KR101790124B1 - Semi-active aircraft intercept system and method - Google Patents

Abstract

Discloses an anti-active vehicle intercept system and method. The present invention relates to a radar system for radiating a radar signal for detecting a target, for analyzing a received signal reflected by the target and for receiving the radar signal, for determining a position of the target, and for generating a position of the identified target as target position information, And a plurality of front antennas for receiving the target position information by performing communication with the launch control radar, moving to track the target according to the target position information, and receiving the signals reflected from the target as front signals, And at least one rear antenna for directly receiving a radiated signal radiated from the launch control radar as a backward signal, synthesizing a plurality of front signals and a rear signal, downconverting the frequency, and analyzing a plurality of frequency downconverted front signals And a guided weapon to determine the position of the target.

Description

[0001] SEMI-ACTIVE AIRCRAFT INTERCEPT SYSTEM AND METHOD [0002]

FIELD OF THE INVENTION The present invention relates to an aircraft interceptor system and method, and more particularly to an anti-active small vehicle interceptor system and method.

The induction method of guided weapons is classified according to the way in which the explorer mounted on the guided weapon searches for the target. The active guiding method is divided into the active homing method, the semi-active homing method and the passive homing method. .

The passive induction method means that the guided weapon does not emit any signal, it senses the heat or electromagnetic wave emitted from the target, and tracks the target. The active induction method is a method in which the navigator of the guided weapon searches for the target And the target is tracked by receiving the reflected and received signal. The semi-active induction method is a mixture of the active induction method and the manual induction method. In the semi-active induction system, an external device radiates electromagnetic waves of a pre-designated waveform toward the target, and the navigator of the guided weapon does not emit a direct signal as in the manual induction method but analyzes only the signal reflected on the target.

The active induction method is advantageous in that it can identify the target quickly because it radiates a signal for detecting the target directly in the navigator mounted in the guided weapon and traces the target by analyzing the reflected signal. However, , There is a problem in that it is not only high in manufacturing cost but also hinders miniaturization of guided weapons.

On the other hand, the passive induction system is advantageous in that the configuration for radiating signals is unnecessary, and guided weapons can be implemented inexpensively. However, since the target is detected by detecting heat or electromagnetic waves emitted from the target, There is a limit.

Semi-active induction method, like the manual induction method, requires no configuration to emit a signal, which makes it possible to implement guided weapons at low cost as compared with the active induction method, and it is possible to detect and track without any restrictions on the target. Therefore, the demand for semi-active guided weapons is continuously increasing.

However, in the case of conventional semi-active guidance guided weapons, basically it is designed to intercept and detect large air vehicles such as missiles, but does not consider intercepting methods for small air vehicles.

Therefore, if a small airplane such as a small rocket, a mortar, or a small-sized airplane approaches the airplane, a similar plurality of small airplanes are fired to respond to the airplane. However, the accuracy is low and it is not efficient and may cause unnecessary additional damage.

Korean Registered Patent No. 10-0985155 (registered on September 28, 2010)

The object of the present invention is to detect a target using both a signal emitted from a launch control radar and a signal reflected on a target through a plurality of front antennas and at least one rear antenna, System.

Another object of the present invention is to provide an anti-active vehicle interception method for achieving the above object.

According to an aspect of the present invention, there is provided an anti-passive vehicle interception system, comprising: a radar system for radiating a radiation signal for detecting a target, analyzing a received signal reflected from the target, A launch control radar for determining the position of the identified target as target position information; And communication with the launch control radar to receive the target location information and move to track the target in accordance with the target location information, wherein the radar signal receives signals reflected on the target as front signals A plurality of front antennas and at least one rear antenna for directly receiving the radiation signals radiated from the launch control radar as rear signals, synthesizing the plurality of front signals and the rear signals, frequency downconverting, An induction weapon for analyzing a plurality of down-converted forward signals to determine a position of the target; .

