• 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.

• 한국항공운항학회지
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• 제26권4호
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• pp.116-121
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• 2018

According to the incresement of aging aircraft, Republic of Korea Air Force (RoKAF) conducted a teardown inspection of aircraft's EWIS (electrical wiring interconnection system) to determine the status of deterioration and the influence of failure occurrences due to it. The inspected aircraft were the retired fighter jets that had been used for more than 40 years. By analyzing defect type and the defect tendency, RoKAF can establish the necessary measures for the usage extension of their fleet and furthermore, the analysis results can be used as a basic data for the preparation of it's aircraft aging. EWIS inspection was done throughout careful visual inspection technique by removing all the ducts and pipes located in the fuselage and wings. For the aircraft wiring where no damage was found, the elongation tests were performed to determine the deterioration of wiring according to the location of the aircraft. The connectors, which is the main cause of intermittent failure, were completely disassembled and inspected for internal damage such as corrosion, abrasion, and traces of foreign objects. The detected defects were classified into 4 severity levels based on the type of damage, and the classified defects were weighted according to the criticality which may affects to it's system to establish the action plan.

• 시스템엔지니어링학술지
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• 제5권1호
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• pp.7-20
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• 2009

This paper describes a case study on the R&D programs of fighter and attacker aircraft such as F-22A, F/A-18E/F, and T/A-50. F-22A and F/A-18E/F were developed in same age. The performance of each program was, however extremely different. F-22A program results in a lot of cost overrun and schedule delay. On the other hand F/A-18E/F program met the cost, schedule, and performance goals. In the T/A-50 program with a super-sonic advanced trainer, T-50 was also developed successfully on planned cost and time by Korea Air-force and KAI. This paper derives key elements for the success of the military aircraft R&D program through lessons learned from th e case study. Each program is analyzed in terms of its background, planning and management.

• 한국항공운항학회지
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• 제6권1호
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• pp.51-69
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• 1998

This paper was studied to present a model for the application of AHP to the selection of fighter planes. For this study, a questionnaire was developed in respect to the criteria of fighter plane and given to 70 reserved officers who had experienced as fighter pilots in Republic of Korean Air Force (ROKAF) to ask their opinions about the candidates for the next-generation fighter planes of the ROKAF. The AHP software developed by Korean Advanced Institute of Science Technology (KAIST) was used to process the data. The result was analyzed by the criteria of selecting military aircraft and the several alternatives for the next-generation fighter planes.

• 한국항공우주학회지
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• 제38권9호
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• pp.907-913
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• 2010

본 논문에서는 공군에서 운용중인 전투기를 활용한 비행시험 수행 시 비행자료를 얻기 위한 외장형 계측시스템 개발에 대하여 서술하였다. 전투기의 외장형 계측시스템은 계측 포드와 영상 포드로 구성된다. 계측 포드는 GPS/AHRS 센서를 이용하여 전투기 비행자세, 속도 및 고도 등의 비행자료를 측정하며, 영상 포드는 2대의 고속카메라와 1대의 일반카메라를 사용하여 비행영상을 획득한다. 개발한 외장형 계측시스템은 환경시험과 지상시험, 그리고 전투기에 장착하여 비행시험을 수행함으로서 성능을 입증하였다.

• 항공산업연구
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• 통권45호
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• pp.67-81
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• 1998

With projections into the future advanced Korea fighter development, the trend of tactical combat aircraft powerplants technique development over the past decade is presented. Ti was particularly focused on current innovative powerplants technologies such as lower density stronger materials and turbomachniery aerodynamics. With reviewing the status of aircraft powerplants which are currently underdeveloped next generation combat aircraft, it shows some core techniques that are needed for developing Korean type combat aircraft.

• 한국컴퓨터정보학회논문지
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• 제24권10호
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• pp.1-9
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• 2019

전투기 조종사는 '비행환경 적응 교육 훈련(APT)'을 이수함으로써 악조건 속에서도 완벽하게 임무를 수행할 수 있도록 능력을 향상시키고 있다. 그러나 비행 시 가속도로 인해 인체 평형기관의 이상으로 'Vertigo(Spatial disorientation)' 현상에 빠지게 되어 추락하는 사고 사례가 발생하고 있다. 이러한 비행착각에 빠지는 전투기 추락 사고는 국내 외를 불문하고 빈번하게 발생하고 있다. 이에 본 연구에서는 전투기에 'Vertigo' 경고 기능을 구현하고자 하였다. 먼저, 항공기 주임무 컴퓨터와 현재 구현되어 있는 경고 기능을 분석하였다. 그리고 항공기 자세 정보를 이용하기 위해 좌표계 시스템을 연구하였다. 이를 바탕으로 전투기가 배면 비행 자세로 일정 시간 이상 하강 시 전방시현장비에 시각적인 경고 기능을 제공하고자 하였다. 본 기능을 구현함으로써 조종사의 비행 안전을 향상시킬 수 있을 것이라고 기대한다. 또한 본 연구 결과를 바탕으로 다른 서브시스템과의 연계를 통한 경고 기능 구현 방안을 제안하고자 한다.

• 한국군사과학기술학회지
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• 제15권5호
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• pp.643-650
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• 2012

This paper presents quantitative method of static combat effectiveness to classify fighter aircraft generations. We have analyzed performance metrics of United States(US), United Kingdom(UK), Russia, France, Sweden' fighters to determine jet-fighter generation. Both nominal and continuous variables were defined and used to present current trend of combat effectiveness.

• 항공우주시스템공학회지
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• 제15권6호
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• pp.42-49
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• 2021

To develop a high-resolution electro-optical/infrared (EO/IR) payload to be mounted on a high-speed and performance fighter aircraft in an external POD for acquiring daytime and nighttime image information on tactical targets, simulations, including flight environments and maneuvers, should be performed. Such simulations are pertinent to predicting the performance of several variables, such as aerodynamic force and inertia load acting on the payload. This paper describes the development of a flight data acquisition and analysis system based on flight simulation software (SW) for mission simulation of super-maneuverability fighter equipped with EO/IR payload. The effectiveness of the system is verified through comparison with actual flight data. The proposed flight data acquisition and analysis system based on FlightGear can be used as an M&S tool for system performance analysis in the development of the EO/IR payload.

• 한국항공우주학회지
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• 제33권7호
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• pp.85-91
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• 2005

군용항공기는 고받음각에서 적절한 조종성 및 항공기 이탈에 대한 안정성을 확보하고 있어야 한다. 고받음각에서 항공기가 이탈에 진입할 수 있는 한계값은 항공기 형상설계에 직결되는 문제이다. 하지만 현대의 고성능 전투기는 전기식 비행제어계통을 사용하여 고받음각 제어법칙을 설계함으로써 한계 값 내에서 항공기의 안정성을 보장하고 있으며 항공기가 이탈 시, 안전하게 회복할 수 있도록 고받음각 제어법칙을 설계한다. 현재 T-50에 적용되어 있는 고받음각 제어법칙은, 세로축 방향으로는 받음각 제한기 및 MPO(Manual Pitch Override) 모드, 가로-방향축으로는 고받음각 이탈제한기, 가로축 명령제한기, 방향축 조종사 명령제한기 및 스핀방지기가 설계되어 있다. 본 논문에서는 T-50 에 적용되어 있는 고받음각 제어법칙을 소개하며, 고받음각 비행시험을 통하여 항공기 안정성에 관한 연구를 수행하였다.