laser oscillator32may be made into a three-dimensional space in the shape of a square pyramid. The space within the square pyramid shape45corresponds to an effective range at which a drone is destroyed. In particular, the destruction effect may further increase when an infinite optical system is used.

The configuration ofFIG.4Ais advantageous in that it is easy to use an optical system with excellent heat durability due to the nature of the weapon, and thus, it is easy to use a very high output. In addition, since the y-axis scanning is slow, the time for the fast x-axis scanning to be repeatedly irradiated to a target increases, and thus, the energy concentration on the same axis is high, so it is easy to use as a weapon for the purpose of destruction.

FIG.4Bis an example of the laser device that performs the y-axis scanning by tilting the reflection optical system51, unlike the embodiment ofFIG.4Ain which the y-axis scanning is performed by tilting the rotating mirror unit20.

The laser beam16is output by the laser oscillator32, and the laser beam16transmitted by the beam transmission optical system40is transmitted to the rotating mirror unit20through the reflection optical system51.

The rotating mirror unit16performs the x-axis scanning. In this case, the laser beam16is irradiated back and forth along the y-axis on the mirror surface of the rotating mirror unit20by tilting the reflection optical system51, thereby performing the y-axis scanning on the focal length in the air.

The configuration ofFIG.4Bmay adjust the tilting angle of the reflection optical system51while having a moderately fast y-axis scanning speed, making it easy to control the size of the surface on which the laser beam is irradiated. Also, considering the agile operation and control convenience, it is advantageous to configure the reflection optical system51to be small. In this case, however, the reflection optical system51has disadvantages for high power and long-term use.

FIG.4Cis an example of the laser device that performs the y-axis scanning by tilting the second rotating mirror unit52, unlike the embodiment ofFIG.4Bin which the y-axis scanning is performed by tilting the reflection optical system51. The rotating mirror unit20may be referred to as the first rotating mirror unit to distinguish it from the second rotating mirror unit52.

Referring toFIG.4C, the second rotating mirror unit52performs the y-axis scanning, and the first rotating mirror unit20performs the x-axis scanning.

Depending on the arrangement of the two rotating mirror units, the x-axis scanning may be performed before the y-axis scanning, and the angles of the two scanning directions may be configured as any angle other than 90°.

When using the plurality of rotating mirror units52and20as illustrated inFIG.4C, the rotating mirror units52and20have advantages in that it has good high-power response and a very fast scanning speed. However, the rotating mirror units52and20are more useful as a detector that quickly scans a wide area to identify a location of an enemy's weapon rather than for the purpose of destruction.

FIG.5is an exemplary diagram of the laser device for aircraft defense to which a plurality of laser oscillators is applied according to another embodiment of the present invention.

Referring toFIG.5, the laser device includes the plurality of laser oscillators32and the rotating mirror unit20.

The laser oscillator32may include the plurality of laser oscillators. For example, the laser oscillator32may include a first laser oscillator and a second laser oscillator.

A first laser beam output by the first laser oscillator may be transmitted to the rotating mirror unit20as a first reflection beam through a beam transmission optical system.

In addition, a second laser beam output by the second laser oscillator may be transmitted to the rotating mirror unit as a second reflection beam that is horizontal to the first reflection beam through the beam transmission optical system.

The beam transmission optical system between the plurality of laser oscillators32and the rotating mirror unit20may include an infinite focus optical system or a condensing optical system.

According to another embodiment, instead of the plurality of laser oscillators32, a single laser oscillator may be used, and a splitter capable of splitting a beam may be used at the rear end of the infinite focus optical system or the condensing optical system to split the beam into multiple laser beams and incident on the rotating mirror unit2.

According to another embodiment of the present invention, as illustrated inFIG.4, the laser beam may also be directly transmitted from the laser oscillator32to the rotating mirror unit20without the beam transmission optical system. The rotating mirror unit20reflects the first laser beam and the second laser beam.

In particular, inFIG.5, a laser beam irradiation surface46including a first scanning surface generated by performing the x-axis and y-axis scanning based on the first reflected beam from which the first laser beam is reflected, and a second scanning surface generated by performing the x-axis and y-axis scanning based on the second reflected beam from which the second laser beam is reflected is illustrated as an example.

FIG.6is an exemplary diagram of the laser device for aircraft defense to which a variable focus optical system is applied according to another embodiment of the present invention.

In particular,FIG.6is an example of the laser device that uses the variable focus optical system instead of the infinite focus optical system or the condensing optical system to increase the efficiency of disabling a target whose location can be determined by the present invention.

Referring toFIG.6, the laser device may include a radar43, a variable focus optical system40-1, an air pump41, and an operator42. Here, the operator42may calculate a pressure of the air pump and may be included in the controller of the laser device.

The radar43may identify aircraft located between the laser beam irradiation areas.

