• 항공우주기술
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• 제3권2호
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• pp.191-196
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• 2004

현재까지의 착륙장치의 연구동향은 대부분이 공기-유압식 완충기의 충격흡수 성능해석에 집중되어 있으며 이러한 연구내용을 판스프링식 복합재료 착륙장치의 해석에 적용하기에는 많은 문제점이 있는 실정이다. 공기-유압식 완충기의 충격흡수 특성은 착륙장치 구조물의 유연성보다 내부 구조의 설계 방식에 따라 영향을 받으나, 판스프링식 복합재료 착륙장치는 재료 자체가 지니는 탄성거동과 감쇠특성으로 충격흡수 역할을 수행한다. 따라서 구조물을 구성하는 재료의 선정 및 형상이 매우 중요하다. 본 연구에서는 실제 착륙장치의 충격 낙하 상태를 정확히 모사 할 수 있는 시험치구를 이용하여 현재 개발 중에 있는 고정식(fixed)복합재료 착륙장치가 갖고 있는 충격흡수특성, 탄성거동 및 감속특성 등을 파악하였다.

• 한국항공우주학회지
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• 제30권4호
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• pp.114-122
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• 2002

착륙장치 시스템의 개발은 설계특성상 충격흡수 성능에 대한 설계 파라메터, 최소한의 작동공간, 복잡성 및 중량과 비용 등의 복합적인 관계를 가지고 있다. 특히 항공기 착륙에 따른 지상충격하중 및 동적거동은 착륙장치 자체 구성품 뿐만 아니라 장착구조물의 설계 하중으로 적용되는 중요한 설계분야이다. 본 연구에서는 T-50 착륙장치를 모델로 ADAMS를 이용하여 지상 충격하중 및 동적거동을 해석할 수 있는 프로그램을 개발하였다. 항공기 운용/환경조건을 고려한 충격흡수특성 해석은 다양한 설계경험을 토대로 수행하였다. 설계변수 설정, 완충기에 작용하는 내력정의, 운동방정식을 유도하여 착륙 수직속도, 착륙 자세, 착륙 수평속도, 완충효율, 장착위치 작용하중 등을 고려한 해석결과와 동적거동 특성을 분석하고 제시하였다. 이러한 해석 결과를 바탕으로 향후 새로운 착륙장치 개발시 범용적인 해석이 용이할 뿐만 아니라 지상/비행시험의 문제점 발생시 고장탐구 해결에 활용할 수 있다.

• International Journal of Aerospace System Engineering
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• 제2권2호
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• pp.83-86
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• 2015

Taking the four-wheel bogie landing gear as an example, the force status of truck-like landing gear during the landing impact was analyzed and the simulation model of four-wheel bogie landing gear was established. Firstly, a landing gear prototyping model was established using CATIA and imported to LMS Virtual.lab. Secondly, dynamic analysis of the landing impact was simulated with the established model. Finally, with the help of LMS Virtual.lab's parametric design ability, the effects of landing approach and truck pitch angle on the landing performance, truck motion and truck beam strength were studied. These conclusions will be useful to the design and analysis of the truck.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2011년 춘계학술대회논문집
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• pp.206-209
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• 2011

During landing approach, an airplane could experience dynamic unstable motion by the combination of a gust and elevator control to cancel the disturbances. This situation is dangerous and could lead to a loss of an airplane. In this paper, numerical analysis was used to study the effect of pitch oscillating 2-D high lift devices in a landing condition. Experimental data on a pitching naca0012 airfoil was used for code validation. Dynamic characteristics of an airfoil, single slotted flap for mid-class passenger aircraft were analyzed. Unsteady Navier-Stokes analysis was performed with Spalart-Allmaras turbulence model for separation dominant low speed flow. As a result, flow hysteresis of a flapped airfoil was more complex than that of an oscillating airfoil. So, dynamic analysis of a flap in a landing condition is very important for operational safety.

• 항공우주시스템공학회지
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• 제4권4호
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• pp.44-48
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• 2010

This paper is used the commercial magneto-rheological(MR) damper for landing gear. The damping characteristics of Commercial MR damper by changing the intensity of the magnetic field are investigated and the dynamic responses of the landing gear. it is set up tset equipment, the landing gear drop test system. The landing gear involved drop testing the gear. The landing gear is tested by implementing sky-hook control algorithm and its performance is evaluated comparing to the result.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 1997년도 추계학술대회논문집; 한국과학기술회관; 6 Nov. 1997
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• pp.345-351
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• 1997

The motion of an aircraft landing gear over rough runway at variable speed is nonstationary. hi this paper, a method for the computation of nonstationary response variance is presented which uses a state space form for the combination of landing gear and runway excitation. The dynamic characteristics of the landing gear under nonstationazy random excitations has also been analyzed using the proposed method. The formulation is for linear systems of arbitrary order and allows any deterministic velocity history.

• 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.

• 한국운동역학회지
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• 제20권1호
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• pp.101-108
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• 2010

Recently, core and neuromuscular training(CNT) is emerging as a clinically relevant tool to improve neuromuscular control and to prevent sports injuries. The purpose of this study was to examine the effect of a 12 weeks CNT program on the dynamic stability after drop landing. The subjects attempted drop landing onto the force platform on single foot from a 40 cm height distance. The collected data was used to calculate the dynamic stability index. The Dynamic stability index was derived by measuring the medial-lateral stability index(MLSI), anterior-posterior stability index(APSI), and the vertical stability index(VSI). In comparison to the control group, the MLSI and APSI showed no difference, yet, it resulted in higher VSI. The results of this study suggest that CNT is worthwhile to be considered as a way to improve neuromuscular control and to prevent traumatic injuries. However, the results are taking into consideration to discuss the limitations of CNT and suggested future approaches.

• 제어로봇시스템학회논문지
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• 제11권6호
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• pp.543-549
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• 2005

This paper deals with modeling and analysis fer the landing motion of a human-body model. First, the dynamic model of a floating human body is derived. The external impulse exerted on the ground as well as the internal impulse experienced at the joints of the human body model is analyzed. Second, a motion planning algorithm exploiting the kinematic redundancy is suggested to ensure stability in terms of ZMP stability condition during a series of landing phases. Four phases of landing motion are investigated. In simulation, the external and internal impulses experienced at the human joints and the ZMP history resulting from the motion planning are analyzed for two different configurations. h desired landing posture is suggested by comparison of the simulation results.

• International Journal of Aeronautical and Space Sciences
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• 제7권1호
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• pp.118-128
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• 2006

This paper deals with auto-landing guidance system design applicable to Smart UAV(Unmanned Aerial Vehicle). The proposed guidance law generates horizontal position, velocity and altitude commands in the longitudinal channel and heading angle command in the lateral channel to track a predetermined trajectory for automatic landing. The longitudinal guidance commands are derived from an approximated dynamic equations in vertical plane. These longitudinal guidance commands are appropriately distributed to each control input as the flight mode of Smart UAV is changed. The concept of VOR(VHF Omni-directional Range) guidance system is applied to generate the required heading angle commands to eliminate the lateral deviation from the desired trajectory. The performance of the proposed guidance system for Smart UAV is evaluated using the nonlinear simulation. Simulation results show that the proposed guidance system for auto- landing provides good tracking performance along the predetermined landing trajectory.