• 한국항공운항학회지
• /
• 제17권3호
• /
• pp.32-39
• /
• 2009

Due to the lack of navigable airspace caused by worldwide air traffic increases, air traffic control(ATC) services are becoming more complex, which results in the increase of aircraft accidents. To cope with these challenges, major aviation institutes abroad are actively conducting research regarding the human factors affecting controllers but as of late, no such specialized activities have been found in Korea. Due to the dynamic attributes of ATC operations, management of controller's situation awareness(SA) and workload, and knowledge on the impact of abnormal aircraft to controllers are very important. Furthermore, using actual flight data of each country will lead to valuable results, because individually, it has different airspace characteristics and air traffic volumes. This study assumed that air traffic difficulties would affect the controller's SA and workload. To testify the above hypothesis, the abnormal air traffic situations are simulated by using ATC simulator. The findings indicated that the effect of traffic situations containing abnormal aircraft on the controller's SA and workload, it led to demand increase and supply decrease in SA, and increased mental demand, temporal demand, effort and mean workload score in the workload.

• Structural Engineering and Mechanics
• /
• 제53권1호
• /
• pp.73-87
• /
• 2015

In case of aircraft impact on nuclear containment structures, the initial kinetic energy of the aircraft is transferred and absorbed by the outer containment, may causing either complete or partial failure of containment structure. In the present study safety analysis of BWR Mark III type containment has been performed. The total height of containment is 67 m. It has a circular wall with monolithic dome of 21m diameter. Crash analysis has been performed for fighter jet Phantom F4. A normal hit at the crown of containment dome has been considered. Numerical simulations have been carried out using finite element code ABAQUS/Explicit. Concrete Damage Plasticity model have been incorporated to simulate the behaviour of concrete at high strain rate, while Johnson-Cook elasto-visco model of ductile metals have been used for steel reinforcement. Maximum deformation in the containment building has reported as 33.35 mm against crash of Phantom F4. Deformations in concrete and reinforcements have been localised to the impact region. Moreover, no significant global damage has been observed in structure. It may be concluded from the present study that at higher velocity of aircraft perforation of the structure may happen.

• International Journal of Aeronautical and Space Sciences
• /
• 제16권3호
• /
• pp.394-406
• /
• 2015

In this work, an efficient aircraft landing simulation strategy is proposed to develop an efficient and reliable hard-landing monitoring procedure. Landing stage is the most dangerous moment during operation cycle of aircraft and it may cause structural damage when hard-landing occurs. Therefore, the occurrence of hard-landing should be reported accurately to guarantee the structural integrity of aircraft. In order to accurately determine whether hard-landing occurs or not from given landing conditions, full nonlinear structural dynamic simulation can be performed, but this approach is highly time-consuming. Thus, a more efficient approach for aircraft landing simulation which uses a hierarchical aircraft landing model and an extended inertia relief technique is proposed. The proposed aircraft landing model is composed of a multi-body dynamics model equipped with landing gear and tire models to extract the impact force and inertia force at touch-down and a linear dynamic structural model with an extended inertia relief method to analyze the structural response subject to the prescribed rigid body motion and the forces extracted from the multi-body dynamics model. The numerical examples show the efficiency and practical advantages of the proposed landing model as an essential component of aircraft hard-landing monitoring procedure.

• 한국환경보건학회지
• /
• 제49권3호
• /
• pp.129-133
• /
• 2023

Background: With the rise in global mobility, aircraft indoor air quality has become a significant public health concern. This study focuses on the health implications of increased travel and bleed air-air drawn from aircraft engines for cabin pressurization and air conditioning. Objectives: This research aims to review the potential health effects related to exposure to aircraft cabin air, particularly the effects of bleed air during fume events. Methods: We conducted a literature review of existing studies on aircraft cabin air quality. We focused on both the immediate and health effects of exposure to cabin air, particularly those related to bleed air contaminants. Results: The review found a possible link between exposure to aircraft cabin air and certain health issues, especially in cabin crew and frequent flyers. There was an increased incidence of respiratory and neurological symptoms related to bleed air exposure. However, the cumulative health effects of frequent air travel remain inconclusive due to limited data. Conclusions: This study highlights the need for improving air quality in aircraft to protect public health. While further research is needed to understand the cumulative effects of frequent air travel, the reduction of exposure to bleed air contaminants should be a priority. These findings underline the need for regulatory changes and technological improvements in aircraft cabin air quality.

• 한국항행학회논문지
• /
• 제19권4호
• /
• pp.278-287
• /
• 2015

항공기 배기가스가 지구의 현재와 미래의 기후에 미치는 잠재적 영향력은 항공산업계가 당면하고 있는 매우 중요한 환경 이슈 중 하나이다. 온실가스 배출의 잠재적 악영향에 대한 우려가 증가함에 따라 항공기의 배기가스 배출을 줄이고 기후에 관한 항공기의 영향을 완화하는 수단 중 하나로 항공기 배기가스를 산정하고 예측하는 시스템 개발의 필요성이 제기되고 있다. 따라서 본 연구에서는 영국 Lissys사에서 개발한 Piano-X 소프트웨어를 사용하여 3가지 항공기 급에 대한 다양한 비행거리와 경로에 대해 유상하중의 변화에 따른 항공기 온실가스 배출량을 산정하였다. 다양한 항속거리와 고도에 따른 경제속도, 장거리 순항속도, 최대 운항거리 속도에 대해 연료소모량도 분석하였다.

