• International Journal of Aeronautical and Space Sciences
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• 제11권3호
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• pp.227-233
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• 2010

In this study, a genetic algorithm was utilized to optimize the stacking sequence of a composite plate subjected to a high velocity impact. The aim is to minimize the maximum backplane displacement of the plate. In the finite element model, we idealized the impactor using solid elements and modeled the composite plate by shell elements to reduce the analysis time. Various tests were carried out to investigate the effect of parameters in the genetic algorithm such as the type of variables, population size, number of discrete variables, and mutation probability.

• 한국정밀공학회:학술대회논문집
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• 한국정밀공학회 2010년도 춘계학술대회 논문집
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• pp.1255-1256
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• 2010

• International Journal of Aeronautical and Space Sciences
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• 제11권3호
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• pp.221-226
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• 2010

The failure of a Kevlar29/Phenolic composite plate under high-velocity impact from an fragment simulation projectile was investigated using the nonlinear explicit finite element code, LS-DYNA. The composite laminate and the impactor were idealized by solid elements, and the interface between the laminas was modeled as a tiebreak type in LS-DYNA. The interaction between the impactor and laminate was simulated using a surface-to-surface eroding contact algorithm. When the stress level meets the given failure criteria, the layer in the element is eroded. Numerical results were verified through existing test results and showed good agreement.

• 환경영향평가
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• 제12권3호
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• pp.211-228
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• 2003

Most environmental impact assessment(EIA) programs around the world require the consideration of human health impacts. Yet relatively few EIA documents adequately address those impacts. This article examines how, why, and to what extent health impacts are analyzed in environmental impact assessments. This article investigates these problems and provides recommendations to improve human health impact assessment(HIA), using methods, procedures and case study. Also, a comprehensive approach for the evaluation of possible health effects in an EIA is described, illustrated with the example of Amsterdam Airport Schiphol. Unlike many EIAs, we estimated quantitatively the impact of aircraft-related pollution in terms of the number of affected people for aircraft noise annoyance, odour annoyance and hypertension. In addition, an analysis of health registry data on cardiovascular and respiratory diseases and a short survey on annoyance and risk perception were carried out.

• Nuclear Engineering and Technology
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• 제50권8호
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• pp.1387-1401
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• 2018

An aircraft impact (AI) on a nuclear power plant (NPP) is considered to be a beyond-design-basis event that draws considerable attention in the nuclear field. As some NPPs have already adopted the seismic isolation technology, and there are relevant standards to guide the application of this technology in future NPPs, a new challenge is that nuclear power engineers have to determine a reasonable method for performing AI analysis of base-isolated NPPs. Hence, dynamic influences of the seismic isolation on the vibration and structural damage characteristics of the base-isolated CPR1000 containment are studied under various aircraft loads. Unlike the seismic case, the impact energy of AI is directly impacting on the superstructure. Under the coupled influence of the seismic isolation and the various AI load, the flexible isolation layer weakens the constraint function of the foundation on the superstructure, the results show that the seismic isolation bearings will produce a large horizontal deformation if the AI load is large enough, the acceleration response at the base-mat will also be significantly affected by the different horizontal stiffness of the isolation bearing. These concerns require consideration during the design of the seismic isolation system.

• Nuclear Engineering and Technology
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• 제54권4호
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• pp.1394-1405
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• 2022

The importance of ensuring the inherent safety and security has been more emphasized in recent years to demonstrate the integrity of nuclear facilities under external human-induced events (e.g. aircraft crashes). This work suggests a simulation methodology to effectively evaluate the impact of a commercial aircraft engine onto a dry storage facility. A full-scale engine model was developed and verified by Riera force-time history analysis. A reinforced concrete (RC) structure of a dry storage facility was also developed and material behavior of concrete was incorporated using three constitutive models namely: Continuous Surface Cap, Winfrith, and Karagozian & Case for comparison. Strain-based erosion limits for concrete were suitably defined and the local responses were then compared and analyzed with empirical formulas according to variations in impact velocity. The proposed methodology reasonably predicted such local damage modes of RC structure from the engine missile, and the analysis results agreed well with the calculations of empirical formulas. This research is expected to be helpful in reviewing the dry storage facility design and in the probabilistic risk assessment considering diverse impact scenarios.

