WO2016104845A1 - Flight test method for evaluating anti-jamming capability - Google Patents

Flight test method for evaluating anti-jamming capability Download PDF

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Publication number
WO2016104845A1
WO2016104845A1 PCT/KR2014/012919 KR2014012919W WO2016104845A1 WO 2016104845 A1 WO2016104845 A1 WO 2016104845A1 KR 2014012919 W KR2014012919 W KR 2014012919W WO 2016104845 A1 WO2016104845 A1 WO 2016104845A1
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tester
jamming
gps
jamming signal
signal
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PCT/KR2014/012919
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French (fr)
Korean (ko)
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조암
최주원
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한국항공우주연구원
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
    • G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
    • G01S19/13—Receivers
    • G01S19/23—Testing, monitoring, correcting or calibrating of receiver elements

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  • the present invention relates to a flight test method for evaluating anti-jamming performance, and more particularly, by minimizing the jamming damage area over the test area by transmitting a jamming signal from the jammer of the vehicle to the tester in the area where there is no GPS user.
  • the present invention relates to a flight test method for evaluating anti-jamming performance by realizing a method of judging the performance of a navigation apparatus, which greatly improves the performance evaluation reliability of a navigation apparatus by a jamming signal.
  • GPS is a satellite navigation system designed to display four satellites at all times on earth by arranging 28 satellites on six orbits over 20,000 Km above ground.
  • GPS is mainly divided into satellite, control, and user parts.
  • the user part refers to the GPS receiver.
  • the GPS signal strength is less than the thermal noise level, and thus is greatly affected by the small jamming signal strength.
  • the prior art KR 10-1030236 B1 2011.04.13 Referring to "GPS adaptive array antenna test phase plane simulator" in FIG. 1, first, the GPS jamming signal generator 110 generates a jamming signal in the GPS band and sends it to the GPS jamming signal phase plane controller 120 at the same time.
  • the phase plane controllers 121 to 125 are input to the phase plane controllers 121 to 125, and then the phase plane controllers 121 to 125 receive information such as phase delays related to the phase plane formation from the phase plane controller 140.
  • phase plane simulation output signals 21, 22, 23, 24, and 25 for the phase difference information between the respective channels are applied to the GPS / GLONASS adaptive array antenna N-channel electronic unit 150.
  • the GPS / GLONASS satellite simulator 130 outputs the GPS signal as an RF signal and outputs the GPS signal to the GPS / GLONASS adaptive array antenna N-channel electronic unit 150 through the satellite signal power divider 126. Transmit GPS signal.
  • the GPS jamming signal and the satellite signal of which the phase plane is simulated are simultaneously input to the satellite navigation receiver 160.
  • the prior art as described above evaluates the effect of the jamming signal on the satellite navigation receiver 160 by simulating the phase plane for the GPS jamming signal without indoor and outdoor test facilities. It is not possible to guarantee the performance of the test. Also, it is a test method that the reliability is remarkably deteriorated because it proceeds in a state where there are many weak jamming signals around.
  • the present invention has been made in order to solve the problems of the prior art as described above, the object is to transmit a jamming signal from the jammer of the aircraft to the tester in the air over the area without the GPS user to minimize the jamming damage area over the test area
  • the aim is to significantly improve the performance evaluation reliability of the navigation apparatus by the jamming signal.
  • the present invention comprises the steps of: flying a flying vehicle 10 equipped with a jammer 4, a laser range finder 6, a camera 8 and the like at a height of 300 m;
  • the GPS receiver 14 After the step of transmitting the jamming signal, the GPS receiver 14 receiving a GPS signal in a state of being affected by the jamming signal in the tester 12;
  • the navigation device 2 is characterized in that the performance is determined in the state that the anti-jamming function is added.
  • the present invention allows the aircraft 10 equipped with a jammer (4), a laser range finder (6), a camera (8), and the like to fly at an altitude of 300 m in an area where there is no GPS user, and then the GPS receiver (14).
