• 항공우주정책ㆍ법학회지
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• 제18권
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• pp.211-245
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• 2003

항공법 개정에 따라 군용항공기의 운용에 관한 입법의 필요성이 제기 되어 군용항공기의 특정에 부합하는 입법 방향의 설정이 필요한 상황이다. 이에 현행 군용항공기지법의 문제점을 분석하고, 외국의 군관련 입법현황을 소개하며, 군관련 항공법의 제 개정시 필요한 내용을 제시함으로써, 군용항공기의 운용에 대한 입법적 지원과 전반적인 개선방향을 연구 검토해 보고자 한다.

• 항공우주정책ㆍ법학회지
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• 제32권1호
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• pp.139-175
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• 2017

국회는 2017년 3월 30일 제조물책임법 일부개정법률안을 국회본회의에서 통과시켰다. 본 개정안에는 무엇보다 피해자인 소비자의 입증책임을 완화시키며 제조물책임의 배상책임을 3배까지 증액하는 신설조항이 있어서, 제조물책임관련 소송이 증대될 것이며, 제조물책임보험 가입이 증가할 것이다. 군용항공기 제작사는 군용항공기의 제작목적이 기동성 위주이며, 군의 작전성을 위주로 운용되기 때문에 현실적으로 군용항공기 제조사들이 군용항공기 제조물책임보험을 들 수 없는 현실 상황하에 군용항공기제작사는 제조물책임법과 하자담보책임, 채무불이행책임의 손해배상 위험에 직면하여 있다. 제조물책임법의 시원지인 미국은 1970년대 제조물책임법이 시행되게 되자, 군용항공기제작사의 책임한도에 대하여 학계, 법조계, 보험업계에서 큰 논란이 있었으며, 군용항공기 제작사의 책임문제를 해결하기 위하여, Government Contractor Defense (GCD, 정부계약자항변) 라는 법리를 판례로 만들어 냈다. 한국과 미국정부가 맺고 실제 적용하고 있는 Foreign Military Sales(FMS) 계약서에는 군용항공기제작사에 대한 면책조항이 있다. 군용항공기 제작사가 높은 제조물책임보험을 들 수 없고, 방산원가에도 제조물책임보험료를 반영시키지 않는 현실에서 외국의 수출을 확대하고 있는 군용항공기제작사는 위기 그 자체에 직면하고 있음을 정확히 알고, 시급히 이러한 위기를 해결할 수 있는 입법개정, 정책수립을 하여야만 한다.

• 한국군사과학기술학회지
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• 제17권6호
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• pp.764-772
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• 2014

The stealth performance of supersonic aircraft in recent air battlefield is one of the most significant feature for latest fighters. Especially, as the technology is advancing, the IR stealth capability becomes more important because of its passive characteristic. To design an aircraft with stealth capability, we must know how much the IR signature is generated from the aircraft. Also, predicting the IR signature of enemy's aircraft is tactically crucial. In this study, we calculated MWIR and LWIR infrared signature of $5^{th}$ generation supersonic aircraft against air-to-air and surface-to-air threat using IR simulation code and CFD coupled procedure.

• 한국국방경영분석학회지
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• 제22권2호
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• pp.166-181
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• 1996

Aircraft survivability is determined by the susceptibility and the vulnerability. The aircraft susceptibility and vulnerability depend upon the hardware and software factors. Each of the hardware and software factors consisted of the qualitative and quantitative attributes varies according to the time of the mission. In order to establish the mathermatical model to analyze and evaluate the aircraft survivability, qualitative factors have to be transformed into quantitative factors. Even if many researches in the area of dynamic concept analysis and conversion of qualitative factors into the quantitative factors has been insufficient. This research enhances these insufficient area by developing a reliable aircarft survivability analysis method. The major areas of this research are as follows. First, a method for the conversion of the qualitative factors into the quantitative factors is developed by combining the Fuzzy Set Theory concept and the Delphi Technique. Second, by using the stochastic network diagram for the dynamic survivability analysis, the aircraft survivability and the probability of kill are calculated from the state probability for the situation during mission. The advantage of the analysis technique developed in this research includes ease of use and flexibility. In other words, in any given aircraft's mission execution under any variable probability density function, the developed computer program is able to analyze and evaluate the aircraft survivability.

• 한국군사과학기술학회지
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• 제17권4호
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• pp.456-462
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• 2014

Infrared(IR) guided heat-seeking missiles uses IR emissions from aircraft to detect and track a target. Due to passive characteristic of the IR guidance, early detection of the missile is difficult and it is significant threat to aircraft survivability. Therefore, IR signature prediction of the aircraft is an important aspect of the stealth technology. In this study, we simulated IR signature of the aircraft in real atmospheric conditions. Aircraft surface temperature distribution was calculated by using RadthermIR code. Based on temperature distribution, IR radiance and BRDF(Bidirectional Reflectance Distribution Function) image were simulated for different weather(seasonal) and background(sky/soil) conditions. The IR contrast tendencies are not aligned with surface temperature or magnitude of target IR radiance. Therefore, it is essential to simulate IR signature with various conditions and background to acquire reliable database.

