KR101667597B1 - Chasing and decoying simulation apparatus between aircraft with flare and seeker and method thereof - Google Patents

Abstract

The present invention provides a simulated aircraft having a first IR lamp representative of an aircraft operating according to a simulation scenario and indicative of the flame characteristics of the actual exhaust of the aircraft and a second IR lamp indicative of the characteristics of the flare fired by the aircraft An IR searcher that recognizes one of the simulated aircraft and the simulated flare as a target based on the optical characteristics of the first and second IR lamps according to a predetermined determination method, A lamp for controlling the illuminance of the first IR lamp and the second IR lamp by predicting the amount of infrared rays generated by the flame of the aircraft exhaust and the flare viewed from the searcher according to the locus of the flare, Tracking-deception simulation between a flare-based aircraft and a navigator including a control unit Device.

Description

≪ Desc / Clms Page number 1 > CHARACTER AND DECOYING SIMULATION APPARATUS BETWEEN AIRCRAFT WITH FLARE AND SEEKER AND METHOD THEREOF Between Flare Based Aircraft &

The present invention relates to an apparatus and method for tracking / deception simulation related to electronic warfare, and more particularly, to a simulation apparatus and method for simulating tracking / deception success between an aircraft of a specific specification and a flare and a searcher And methods.

Flare is widely used as aircraft survival equipment to fire guided missiles equipped with an infrared seeker (IR Seeker) to detect aircraft flames.

In the modern war, the ability to perform electronic warfare is the power that determines the victory and defeat of the war. The results of the various wars that erupted in the latter half of the twentieth century and the first half of the twenty - first century showed the importance of electronic warfare capability.

As the days go by, the latest aircraft have been equipped with more precise and complex electronic warfare capabilities, but the price of the latest aircraft has reached dozens of times that of conventional aircraft, and it is not easy to buy unless it is economically powerful.

If such an expensive aircraft were to be shot down by a low-cost missile, this would result in enormous losses both on the power side and on the economic side.

As a result, the development of aviation survival equipment capable of protecting expensive aircraft on one side has been actively developed, and on the other side, various weapons capable of tracking down the aircraft to the end have been actively developed. Although new windows and shields are being developed in this way, it is difficult to confirm if the window can actually penetrate the shield or block the window with a shield, unless actual combat situations occur.

Korean Patent No. 10-1188768 discloses a " three-dimensional helicopter posture simulator for verifying the performance of aviation survival equipment and its method ", and specifically, a helicopter is a helicopter A simulator technology has been proposed for verifying whether the execution of the chaff / flare response is successfully performed by analyzing the threat information according to the startup situation. This simulator technology is a three-dimensional helicopter posture simulator technology proposed for various flight attitude tests in place of a constrained practical flight environment, and has a limitation that can not provide a solution to verify whether the helicopter is actually protected from the guided missile .

Thus, every time a new weapon is developed, the aircraft and guided missile explorer (s) capable of verifying whether allied aircraft can be protected from enemy guided missiles or allied guided missiles capable of shooting enemy aircraft seeker) needs to be supplemented.

Therefore, it is urgent to develop a simulator that can predict the success of tracking - deception by easily applying the specifications and algorithm of the new weapon system.

It is an object of the present invention to provide a simulation apparatus and method that can verify mutual performance between an aircraft, a flare, and an infrared ray explorer by simulating whether an infrared ray searcher of a guided missile can be deceived through a flare.

A track-debit simulation apparatus between a flare-based aircraft and an explorer according to an embodiment of the present invention for realizing the above-mentioned problems is characterized in that it is an apparatus for representing an aircraft operating according to a simulation scenario, 1 simulated aircraft with an IR lamp; A simulated flare having a second IR lamp indicative of a characteristic of a flare fired by the aircraft; An IR searcher that recognizes one of the simulated aircraft and the simulated flare as a target based on the optical characteristics of the first and second IR lamps according to a predetermined determination method; And estimating an amount of infrared rays generated by the flame of the aircraft exhaust and the flare viewed from the searcher according to the locus of the aircraft and the flare and the accessibility of the searcher according to the simulation scenario, And a lamp controller for controlling the illuminance of the second IR lamp.

According to one embodiment related to the present invention, the simulated aircraft includes a light output port; And a diaphragm configured to adjust an open area of the light output port to adjust an amount of light emitted from the first IR lamp through the light output port.