  • the jammer 4 transmits a jamming signal to the tester 12 to determine the performance of the navigation device 2. Since the performance of the navigation apparatus can be evaluated in the operating environment, the reliability of the performance evaluation of the navigation apparatus 2 is remarkably improved.
  • 1 is a phase planar simulator for testing a GPS adaptive array antenna according to the related art.
  • Figure 2 shows the performance of the navigation device using the aircraft and tester which is an embodiment of the present invention
  • the present invention is to determine the performance change occurring in the navigation apparatus 2 under the influence of the jamming signal in the process of receiving the GPS signal transmitted from the satellite navigation system, the performance of the navigation apparatus (2)
  • the test method for determining is described in Figure 2 as follows.
  • a jammer 4 for generating a jamming signal, a laser range finder 6, and a camera 8 are mounted on the aircraft 10, respectively, and the vehicle 10 flies at an altitude of 300 m. Conduct.
  • the altitude of the vehicle 10 can be changed according to the situation, the place where the aircraft 10 is flying so as not to be affected by the jamming signal by selecting the area where the GPS user is not.
  • the tester 12 After the flying step of the vehicle 10, the tester 12 performs a step of flying at an altitude of 100m with the navigation device 2 and the GPS receiver 14 mounted.
  • the altitude of the tester 12 can be changed according to the situation.
  • the jammer 4 of the vehicle 10 transmits a jamming signal.
  • the aircraft 10 flying at a high altitude is directed to the tester 12 flying at a low altitude, and then transmits a jamming signal, wherein the jammer 4 radiates to the opposite side of the test machine 12.
  • the jamming signal is absorbed by 20 to 30dB by the body of the aircraft 10, thereby minimizing the jamming damage area formed over the test area.
  • the relative position of the tester 12 flying at a low altitude through the camera 8 mounted on the vehicle 10 is detected so that the jammer 4 is directed to the tester 12, and at the same time, the laser distance.
  • the distance between the vehicle 10 and the tester 12 is measured through the measuring device 6.
  • the distance between the vehicle 10 and the tester 12 is measured through the laser range finder 6, but may be measured by mounting another distance measuring means to the vehicle 10.
  • the GPS receiver 14 After the step of transmitting the jamming signal, the GPS receiver 14 receives a GPS signal in a state in which the tester 12 is affected by the jamming signal.
  • the jamming signal transmitted from the jammer 4 is also received.
  • the navigation device 2 mounted on the tester 12 is affected by the jamming signal. Performance changes as you receive it.
  • the tester 12 After the step of receiving the GPS, the tester 12 performs the step of determining the performance of the navigation apparatus 2 caused by the influence of the jamming signal.
  • the tester 12 since the intensity of the jamming signal radiated from the jammer 4 to the tester 12 is inversely proportional to the square of the distance, the tester 12 reaches the tester 12 with a smaller intensity of the jamming signal than when transmitted.
  • the distance from the vehicle 10 to the tester 12 is measured by the laser range finder 6 and transmitted from the jammer 4 of the vehicle 10 to the tester 12 through the measured distance as described above. It is possible to know the intensity of the jamming signal reached, and it is also possible to actively adjust the signal intensity transmitted from the jammer 4.
  • the navigation device 2 is affected.
  • the navigation device 2 is applied to the jamming signal.
  • the current performance state of the navigation device 2 by checking how the performance has been degraded, how much the navigation device 2 has normally operated, and how much the navigation device 2 can withstand according to the magnitude of the jamming signal. Will be judged.
  • the intensity of the jamming signal is 30dB or less, it will operate normally to some extent, but if the strength of the jamming signal is 30dB or more, Significantly lowered.
  • the navigation device 2 by adding an array antenna to the navigation device 2 or integrating an inertial sensor or the like, the anti-jamming performance can be improved. In this case, even when the intensity of the jamming signal is 80 dB to 85 dB, the navigation device 2 can operate normally. do.
  • the performance of the navigation apparatus 2 is judged in both the case of the anti-jamming function and the case of the addition of the anti-jamming function. It can increase.

