• 한국소음진동공학회논문집
• /
• 제15권6호
• /
• pp.718-723
• /
• 2005

The purpose of this study is to present a fundamental data for evaluating aircraft noise of building site development. By the field experiments and the predicted equal noise level contours using the INM program, actual condition in the building site development arranged district was investigated. In order to get the results, Analysis of factors effected on noise level, sound level on the rate of increase to aircraft demand and difference on the aircraft noise levels according to floor level in apartment house was carried out. As a result the influence of the take-off and landing direction were appeared greatly. The influences of the height at receiving point, movement number of aircraft and increase to aircraft demand were appeared small And the influence of 1 day average WECPNL must be considered.

• 환경영향평가
• /
• 제18권3호
• /
• pp.143-150
• /
• 2009

The present study investigates the effects of the flight paths of military aircraft on noise map and its WECPNL(Weighted Equivalent Continuous Perceived Noise Level) distribution. Aircraft noise modeling and simulation have been performed on a Korean military air base by means of INM(Integrated Noise Model) with the input data of airfield location, aircraft specifications, flight paths and aircraft's operation schedules. The result of noise modelling has been verified in comparison with the result of measured noise level. The flight path of military aircraft, as the key parameter of the present study, was modeled by combining takeoff, overfly, approach and touch-and-go modes. The present INM simulations have been conducted for various flight path cases with different takeoff, approach modes and overfly modes. The simulation results showed that the change of flight path can remarkably affect the noise influence region and the WECPNL distribution around the airfield.

• 경영과학
• /
• 제25권2호
• /
• pp.111-127
• /
• 2008

This paper analyzes the technological competitiveness of aircraft-based industries that are the basis for the development of aircraft industry in Korea. By performing expert interviews with industry specialists in the field of aircraft technology, the paper categorizes eight fields that are fundamental to the development of the aircraft industry. By analyzing patents of G7 countries and Korea made in the US from 1995 to 2006 we were able to identify the technological specificities and competencies of each country. RTA (Revealed Technology Advantage) index and CII (Current Impact Index) are used to examine the technological specificity and technological competence respectively. Finally, by introducing the TCI (Technological Competitiveness Index) the paper is able to consider both the quantitative level and the qualitative level of patents for each field in the aircraft industry. By analyzing the TCI, the paper concludes that Korea has high technological prowess centered around IT industries such as semi-conductors/ electronics component, communication appliances and consumer electronics. Also Korea is relatively competitive in the precision instruments industry.

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

• Structural Engineering and Mechanics
• /
• 제78권1호
• /
• pp.31-39
• /
• 2021

To investigate numerically the effect of all parameters on the outcome of an aircraft impact into robust engineering structures like nuclear power plant containments is a tedious task. In order to reduce the problem to a manageable size, we propose a single dimensionless parameter, the damage potential, to characterize the main features of the impact. The damage potential, which is the ratio of the initial kinetic energy of the aircraft to the work required to crush it, enables us to find the crucial parameter settings that need to be modelled numerically in detail. We show in this paper that the damage potential is indeed the most important parameter of the impact that determines the time-dependent reaction force when either finite element (FE) modelling or the Riera model is applied. We find that parameters that do not alter the damage potential, like elasticity of the target, are of secondary importance and if parameters are altered in a way that the damage potential remains the same then the course of the impact remains similar. We show, however, that the maximum value of the reaction force can be higher in case of elastic targets than in case of rigid targets due to the vibration of the target. The difference between the Riera and FE model results is also found to depend on the damage potential.

• 환경영향평가
• /
• 제21권6호
• /
• pp.893-901
• /
• 2012

Aircraft noise model such as FAA Integrated Noise Model(INM) has recently been used for forecasting the impact of noise in a residential area near an airport and quantifying the effect of various options for noise mitigation. The noise modeling should be reliable and precise in order to ensure the quality of the results provided. In this study, the validation of the noise levels simulated by the INM against measurement data recorded continuously at multiple monitoring sites was discussed. As a result of validation, the quality of the input data used as a fixed point profiles for the INM was enhanced. The noise contour maps were designed as a way to evaluate the aircraft noise of the vicinity of the airfield. The results of this study indicate that the validation of aircraft noise model by the measurement data would be required for the accurate assessment of the aircraft noise levels.