According to another embodiment of the present invention, the simulated flare includes a light output port; And a diaphragm configured to adjust an open area of the light output port to adjust an amount of light emitted from the second IR lamp through the light output port.

According to another embodiment of the present invention, the lamp control unit further includes a power supply unit for supplying power to the first IR lamp and the second IR lamp, So as to control the illuminance.

According to another embodiment of the present invention, a tracking-debit simulation apparatus between a flare-based aircraft and a searcher is configured to detect a trajectory in space of the aircraft and the flare moving according to the simulation scenario, A search-view calculation unit for converting the search result into a trajectory of an image; And a motion control unit for controlling the motion of the simulated aircraft and the simulated flare based on a locus on the two-dimensional plane.

The present invention also relates to a method of operating a simulator, comprising: separating and moving a simulated aircraft and a simulated flare according to a simulation scenario; Controlling the illuminance of the first IR lamp of the simulated aircraft and the second IR lamp of the simulated flare based on the position and specification of the simulated aircraft and the simulated flare and the tracking access of the explorer; And the searcher selecting and tracking one of the simulated aircraft and the simulated flare as a target based on the illuminance of the first and second IR lamps, and initiating a tracking-debit simulation method between the flare-based aircraft and the navigator do.

According to one example related to the present invention, the step of separating and moving the simulated aircraft and the simulated flare to implement relative positions when the explorer sees the simulated aircraft and the simulated flare on simulation, The simulated flare is moved on a two-dimensional plane, and a relative position of the searcher with movement and approach is controlled by controlling the illuminance of the first and second IR lamps.

According to the present invention, the superiority between a specific specification aircraft, flare, and IR searcher can be briefly confirmed through simulation. If the present invention is actively applied to the development of a new weapon system, a solution that can easily solve technical problems of a friendly weapon system can be provided.

BRIEF DESCRIPTION OF THE DRAWINGS Figure 1 is a schematic block diagram of a flare-based aircraft-seeker interrogator tracking-devise simulator in accordance with an embodiment of the present invention.
FIG. 2 is a conceptual diagram showing an example of a simulated object provided to facilitate control of the amount of light that can replace the simulated aircraft and / or simulated flare shown in FIG. 1. FIG.
FIGS. 3 and 4 are conceptual diagrams for explaining an algorithm for mapping the coordinates of the aircraft and the flare in the three-dimensional space to the coordinates of the two-dimensional plane on the basis of the time when the explorer views the aircraft and the flare.
FIG. 5 is a flowchart illustrating a method of operating a tracking-debit simulation apparatus between a flare-based aircraft and a searcher in accordance with an embodiment of the present invention.

Hereinafter, an apparatus and method for tracking-debit simulation between a flare-based aircraft and a searcher according to the present invention will be described in detail with reference to the drawings.

As used herein, the singular forms "a", "an" and "the" include plural referents unless the context clearly dictates otherwise.

It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory and are intended to provide further explanation of the invention as claimed. , ≪ / RTI > equivalents, and alternatives.

FIG. 1 is a schematic block diagram of a flare-based aircraft-seeker-to-seeker-trace-simulator apparatus in accordance with an embodiment of the present invention.

1, a simulation apparatus according to an embodiment of the present invention includes a simulation controller 10, a simulated aircraft 20, a simulated flare 30, a searcher 40, a search-view calculator 50, A control unit 60 and a lamp control unit 70.

The simulation control unit 10 inputs and receives specifications of a simulation scenario and / or an aircraft, a searcher 40, a flare and the like from a user, and performs simulation according to the set scenarios and characteristics of the weapon system. The simulation control unit 10 may be implemented as a server (or PC) and a simulation program that perform overall simulation.

The simulated aircraft 20 is representative of an aircraft operating according to a simulation scenario, and may be installed in an actual simulator. The simulated aircraft 20 can be controlled to move in accordance with the scenario by matching the three-dimensional aircraft operation to the two-dimensional space. The simulated aircraft 20 may have its position fixed according to simulation modeling.

The simulated aircraft 20 may be provided with a first IR lamp that exhibits characteristic flame characteristics of the aircraft. In addition, the simulated aircraft 20 may optionally include a diaphragm, a power supply, or the like that can control the amount of infrared radiation being emitted.