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  • Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Position Fixing By Use Of Radio Waves (AREA)

Abstract

The present invention relates to a flight test method for evaluating an anti-jamming capability, and the purpose of the present invention is to innovatively improve performance evaluation reliability of a navigation system (2) through a jamming signal by implementing a method for determining the performance of the navigation system (2) by transmitting the jamming signal from a jammer (4) of a flight vehicle (10) to a tester (12), in the sky above a broad region where there is no GPS user. To this end, the present invention comprises: a step for enabling the flight vehicle (10), which has the jammer (4), a laser distance meter (6), a camera (8) and the like mounted thereon, to fly at an altitude of 300 m; a step for enabling the tester (12), which has the navigation system (2) and a GPS receiver (14) mounted thereon, to fly at an altitude of 100 m after the step for enabling the flight vehicle (10) to fly; step for enabling the jammer (4) of the flight vehicle (10) to transmit the jamming signal after the step for enabling the tester (12) to fly; a step for enabling the GPS receiver (14) to receive a GPS signal when the tester (12) is influenced by the jamming signal after the step for transmitting the jamming signal; and a step for enabling the tester (12) to determine the performance of the navigation system (2), which is influenced by the jamming signal, after the step for receiving the GPS signal.

Description

항재밍 성능 평가를 위한 비행 시험방법Flight test method for anti-jamming performance evaluation
본 발명은 항재밍 성능 평가를 위한 비행 시험방법에 관한 것으로써, 더욱 상세하게는 GPS 사용자가 없는 지역의 상공에서 비행체의 잼머로부터 재밍신호를 시험기로 전송하여 시험지역 상공의 재밍 피해 영역을 최소화 하면서 항법장치의 성능을 판단하는 방법을 실현함으로써, 재밍신호에 의한 항법장치의 성능 평가 신뢰도를 획기적으로 향상시키는 항재밍 성능 평가를 위한 비행 시험방법에 관한 것이다. The present invention relates to a flight test method for evaluating anti-jamming performance, and more particularly, by minimizing the jamming damage area over the test area by transmitting a jamming signal from the jammer of the vehicle to the tester in the area where there is no GPS user. The present invention relates to a flight test method for evaluating anti-jamming performance by realizing a method of judging the performance of a navigation apparatus, which greatly improves the performance evaluation reliability of a navigation apparatus by a jamming signal.
일반적으로, GPS는 지상 20,000 Km 상공의 6대 궤도면에 28개의 위성을 배치하여 지구상 어디에서나 항상 4개의 위성이 보일 수 있도록 설계된 위성 항법 시스템으로, GPS는 크게 위성부분, 관제부분, 사용자 부분으로 나누어지며, 사용자 부분은 GPS 수신기를 말한다. In general, GPS is a satellite navigation system designed to display four satellites at all times on earth by arranging 28 satellites on six orbits over 20,000 Km above ground. GPS is mainly divided into satellite, control, and user parts. The user part refers to the GPS receiver.
상기 GPS 신호세기는 열잡음(thermal noise) 수준 이하라서 작은 재밍(jamming) 신호 세기로도 큰 영향을 받게 된다. The GPS signal strength is less than the thermal noise level, and thus is greatly affected by the small jamming signal strength.
따라서, 재밍신호에 의해 나타나는 항법장치의 성능을 정확히 평가하기 위해서는, 항법장치 사용자가 없는 넓은 지역과 시험장비를 필요로하게 된다. Therefore, in order to accurately evaluate the performance of the navigation system indicated by the jamming signal, a large area and test equipment without a navigation device user are required.