The laser device may detect a plurality of aircraft, for example, a distance L1or L2with the highest density of a group of drones, by using the radar43for the purpose of detecting the location, and may change a curvature of an optical surface of the variable focus optical system40-1so that a focus is formed on the location L1or L2.

The variable focus optical system40-1is configured to change the curvature of the optical surface by adjusting air pressure inside the mirror. The laser device may calculate a pump pressure of the air pump41and operate the air pump41.

The focal length L1or L2changes by changing the curvature of the mirror surface of the variable focus optical system40-1. The focal length L1or L2is not fixed and is actively variable.

InFIG.6, the controller may calculate the pump pressure of the air pump41and control the operation of the air pump41when the number of aircraft identified by the radar43is less than a preset threshold.

The laser device may change a first focal length to a second focal length by changing the curvature of the mirror surface of the variable focus optical system40-1.

Accordingly, the laser beam irradiation area may be newly generated. InFIG.6, the case where the laser beam irradiation area is a square pyramid is illustrated. In particular, the focal length L1or L2is variable, so the laser beam irradiation surface may be widened or narrowed.

FIG.7is a block diagram of the laser device for aircraft defense according to an embodiment of the present invention.

Referring toFIG.7, the laser beam output by the laser oscillator32is transmitted to a LASER BEAM IRRADIATION AREA GENERATOR420, so the laser beam irradiation surface44is irradiated.

The LASER BEAM IRRADIATION AREA GENERATOR420may generate the laser beam irradiation area in the air based on the laser beam output from the laser oscillator32.

The LASER BEAM IRRADIATION AREA GENERATOR420may include, for example, the infinite focus optical system or the condensing optical system.

In another embodiment, the LASER BEAM IRRADIATION AREA GENERATOR420may include the variable focus optical system.

The LASER BEAM IRRADIATION AREA GENERATOR420may include the rotating mirror unit20. In addition, although not illustrated, the LASER BEAM IRRADIATION AREA GENERATOR420may include at least one of the tilting unit for tilting the rotating mirror unit20and the tilting unit for tilting the reflection optical system included in the beam transmission optical system.

In addition, the LASER BEAM IRRADIATION AREA GENERATOR420may generate the laser beam area45including the laser beam irradiation surface44by the reflection of the rotating mirror unit20.

Meanwhile, the controller100controls the overall operation and function of each component of the laser device. To this end, the controller100may be configured to include one or more processors. The controller100may be configured to include a central processing unit CPU, a micro processor unit MPU, a micro controller unit MCU, or any type of processor well known in the technical field of the present invention. The controller100may also include a memory, for example, a RAM, as a component. In addition, the controller100may store at least one application or program for executing a method according to an embodiment of the present invention.

According to an embodiment of the present invention, the controller100may control a reflection angle of the beam transmission optical system40, a rotation speed of the rotating mirror unit, a tilting angle of the tilting unit, and a beam output of the laser oscillator to adjust a scan angle, a scan length, a scan speed, and a telecentricity error incident on an object of the laser beam.

FIG.8is a flowchart of a method of operating a laser device for aircraft defense ofFIG.7. Each step ofFIG.8is performed by the laser device, and specifically, may be performed by the calculation of the controller of the laser device.

Referring toFIG.8, the laser device outputs the laser beam through the laser oscillator32, S10.

The laser device may transmit the laser beam to the rotating mirror unit20through the beam transmission optical system in S20.

The laser device may generate the laser beam irradiation area including a laser irradiation surface, first irradiation surface, located at the first focal length in the air by reflecting the laser beam through the rotating mirror unit20in S30.

The laser device may determine whether the density of the aircraft within the generated laser beam irradiation area is equal to or greater than a threshold in S40. Accordingly, when the density of the aircraft is equal to or greater than the threshold, the laser device may destroy the aircraft on the laser beam irradiation area generated in the air in S50.

On the other hand, when the density of the aircraft is less than the threshold, the laser device may newly generate a laser beam irradiation area including a laser irradiation surface, second irradiation surface, located at the second focal length in S45.

The determination and/or calculation methods of a controller100according to an embodiment of the present invention described with reference to the accompanying drawings so far may be performed by executing a computer program implemented as a computer-readable code. The computer program may be transmitted from a first computing device to a second computing device through a network such as the Internet, installed in the second computing device, and thus used in the second computing device. Both of the first computing device and the second computing device include a server device, a fixed computing device such as a desktop PC, and a mobile computing device such as a notebook, a smartphone, and a tablet PC.

The embodiments of the present invention have been described hereinabove with reference to the accompanying drawings, but it will be understood by one of ordinary skill in the art to which the present invention pertains that various modifications and alterations may be made without departing from the technical spirit or essential feature of the present invention. Therefore, it is to be understood that the embodiments described hereinabove are illustrative rather than being restrictive in all aspects.