The simulated flare 30 is for simulating the flare fired by the aircraft on the simulation, and may include a second IR lamp indicative of the flame characteristics of the flare. In addition, the simulated flare 30 may optionally include a diaphragm, a power supply, or the like that can control the amount of infrared rays radiated during movement according to a predetermined specification.

The simulation scenario determines the environment in which the flare 30 is radiated, the specification of the aircraft, the initial velocity, the propulsive acceleration, and the like. Therefore, the moving speed of the flare 30 is determined according to the initial speed of the aircraft, the propulsive acceleration, the air resistance at the free fall, the specification of the flare, etc., and the characteristics of the flame are different depending on the simulation scenario, the specifications of the flare 30,

The flame characteristics of the aircraft and / or the flare may be controlled by the illumination control of the first IR lamp and the second IR lamp. For example, the illumination control of the first IR lamp may be implemented by controlling the amount of power supplied to the first IR lamp, the amount of light emitted from the first IR lamp, and the like. The flame characteristics of such an aircraft and / or flare should be controlled such that the amount of light received by the searcher 40 may vary as the relative distance to the searcher 40 varies, as will be described later.

FIG. 2 is a conceptual diagram showing an example of a simulated object which is provided to facilitate control of the amount of light that can replace the simulated aircraft 20 and / or the simulated flare 30 shown in FIG. The simulated body may be applied to the simulated aircraft 20 and / or the simulated flare 30 and the shape and detailed structure thereof may be suitably changed according to the characteristics of the simulated aircraft 20 and / or the simulated flare 30 have.

Referring to FIG. 2, the simulator has a form in which an IR lamp 81 is provided inside the housing 80. The infrared ray output from the IR lamp is emitted through a light output port formed in the housing 80. The light output port is provided with a diaphragm 82 configured to adjust the open area of the light output port, .

In this simulated apparatus in which the shape of the simulated aircraft 20 and the simulated flare 30 are not important, the aircraft and the flare can be replaced by a simulator capable of controlling the amount of light.

Referring again to FIG. 1, the searcher 40 may be implemented with an actual searcher to be simulated or a simulated searcher corresponding thereto. The searcher 40 may be implemented as a searcher installed on a surface-to-air IR guided vehicle, for example, or may be implemented by reconstructing a searcher of the same specification. In accordance with the simulation scenario, one of the simulated aircraft 20 and the simulated flare 30 As a target.

The search-view calculation unit 50 maps the aircraft moving in the three-dimensional space and the flare on the two-dimensional plane corresponding to the view viewed from the navigator 40 in motion in the simulation scenario, thereby simulating the motion in the three- Into a simple motion that is easy to simulate within the allowed space.

The ultimate goal of the simulation is to verify whether the navigator 40 continues to track the aircraft or if it is deceived by the flare and stops tracking the aircraft. The above-described verification can be performed more easily by converting the motion of the aircraft and the flare in the space by the search-view calculation unit 50 into a planar view that is viewed from the searcher 40.

The mapping algorithm of the search-view calculating unit 50 will be described in more detail with reference to FIG. 3 and FIG.

3 and 4 are conceptual diagrams for explaining an algorithm for mapping the coordinates of the aircraft and the flare in the three-dimensional space to the two-dimensional plane coordinates based on the point of time when the searcher 40 views the aircraft and the flare.

Referring to FIG. 3, the aircraft, flare, and searcher 40 are located at A, F, and M, respectively, and the distance between the navigator 40 and the aircraft is d.

When selecting the origin as an arbitrary point on the 3D spatial coordinate, the coordinates of the plane and the flare can be determined. As shown, the coordinates of the plane can be expressed as (Ax, Ay, Az) and the coordinates of the flare can be expressed as (Fx, Fy, Fz).

In order to obtain the coordinates of the plane and flare converted into the two-dimensional virtual coordinate system to be newly constructed, the origin of the two-dimensional virtual coordinate system is defined.

First, let A 'be the intersection point when the aircraft is orthogonally projected on the plane for an arbitrary plane (Y = Fy) having the same height as the flare, and the coordinates of A' become (Ax, Fy, Az).

Next, a straight line extending from the position (M) to A 'of the searcher 40 is extended to obtain a straight line. Here, crossing points O 'are obtained by passing a straight line orthogonal to the straight line passing through the position A of the aircraft.

The intersection O 'is defined as the origin of the two-dimensional virtual coordinate system to be sought.