한편, 종래의 기술인 KR 10-1030236 B1 2011.04.13. "GPS 적응 배열 안테나 시험용 위상면 모의장치"를 도 1 에서 살펴보면, 먼저 GPS 재밍신호 발생장치(110)는 GPS 대역 내의 재밍신호를 생성하여 GPS 재밍신호 위상면 제어기(120)로 보내는 동시에 각 채널의 위상면 제어기(121∼125)에 입력되게 하며, 이후로 위상면 제어기(121∼125)에는 위상면 형성과 관련된 위상지연 등의 정보를 위상면 제어장치(140)로 부터 입력 받는다. On the other hand, the prior art KR 10-1030236 B1 2011.04.13. Referring to "GPS adaptive array antenna test phase plane simulator" in FIG. 1, first, the GPS jamming signal generator 110 generates a jamming signal in the GPS band and sends it to the GPS jamming signal phase plane controller 120 at the same time. The phase plane controllers 121 to 125 are input to the phase plane controllers 121 to 125, and then the phase plane controllers 121 to 125 receive information such as phase delays related to the phase plane formation from the phase plane controller 140.
상기 이후로, 각 채널 간의 위상차 정보에 대한 위상면 모의 출력신호 (21,22,23,24,25)를 GPS/GLONASS 적응 배열안테나 N-채널 전자부(150)로 인가한다. After that, the phase plane simulation output signals 21, 22, 23, 24, and 25 for the phase difference information between the respective channels are applied to the GPS / GLONASS adaptive array antenna N-channel electronic unit 150.
그리고, GPS/GLONASS 위성시뮬레이터(130)는 GPS 신호를 RF신호로 출력하여 위성신호 전력분배기(126)를 통해 GPS/GLONASS 적응 배열안테나 N-채널 전자부(150)에 위상지연이 없는 일정한 전력의 GPS신호를 전달한다. In addition, the GPS / GLONASS satellite simulator 130 outputs the GPS signal as an RF signal and outputs the GPS signal to the GPS / GLONASS adaptive array antenna N-channel electronic unit 150 through the satellite signal power divider 126. Transmit GPS signal.
상기 이후로, 위상면이 모의된 GPS 재밍신호와 위성신호는 위성항법수신기 (160)로 동시에 입력된다. Since the above, the GPS jamming signal and the satellite signal of which the phase plane is simulated are simultaneously input to the satellite navigation receiver 160.
상기와 같은 종래의 기술은 실내 및 야외 시험시설 없이 GPS 재밍신호에 대한 위상면을 모의함으로써, 위성항법수신기(160)에 대한 재밍신호 영향을 평가하게 되는데, 이러한 방식은 실제 운용 환경에서의 항법 장치의 성능을 보장할 수 없으며, 또한 주변에 약한 재밍신호가 많이 있는 상태에서 진행하게 됨으로 신뢰성이 현저히 저하되는 시험방법이 된다. The prior art as described above evaluates the effect of the jamming signal on the satellite navigation receiver 160 by simulating the phase plane for the GPS jamming signal without indoor and outdoor test facilities. It is not possible to guarantee the performance of the test. Also, it is a test method that the reliability is remarkably deteriorated because it proceeds in a state where there are many weak jamming signals around.
본 발명은 상기와 같은 종래기술의 문제점을 해소하기 위해 안출한 것으로써, 그 목적은 GPS 사용자가 없는 지역의 상공에서 비행체의 잼머로부터 재밍신호를 시험기로 전송하여 시험지역 상공의 재밍 피해 영역을 최소화 하면서 항법장치의 성능을 판단하는 방법을 실현함으로써, 재밍신호에 의한 항법장치의 성능 평가 신뢰도를 획기적으로 향상시키고자 하는 데에 있다. The present invention has been made in order to solve the problems of the prior art as described above, the object is to transmit a jamming signal from the jammer of the aircraft to the tester in the air over the area without the GPS user to minimize the jamming damage area over the test area By realizing the method of judging the performance of the navigation apparatus, the aim is to significantly improve the performance evaluation reliability of the navigation apparatus by the jamming signal.