A front antenna unit having a plurality of front antennas spaced apart from each other at an equal angle to each other in front of a tubular body of the guided weapon; A rear antenna unit having at least one rear antenna disposed behind the body; A receiver for combining a plurality of the front signals and the rear signals to perform frequency downconversion and converting a plurality of frequency downconverted forward signals into digital signals; Generating a high angle signal and an azimuth angle signal for determining a relative position between the sum signal and the target by combining a plurality of the digital signals according to arrangement positions of the plurality of front antennas, A signal processing unit for discriminating a distance and a relative position from the azimuth signal to the target and generating distance information, altitude aiming error information, and azimuth aiming error information according to the distance and relative position to the discriminated target; A drive and propulsion unit for providing the driving force of the guided weapon and driving the pin to adjust the flying direction of the guided weapon; And an induction control unit for receiving the distance information, the high-altitude aiming error information, and the azimuthal aiming error information and controlling the driving and pushing unit such that the target is located at a line of sight of the guided weapon; And a control unit.

Wherein the receiver comprises: a distributor for receiving and distributing the backward signal; A plurality of synthesizers each receiving the front signal from a corresponding front antenna among the plurality of front antennas and synthesizing the front signal distributed and applied by the distributor and frequency downconverting; A filter unit for filtering the plurality of forward signals frequency downconverted by the plurality of synthesizers to remove noise; And an AD converter for converting each of the plurality of forward signals output from the filter unit into a digital signal; And a control unit.

The front antenna unit may include four front antennas distributed at uniform intervals with respect to the front center of the guided weapon, and the direction of the front antenna is adjusted in response to the control of the signal processing unit.

Wherein the signal processing unit receives the four digital signals corresponding to the four front antennas to generate the sum signal and adds the digital signals corresponding to the two front antennas arranged in the row direction among the four digital signals, And generates two high-angle signals by subtracting the two generated row signals from each other to generate the high-angle signal, wherein the two high-angle signals corresponding to the two front-side antennas arranged in the column direction among the four digital signals And generating the azimuth signal by subtracting the generated two column signals from each other.

Wherein the front antennas are arranged in a predetermined pattern and are grouped in rows; And a plurality of phase shifters for phase-controlling signals applied from the plurality of feed elements in a group unit in response to control of the signal processing unit; Scale antenna module according to the present invention.

And the radiation signal is an FMCW signal of the Ka band.

According to an aspect of the present invention, there is provided an anti-passive air vehicle interception method, wherein a launch control radar emits a radiation signal for detecting a target, and the radiation signal is reflected on the target, Determining a position of the target and generating a position of the identified target as target position information; Guided weapons communicate with the launch control radar and the launch control radar to receive the target location information and move to track the target in accordance with the target location information; Wherein the guided weapon receives as a front signal a signal in which the radiation signal is reflected on the target via a plurality of front antennas and the radiation signal radiated from the launch control radar via at least one rear antenna directly as a back signal Receiving; And synthesizing a plurality of the forward signals and the backward signals to frequency downconvert the plurality of forward signals and analyzing a plurality of the forward signals subjected to frequency downconversion to discriminate the position of the target; .

Accordingly, the anti-passive vehicle intercept system and method of the present invention includes a plurality of antennas disposed at predetermined angular intervals in front of an induction vehicle, and at least one antenna disposed in the rear, Since the FMCW signal is received through a plurality of front antennas and the FMCW signal radiated from the launch control radar is directly received through the rear antenna to obtain the distance and angle information of the target, In addition to being capable of precise navigation, it can precisely intercept small aircraft. Especially, the distance, elevation angle and azimuth position of the target can be precisely detected through a plurality of antennas disposed in front.

1 shows the concept of a semi-active induction method.
2 shows a configuration of an induction weapon according to an embodiment of the present invention.
3 shows a detailed configuration of the front antenna unit of Fig.
Fig. 4 shows a detailed configuration of the receiving unit in Fig.
FIG. 5 is a diagram for explaining a concept of determining the position of a target from a signal applied to the signal processing unit of FIG. 2; FIG.
6 is a view for explaining the operation effect of the anti-passive air vehicle intercept system of the present invention.
FIG. 7 is a view for explaining characteristics of a radiation signal used in the semi-active air vehicle intercept system of the present invention.
8 illustrates an anti-passive air vehicle interception method 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.

BEST MODE FOR CARRYING OUT THE 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 shows the concept of a semi-active induction method.

