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

• 한국군사과학기술학회지
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• 제14권5호
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• pp.805-811
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• 2011

Aircraft MLG and wing structures have been recognized as fatigue critical structures and exposed to the risk of fatigue crack initiation and propagation. Furthermore, these structures are frequently subjected to serious dynamic loading condition during a Hard Landing which may lead to their failure. Especially, structural integrity of MLG and wing components is decreased as the flight time increased because of the fatigue damage accumulated on the aircraft. In this study, the effects of Hard Landing on the MLG and wing components of aging aircraft were evaluated by using numerical approach. To achieve the aim, a finite element model has been developed and simulations were conducted by varying the landing conditions. As a result, it was revealed that the high stress concentration phenomenon was occurred at the lower Side Brace of MLG. Thereby, the intensified inspection for the lower Side Brace should be considered to prevent unexpected aircraft mishap.

• 한국군사과학기술학회지
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• 제15권6호
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• pp.746-753
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• 2012

ROK military helicopters are frequently exposed to the hazard situations due to the characteristic of operation. Especially, helicopter accident may lead to critical damage of human and structure. Accordingly, pilots have to train the autorotation procedures and learn the skill to prevent hard landing. In this paper, the behavior of skid gear subject to the helicopter autorotation was conducted by using numerical method. The computer simulation approach by using finite element method was employed to accomplish this goal. Additionally, the behavior of skid gear was evaluated for the different landing conditions. In conclusion, the maximum stress concentration was occurred at the attached area of skid cross-tube to the fuselage. Also, it was revealed that the most proper attitude was level landing to prevent hard landing.

• 한국산학기술학회논문지
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• 제20권7호
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• pp.20-25
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• 2019

본 연구에서는 동체착륙 방식의 소형 고정익 무인항공기의 구조적 취약점 분석 및 품질 개선에 대한 연구를 실시하였다. 소형 고정익 무인항공기는 일반 비행체와는 달리 활주로를 사용하지 않는 투척이륙과 동체착륙 방식을 많이 사용한다. 이러한 방식은 좁은 공간에서 이륙, 착륙이 가능하여 운용적으로 많은 장점이 있다. 하지만, 동체착륙은 비행체 구조에 강한 충격이 발생하여 작은 설계 오류로 심각한 파손을 발생시킬 수 있다. 본 연구 대상인 비행체 또한 착륙과정에서 특정 부위에 지속적인 파손이 발생하였다. 이러한 현상의 정확한 원인분석을 위해 파손이 발생한 부위를 3D 구조 해석프로그램(ABAQUS)을 활용하여 구조 해석을 실시하여 정확한 위치를 파악하였고 구조해석에 정확성을 높이기 위해 시편 시험을 통해 재료의 물성치 정보를 획득하였다. 해석 결과 구조적 취약점을 확인하여 개선을 진행하였고 품질이 향상된 구조물을 운용 중 최대 충격량의 1.5배의 더 높은 수준의 실제 충격시험을 통해 검증함으로써 연구의 타당성을 입증하였다.

• KSTLE International Journal
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• 제3권2호
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• pp.114-118
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• 2002

In this work, head-disk interactions are studied when flying height becomes lower than laser bump height on the landing zone of a disk. With the reduction of the spinning speed in a spin stand, the flying height is decreased under the height of laser bumps. Conventional and padded pico sliders sweep between landing Bone and data zone and, then, the dynamic behavior of the pico sliders and head-disk impacts are investigated using AE and stiction/friction signals. After 200n cycle-sweep tests, bearing analysis and AFM analysis indicate that there are some signs of wear and plastic deformation in the landing zone of a disk, although AE and stiction/friction signals are not significantly changed during the sweep tests. The experimental results of this paper suggest that in CSS tests at component level, more rigorous examination methods of wear and plastic deformation might be necessary as flying height becomes getting lower.

• 한국항공운항학회지
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• 제31권4호
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• pp.1-6
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• 2023

EBT has designed and implemented a training program that relies on evidence from events such as Flight Operation Quality Assurance (FOQA), accidents, and incidents specific to each airline. The goal is to enhance the overall skills of the flight crew. This involves assessing the capabilities of individual crew members and, based on the findings, providing additional training to address any shortcomings. To create a training program aligned with the objectives of EBT, this study focused on analyzing data from hard landing incidents in domestic airlines obtained through FOQA events. A practical EBT training program was then developed, specifically targeting adverse weather conditions. The program evaluates landing capabilities, and the results guide the supplementation of any deficiencies in the landing skills of each flight crew member, ultimately aiming to enhance their confidence.

