• Nuclear Engineering and Technology
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• 제53권5호
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• pp.1686-1704
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• 2021

This study addresses the numerical simulation of the shield building of an AP1000 nuclear power plant (NPP) subjected to a large commercial aircraft impact. First, a simplified finite element model (F.E. model) of the large commercial Boeing 737 MAX 8 aircraft is established. The F.E. model of the AP1000 shield building is constructed, which is a reasonably simplified reinforced concrete structure. The effectiveness of both F.E. models is verified by the classical Riera method and the impact test of a 1/7.5 scaled GE-J79 engine model. Then, based on the verified F.E. models, the entire impact process of the aircraft on the shield building is simulated by the missile-target interaction method (coupled method) and by the ANSYS/LS-DYNA software, which is at different initial impact velocities and impact heights. Finally, the laws and characteristics of the aircraft impact force, residual velocity, kinetic energy, concrete damage, axial reinforcement stress, and perforated size are analyzed in detail. The results show that all of them increase with the addition to the initial impact velocity. The first four are not very sensitive to the impact height. The engine impact mainly contributes to the peak impact force, and the peak impact force is six times higher than that in the first stage. With increasing initial impact velocity, the maximum aircraft impact force rises linearly. The range of the tension and pressure of the reinforcement axial stress changes with the impact height. The perforated size increases with increasing impact height. The radial perforation area is almost insensitive to the initial impact velocity and impact height. The research of this study can provide help for engineers in designing AP1000 shield buildings.

• Nuclear Engineering and Technology
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• 제54권1호
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• pp.326-342
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• 2022

Comparative analyses of a shield building subjected to a large commercial aircraft impact between decoupling method and coupling method are performed in this paper. The decoupling method is applying impact force time-history curves on impact area of the shield building to study impact damage effects on structure. The coupling method is using a model including aircraft and shield building to perform simulation of the entire impact process. Impact force time-history curves of the fuselage, wing and engine and their total impact force time-history curve are obtained by the entire aircraft normally impacting the rigid wall. Taking aircraft structure and impact progress into account some loading areas are determined to perform some comparative analyses between decoupling method and coupling method, the calculation results including displacement, plastic strain of concrete and stress of steel plate in impact area are given. If the loading area is determined unreasonably, it will be difficult to assess impact damage of impact area even though the accurate impact force of each part of aircraft obtained already. The coupling method presented at last in this paper can more reasonably evaluate the dynamic response of the shield building than the decoupling methods used in the current nuclear engineering design.

• Nuclear Engineering and Technology
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• 제53권9호
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• pp.3085-3099
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• 2021

Investigations of large commercial aircraft impact effect on nuclear power plant (NPP) buildings have been drawing extensive attentions, particularly after the 9/11 event, and this paper aims to numerically assess the damage and vibrations of NPP buildings subjected to aircrafts crash. In Part I of present paper, two shots of reduce-scaled model test of aircraft impact on NPP were conducted based on the large rocket sled loading test platform. In the present part, the numerical simulations of both scaled and prototype aircraft impact on NPP buildings are further performed by adopting the commercial program LS-DYNA. Firstly, the refined finite element (FE) models of both scaled aircraft and NPP models in Part I are established, and the model impact test is numerically simulated. The validities of the adopted numerical algorithm, constitutive model and the corresponding parameters are verified based on the experimental NPP model damages and accelerations. Then, the refined simulations of prototype A380 aircraft impact on a hypothetical NPP building are further carried out. It indicates that the NPP building can totally withstand the impact of A380 at a velocity of 150 m/s, while the accompanied intensive vibrations may still lead to different levels of damage on the nuclear related equipment. Referring to the guideline NEI07-13, a maximum acceleration contour is plotted and the shock damage propagation distances under aircraft impact are assessed, which indicates that the nuclear equipment located within 11.5 m from the impact point may endure malfunction. Finally, by respectively considering the rigid and deformable impacts mainly induced by aircraft engine and fuselage, an improved Riera function is proposed to predict the impact force of aircraft A380.