A straight line connecting the position A of the aircraft from the origin O 'of the two-dimensional virtual coordinate system constitutes the first axis Y' of the virtual coordinate system. A straight line connecting the origin O 'of the two-dimensional virtual coordinate system from the position M of the searcher 40 and a straight line passing through the origin O' of the virtual coordinate system orthogonal to the first axis Y ' , A straight line intersecting the straight line connecting the position (M) of the searcher (40) and the flare position (F) constitutes the second axis (X ') of the virtual coordinate system.

The virtual coordinate system is a planar coordinate system composed of X'-Y 'axes, and may be referred to as a planar coordinate system viewed from the viewpoint of the searcher 40.

The simulation scenario suggests the flight path of the aircraft, the travel path of the flare, the simulation environment (e.g., wind, air resistance, etc.), and the access location of the navigator 40. Accordingly, the distance d of the aircraft from the searcher 40, the angle? Formed by the aircraft and the origin O 'of the two-dimensional virtual coordinate system about the searcher 40, the flare F ) And the origin O 'of the two-dimensional virtual coordinate system can be determined after the origin O' is determined.

Accordingly, the coordinates of the aircraft on the two-dimensional virtual coordinate system become (0, y '), the coordinates of the flare become (x', 0), and x 'and y' are determined as follows.

The 2D virtual coordinate system can actually be seen when the aircraft is flying over the sky, and this coordinate system can be reduced to the actual simulator space.

Referring to FIG. 4, a tetrahedron constituted by O'AF'M has a proportional relation with a tetrahedron constituted by O "A'F" M, and thus the virtual coordinate system (X'-Y ') corresponds to a simulation coordinate system X "-Y"). The origin (O ') of the virtual coordinate system corresponds to the origin (O') of the simulation coordinate system and the coordinates (0, y ') of the aircraft are the coordinates (0, y ") of the simulated aircraft 20, x ', 0) can be converted to the coordinates (x ", 0) of the simulated flare 30.

Here, the x ", y" coordinates can be determined using the proportional relation and the trigonometric function as follows.

Where d is defined as the distance between the navigator 40 and the aircraft and l is defined as the distance between the navigator 40 and the mock aircraft 20.

Equations (3) and (4) provide very interesting results when the distance between the searcher 40 and the simulated aircraft 20 is fixed. That is, the positions of the simulated aircraft 20 and the simulated flare 30 are determined by the viewing angle viewed from the searcher 40. This is because the simulated aircraft 20 and the simulated aircraft 20 are moved to a virtual coordinate system having a constant distance around the searcher 40 This means that the simulated flare 30 moves.

As described above, it is possible to control the motion of the flare by converting the motion in the three-dimensional space into the motion on the two-dimensional plane viewed from the searcher 40. However, since it is also possible to estimate and control the copper lines of the flare in order to simplify the simulation, the technical idea of the present invention is not limited to the coordinate transformation algorithm as in the above expression.

Referring again to FIG. 1, the motion controller 60 implements a change in view, that is, a two-dimensional motion, viewed from the searcher 40, and is a two-dimensional plane And controls the continuous motion by moving the simulated aircraft 20 and the simulated flare 30 to positions on the plane. The motion control unit 60 may include a two-axis motor for two-dimensionally moving the simulated aircraft 20 and the simulated flare 30, and an inverter for driving the two-axis motor.

The lamp control unit 70 predicts the amount of infrared rays generated by the flame and the flare of the aircraft exhaust viewed from the searcher 40 according to the trajectory of the aircraft and the flare and the accessibility of the searcher 40 according to the simulation scenario, The first IR lamp provided in the first flare unit 20 and the second IR lamp provided in the simulated flare unit 30 are controlled.

A power supply unit (not shown) for controlling the amount of power supplied to the first IR lamp and / or the second IR lamp may be further included for controlling the illuminance of the first IR lamp and / or the second IR lamp. Alternatively, the simulated aircraft 20 and / or the simulated flare 30 may further include a diaphragm 82 (see FIG. 2) for controlling the amount of light generated in the first IR lamp and / or the second IR lamp.

The lamp controller 70 controls the power supply amount of the power supply unit or the diaphragm value of the diaphragm, thereby realizing a quantity of light that can be perceived at the time of the searcher 40.

5 is a flowchart illustrating a method of operating a tracking-debit simulation apparatus between a flare-based aircraft and the searcher 40 according to an embodiment of the present invention.

