레이더경보수신기용 CD대역 진폭비교 방향탐지 정확도 측정 시스템 개발

현예지,최남우,최혁재,조원택,김성훈 대한전자공학회 2022 전자공학회논문지 Vol.59 No.11

Radar Warning Receiver(RWR) is Electronic Warfare Support equipment, which detects and measures threat radar signal in high speed then provides real time warning. This paper describes the development of an amplitude comparison direction finding accuracy measuring system for CD band RWR, which is intended to be loaded on aircraft for the first time in Korea. The developed RWR equipment receives CD band signal from Blade Antenna, executes signal processing in RF and Digital module, and derives angle of arrival(AOA) using the amplitude comparison direction finding logic. Since CD band blade antenna has an unbalanced beam pattern, unlike EJ band or spiral antenna, this paper measures direction finding accuracy by adding a beam calibration algorithm. As a result of conducting a radiation test on the CD band in the anechoic chamber to verify the direction finding accuracy, the performance is confirmed that the average CD band direction finding accuracy is measured by 6.73% higher than the target performance of OO degree RMS in 360 degree azimuth and 45 degree elevation range.

회전익 항공기용 레이더 경보수신기 결함 원인분석을 통한 개선방안 연구

정혜수,권태현,손원애,박정호 국방기술품질원 2023 국방품질연구논집 Vol.5 No.1

A radar warning receiver is an aircraft electronic device that detects and analyzes threat signals around the aircraft and alerts pilots to the analyzed threat signals to improve aircraft viability. Defective phenomena of radar warning receivers occur between aircraft operations such as power failure and boot errors. Consequently, there is a need to resolve radar warning receiver defects and improve quality. In this study, the cause of the defect phenomena was analyzed and improvement measures for each identified defect cause were presented. Process improvement was carried out to solve defects caused by the cause of occurrence, and process measures were added to strengthen product inspection procedures and prevent defects. The validity of design improvement was verified through the component and aircraft system flight test.

Signal Processing Algorithm to Reduce RWR Electro-Magnetic Interference with Tail Rotor Blade of Helicopter

Hyo-Bin Im,Eun-Kyoung Go,Un-Seob Jeong,Si-Chan Lyu 한국항공우주학회 2009 International Journal of Aeronautical and Space Sc Vol.10 No.2

In the environment where various and complicated threat signals exist, RWR (Radar Warning Receiver), which can warn pilot of the existence of threats, has long been a necessary electronic warfare (EW) system to improve survivability of aircraft. The angle of arrival (AOA) information, the most reliable sorting parameter in the RWR, is measured by means of four-quadrant amplitude comparison direction finding (DF) technique. Each of four antennas (usually spiral antenna) of DF unit covers one of four quadrant zones, with 90 degrees apart with nearby antenna. According to the location of antenna installed in helicopter, RWR is subject to signal loss and interference by helicopter body and structures including tail bumper, rotor blade, and so on, causing a difficulty of detecting hostile emitters. In this paper, the performance degradation caused by signal interference by tail rotor blades has been estimated by measuring amplitude video signals into which RWR converts RF signals in case a part of antenna is screened by real tail rotor blade in anechoic chamber. The results show that corruption of pulse amplitude (PA) is main cause of DF error. We have proposed two algorithms for resolving the interference by tail rotor blades as below: First, expand the AOA group range for pulse grouping at the first signal analysis phase. Second, merge each of pulse trains with the other, that signal parameter except PRI and AOA is similar, after the first signal analysis phase. The presented method makes it possible to use RWR by reducing interference caused by blade screening in case antenna is screened by tail rotor blades.

Signal Processing Algorithm to Reduce RWR Electro-Magnetic Interference with Tail Rotor Blade of Helicopter

Im, Hyo-Bin,Go, Eun-Kyoung,Jeong, Un-Seob,Lyu, Si-Chan The Korean Society for Aeronautical and Space Scie 2009 International Journal of Aeronautical and Space Sc Vol.10 No.2