• Nuclear Engineering and Technology
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• 제52권2호
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• pp.381-396
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• 2020

Investigations of the commercial aircraft impact effect on nuclear island infrastructures have been drawing extensive attention, and this paper aims to perform the safety assessment of Generation III nuclear power plant (NPP) buildings subjected to typical commercial aircrafts crash. At present Part I, finite element (FE) models establishment and validations for both the aircrafts and NPP buildings are performed. (i) Airbus A320 and A380 aircrafts are selected as the representative medium and large commercial aircrafts, and the corresponding fine FE models including the skin, beam, fuel and etc. are established. By comparing the numerically derived impact force time-histories with the existing published literatures, the rationality of aircrafts models is verified. (ii) Fine FE model of the Chinese Zhejiang Sanao NPP buildings is established, including the detailed structures and reinforcing arrangement of both the containment and auxiliary buildings. (iii) By numerically reproducing the existing 1/7.5 scaled aircraft model impact tests on steel plate reinforced concrete (SC) panels and assessing the impact process and velocity time-history of aircraft model, as well as the damage and the maximum deflection of SC panels, the applicability of the existing three concrete constitutive models (i.e., K&C, Winfrith and CSC) are evaluated and the superiority of Winfrith model for SC panels under deformable missile impact is verified. The present work can provide beneficial reference for the integral aircraft crash analyses and structural damage assessment in the following two parts of this paper.

• Nuclear Engineering and Technology
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• 제52권2호
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• pp.417-428
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• 2020

Investigations of the commercial aircraft impact effect on nuclear island infrastructures have been drawing extensive attention, and this paper aims to perform the safety assessment of Generation III nuclear power plant (NPP) buildings subjected to typical commercial aircrafts crash. At present Part III, the local damage of the rigid components of aircraft, e.g., engine and landing gear, impacting the steel concrete (SC) structures of NPP containment is mainly discussed. Two typical SC target panels with the thicknesses of 40 mm and 100 mm, as well as the steel cylindrical projectile with a mass of 2.15 kg and a diameter of 80 mm are fabricated. By using a large-caliber air gas gun, both the projectile penetration and perforation test are conducted, in which the striking velocities were ranged from 96 m/s to 157 m/s. The bulging velocity and the maximal deflection of rear steel plate, as well as penetration depth of projectile are derived, and the local deformation and failure modes of SC panels are assessed experimentally. Then, the commercial finite element program LS-DYNA is utilized to perform the numerical simulations, by comparisons with the experimental and simulated projectile impact process and SC panel damage, the numerical algorithm, constitutive models and the corresponding parameters are verified. The present work can provide helpful references for the evaluation of the local impact resistance of NPP buildings against the aircraft engine.

• 항공우주정책ㆍ법학회지
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• 제29권2호
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• pp.3-54
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• 2014