5, first, the simulation control unit 10 sets a simulation scenario, a specification of a weapon system, and a natural environment characteristic (S1), and controls the flight of the aircraft and the aircraft signal according to the simulation scenario S2).

In a scenario in which the aircraft encounters the searcher 40, the searcher 40 tracks the aircraft signal according to a predetermined specification (S3).

Next, according to a preset specification, the aircraft recognizes the tracking of the searcher 40 and flares the flare (S4).

The search-view calculator 50 converts the coordinates of the aircraft and the flare in the three-dimensional space into two-dimensional plane coordinates based on the viewpoint of the searcher 40 looking at the aircraft and the flare (S5). At this time, the two-dimensional plane coordinates can be reduced to the level that can be performed in the simulator, that is, the simulation coordinate system level as described above.

Next, the motion controller 60 controls the motion of the simulated aircraft 20 representing the aircraft and / or the simulated flare 30 representing the flare based on the two-dimensional plane coordinates (S6).

At this time, the lamp control unit 70 determines whether or not the first (first) and second (second) lamps of the simulated airplane 20 viewed from the explorer 40, considering the approach position of the explorer 40, the specifications such as the combustion characteristics of the aircraft and the flare, The illuminance of the second IR lamp of the IR lamp and the simulated flare 30 is predicted and controlled (S7).

The searcher 40 senses the infrared of the first IR lamp and the second IR lamp according to a predetermined specification, i.e., a determination algorithm, and selects one of the simulated aircraft 20 and the simulated flare 30 as a target, It is evaluated whether the searcher 40 succeeded in tracking or whether the aircraft succeeded in deceiving the searcher 40 (S8).

It will be apparent to those skilled in the art that the present invention may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. Accordingly, the foregoing detailed description should not be construed in a limiting sense in all respects, but should be considered as illustrative. The scope of the present invention should be determined by rational interpretation of the appended claims, and all changes within the scope of equivalents of the present invention are included in the scope of the present invention.

Claims (7)

A simulated aircraft representative of an aircraft operating according to the simulation scenario and having a first IR lamp representative of the flame characteristics of the actual exhaust of the aircraft;
A simulated flare having a second IR lamp indicative of a characteristic of a flare fired by the aircraft;
A searcher for recognizing one of the simulated aircraft and the simulated flare as a target based on optical characteristics of the first and second IR lamps according to a predetermined determination method;
Estimating the amount of infrared rays generated by the flame of the aircraft exhaust and the flare viewed from the searcher according to the trajectory of the aircraft and the flare and the accessibility of the searcher according to the simulation scenario, A lamp controller for controlling the illuminance of the second IR lamp;
A search-view calculator for converting a trajectory in space of the aircraft and the flare moving according to the simulation scenario into a locus on a two-dimensional plane viewed by the searcher; And
And a motion controller for controlling the motion of the simulated aircraft and the simulated flare based on the trajectory on the two-dimensional plane. The method according to claim 1,
The simulated aircraft,
Light output port; And
Further comprising a diaphragm configured to adjust an open area of the light output port to adjust an amount of light emitted from the first IR lamp through the light output port. - Deceptive simulation device. The method according to claim 1,
In the simulated flare,
Light output port; And
Further comprising a diaphragm configured to adjust an open area of the light output port to adjust an amount of light emitted from the second IR lamp through the light output port. - Deceptive simulation device. The method according to claim 1,
Further comprising a power supply for supplying power to the first IR lamp and the second IR lamp,
Wherein the lamp control unit is configured to control the illuminance by adjusting the magnitude of power supplied to the first and second IR lamps in the power supply unit. delete Separating the simulated aircraft and the simulated flare according to the simulation scenario;
Controlling the illuminance of the first IR lamp of the simulated aircraft and the second IR lamp of the simulated flare based on the position and specification of the simulated aircraft and the simulated flare and the tracking access of the explorer; And
The searcher selecting and tracking one of the simulated aircraft and the simulated flare as a target based on the illuminance of the first and second IR lamps,
In order to simulate the relative position of the navigator when viewing the simulated aircraft and the simulated flare,
Wherein separating and moving the simulated aircraft and the simulated flare comprises moving the simulated aircraft and the simulated flare on a two-
Wherein the relative position of the searcher with respect to movement and access is implemented by controlling the illuminance of the first and second IR lamps. delete

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