FIG. 1 is a diagram of a semi-active induction system interfacing system. As a surface-to-air interception system, a ground-based launch control radar (FCR) and a guided weapon (GW) And a launching unit (LC) for launching the GW.

The semi-active induction system emits signals for detecting targets in a launch control radar (FCR), which is provided separately from guided weapons (GW), thus eliminating the need for a configuration to emit signals to guided weapons (GW) The manufacturing cost of guided weapons (GW) is low, and it is advantageous for miniaturization. In addition, the radar device RA that emits a signal can control the intensity of a signal to be received and emit the signal, so that it is possible to intercept a relatively long distance target (TG).

However, semi-active induction weapons do not emit signals themselves, unlike active induction systems, and thus have a disadvantage in that they are slow to identify targets. The induction control unit, which is a control unit of the guided weapon GW, controls the guided weapon GW to move to the anticipated movement position of the target TG through the proportional navigation control method, Perform tracking.

2 shows a configuration of an induction weapon according to an embodiment of the present invention.

2, the guided weapon GW includes a front antenna unit 110, a rear antenna unit 120, a receiving unit 130, a signal processing unit 140, an induction steering unit 150, a driving and propelling unit 160 .

The front antenna unit 110 is configured to detect a reflection signal reflected from the target TG by a radiation signal radiated from the FCR and the conventional guided weapon GW using a semi-active induction system And a front antenna. However, the conventional guided weapon GW has one antenna on the front surface of the guided weapon GW, while the front antenna unit 110 of the present invention has a plurality of (Front) antennas FANT1 to FANT4.

Each of the plurality of front antennas FANT1 to FANT4 is an elliptic wafer-scale antenna module, and may be implemented as a phased shift array antenna. As is known, a phased shift array antenna includes a plurality of feed elements arranged in a predetermined pattern, and each of the plurality of feed elements is divided into a plurality of feed elements by a beam forming technique for adjusting phases of signals applied to each of the plurality of feed elements. It is possible to adjust the direction of the antenna. Therefore, each of the plurality of front antennas FANT1 through FANT4 can be oriented in a direction to sense a signal received in front of the guided weapon GW. The direction of the plurality of front antennas FANT1 to FANT4 may be adjusted according to the control of the signal processing unit 140. [

In principle, the number of front antennas FANT1 to FANT4 is not limited. However, as shown in the front view separately shown in FIG. 2, if the number of front antennas FANT1 to FANT4 is four, Four front antennas (FANT1 to FANT4) are arranged for different quadrants in the quadrature plane. Therefore, the position of the target TG can be very easily confirmed by analyzing the signals received by each of the four front antennas FANT1 through FANT4. Therefore, it is assumed that the front antenna unit 110 includes four front antennas FANT1 through FANT4.

The rear antenna unit 120 is configured to directly detect a radiation signal radiated from the FCR. The rear antenna unit 120 is disposed behind the front antenna unit 110 of the guided weapon GW with at least one rear antenna (RANT). Conventional guided weapons (GW) do not include a configuration for directly sensing radiation signals. However, according to the present invention, the rear antenna unit 120 directly receives a radiation signal and combines the received radiation signal with a signal received from each of a plurality of front antennas FANT1 to FANT4 of the front antenna unit 110, Increase the precision and make it possible to search for small aircraft.

It is preferable that the rear antenna unit 120 is disposed behind the front antenna unit 110 because the radiation signal emitted from the launch control radar FCR is mostly received from the rear of the guided weapon GW, It is not necessary to check the exact position of the launch control radar (FCR), so that only one rear antenna (RANT) may be provided. However, since the position of the target TG can be confirmed more accurately when the guided weapon GW recognizes the position of the launch control radar FCR, the rear antenna unit 120 has a plurality of rear antennas RANT It is possible.

The receiving unit 130 receives a signal transmitted through at least one rear antenna RANT of the plurality of front antennas FANT1 to FANT4 and the rear antenna unit 120 of the front antenna unit 110 and outputs the signal to the signal processing unit 140. [ Into a signal that can be analyzed.