• 대한토목학회논문집
• /
• 제31권5A호
• /
• pp.369-378
• /
• 2011

본 논문은 RC(Reinforced Concrete), SC(Steel-Plate Concrete) 격납구조에 대한 대형 민항기 충돌에 관한 응답해석을 Hydrocode인 Autodyn-3D를 통해 수행하였다. 이전에 연구된 대부분의 항공기 충돌 해석에서의 충격 하중은 국부적인 부분(동체면적의 약 2배)에 대해 Riera의 충격하중함수를 적용하는 방법을 이용하여왔다. 하지만, 본 논문에서는 실제 Boeing 767과 유사한 모델을 구현하여 대상 구조체에 직접 충돌 시켜 나타나는 현상을 비교 분석 하였으며, 항공기 모델은 강성벽(Rigid Target)에 대해 항공기를 충돌 시켰을 시 발생되는 충돌하중이력곡선과, Riera 함수를 이용한 충돌하중이력곡선과의 비교를 통하여 검증하였다. 항공기 충돌 시, SC 격납구조에 대한 충돌저항능력 및 응답, 안전성 효과를 평가 하기 위해 무근 콘크리트(Plain Concrete:PC), 철근 콘크리트(Reinforced Concrete:RC), 철근 콘크리트와 완전 부착된 내부 Liner Plate(CLP:Containment Liner Plate), 그리고 SC 격납구조에 대한 해석을 수행하였다. 따라서 항공기 충돌과 같은 비정상충격하중이 RC구조와 SC구조에 가해질 경우에 대한 거동 예측이 가능하며, 보수적인 안전성이 요구되는 RC 원전 격납건물에 SC구조를 적용하면 상대적인 안전성 증대 효과를 기대 할 수 있을 것으로 보여진다.

• 한국소음진동공학회논문집
• /
• 제22권2호
• /
• pp.179-186
• /
• 2012

The potential hazards resulting from a low-velocity impact(bird-strike, tool drop, runway debris, etc.) on aircraft structures, such as engine nacelle or leading edges has been a long-term concern to the aircraft industry. Certification authorities require that exposed aircraft components must be tested to prove their capability to withstand low-velocity impact without suffering critical damage. In most of the past research studies unloaded specimens have been used for impact tests, however, in reality it is much more likely that a composite structure is exposed to a certain stress state when it is being impacted, which can have a significant effect on the impact performance. And the radiated impact sound induced by impact is analyzed for the damage detection evaluation. In this study, an investigation was undertaken to evaluate the effect in-plane loading on the impact force and sound of composite laminates numerically.

• 한국항공우주학회지
• /
• 제34권8호
• /
• pp.41-46
• /
• 2006

충격응답함수와 조정법(regularization methods)을 이용하여 항공기 날개의 충격하중 복원 가능성을 검토하였다. 충격하중에 대한 구조의 응답을 내타낼 수 있는 충격응답함수를 날개 유한요소모델의 강성과 질량 자료로 유도하였다. 일반적으로 부적합(ill-posed) 특성을 지닌 충격응답함수의 역행렬은 반복 Tikhonov 조종법(Iterative Tikhonov Regularization Method)과 일반화 특이치 분해법(Generalized Singular Value Decomposition Method)을 사용하여 구하였다. 수치적 입증을 위하여 전투기급 주익을 사용하였다. 해당 주익의 유한요소해석을 통하여 임의의 충격하중에 대한 변위와 변형률을 계산하였으며, 이를 충격응답함수로 계산한 결과와 비교하였다. 또한, 유한요소해석에서 계산된 변형률을 사용하여 충격하중을 복원하였다. 수치적 입증 결과 항공기 구조의 충격하중 모니터링이 본 방법으로 가능할 수 있음을 보여주었다.

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