오랜 논의와 노력 끝에 우리나라 상법 제6편 항공운송편이 신설되어 2011년 11월부터 시행되었다. 상법 항공운송편은 국내항공운송으로 인해 발생한 항공 운송인의 손해배상책임 문제와 항공기 운항으로 인해 발생한 지상 제3자에 대한 항공기운항자의 손해배상책임 문제 등을 규율하기 위해 제정되었다. 상법 항공운송편은 관련 국제 조약들과 항공선진국들의 국내입법을 충분히 비교 검토하여 우리 법으로 수용하였기 때문에 국제 기준에 부합한다는 장점도 있지만, 항공기운항자의 지상 제3자에 대한 손해배상책임 규정을 중심으로 다음과 같이 개선해야 할 내용들도 포함하고 있다. 첫째, 상법 항공운송편상 항공기운항자의 지상 제3자 손해에 대한 배상책임 한도액은 피해자에 대한 적절한 배상을 하기에는 너무 낮은 수준으로 규정되어 있어 상향될 필요성이 있다. 따라서 독일과 같이 2009년 체결된 일반위험협약 및 불법방해배상협약의 관련 내용을 수용하여 항공기의 중량에 따른 분류기준을 10단계로 세분화하고 총 책임한도액을 최대 7억 SDR까지 상향시키면서, 인적 손해에 대한 배상책임한도액은 기존의 법무부 검토안처럼 최근의 물가상승률을 반영하여 현 규정의 5배 수준인 1인당 62만5천SDR까지 상향 조정하는 방안을 생각해 볼 수 있다. 이 방안이 한 사고당 항공사에게 일반적으로 보험으로서 보장되는 단일배상책임한도액이나 다양화 된 항공기 제원을 반영하면서도 지상 제3자에게 현실에 맞는 적절한 손해배상을 할 수 있다는 점에서 가장 바람직하다고 본다. 둘째, 항공기운항자는 현 상법 항공운송편상 항공기 납치 공격이나 9 11 테러와 같은 항공기를 이용한 공격행위 등과 같은 항공기테러에 의한 지상 제3자의 손해에 대하여도 무과실책임을 부담한다. 이에 관하여는 항공기운항자에게 지나치게 가혹하고 불합리한 입법이라는 견해가 있지만, 항공기운항자에게도 일정 부분 테러를 방지할 법적 의무가 있고 피해를 입은 제3자 구제 측면에서 그것이 항공기운항자에게 지나치게 가혹하거나 불합리하다고 생각되지는 않는다. 그러나 9 11테러와 같이 조직화 된 테러단체에 의해 항공기가 테러에 이용되어 지상 제3자 피해가 발생한 경우에도 항공기운항자가 피해자들에게 무과실책임을 지도록 하는 것은 불합리하며, 이러한 경우에는 항공기운항자의 책임이 면제되는 방향으로 상법 항공운송편 규정은 개정되어야 할 것이다. 셋째, 항공기사고와 같은 항공기 운항으로 인한 피해의 엄청난 규모를 고려해 볼 때, 다수의 피해자들이 경제적 어려움에 직면할 수 있으므로 항공여객의 인적 손해에 대한 항공운송인의 배상책임 발생 시 적용되는 선급금 지급 규정을 항공기운항자의 책임 발생 사례에도 준용할 필요가 있다고 본다. 넷째, 현행 상법 항공운송편상 항공기운항자의 손해배상책임 규정은 항공기 운항으로 인한 피해가 지상 또는 수면 및 수중에서 발생된 경우에만 적용되고 공중에서 발생한 피해에는 적용되지 않는다. 하지만 다른 항공기의 운항으로 인한 공중에서 발생된 항공기 등의 손해가 지상이나 수면 및 수중에서 발생한 손해와 차이가 있다고 볼 수 없다. 그러므로 상법 항공운송편상 '지상 제3자'라는 용어에서 '지상'이란 용어를 삭제하여 다른 항공기 운항으로 인한 공중에서의 항공기 등의 손해에도 상법 항공운송편상 항공기운항자의 지상 제3자 손해 배상책임 관련 규정이 적용될 수 있게 하는 것이 바람직하다고 본다. 위에서 제시된 상법 항공운송편상 항공기운항자의 지상 제3자 손해에 대한 배상책임 관련 규정의 개선방안 검토와 동 규정의 보완을 위한 지속적인 관심과 노력을 통하여, 상법 항공운송편이 피해를 입은 지상 등의 제3자에게 현실에 맞는 적절한 배상을 할 수 있게 하면서도 항공기운항자에게 과도한 부담을 지우지 않는 상호 간의 이익 균형상 더욱 바람직한 방향으로 발전되기를 희망한다.

• 항공우주산업기술동향
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• 제7권2호
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• pp.95-105
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• 2009

연료전지는 소음이 낮고$CO_2$ 배출이 없는 친환경적 특성을 기반으로 항공기 추진시스템에 적용되고 있으며, 현재 연료전지를 탑재한 여러 종류의 무인항공기와 소형 유인항공기 개발이 진행되고 있다. 항공기용 연료전지는 대표적으로 PEMFC(Proton Exchange Membrane Fuel Cell)방식과 SOFC(Solid Oxide Fuel Cell) 방식으로 분류되며, 항공기의 임무 및 운용조건에 적합한 연료전지 시스템이 개발되고 있다. 무인항공기의 경우 대부분 PEM 연료전지 기술을 기반으로 군용 또는 상용으로 활용할 수 있는 다양한 형태와 크기의 항공기가 개발되고 있으며, 시스템의 안정성과 운용시간이 더욱 향상될 것이다. 소형 유인항공기에서는 추진시스템을 연료전지로 대체하기 위한 많은 연구가 수행되고 있으며, 또한 대형 상용 항공기의 보조동력장치(APU)에 연료전지를 적용하여 성능을 높이기 위한 개발이 진행되고 있다. 향후, 연료전지항공기는 연료전지의 전력밀도 증가와 더불어 신뢰성과 효율을 더욱 향상시킬 것으로 기대된다.