본 발명은 첫째, 잼머(4)와, 레이저거리측정기(6)와, 카메라(8) 등이 장착된 비행체(10)를 300m 고도로 비행하는 단계; The present invention comprises the steps of: flying a flying vehicle 10 equipped with a jammer 4, a laser range finder 6, a camera 8 and the like at a height of 300 m;
상기 비행체(10) 비행단계 이후로, 항법장치(2)와 GPS수신기(14)가 장착된 시험기(12)를 100m 고도로 비행하는 단계; Flying the tester 12 equipped with the navigation device 2 and the GPS receiver 14 at an altitude of 100 meters after the flying step of the vehicle 10;
상기 시험기(12) 비행단계 이후로, 비행체(10)의 잼머(4)에서 재밍신호를 송신하는 단계; Transmitting a jamming signal from the jammer 4 of the vehicle 10 after the flight of the tester 12;
상기 재밍신호를 송신하는 단계 이후로, 시험기(12)에서 재밍신호의 영향을 받는 상태에서 GPS수신기(14)가 GPS 신호를 수신하는 단계; After the step of transmitting the jamming signal, the GPS receiver 14 receiving a GPS signal in a state of being affected by the jamming signal in the tester 12;
상기 GPS를 수신하는 단계 이후로, 시험기(12)에서 재밍신호의 영향으로 일어나는 항법장치(2)의 성능을 판단하는 단계;로 된 것을 특징으로 한다. After the step of receiving the GPS, determining the performance of the navigation device 2 caused by the influence of the jamming signal in the tester 12;
둘째, 상기 항법장치(2)는 항재밍 기능이 추가된 상태에서 성능을 판단하게 되는 것을 특징으로 한다. Second, the navigation device 2 is characterized in that the performance is determined in the state that the anti-jamming function is added.
본 발명은 GPS 사용자가 없는 지역의 상공에서 잼머(4)와, 레이저거리측정기(6)와, 카메라(8) 등을 장착한 비행체(10)를 300m 고도로 비행하게 한 다음, GPS수신기(14)와 항법장치(2)를 장착한 시험기(12)를 100m 고도로 비행하게 하는 상태에서, 잼머(4)로부터 재밍신호를 시험기(12)로 송신하여 항법장치(2)의 성능을 판단하게 됨으로, 실제 운용 환경에서 항법장치의 성능 평가가 가능하여 항법장치(2)의 성능 평가 신뢰도가 획기적으로 향상되는 효과가 있다. The present invention allows the aircraft 10 equipped with a jammer (4), a laser range finder (6), a camera (8), and the like to fly at an altitude of 300 m in an area where there is no GPS user, and then the GPS receiver (14). In the state of letting the tester 12 equipped with the navigation device 2 fly at an altitude of 100 m, the jammer 4 transmits a jamming signal to the tester 12 to determine the performance of the navigation device 2. Since the performance of the navigation apparatus can be evaluated in the operating environment, the reliability of the performance evaluation of the navigation apparatus 2 is remarkably improved.
도 1 은 종래의 기술인 GPS 적응배열 안테나 시험용 위상면 모의장치의 1 is a phase planar simulator for testing a GPS adaptive array antenna according to the related art.
블록도.         Block diagram.
도 2 는 본 발명의 실시예인 비행체와 시험기를 이용하여 항법장치의 성능을 Figure 2 shows the performance of the navigation device using the aircraft and tester which is an embodiment of the present invention
평가하는 상태도.         State diagram to evaluate.
본 발명은 위성 항법시스템으로 부터 송신된 GPS 신호를 수신하는 과정에서, 재밍(jamming)신호의 영향으로 항법장치(2)에서 일어나는 성능변화를 판단하기 위한 것으로, 상기 항법장치(2)의 성능을 판단하기 위한 시험방법을 도 2 에서 설명하면 다음과 같다. The present invention is to determine the performance change occurring in the navigation apparatus 2 under the influence of the jamming signal in the process of receiving the GPS signal transmitted from the satellite navigation system, the performance of the navigation apparatus (2) The test method for determining is described in Figure 2 as follows.