Here, the receiving unit 130 combines the signals received by the plurality of front antennas FANT1 through FANT4 with the radiation signals received through the rear antenna unit 120, downconverts the frequency, and outputs a plurality of downconverted signals And transmits the digital signal to the signal processing unit 140.

The signal processing unit 140 determines a direction in which the plurality of front antennas FANT1 through FANT4 sense a reflected signal and detects a direction in which the plurality of front antennas FANT1 through FANT4 sense the determined direction, .

Then, the position of the target TG is discriminated by combining and analyzing a plurality of digital signals applied from the receiving unit 130. A method of determining the position of the target (TG) using the plurality of digital signals by the signal processing unit 140 will be described later in detail.

The signal processing unit 140 may be configured to transmit the guidance weapon GW to the induction control unit 600 until the guided weapon GW is launched from the launching base LC and can directly determine the position of the target TG using a plurality of digital signals. It is possible to determine the directing directions of the plurality of front antennas FANT1 to FANT4 based on the target position information on the basis of the target position information on the basis of the target position information, And determines the direction of each of the front antennas FANT1 to FANT4.

In the present invention, the front antenna unit 110, the rear antenna unit 120, the receiving unit 130, and the signal processing unit 140 are configured for a searcher mounted on the guided weapon GW. That is, the guided weapon GW of the present invention includes a search unit including a front antenna unit 110, a rear antenna unit 120, a receiving unit 130, and a signal processing unit 140.

Meanwhile, the induction control unit 150 may include a communication unit (not shown) to perform communication with the launch control radar (FCR). The induction control unit 150 drives the driving and propelling unit 160 to fire the guided weapon GW from the launching base LC when a launch command is issued from the launch control radar FCR. And controls the drive and propulsion unit 160 to move to the expected movement position of the target TG applied from the launch control radar (FCR). The induction control unit 600 periodically communicates with the launch control radar (FCR) to receive the target position information and to drive and drive the guided weapon GW to the anticipated movement position of the target TG 160 and transmits the target position information of the target TG to the signal processing unit 140. [ In response to the target position information, the signal processing unit 140 searches the target TG by adjusting the direction of each of the plurality of front antennas FANT1 through FANT4 using the beam forming technique.

When the signal processing unit 140 detects the target and transmits the target detection information, the induction control unit 150 calculates the anticipated movement path of the target by analyzing the direction, movement speed, and distance of the target included in the target detection information , And controls the driving and propelling unit 160 to move the guided weapon GW to the predicted movement path.

The driving and propelling unit 160 is ignited under the control of the induction control unit 150 to provide a driving force for flying the guided weapon GW and drives the fin of the guided weapon GW, (GW).

Although not shown, a guided weapon (GW) is provided with a warhead for hitting a target, and is capable of detonating the warhead even when the guided weapon (GW) does not directly touch the target (TG) A proximity sensor (not shown) may be further provided.

3 shows a detailed configuration of the front antenna unit of Fig.

3, it is assumed that the front antenna unit 110 includes four front antennas FANT1 through FANT4. Each of the four front antennas FANT1 to FANT4 includes a plurality of feed elements arranged in a predetermined pattern and the plurality of feed elements can be grouped in a row unit or a column unit and phase-controlled in group units. In this case, the plurality of the feeding elements are not individually controlled but are grouped in units of rows or columns and controlled in units of groups. This is because the induction weapon GW of the present invention is different from the guided weapon having a single antenna As shown in Fig. For conventional guided weapons with a single antenna, omnidirectional beamforming must be performed so that the target can be detected over a wide angle range based on the direction of the guided weapon. In addition, there has been a case where the direction of the antenna itself is adjusted by mounting the antenna on the biaxial gimbals and driving the biaxial gimbals so that an area that can not be detected by the omnidirectional beam forming can be detected.