In the environment where various and complicated threat signals exist, RWR (Radar Warning Receiver), which can warn pilot of the existence of threats, has long been a necessary electronic warfare (EW) system to improve survivability of aircraft. The angle of arrival (AOA) information, the most reliable sorting parameter in the RWR, is measured by means of four-quadrant amplitude comparison direction finding (DF) technique. Each of four antennas (usually spiral antenna) of DF unit covers one of four quadrant zones, with 90 degrees apart with nearby antenna. According to the location of antenna installed in helicopter, RWR is subject to signal loss and interference by helicopter body and structures including tail bumper, rotor blade, and so on, causing a difficulty of detecting hostile emitters. In this paper, the performance degradation caused by signal interference by tail rotor blades has been estimated by measuring amplitude video signals into which RWR converts RF signals in case a part of antenna is screened by real tail rotor blade in anechoic chamber. The results show that corruption of pulse amplitude (PA) is main cause of DF error. We have proposed two algorithms for resolving the interference by tail rotor blades as below: First, expand the AOA group range for pulse grouping at the first signal analysis phase. Second, merge each of pulse trains with the other, that signal parameter except PRI and AOA is similar, after the first signal analysis phase. The presented method makes it possible to use RWR by reducing interference caused by blade screening in case antenna is screened by tail rotor blades.

레이더경보수신기를 위한 시험평가 지원장비 개발

최호준,권지연,김도현 韓國防衛産業學會 2011 韓國防衛産業學會誌 Vol.18 No.1

ADD 3.0 기반 전자전 소프트웨어의 계층적 아키텍처 연구

이정우,김수진,허진혁,장효정,한진우 한국군사과학기술학회 2024 한국군사과학기술학회지 Vol.27 No.2

Development of electronic warfare(EW) software has become increasingly challenging due to stricter regulations,shorter development cycles, and increased reliability testing. Consequently, software development often proceedswithout proper architecture design, which can lead to missing critical quality requirements and potential systemredesigns. In this study, we propose using Attribute-Driven Design(ADD) 3.0 to design software architecturespecifically tailored for EW systems, enabling a more systematic approach to address quality requirements. Thepaper presents an overview of EW software and ADD 3.0 methodology, followed by an analysis of thearchitecture design results using static and dynamic views. The paper concludes by discussing the effectiveness ofthe proposed architecture design.

전자전 장비 비행시험 기술 연구

김현경(Hyeonkyeong Kim) 항공우주시스템공학회 2023 항공우주시스템공학회 학술대회 발표집 Vol.2023 No.10

몬테카를로 모사법을 이용한 무인전투기의 위약도에 영향을 미치는 파라미터와 민감도에 대한 연구

최광식(Kwang Sik Choi),이경태(Kyung Tae Lee) 한국항공우주학회 2011 韓國航空宇宙學會誌 Vol.39 No.3

종래의 stand-off 무인항공기가 감시와 정찰에 초점이 맞춰져 있었다면, 무인전투기는 여기서 더 발전하여 극한상황에서의 전투임무를 수행한다. 미래의 전장에서 무인전투기는 유인전투기가 수행하였던 적 방공망제압임무(SEAD)와 같은 극한상황의 임무를 수행할 것이며, 임무 수행 중 지대공 미사일등과 같은 각종 위협에 직면하게 될 것이다. 현재 항공기의 전투생존성에 대하여 많은 연구가 진행되고 있지만 이것은 대부분 유인전투기의 위약도와 취약도를 개선하는 방안에 대한 것이다. 무인전투기의 생존성을 고려한 설계는 일반적으로 유인전투기와 유사할 수 있으나, 임무수행환경 및 형상과 성능에 있어 유인전투기와 차이가 존재하므로 생존성에 영향을 미치는 변수들에 있어 정량적, 정성적인 차이가 존재 한다. 본 논문에서는 무인전투기의 생존성 요소 중 위약도에 영향을 주는 요소를 유인전투기인 F-16C/D와 무인전투기 X-45A를 예제로 하여 식별하고 그 민감도를 몬테카를로 모사법을 이용하여 분석하였다. The typical missions for the current stand-off UAVs are surveillance and reconnaissance. On the other hand, the primary mission for the future UCAS will be combat mission such as SEAD under the man-made ultimately hostile environment including SAM, antiaircraft artillery, threat radar, etc. Therefore, one of the most important challenges in UCAS design is improvement of survivability. The current studies for aircraft combat survivability are focused on the improvement of susceptibility and vulnerability of manned aircraft system. Although the survivability design methodology for UCAS might be very similar to the manned combat system but there are some differences in mission environment, system configuration, performance between manned and unmanned systems. So the parameters and their sensitivities which affect aircraft combat survivability are different in qualitatively and quantitatively. The susceptibility related parameters for F-16 C/D and X-45A as an example of manned and unmanned system are identified and the susceptibility parameter sensitivities are analyzed by using Monte-Carlo Simulation in this study.