먼저, 재밍신호를 발생시키는 잼머(jammer)(4)와, 레이저거리측정기(6)와, 카메라(8)를 각각 비행체(10)에 장착하고, 상기 비행체(10)가 300m 고도로 비행하는 단계를 실시한다. First, a jammer 4 for generating a jamming signal, a laser range finder 6, and a camera 8 are mounted on the aircraft 10, respectively, and the vehicle 10 flies at an altitude of 300 m. Conduct.
이때, 비행체(10)의 고도는 상황에 따라 변경할 수 있으며, 상기 비행체(10)가 비행하는 장소는 GPS 사용자가 없는 지역을 선택함으로써 재밍신호의 영향을 받지 않도록 한다. At this time, the altitude of the vehicle 10 can be changed according to the situation, the place where the aircraft 10 is flying so as not to be affected by the jamming signal by selecting the area where the GPS user is not.
상기 비행체(10)가 비행하는 단계 이후로, 시험기(12)에 항법장치(2)와 GPS수신기(14)를 장착한 상태에서 100m 고도로 비행하는 단계를 실시한다. After the flying step of the vehicle 10, the tester 12 performs a step of flying at an altitude of 100m with the navigation device 2 and the GPS receiver 14 mounted.
이때, 시험기(12)의 고도는 상황에 따라 변경할 수 있다. At this time, the altitude of the tester 12 can be changed according to the situation.
상기 시험기(12)가 비행하는 단계 이후로, 비행체(10)의 잼머(4)에서 재밍신호를 송신하는 단계를 실시한다. After the tester 12 flies, the jammer 4 of the vehicle 10 transmits a jamming signal.
상기와 같이 고고도로 비행하는 비행체(10)에서는 잼머(4)를 저고도로 비행하는 시험기(12)로 향하게 한 다음 재밍신호를 송신하게 되는데, 이때 잼머(4)에서 시험기(12) 반대편 상공으로 방사되는 재밍신호는 비행체(10) 동체에 의해 20dB∼30dB 가 흡수됨으로써, 시험 영역 상공에 형성되는 재밍 피해 지역을 최소화 한다. As described above, the aircraft 10 flying at a high altitude is directed to the tester 12 flying at a low altitude, and then transmits a jamming signal, wherein the jammer 4 radiates to the opposite side of the test machine 12. The jamming signal is absorbed by 20 to 30dB by the body of the aircraft 10, thereby minimizing the jamming damage area formed over the test area.
상기와 같은 상태에서 비행체(10)에 장착된 카메라(8)를 통하여 저고도로 비행하는 시험기(12)의 상대 위치를 파악하여 잼머(4)가 시험기(12)를 지향하도록 하고, 동시에 상기 레이저거리측정기(6)를 통하여 비행체(10)와 시험기(12)간의 거리를 측정한다. In this state, the relative position of the tester 12 flying at a low altitude through the camera 8 mounted on the vehicle 10 is detected so that the jammer 4 is directed to the tester 12, and at the same time, the laser distance. The distance between the vehicle 10 and the tester 12 is measured through the measuring device 6.
이때, 상기 비행체(10)와 시험기(12)간의 거리 측정은 레이저거리측정기(6)를 통하여 실시하게 되지만, 다른 거리 측정수단을 비행체(10)에 장착하여 거리를 측정하여도 무방하다. In this case, the distance between the vehicle 10 and the tester 12 is measured through the laser range finder 6, but may be measured by mounting another distance measuring means to the vehicle 10.
상기 재밍신호를 송신하는 단계 이후로, 시험기(12)에서 재밍신호의 영향을 받는 상태에서 GPS수신기(14)가 GPS 신호를 수신하는 단계를 실시한다. After the step of transmitting the jamming signal, the GPS receiver 14 receives a GPS signal in a state in which the tester 12 is affected by the jamming signal.
상기와 같이 GPS수신기(14)쪽으로 GPS 신호가 수신되는 과정에서 잼머(4)로부터 송신된 재밍신호도 함께 수신 되는데, 이때 상기 시험기(12)에 장착된 항법장치(2)는 재밍신호의 영향을 받게 됨으로 성능에 변화가 일어난다. In the process of receiving a GPS signal toward the GPS receiver 14 as described above, the jamming signal transmitted from the jammer 4 is also received. At this time, the navigation device 2 mounted on the tester 12 is affected by the jamming signal. Performance changes as you receive it.