• Nuclear Engineering and Technology
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• 제53권6호
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• pp.1858-1868
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• 2021

Resisting an accidental impact of large commercial aircrafts is an important aspect of advanced nuclear power plant (NPP) design. Especially after the 9·11 event, some regulations were enacted, which required the design of NPPs should consider the accidental impact of large commercial aircrafts. Normal working of equipment is important for stopping reactor under an impact when an NPP is in operation. However, there is a lack of reliable analysis and research on the impact test of nuclear prototype equipment. Therefore, in order to study the response of the equipment under high acceleration impact, a centrifugal pump is selected as the research object to perform the impact test. A horizontal half-sinusoidal pulse wave was applied to the working pump. The test results show that the horizontal response of the motor and flange is greater compared to other parts, as well as the vertical response of the coupling. The stress response of the pump body support and motor support is high, hence these parts should be considered in the design of the pump. Finally, combined with the damage and stress evaluation results of the pump under different amplitudes, the ultimate impact acceleration that the pump can withstand is given.

• Nuclear Engineering and Technology
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• 제53권9호
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• pp.3068-3084
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• 2021

Investigations of large commercial aircraft impact effect on nuclear power plant (NPP) buildings have been drawing extensive attentions, particularly after the 9/11 event, and this paper aims to experimentally assess the damage and vibrations of NPP buildings subjected to aircraft crash. In present Part I, two shots of reduce-scaled model test of aircraft impacting on NPP building were carried out. Firstly, the 1:15 aircraft model (weighs 135 kg) and RC NPP model (weighs about 70 t) are designed and prepared. Then, based on the large rocket sled loading test platform, the aircraft models were accelerated to impact perpendicularly on the two sides of NPP model, i.e., containment and auxiliary buildings, with a velocity of about 170 m/s. The strain-time histories of rebars within the impact area and acceleration-time histories of each floor of NPP model are derived from the pre-arranged twenty-one strain gauges and twenty tri-axial accelerometers, and the whole impact processes were recorded by three high-speed cameras. The local penetration and perforation failure modes occurred respectively in the collision scenarios of containment and auxiliary buildings, and some suggestions for the NPP design are given. The maximum acceleration in the 1:15 scaled tests is 1785.73 g, and thus the corresponding maximum resultant acceleration in a prototype impact might be about 119 g, which poses a potential threat to the nuclear equipment. Furthermore, it was found that the nonlinear decrease of vibrations along the height was well reflected by the variations of both the maximum resultant vibrations and Cumulative Absolute Velocity (CAV). The present experimental work on the damage and dynamic responses of NPP structure under aircraft impact is firstly presented, which could provide a benchmark basis for further safety assessments of prototype NPP structure as well as inner systems and components against aircraft crash.

• 대기
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• 제32권4호
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• pp.323-340
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• 2022

We analyzed the high-resolution wind data of Aircraft-Based Observation from the Mode-Selective Enhanced Surveillance (Mode-S EHS) data in Korea. For assessment of its quality, the Mode-S wind data was compared with the ECMWF ReAnalysis 5 (ERA5) reanalysis and Aircraft Meteorological Data Relay (AMDAR) data for more than 3-months from 7 May 2021 to 24 August 2021 near Incheon International Airport, Korea. Considering that the AMDAR reports are not provided by all commercial aircraft, total number of the Mode-S derived wind data with a second sampling rate was about twice larger than that of available AMDAR wind data. After the quality control procedures by removing erroneous samples, it was found that the root mean square errors (RMSEs) of the Mode-S retrieved winds are similar to that from the AMDAR winds. In particular, between 550 and 650 hPa levels, RMSE of the Mode-S (AMDAR) zonal wind against ERA5 data was about 2.3 m s^-1 (1.9 m s^-1), and those increased to 3.3 m s^-1 (2.4 m s^-1) in 200~500 hPa levels. A similar trend was found in the meridional wind, but a distinct positive mean bias of 2.16 m s^-1 was observed between 875 and 1,000 hPa levels. Winds retrieved from the Mode-S also showed a good agreement directly with AMDAR data. As the Mode-S provides a large amount of data with a reliable quality, it can be useful for both data assimilation in the numerical weather prediction model and situational awareness of wind and turbulence for aviation safety in Korea.