• 한국항공우주학회지
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• 제36권1호
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• pp.39-47
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• 2008

GPS에 의사위성(PL: Pseudolite)을 추가하여 고도 정확도를 향상시키면 무인 항공기의 착륙 성능이 향상된다. 그러나 GPS 위성이 계속 움직이고, 매번 착륙 위치가 바뀌는 환경에서 원하는 정확도를 얻을 수 있도록 의사위성을 설치하고 운영하는 것은 매우 어려운 일이다. GPS와 의사위성으로 얻을 수 있는 서비스의 범위와 측위 정확도는 시뮬레이터로 예측 가능하고 정확하게 예측된 정보는 무인항공기의 운영을 위하여 매우 중요하다. 본 논문에서는 효과적인 의사위성의 활용을 위하여 GPS/PL 시뮬레이터를 개발하고 그 성능을 평가하였다. 시뮬레이터의 서비스 범위 예측은 의사위성의 설치 위치 및 개수, 송신 전력과 무인 항공기의 고도를 고려하여 GIS 데이터와 광선 방출 기법을 이용하여 계산하였다. 측위 정확도는 GPS와 의사위성을 동시에 사용하여 구한 DOP와 NSP를 이용하여 분석하였다. 실제 수신기의 출력과 비교하여 구현된 시뮬레이터를 검증하였으며, 시뮬레이션 결과 2개 이상의 의사위성의 추가로 무인항공기의 자동 착륙에서 요구되는 정확도를 만족시킬 수 있음을 확인하였다.

• 제어로봇시스템학회논문지
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• 제14권1호
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• pp.95-103
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• 2008

This paper deals with the problem of autolanding for aircraft under windshear environment for which the landing trajectory is given. It is well known that the landing maneuver in windshear turbulence is very dangerous and hard for the pilot to control because windshear is unpredictable in when and where it happens and its aerodynamic characteristics are complicated. In order to accomplish satisfactory autolanding maneuver in this environment, we propose a gain-scheduled controller. The proposed controller consists of three parts: PID controller, called baseline controller, which is designed to satisfy requirements of stability and performance without considering windshear, gain scheduler based on fuzzy logic, and safety decision logic, which decides if the current autolanding maneuver needs to be aborted or not. The controller is applied to a 6-DOF simulation model of the associated airplane in order to illustrate the effectiveness of the proposed control algorithm. It is noted that a cross wind in the lateral direction is included to the simulation model. From the simulation results it is observed that the proposed gain scheduled controller shows superior performance than the case of controller without gain scheduling even in severe downburst and tailwind region of windshear. In addition, touchdown along centerline of the runway is more precise for the proposed controller than for the controller without gain scheduling in the cross wind and the tailwind.

• 한국윤활학회:학술대회논문집
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• 한국윤활학회 2001년도 제33회 춘계학술대회 개최
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• pp.122-126
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• 2001

Magnetic hard disk drive is continually being pushed to reduce head-disk spacing for higher recording densities. The current minimum spacing between the air-bearing slider and disk has been reduced to under 15 nm. In this work, it was investigated if flying height could be lowered under the height of laser bumps. With the reduction of the spinning speed, the flying height was decreased under the height of laser bumps. When a head swept between landing zone and data zone, the head-disk impact was monitored using AE and friction signals. It is demonstrated that magnetic hard disk drive could be operated without tribological failures under the height of laser bumps.

• 융합보안논문지
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• 제16권6_1호
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• pp.15-24
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• 2016

인천상륙작전은 1950년 9월 15일에 연합군과 한국 해병대가 실시한 한반도 최초의 연합상륙작전이었다. 인천상륙작전의 역사적 의의는 낙동강방어전선에서 반격을 위한 공세이전으로 전환시켜 수도 서울 탈환이라는 계기를 마련하였다는 점에 있다. 인천상륙작전간 한국해병대는 미군들의 주요지휘관들로부터 "한국 해병대의 철저한 전투수행에는 어떠한 결함도 발견할 수 없었다"고 격찬을 받으면서 위국헌신의 희생정신으로 한국해병대의 위용을 전 세계에 과시하였다. 오늘날 우리 해병대가 국민들에게 사랑과 신뢰를 받으면서 국민의 군대로서 성장할 수 있었던 것은 평시 강한 훈련을 통하여 유사시를 대비했기 때문이었다. 앞으로도 장병들의 주적개념과 국가관을 확립토록 정신교육을 강화하고 또한 강한 훈련을 통하여 싸우면 반드시 이긴다라는 자신감을 배양토록 힘써야 할 것이다. 특히 구타 및 가혹행위 등의 잘못된 전통을 척결하여야 할 것이다. 선배해병들의 피와 땀과 눈물어린 전통을 보다 계승 발전시켜 국민에게 신뢰받는 해병대가 되도록 최선을 다해야 할 것이다.