• 한국정밀공학회지
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• 제29권6호
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• pp.654-663
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• 2012

Damage induced by low velocity impact loading in aircraft composite is the form of failure which is frequently occurred in aircraft. As the consequences of impact loading in composite laminates, matrix cracking, delamination and eventually fiber breakage for higher impact energies can be occurred. Even when no visible impact damage is observed, damage can exist inside of composite laminates and carrying load of the composite laminates is considerably reduced. The objective of this study is to evaluate and predict residual strength behavior of composite laminates by impact loading and for this, tensile test after impact was carried out on composite laminates made of woven CFRP.

• 한국전산구조공학회논문집
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• 제26권2호
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• pp.157-164
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• 2013

본 연구에서는 여객용 항공기 충돌 시 강섬유보강콘크리트를 사용한 철근콘크리트 원전 격납건물의 구조적 거동을 유한요소해석을 이용하여 고찰한다. 항공기 충돌에 의해 원전 격납건물에 가해지는 하중은 Riera 충격하중 시간함수와 충돌 시 접촉면적을 이용하여 모델링하였다. 강섬유보강콘크리트의 재료모델은 CSCM Concrete Model을 사용하였다. 기존에 제안된 강섬유보강콘크리트의 강도예상모델을 이용하여 재료모델의 입력변수를 결정하였다. 강섬유의 함유량에 따른 원전 격납 건물의 항공기 충돌에 대한 구조적 거동을 상용 유한요소 해석 프로그램인 LS-DYNA를 이용하여 해석하였다. 해석결과를 바탕으로 항공기 충돌에 대한 저항성을 평가하였으며, 보수적인 안전성이 요구되는 원전 격납건물에 강섬유보강콘크리트를 적용할 경우 항공기 충돌에 대한 저항성 증대 효과를 기대할 수 있는 것으로 고찰되었다.

• Composites Research
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• 제25권4호
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• pp.105-109
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• 2012

최근 국내에서 미국과 상호항공안전협정 체결을 위한 소형 항공기가 연구 개발 중이다. 연구 대상 항공기는 경량화 하여 연료 절감을 위해 전기체 복합재료가 적용되었다. 그러나 복합재 구조는 외부의 충격 손상에 취약한 구조이다. 따라서 항공기 구조물은 충격 손상에 대한 압축 파손 강도를 고려하여 손상 허용 설계가 반드시 수행되어야 한다. 이는 복합재 구조 항공기 인증에 매우 중요한 요소이다. 본 연구에서는 항공기 복합재 구조에 적용된 두꺼운 적층판에 대한 손상 허용 연구를 수행하였다. 두꺼운 적층판의 세 가지 형태인 손상이 없는 시편, 구멍 손상 및 충격 손상이 적용된 시편의 압축 하중 하에서 손상 허용 기준이 평가되었다.

• 한국항공우주학회지
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• 제38권9호
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• pp.862-868
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• 2010

국내에서 미국과 상호항공안전협정 체결을 위해 소형 항공기를 개발 중이다. 연구 대상 항공기는 경량화를 위하여 전기체 복합재료가 적용되었다. 그러나 복합재 구조는 충격 손상에 취약하다. 따라서 본 연구에서는 항공기 복합재 구조의 손상 평가 및 유지 보수 기법 연구를 수행하였다. 탄소/에폭시 UD 라미네이트와 탄소/에폭시 패브릭 스킨-허니컴코어 샌드위치 복합재 라미네이트의 손상은 중량 낙하식 충격 시험기를 활용하여 모사되었으며 손상된 시편은 손상 부위 제거 후 외부 패치 적용 방안을 적용하여 수리하였다. 손상 전 시편, 손상 후 시편, 유지 보수된 시편의 압축 강도 시험 및 해석 결과를 비교하였다. 그리고 마지막으로 유지 보수 후 강도 복원 능력이 평가되었다.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2014년도 추계학술대회 논문집
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• pp.701-703
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• 2014