However, in the case of the present invention, as shown in FIG. 2, when a plurality of front antennas FANT1 to FANT4 are disposed at positions respectively designated in front of the guided weapons GW, each front antenna only senses a designated area . That is, it is only necessary to detect the area in the designated quadrant, and it is not necessary to detect the sensing area of the adjacent front antenna. Therefore, even if each of the plurality of front antennas FANT1 to FANT4 varies in the direction of the beam only in the uniaxial direction with respect to the traveling direction of the guided weapon GW, the signal detected by each of the plurality of front antennas FANT1 to FANT4 By integrating and interpreting, the target can be detected in a wide range of areas. Considering the operation of the signal processing unit 140 described below, when the front antennas FANT1 to FANT4 perform beamforming in the two-axis direction rather than the one-axis direction to sense the signal, You can not. Accordingly, in the present invention, as shown in FIG. 3, a plurality of feed elements in each of the front antennas FANT1 to FANT4 are grouped in rows or columns, and are phase-controlled in group units. In the present invention, the rows of the plurality of feeding elements of each of the plurality of front antennas FANT1 to FANT4 are grouped in the row unit or grouped in units of rows according to the arrangement direction of the plurality of front antennas FANT1 to FANT4, ) And the vertical direction, and is grouped in units of rows.

Each of the plurality of front antennas FANT1 to FANT4 is implemented as a module so that a plurality of phase shifters PS and a plurality of low noise amplifiers . The plurality of phase warps (PS) and the plurality of low noise amplifiers (LNA) are provided in the number corresponding to the number of the feeding element groups, and each of the plurality of phase warps (PS) (LNA) low-noise amplifies a signal applied at a corresponding phase shift (PS) and transmits the amplified signal to a receiving unit 130 do.

In the above description, the plurality of front antennas FANT1 to FANT4 are implemented in the form of a module, and a plurality of phase shift keyers (PS) and a plurality of LNAs are provided. However, PS) and a plurality of low noise amplifiers (LNAs) may be provided in the receiving unit 130.

Although not shown, at least one rear antenna may also be configured similar to the front antennas FANT1 through FANT4 of FIG.

Fig. 4 shows a detailed configuration of the receiving unit in Fig.

4, the receiving unit 130 includes a distributor DV, a plurality of mixers MX1 to MX4, a filter unit FT, and an AD converter ADC.

The distributor DV distributes the signals received from the rear antenna unit 120 and delivers the signals to a plurality of mixers MX1 to MX4. 4, the receiving unit 130 further includes a low noise amplifier (LNA), and the distributor DV may be configured to receive and distribute the low noise amplified signal. In some cases, as in the case of the plurality of front antennas FANT1 to FANT4 shown in FIG. 3, the rear antenna RANT may be implemented as a module to include a low noise amplifier (LNA).

Each of the plurality of mixers MX1 to MX4 combines a signal applied from a corresponding front antenna among a plurality of front antennas FANT1 through FANT4 and a signal distributed and applied from a distributor DV. Hereinafter, for convenience of explanation, a signal applied from a plurality of front antennas FANT1 through FANT4 is referred to as a front signal, and a signal applied from a rear antenna RANT is referred to as a rear signal.

The plurality of mixers MX1 to MX4 perform frequency down conversion of the forward signal to the intermediate frequency signal of the intermediate frequency band by combining the corresponding forward signal among the plurality of forward signals with the distributed backward signal. As described above, the backward signal is a signal that receives a radiated signal radiated from the FCR, and the front signal is a radar signal radiated from the FCR and is a reflected signal reflected from the target TG Most cases. Therefore, when the forward signal and the backward signal are synthesized, the receiver can acquire the intermediate frequency signal in the same manner that the receiving unit combines the radiation signal and the reception signal to generate the intermediate frequency signal in the active induction type weapon GW.

The filter unit FT band-pass filters the obtained intermediate frequency signal to remove noise. The AD converter converts the intermediate frequency signal from which noise has been removed into a digital signal and transmits the digital signal to the signal processing unit 140.

FIG. 5 is a diagram for explaining a concept of determining the position of a target from a signal applied to the signal processing unit of FIG. 2; FIG.

5 will be described with reference to the arrangement of a plurality of front antennas FANT1 to FANT4 of the front antenna unit 110 shown in FIG. 2. The signal processing unit 140 includes a receiving unit 130, And receives a plurality of digital signals. Then, a sum signal (?) Is generated by summing a plurality of digital signals.