• 한국압력기기공학회 논문집
• /
• 제18권2호
• /
• pp.50-53
• /
• 2022

To investigate the validity of the finite element analysis program to assess structural integrity of a spent nuclear fuel transport cask subjected to extreme impact loads, structural integrity of the cask for the case of an aircraft engine collision is evaluated using three FE analysis programs: Autodyn, Speed and ABAQUS explicit version. As a result of all analyses, it is confirmed that no penetration occurred in the cask wall. Even though the different programs are used, it is identified that there are insignificant differences in the FE analysis variables such as von Mises effective stress and equivalent plastic strain among the programs.

• Advances in aircraft and spacecraft science
• /
• 제10권6호
• /
• pp.555-572
• /
• 2023

Airplanes in flight collide with raindrops, and the leading edges of the airframe can be damaged when colliding with raindrops. A single waterjet testing platform was created to study rain erosion damage. Carbon fiber samples with three types of skins were studied and the mechanical properties were measured using a nanoindentation instrument. The research results show that the impact force on the sample increases with the continuous increase in the impact speed of raindrops, which leads to an increase in the damage area. Sheathing with low surface roughness is more damaged than other sheathings due to its rougher surface, and the result proves that surface roughness has a more significant effect on rain erosion damage to sheathings compared to their hardness.

• 항공우주기술
• /
• 제6권1호
• /
• pp.19-28
• /
• 2007

본 연구에서는 올레오-뉴메틱(Oleo-pneumatic) 완충장치와 차등 제동 조향(Differential Braking Steering)을 위한 캐스터링 휠 포크(Castering Wheel Fork)가 적용된 소형항공기용 전방착륙장치의 충격하중 해석을 위한 비선형 2 자유도 수학적 모델을 생성하고, 수치해석 기법을 이용하여 시간에 따른 충격응답을 구하였다. 생성된 전방착륙장치의 수학적 모델은 타이어의 충격 시 동적 특성과 스트루트 기울기, 캐스터에 의한 모멘트, 타이어 접촉과 조향 등에 의해 발생하는 측면하중에 의한 올레오 스트루트 내부의 마찰 특성 등의 비선형 요소들을 포함하고 있다. 또 생성된 운동방정식의 수치해석은 4차 Runge-Kutta 방식을 이용하였으며, 운동방정식 및 수치해의 정확도를 평가하기 위한 타 항공기에 기 적용된 전방 착륙장치의 낙하시험 결과와의 비교 검증과정을 수행하였다.

• 대한기계학회:학술대회논문집
• /
• 대한기계학회 2000년도 추계학술대회논문집A
• /
• pp.250-255
• /
• 2000

Damage induced by low velocity impact loading in aircraft composite laminates is the form of failure which is occurred frequently in aircraft. Low velocity impact can be caused either by maintenance accidents with tool drops or by in-flight impacts with debris. 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 the carrying load of the composite laminates is considerably reduced. The reduction of strength and stiffness by impact loading occurs in compressive loading due to laminate buckling in the delaminated areas. The objective of this study is to determine inside damage of composite laminates by impact loading and to determine residual compressive strength and the damage growth mechanisms of impacted composite laminates. For this purpose a series of impact and compression after impact tests are carried out on composite laminates made of carbon fiber reinforced epoxy resin matrix with lay up pattern of $[({\pm}45)(0/90)_2]s$ and $[({\pm}45)(0)_3(90)(0)_3({\pm}45)]$. UT-C scan is used to determine impact damage characteristics and CAI(Compression After Impact) tests are carried out to evaluate quantitatively reduction of compressive strength by impact loading.

• EDISON SW 활용 경진대회 논문집
• /
• 제6회(2017년)
• /
• pp.259-269
• /
• 2017

Gust load is a very important load factor in designing various structures of an aircraft and judging its stability. This is because the blast effect on the aircraft in operation increases the risk of damage to the structure of the aircraft and causes a negative impact such as shortening the fatigue life by generating vibration. Particularly in the case of wing, a change in angle of attack is caused by gust load, and an additional lift acts on the wing, thereby being exposed to various excitational environments. Severe structural damage to the aircraft may occur if the natural frequencies of the aircraft wing are close to or coincident with the frequencies of the gust load applied to the wing. Recent trends of research include flight dynamics analysis considering discontinuous gusts or structural optimization of the blades under gust load. A number of studies have been conducted to interpret gust load response in consideration of irregularities in gusts. In this paper, we tried to imagine the situation of the aircraft subjected to the gust load as realistic as possible, and proposed an algorithm to track back the critical gust profile according to given aircraft characteristics from the viewpoint of preliminary engineering prediction.