• International Journal of Aeronautical and Space Sciences
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• 제15권3호
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• pp.309-319
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• 2014

This paper mainly focuses on the conceptual design and stealth performance of the three-surface military aircraft. A three-dimensional (3-D) digital mock-up of the three-surface strike fighter with stealth feature was designed and the schemes of carrying missiles were analyzed in CATIA. Based on physical optics principle and the Method of Equivalent Currents (MEC), a numerical simulation of the RCS feature of the aircraft was carried out with RCSPlus which is a software designed by Beihang University. The paper contributes to the RCS feature analysis of the whole plane and different parts on X-band, S-band and UHF-band and a comparison of RCS feature to Su-37 and T-50 military aircraft is drawn. On X-band, the pitch angle of the incident wave was $0^{\circ}$, and the result shows: (1) Compared with Su-37 aircraft, the forward scattering RCS of the three-surface strike aircraft was reduced to 14.9%, the side scattering RCS to 9.6% and the back scattering RCS to 40.2%. (2) Compared with T-50 aircraft, the forward scattering RCS was reduced to 38.61%, and the side scattering RCS to 67.26%. This paper should be useful for researchers in conceptual design and stealth technology of the military aircraft.

• 한국항공우주학회지
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• 제45권8호
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• pp.639-646
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• 2017

본 논문에서는 군용 항공기를 위한 새로운 하중 모니터링 시스템에 대하여 소개하였다. 이 시스템은 항공기에 장착되는 센서와 탑재장비 및 지상에서 운용되는 지상분석장비로 구성된다. 이 시스템을 이용하여 항공기에 작용하는 구조정적하중을 비행파라미터로 추정할 수 있을 뿐 아니라, 정적하중, 동적하중 및 예상치 못한 이벤트에 의한 구조물의 응답을 센서로 측정할 수 있다. 특히 다점 측정이 가능한 광섬유 센서를 사용하였다. 탑재장비는 관련 군사규격서의 요구도를 만족하도록 설계되었으며, 일련의 환경시험으로 입증하였다. 본 시스템은 비행시험에 앞서 지상구조시험에 사용되고 평가되었으며, 향후 비행시험평가를 통하여 군용 항공기의 구조하중 모니터링 시스템으로 사용될 예정이다.

• 한국군사과학기술학회지
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• 제22권2호
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• pp.224-232
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• 2019

This paper presents guidelines for the verification test on electromagnetic environmental effects of a commercial derivative military aircraft. To prove the safety-of-flight of a renovated aircraft and appropriate working of electronic system/device, E3 test and analysis at the system level should be performed prior to its operations on real warfare. For the aircraft modified with Falcon 2000S, we concentrate on intra-system EMC, EMRADHAZ (Electromagnetic Radiation Hazards), electrical bonding, P-Static as test and lightning as analysis from a airworthiness certification point of view based on MIL-STD-464, MIL-HDBK-516. As a result, it is verified that the modified aircraft has enough electromagnetic compatibility capabilities under EME(Electromagnetic Environment). In the process, test and analysis methods considering shielding effectiveness(SE) are applied.

• 전기학회논문지
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• 제66권9호
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• pp.1341-1350
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• 2017

In this paper, a high reliability 30W DC-DC converter is designed considering military standard (MIL-STD) for military applications such as guided weapon and aircraft. The performances and specifications of conventional military grade DC-DC converter are practically analyzed. The requirements for military grade DC-DC converter are established in consideration of MIL-STD and analysis results of conventional product. Two isolated DC-DC converter, forward and fly-back converter, are designed and compared to determine topology. From experimental results under various operating conditions, the forward topology satisfied performances and specifications of MIL-STD for military DC-DC converter.

• 한국컴퓨터정보학회논문지
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• 제24권2호
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• pp.111-118
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• 2019

Recent trends in modern warfare are increasing in importance for air warfare, information warfare, and warfare. The technology of the weapon system software is rapidly developing, and the silent information war to hack it is still going on. Currently, the FA-50 aircraft has a function that can be initialized by a simple switch operation to protect the main military information in the event of an emergency. However, there are limitations in the existing Zeroize function, and this study was carried out to supplement this. First, we compare and analyze the memory structure of aircraft operating in our military, and examined the currently implemented Zeroize function. Second, we reviewed various methods to overcome the limitation of existing Zeroize function. Third, we implement the existing Zeroize function without additional manipulation. In this paper, we propose that the implementation of this feature will enable us to protect our military data more securely and suggest that we should continue to look for ways to enhance security for our technology in the future.