The digital signals corresponding to the two front antennas FANT1, FANT2, FANT1, and FANT2 arranged in the row direction among the plurality of front antennas FANT1 through FANT4 are summed to generate two row signals, Thereby generating the high angle signal DELTA EL.

Meanwhile, the signal processing unit 140 combines the digital signals corresponding to the two front antennas (FANT1, FANT4, FANT2, FANT3) arranged in the column direction among the plurality of front antennas FANT1 to FANT4, And generates an azimuth signal? AZ by subtracting the signals from each other.

The signal processing unit 140 can determine the distance to the target TG and the relative position using the generated three signals when the sum signal?, The high angle signal? EL and the azimuth angle signal? AZ are generated . The technique of determining the distance and the relative position with respect to the target (TG) using the sum signal (Σ), the high angle signal (ΔEL) and the azimuth signal (ΔAZ) is a technique already used in the existing monopulse radar, I do not explain to you.

When the distance and relative position of the target TG are determined from the sum signal?, The high angle signal? EL and the azimuth angle signal? AZ, the signal processing unit 140 calculates the distance RANGE, the elevation boresight error and azimuth boresight error information to the induction control unit 150. [

The induction control unit 150 can move the guided weapon GW such that the target TG is positioned at the front of the guided weapon GW, that is, the line of sight.

6 is a view for explaining the operation effect of the anti-passive air vehicle intercept system of the present invention.

The guided weapon GW is fired at a close range (e.g., within 20 meters) from the launch control radar (FCR), and the direction in which the radiation signal is emitted from the launch control radar (FCR) (FANT1 to FANT4) of the front antenna unit 110 that receives the front signal and generates the intermediate frequency signal of the forward signal using the backward signal when the change in the angle between the viewing angles of the front antennas The guided weapon (GW) of the present invention, which can determine the position of the target according to the arrangement structure, can obtain almost the same tracking performance as that of the active induction method in which the guided weapon emits the direct radiation signal. That is, high-speed precise tracking becomes possible.

FIG. 7 is a view for explaining characteristics of a radiation signal used in the semi-active air vehicle intercept system of the present invention.

As described above, the present invention relates to an anti-passive vehicle intercept system for intercepting a small flying object such as a small rocket, a mortar, and a cannonball as a target (TG), in which an emission signal requires high distance resolution and low bandwidth It is assumed that a signal of a frequency modulated continuous wave (FMCW) waveform is used. In particular, it is assumed that the radiation signal of the FMCW waveform of the Ka band is emitted.

As shown in FIG. 6, when the sweep bandwidth? F of the radiation signal is 900 MHz, another resolution in bandwidth is calculated as 0.167 m according to Equation (1).

Assuming that the size of a small flying object (TG) is 1 m, six distance cells are needed to identify the target (TG). And if the target (TG) has a detection distance of 1Km, 6000 distance cells are needed. As shown in FIG. 6, when the sweep time is 1 ms, the beat frequency (BF) is calculated according to Equation (2).

The minimum sampling rate should be at least twice according to the Nyquist criterion, so the frequency of the radiated signal should be at least 24 MHz. Considering the characteristics of the anti-aliasing filter, the frequency of the radiation signal is generally set to 2.5 times the bit frequency BF. That is, the sampling rate for the frequency BF can be set to a setting of 30 MHz.

8 illustrates an anti-passive air vehicle interception method according to an embodiment of the present invention.

Referring to FIGS. 1 to 6, the semi-active air vehicle interception method of FIG.

First, the launch control radar (FCR) radiates the emission signal of the FM band type of the Ka band, and the target (TG) is searched by analyzing the reflected reception signal (S10).

The launch control radar (FCR) determines if the target is detected (S20). If it is determined that the target has been detected, the launch control radar (FCR) issues a launch command to the launch pad (LC) and guided weapon (GW) to cause the guided weapon (GW) to fire from the launch pad (LC) (S30). At this time, the launch control radar (FCR) transmits the target position information including the position, movement direction, distance, and speed of the identified target to the guided weapon (GW), so that the guided weapon (GW) Can be confirmed in advance. And the orientation of the launching platform LC can be adjusted so that the guided weapon GW is immediately launched into the expected movement position of the target.