The intense noise generated by military aircraft hans a significant impact on ground crews and their families on airbase. For minimizing the impact of the aircraft noise on the airport, appropriate indoor noise standard is required. This paper studied to establish the indoor noise standard on the military airport. The aircraft noise was measured and analyzed the frequence characteristics. the remodeling of office for the noise mitigation was enforced to verify the appropriate internal noise standard and to select the method of reinforcement. The noise standard was classified three categories according to the dwelling, office and usage of building with flight train facilities and banishment in military airfield.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 1997년도 춘계학술대회논문집; 경주코오롱호텔; 22-23 May 1997
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• pp.388-393
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• 1997

As the aircraft noise become the serious matter nowadays, registrations controlling the noise emission from aircraft are established to set up noise protection areas such as residential buildings and schools. Several methods are used to assess the noise impact of an airport on its surroundings. WECPNL is used as the aircraft legislation noise index in Korea and in Japan. In this paper, experiments were made to assess the total noise impact of Kwangju airport area by using WECPNL. Also restrictions related to buildings in this area and grants were reviewed to improve building attention in the inner zone.

• 한국항공운항학회지
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• 제18권1호
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• pp.58-63
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• 2010

Introduction : Head trauma is the main cause of death in aircraft crash. In a Michigan study of structurally survivable, fatal accidents, 80% of the fatally injured had received head trauma. We tried to develop a new helmet for passengers, and perform its efficiency test. Methods : An aircraft helmet requires an excellent protection against head trauma, lightness, and small volumes. In addition, it must be wearable, fire resistant, and non toxic when it is burning. We developed two new helmets made from silicone foam which met all theses requirements. One was thin (2.5cm), and the other was thick (6.3cm). These looked like a motorcycle helmet and had only a soft silicone as liner material without an outer hard shell. Therefore we can carry them easily inside aircrafts. The standard test for helmet is Snell's drop test. It measures the impact acceleration of head shaped metal wearing helmet during we drop it at certain heights. Impact sites were total 5 sites (front, back, right, left and top) for each helmet. All these sites were impacted twice. Results : The thickness of impact sites varied from 2.5cm to 6.3cm. The impact acceleration of 2.5cm thickness site when it was dropped from 1.0 meter was 379g. But, that of 6.3cm thickness site when it was dropped from 1.5 meter was only 163g. Unfortunately, both helmets didn't meet the Snell Standard for motorcycle helmets. Discussion : If we add suitable outer hard shell, and change its thickness and design, the efficiency will be increased. A study indicated that helmet could reduce the risk of head trauma up to 85%. We made helmet for passengers in aircraft crash for the first time. If we improve its weak points, it will decrease the frequency of head trauma in aircraft craft.

• Smart Structures and Systems
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• 제6권2호
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• pp.147-165
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• 2010

Impact damage detection in composite structures has gained a considerable interest in many engineering areas. The capability to detect damage at the early stages reduces any risk of catastrophic failure. This paper compares two advanced signal processing methods for impact location in composite aircraft structures. The first method is based on a modified triangulation procedure and Genetic Algorithms whereas the second technique applies Artificial Neural Networks. A series of impacts is performed experimentally on a composite aircraft wing-box structure instrumented with low-profile, bonded piezoceramic sensors. The strain data are used for learning in the Neural Network approach. The triangulation procedure utilises the same data to establish impact velocities for various angles of strain wave propagation. The study demonstrates that both approaches are capable of good impact location estimates in this complex structure.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 1998년도 춘계학술대회논문집; 용평리조트 타워콘도, 21-22 May 1998
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• pp.728-734
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• 1998

Aircraft noise is one of the main causes of environmental impact. It is more serious than any other noise nuisance. It has become an increasing source of annoyance to the large number of people who live in communities near airports. This paper demonstrates the prediction of aircraft noise using Integrated Noise Model(INM) 5.1 developed by U.S. FAA and aircraft noise contour map near airports.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2000년도 춘계학술대회논문집
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• pp.110-116
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• 2000

Aircraft noise is one of the main causes of environmental impact. It is more serious than any other noise nuisance. It has become an increasing source of annoyance to the large number of people who live in communities near airports. This paper demonstrates the prediction of aircraft noise using Integrated Noise Model (INM) 5.1 developed by U.S. FAA and aircraft noise contour map near airports.