상기 GPS를 수신하는 단계 이후로, 시험기(12)에서 재밍신호의 영향으로 일어나는 항법장치(2)의 성능을 판단하는 단계를 실시한다. After the step of receiving the GPS, the tester 12 performs the step of determining the performance of the navigation apparatus 2 caused by the influence of the jamming signal.
상기와 같이 잼머(4)로부터 시험기(12)로 방사된 재밍신호의 세기는 거리의 제곱에 반비례하기 때문에 송신될때 보다는 작은 재밍신호의 세기로 시험기(12)에 도달하게 된다. As described above, since the intensity of the jamming signal radiated from the jammer 4 to the tester 12 is inversely proportional to the square of the distance, the tester 12 reaches the tester 12 with a smaller intensity of the jamming signal than when transmitted.
상기 비행체(10)에서 부터 시험기(12)까지의 거리는 레이저거리측정기(6)로 측정하게 되고, 상기와 같이 측정된 거리를 통하여 비행체(10)의 잼머(4)로부터 송신되어 시험기(12)에 도달한 재밍신호의 세기를 알 수 있게 되며, 상기 잼머(4)에서 송신되는 신호 세기를 능동적으로 조절하는 것도 가능하다. The distance from the vehicle 10 to the tester 12 is measured by the laser range finder 6 and transmitted from the jammer 4 of the vehicle 10 to the tester 12 through the measured distance as described above. It is possible to know the intensity of the jamming signal reached, and it is also possible to actively adjust the signal intensity transmitted from the jammer 4.
계속하여, 상기와 같이 잼머(4)로부터 송신된 재밍신호가 시험기(12)에 도달하면 항법장치(2)는 영향을 받게 되는데, 이때 상기 시험기(12)에서는 항법장치(2)가 재밍신호에 의해 성능이 얼마나 저하 되었는지, 항법장치(2)가 정상적으로 얼마나 작동하였는지, 항법장치(2)가 재밍신호의 크기에 따라서 어느 정도 견딜 수 있는지 등을 확인함으로써, 상기 항법장치(2)의 현재 성능 상태를 판단하게 된다. Subsequently, when the jamming signal transmitted from the jammer 4 reaches the tester 12 as described above, the navigation device 2 is affected. In this tester 12, the navigation device 2 is applied to the jamming signal. The current performance state of the navigation device 2 by checking how the performance has been degraded, how much the navigation device 2 has normally operated, and how much the navigation device 2 can withstand according to the magnitude of the jamming signal. Will be judged.
한편, 상기 항법장치(2)의 경우 항재밍 능력이 없는 일반적인 성능이라면 재밍신호의 세기가 30dB 이하일 경우 어느 정도는 정상적으로 작동하게 되지만, 재밍신호의 세기가 30dB 이상일 경우 항법장치(2)의 성능은 현저히 저하된다. On the other hand, in the case of the general performance without the anti-jamming capability of the navigation device (2), if the intensity of the jamming signal is 30dB or less, it will operate normally to some extent, but if the strength of the jamming signal is 30dB or more, Significantly lowered.
반면에, 상기 항법장치(2)에 배열 안테나를 추가하거나 관성센서 등을 통합해서 항재밍 성능을 높일 수 있는데, 이때 재밍신호의 세기가 80dB∼85dB 이더라도 항법장치(2)는 정상적으로 작동할 수 있게 된다. On the other hand, by adding an array antenna to the navigation device 2 or integrating an inertial sensor or the like, the anti-jamming performance can be improved. In this case, even when the intensity of the jamming signal is 80 dB to 85 dB, the navigation device 2 can operate normally. do.