Guided weapons (GW), when fired from the launcher (LC), travel by setting the travel route based on the target location information from the launch control radar (FCR) and communicate with the launch control radar (FCR) And corrects the movement route by receiving the target location information, and moves.

The guided weapon GW receives a plurality of forward signals through a plurality of front antennas FANT1 to FANT4 of the front antenna unit 110 while moving to a position corresponding to the target position information, The backward signal is received through one rear antenna (RANT) (S50).

Then, the sum signal?, The high angle signal? EL, and the azimuth signal? (?) Are generated by combining the plurality of forward signals with the backward signals, downconverting the frequency, converting the signals into digital signals, (Step S60). The signal processing unit 140 of the guided weapon GW analyzes the sum signal?, The high angle signal? EL and the azimuth angle signal? AZ to determine whether the target TG is detected (S70).

When the target TG is detected, the signal processing unit 140 determines the distance and the relative position between the sum signal?, The high angle signal? EL and the azimuth signal? AZ, and the target TG, Error and azimuthal aiming error information to the induction control unit 150 (S80).

The induction control unit 150 controls the driving and propelling unit 160 so that the target TG is positioned on the line of sight of the guided weapon GW in response to the distance, the elevation aiming error and the azimuthal aiming error information, ), Thereby tracking the target TG (S90).

Then, it is determined whether the target TG is very close to reaching the intercept distance (S100). The intercept distance can be determined by whether a proximity sensor (not shown) provided in the guided weapon GW detects a target. If it is determined that the target TG has reached the intercept distance, the guided weapon GW intercepts the target by detonating the internal warhead (S110).

The method according to the present invention can be implemented as a computer program stored in a medium for execution in a computer. Where the computer-readable medium can be any available media that can be accessed by a computer, and can also include both computer storage media. Computer storage media includes both volatile and nonvolatile, removable and non-removable media implemented in any method or technology for storage of information such as computer readable instructions, data structures, program modules or other data, (Digital Versatile Disk) -ROM, a magnetic tape, a floppy disk, an optical data storage device, and the like.

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.

Claims (13)

