• 한국항공운항학회지
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• 제30권1호
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• pp.12-19
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• 2022

The exhaust wake of an aircraft engine is discharged in a high temperature and high speed, which can damage objects such as an aircraft in the rear. The exhaust wake can lift small foreign substances lying on the ground or falling off, and the floating foreign substances can enter the intake duct of the aircraft moving from the rear and cause engine FOD (Foreign Object Damage). This study experimentally analyzed how the engine exhaust wake generated from military jet fighters affects the movement of foreign substances and evaluated the effects of foreign substances on the damaged area by measuring wake velocity. The simulation and field experimental results confirmed that the effect of exhaust wake increases as the rear position closer, and that foreign substances lifted by the wake can act as FOD to the adjacent rear aircraft.

• 한국항공운항학회지
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• 제22권1호
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• pp.130-135
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• 2014

FOD(Foreign Object Debris) has the potential threat to damage aircraft during critical phases of take-off and landing roll with some objects including metal on the runway. FOD can be found anywhere on an airport's air operation areas such as runway, taxiway and apron. It can lead to catastrophic loss of life and airframe, and increased maintenance and operating costs. In this paper, we defined FOD and surveyed its riskiness and necessity of automatic FOD detection system. We compared the requirements of the environment in Korea to the FAA advisory circular. Also we analyzed operation methods of FOD detection systems already installed at some airports. Based on the surveys mentioned above, we propose hybrid type of FOD detection system considering the environment in Korea which uses millimeter wave radar, optical camera and thermal imaging camera to detect FOD efficiently. In management approach, fixed type of the system should be installed for real-time monitoring, and mobile type of the system can be used additionally.

• 한국항행학회논문지
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• 제20권3호
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• pp.210-217
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• 2016

전 세계 공항의 이동지역 내 이물질인 FOD (foreign object defective)에 의한 피해 량이 연간 2억불에 달하고 있다. 2000년 샤를드골 공항에서는 FOD로 인한 133명의 인명피해가 발생하기도 했다. 국내에도 각 공항별로 FOD로 인한 사고발생 및 장비의 수리 등 직 간접적인 피해가 발생하고 있는 상황이다. 이에 항공안전기술개발 사업의 일환으로 공항 내 항공기 이동지역 이물질 자동탐지 시스템의 개발이 진행 중에 있다. 분석 결과에 의하면 운용 방식의 특성상 민간 공항의 경우 고정식 감시를 요구했고 군 공항은 이동식을 선호했다. 본 논문에서는 군 민간 FOD 탐지 시스템의 요구조건을 파악하여 국내 조건에 맞는 최소 성능 사양을 분석하였다.

• 한국추진공학회지
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• 제11권3호
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• pp.58-64
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• 2007

항공기 엔진 흡입구는 개발시에 조류 충돌에 대한 충분한 안전성을 검토하여 설계 되어야 한다. 항공기의 속도가 점차 증가함에 따라 FOD(Foreign object damage)에 따른 항공기의 사고가 증가하고 있다. 특히 이착륙시 활주로 주변 새들에 의한 항공기 사고는 경제적 손실을 비롯해 탑승객의 생명과 연결되는 중요한 문제이다. 본 연구에서는 유한 요소 상용 코드인 MSC/DYTRAN을 이용해 엔진 흡입구 낫셀 구조에 대한 조류 충돌 해석을 수행하였다. 해석 결과의 타당성 검증을 위해 선행 연구 결과와 비교한 후 조류 충돌 해석 결과의 거동을 분석하였다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2007년도 제28회 춘계학술대회논문집
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• pp.67-70
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• 2007

항공기 엔진 흡입구는 개발시에 조류 충돌에 대한 충분한 안전성을 검토하여 설계되어야 한다 항공기의 속도가 점차 증가함에 따라 FOD(Foreign object damage)에 따른 항공기의 사고가 증가하고 있다. 특히 이착륙시 활주로 주변 새들에 의한 항공기 사고는 경제적 손실을 비롯해 탑승객의 생명과 연결되는 중요한 문제이다 본 연구에서는 유한 요소 상용 코드인 MSC/DYTRAN을 이용해 엔진 흡입구 낫셀 구조에 대한 조류 충돌 해석을 수행하였다. 해석 결과의 타당성 검증을 위해 선행 연구 결과와 비교한 후 조류 충돌 해석 결과의 거동을 분석하였다.