상기와 같이 항법장치(2)에 대한 성능 판단은 항재밍 기능을 제외한 상태에서 진행하는 경우와, 항재밍 기능을 추가한 상태에서 진행하는 경우를 모두 시험함으로써 비행시험에 의한 평가 방법에 대한 신뢰도를 높일 수 있다. As described above, the performance of the navigation apparatus 2 is judged in both the case of the anti-jamming function and the case of the addition of the anti-jamming function. It can increase.
상기와 같은 본 발명의 바람직한 실시 예를 첨부된 도면에 의하여 상세히 설명하였지만, 본 발명은 여기에 기재된 실시 예에 한정되는 것이 아니고, 이 기술 분야에서 통상의 지식을 가진 당업자라면 본 발명의 기술적 사상 및 범위를 벗어나지 않는 범위 내에서 다양하게 수정 및 변형할 수 있을 것이다. Although the preferred embodiments of the present invention as described above in detail by the accompanying drawings, the present invention is not limited to the embodiments described herein, those skilled in the art having ordinary skill in the art Various modifications and variations can be made without departing from the scope.
(부호의 설명)(Explanation of the sign)
2:항법장치 4:잼머 2: navigator 4: jammer
6:레이저거리측정기 8:카메라 6: laser range finder 8: camera
10:비행체 12:시험기 10: flight 12: testing machine
14:GPS수신기 14: GPS receiver

Claims (3)

  1. 잼머(4)와, 레이저거리측정기(6)와, 카메라(8) 등이 장착된 비행체(10)를 300m 고도로 비행하는 단계; Flying the aircraft 10 equipped with the jammer 4, the laser range finder 6, the camera 8, and the like at a height of 300 m;
    상기 비행체(10) 비행단계 이후로, 항법장치(2)와 GPS수신기(14)가 장착된 시험기(12)를 100m 고도로 비행하는 단계; Flying the tester 12 equipped with the navigation device 2 and the GPS receiver 14 at an altitude of 100 meters after the flying step of the vehicle 10;
    상기 시험기(12) 비행단계 이후로, 비행체(10)의 잼머(4)에서 재밍신호를 송신하는 단계; Transmitting a jamming signal from the jammer 4 of the vehicle 10 after the flight of the tester 12;
    상기 재밍신호를 송신하는 단계 이후로, 시험기(12)에서 재밍신호의 영향을 받는 상태에서 GPS수신기(14)가 GPS 신호를 수신하는 단계; After the step of transmitting the jamming signal, the GPS receiver 14 receiving a GPS signal in a state of being affected by the jamming signal in the tester 12;
    상기 GPS를 수신하는 단계 이후로, 시험기(12)에서 재밍신호의 영향으로 일어나는 항법장치(2)의 성능을 판단하는 단계;로 된 것을 특징으로 하는 항재밍 성능 평가를 위한 비행 시험방법. After the step of receiving the GPS, determining the performance of the navigation device (2) caused by the influence of the jamming signal in the tester (12); flight test method for the anti-jamming performance evaluation.
  2. 제 1 항에 있어서, The method of claim 1,
    상기 항법장치(2)는 항재밍 기능이 추가된 상태에서 성능을 판단하게 되는 것을 특징으로 한 항재밍 성능 평가를 위한 비행 시험방법. The navigation device (2) is a flight test method for evaluating the anti-jamming performance, characterized in that to determine the performance in the state where the anti-jamming function is added.
  3. 제 1 항 또는 제 2 항에 있어서, The method according to claim 1 or 2,
    상기 비행체(10)에서는 카메라(8)로 시험기(12)의 위치를 파악하고, 상기 레이저측정기(6)로 시험기(12)의 거리를 측정하는 것을 특징으로 한 항재밍 성능 평가를 위한 비행 시험방법. In the vehicle 10, a camera 8 detects the position of the tester 12, and measures the distance of the tester 12 with the laser measuring device 6, wherein the test method for anti-jamming performance evaluation .
PCT/KR2014/012919 2014-12-24 2014-12-26 Flight test method for evaluating anti-jamming capability WO2016104845A1 (en)

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