A radar system for radiating a radiated signal for detecting a target, analyzing a received signal reflected from the target to determine a position of the target, and generating a position of the identified target as target position information, ; And
The radar system comprising: a radar system for communicating with the launch control radar to receive the target location information and move to track the target in accordance with the target location information, And at least one rear antenna for directly receiving the radiation signal radiated from the launch control radar as a rear signal, synthesizing each of the plurality of the front signals and the rear signal, downconverting the frequency, An induction weapon for analyzing a plurality of the converted forward signals to determine a position of the target; Lt; / RTI >
The guided weapon may include,
A front antenna unit having a plurality of front antennas spaced apart from each other at an equal angle to each other in front of a tubular body of the guided weapon;
A rear antenna unit having at least one rear antenna disposed behind the body;
A receiver for combining a plurality of the front signals and the rear signals to perform frequency downconversion and converting a plurality of frequency downconverted forward signals into digital signals;
Generating a high angle signal and an azimuth angle signal for determining a relative position between the sum signal and the target by combining a plurality of the digital signals according to arrangement positions of the plurality of front antennas, A signal processing unit for discriminating a distance and a relative position from the azimuth signal to the target and generating distance information, altitude aiming error information, and azimuth aiming error information according to the distance and relative position to the discriminated target;
A drive and propulsion unit for providing the driving force of the guided weapon and driving the pin to adjust the flying direction of the guided weapon; And
An induction control unit for receiving the distance information, the elevation aiming error information, and the azimuthal aiming error information and controlling the driving and pushing unit such that the target is positioned at a line of sight of the guided weapon; Wherein the anti-passive anti-aircraft intercept system comprises: delete The apparatus of claim 1, wherein the receiver
A distributor for receiving and distributing the rear signals to output a plurality of signals;
A plurality of synthesizers each receiving the front signal from a corresponding front antenna among the plurality of front antennas and synthesizing the front signal distributed and applied by the distributor and frequency downconverting;
A filter unit for filtering the plurality of forward signals frequency downconverted by the plurality of synthesizers to remove noise; And
An AD converter for converting each of the plurality of forward signals output from the filter unit into a digital signal; Wherein the anti-passive anti-aircraft intercept system comprises: The antenna device according to claim 3, wherein the front antenna portion
And the four front antennas are distributed and arranged at uniform intervals with respect to the front center of the guided weapon, and the direction of the direction is adjusted in response to the control of the signal processing unit, respectively. 5. The apparatus of claim 4, wherein the signal processing unit
Four digital signals corresponding to the four front antennas are received and added to generate the sum signal,
The two digital signals corresponding to the two front antennas arranged in the row direction among the four digital signals are summed to generate two row signals and the generated two row signals are subtracted from each other to generate the high angle signal In addition,
Two digital signals corresponding to the two front antennas arranged in the column direction among the four digital signals are summed to generate two column signals and the generated two column signals are subtracted from each other to generate the azimuth signal Wherein the anti-passive anti-aircraft intercept system comprises: 5. The antenna of claim 4, wherein the front antenna
A plurality of feed elements arranged in a predetermined pattern and grouped in rows; And
A plurality of phase shifters for phase-controlling signals applied from the plurality of feed elements in a group unit in response to the control of the signal processing unit; Wherein the antenna is implemented as a wafer-scale antenna module. The method of claim 1,
Ka-band FMCW signal. In an anti-active vehicle intercept method,
The launch control radar emits a radiation signal for detecting a target, and the radiation signal is reflected on the target to analyze the received signal to determine the position of the target, and the position of the identified target is generated as the target position information ;
Guided weapons communicate with the launch control radar and the launch control radar to receive the target location information and move to track the target in accordance with the target location information;
Wherein the guided weapon receives as a front signal the signal with the radiation signal reflected on the target through a plurality of front antennas and the radiation signal emitted from the launch control radar via at least one rear antenna directly as a back signal Receiving; And
Synthesizing each of the plurality of forward signals and the backward signal to perform frequency downconversion, and analyzing a plurality of frequency downconverted forward signals to discriminate the position of the target; Lt; / RTI >
Wherein the step of receiving as the backward signal comprises:
Receiving a plurality of the forward signals through a plurality of the front antennas spaced apart from each other at an equal angle in front of the tubular body of the guided weapon; And
Receiving at least one said rear signal through at least one said rear antenna disposed behind said body; Wherein the anti-passive anti-aircraft intercept method comprises: delete 9. The method of claim 8, wherein receiving as the backward signal comprises:
A plurality of feed elements arranged in rows and grouped in a predetermined pattern in each of the front antennas in accordance with the control of the signal processing unit to adjust a direction of each of the plurality of front antennas before the step of receiving the front signal, Setting a phase adjustment value for the phase shifter; Further comprising the step of: 9. The method of claim 8, wherein determining the location of the target
Synthesizing each of the plurality of forward signals and the backward signal and performing frequency down conversion;
Converting a plurality of frequency down-converted forward signals into digital signals;
Generating a high angle signal and an azimuth angle signal for determining a relative position between the sum signal and the target by combining a plurality of the digital signals according to arrangement positions of the plurality of front antennas;
Determining a distance and a relative position between the sum signal, the high angle signal and the azimuth signal; And
Generating distance information, altitude sighting error information, and azimuth sighting error information according to distances and relative positions with the identified target; Wherein the anti-passive anti-aircraft intercept method comprises: 12. The method of claim 11, wherein the semi-
Moving the guided weapon in response to the distance information, the elevation aiming error information and the azimuthal aiming error information such that the target is located at the line of sight of the guided weapon; Further comprising the step of: 12. The method of claim 11, wherein generating the azimuth signal comprises:
Generating a sum signal by summing four digital signals corresponding to four front antennas distributed at uniform intervals based on the front center of the guided weapon;
The two digital signals corresponding to the two front antennas arranged in the row direction among the four digital signals are summed to generate two row signals and the generated two row signals are subtracted from each other to generate the high angle signal ; And
Two digital signals corresponding to the two front antennas arranged in the column direction among the four digital signals are summed to generate two column signals and the generated two column signals are subtracted from each other to generate the azimuth signal ; Wherein the anti-passive anti-aircraft intercept method comprises:

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