• 한국안전학회지
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• 제18권2호
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• pp.34-39
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• 2003

In this paper, when CF/PEEK laminates for high efficiency space structure are subjected to FOD(Foreign Object Damage), the effects of temperature change on the impact damages(interlaminar separation and transverse crack) of CF/PEEK laminates and the relationship between residual lift and impact damages are experimentally investigated. Composite laminates used in this experiment are CF/PEEK orthotropic laminated plates, which have two-interlaces [$0^{\circ}_4/90^{\circ}_8/0^{\circ}_4$]. A steel ball launched by the air gun collides against CF/PEEK laminates to generate impact damages. And then CF/PEEK specimens with impact damages are observed by a scanning acoustic microscope under room and high temperatures. In this experimental results, various relations are experimentally observed including the delamination area vs. temperature change, the bending strength vs. impact energy and the residual bending strength vs. impact damage of CF/PEEK laminates.

• 한국자동차공학회논문집
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• 제2권6호
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• pp.66-75
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• 1994

In this paper, the effects of temperature change on the impact damages of CF/PEEK laminates are experimentally investigated. Composite laminates used in this experiment are CF/PEEK orthotropic laminated plates, which have two-interfaces$[0^{\circ}_4/90^{\circ}_4]_{9+} A steel ball launched by the air gun collides against CFRP laminates to generate impact damage. The delamination damages are oberved by a scanning acoustic microscope. And various relations are experimentally observed including the impact energy vs. delamination area, the specimen temperature vs. transverse crack, and the impact energy vs. residual bending strength of carbon fiber peek composite laminates subjected to FOD(Foreign Object Damage) under high temperatures.

• 대한기계학회논문집
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• 제18권8호
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• pp.1930-1938
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• 1994

In this paper, the effects of temperature change on the impact of CFRP laminates was experimentally studied. Composite laminates used for this experiment are CFRP orthotropic laminated plates, which have two-interfaces$[0_6^{\circ}/90_7^{\circ}]_s$ and four-interfaces$[0_3^{\circ}/90_6^{\circ}/0_3^{\circ}]_s$. The interrelations between the impact energy vs. delamination area, the impact energy vs. residual bending strength, and the interlayer delamination area vs. the decrease of the residual flexural strength of carbon fiber epoxy composite laminates subjected to FOD(Foreign Object Damage) under high temperatures were experimentally observed.

• 한국안전학회지
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• 제11권3호
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• pp.44-52
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• 1996

An experimental study on the effects of temperature change on the impact damages of CFRP aminates was made through an observation of the interrelations between the Impact energy vs. delamination area, the impact energy vs. residual bending strength, and the delamination area vs. the decreasing of the residual bending strength for CF/EPOXY and CF/PEEK composite laminates subjected to FOD (Foreign Object Damage) under high temperatures.

• 항공우주시스템공학회지
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• 제2권2호
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• pp.1-7
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• 2008

Recently the wind energy has been alternatively used as a renewable energy resource instead of the mostly used fossil fuel due to its lack and environmental issues. This work is to propose a structural design and analysis procedure for development of the low noise 100W class small wind turbine system which will be applicable to relatively low speed region like Korea and for the domestic use. Structural analysis including load cases, stress, deformation, buckling, vibration and fatigue life was performed using the Finite Element Method, the load spectrum analysis and the Miner rule. In order to evaluate the designed structure, the structural test was carried out and its test results were compared with the estimated results. In addition, the blade should be safe from the impact damage due to FOD(Foreign Object Damage) including the bird strike. In order to analize the bird strike penomena on the blade, MSC. Dytran was used, and the applied method Arbitrary Lagrangian-Eulerian was evalud by comparison with the previous study results.