• 한국전산구조공학회논문집
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• 제34권3호
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• pp.137-149
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• 2021

장교는 공공성이 매우 높은 사회기반시설물로 운용 중 안전성 확보가 필수적이며, 붕괴 또는 파손 시 신속한 대처가 필요하다. 사장교의 붕괴 또는 파손을 야기시킬 수 있는 원인은 크게 자연재난과 사회재난으로 분류할 수 있다. 이 중 사회재난에 속하는 충돌사고는 차량이 교량 하부구조인 교각에 충돌하는 사고, 항공기의 결함으로 인한 추락사고 등이 있을 것이며, 해상교량의 경우 주탑 하단에서의 선박 충돌사고가 있을 것이다. 본 연구에서는 수치해석적 접근법을 기반으로 항공기 충돌에 대한 사장교의 구조거동을 평가하는 절차를 제안하고, 충돌해석을 수행하여 절차의 타당성을 보였다. 제안된 절차에는 1) 적절한 항공기 충돌 시나리오 설정, 2) 사장교의 복잡한 거동 메커니즘을 고려한 구조 모델링, 3) 충돌해석을 통한 구조거동 평가가 포함된다. 해석 결과, 본 연구에서 설정한 시나리오는 대상 교량에 큰 영향을 미치지 못하는 것으로 나타났지만, 향후 다양한 시나리오를 통한 충돌해석을 수행한다면 교량에 심각한 손상을 일으키는 하중 위치 및 임계 하중 수준을 결정할 수 있을 것으로 판단한다. 본 연구에서 수행한 충돌해석 절차를 바탕으로 사장교에서 발생하는 항공기 충돌에 대한 간접적인 평가가 가능할 것으로 기대된다.

• Nuclear Engineering and Technology
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• 제49권2호
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• pp.411-425
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• 2017

Using a probabilistic safety assessment, a risk evaluation framework for an aircraft crash into an interim spent fuel storage facility is presented. Damage evaluation of a detailed generic cask model in a simplified building structure under an aircraft impact is discussed through a numerical structural analysis and an analytical fragility assessment. Sequences of the impact scenario are shown in a developed event tree, with uncertainties considered in the impact analysis and failure probabilities calculated. To evaluate the influence of parameters relevant to design safety, risks are estimated for three specification levels of cask and storage facility structures. The proposed assessment procedure includes the determination of the loading parameters, reference impact scenario, structural response analyses of facility walls, cask containment, and fuel assemblies, and a radiological consequence analysis with dose-risk estimation. The risk results for the proposed scenario in this study are expected to be small relative to those of design basis accidents for best-estimated conservative values. The importance of this framework is seen in its flexibility to evaluate the capability of the facility to withstand an aircraft impact and in its ability to anticipate potential realistic risks; the framework also provides insight into epistemic uncertainty in the available data and into the sensitivity of the design parameters for future research.

• 항공우주시스템공학회지
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• 제7권1호
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• pp.39-43
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• 2013

In this study, damage assesment and repair technique of aircraft adopted on Sandwich composite structure were performed. The sandwich composite structure were damaged by drop weight type impact test machine. The damaged sandwich composite structure was repaired using external patch repair method after removing damaged area. This study presents comparison results of the experimental investigation between the impact damaged and the repaired specimen.

• 한국전산구조공학회논문집
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• 제27권5호
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• pp.437-450
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• 2014

원전의 항공기 충돌 리스크 평가에 사용되는 대표매개변수를 선정하기 위한 방법론을 개발하였다. 대상 원전은 국내의 대표적인 경수로형 원전 중 하나로 선정하여 3차원 유한요소 해석 모델을 구축하였다. 콘크리트 재료모델에는 소성손상모델이 적용되었으며, 강재는 다중선형곡선거동을 가지는 것으로 모델링하였다. 운동에너지, 전체 충격량, 최대 충격량, 최대 하중등 4종의 대표매개변수 후보군을 선정하였다. 각각의 매개변수 후보군은 모두 충돌 속도와 질량의 함수로 표현되므로, 충돌속도 50~200m/s, 항공유량 30~90%의 범위에 대하여 매개변수값을 도출하고 충돌 해석을 수행하여, 충돌 시의 구조 응답과의 상관관계를 분석하였다. 모든 해석에서 항공기의 기종은 보잉767 기종으로 선정하였다. 충돌해석에는 Riera의 하중-시간 이력 함수를 이용한 해석기법을 적용하였다. 매개변수와 충돌 시 응답의 상관관계 적합성은 결정계수값을 이용하여 분석하였다. 4 종의 대표매개변수 후보군 중 최대 하중값이 가장 직관적일 뿐만 아니라 본 연구에서의 해석 케이스에서는 응답과의 상관성도 가장 뛰어난 것으로 나타남에 따라, 항공기충돌 리스크 평가를 위하여 가장 적합한 매개변수라 할 수 있을 것으로 판단되었다.