• 한국항해항만학회지
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• 제27권3호
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• pp.247-252
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• 2003

This paper is mainly concerned with the assessment of safe navigation between ships moving each other in restricted waterways. The numerical simulation of manoeuvring motion was conducted parametrically to propose an appropriate safe speed and distance, which is required to avoid sea accident under the different conditions, such as ship-velocity ratios, ship-length ratios, separation and stagger between ships. As for the calculation parameters, the ratios of velocity difference between two ships were considered as 0.6, 1.2, 1.5 and the ones of ship-length difference were regarded were regarded as 0.5, 1.0, 1.18. From the inspection of this investigation, it indicates the following result. Firstly, the separation between ships is more needed for the small vessel, compared to the large vessel. Secondly, the lateral distance between ships is necessarily required for the velocity ration of 1.2, compared to the cases of 0.6 and 1.5. The manoeuvring characteristics based on this investigation will be very useful for keeping the safety of navigation from the practical point of ships design and traffic control in confined water.

• 한국항공우주학회지
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• 제32권6호
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• pp.72-80
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• 2004

본 논문에서는 추력중단 후 무유도방식 유도탄의 추력비행단계 유도알고리듬의 설계과정을 다룬다. 유도의 목적은 추력중단 시점에서 요구속도벡터를 성취하기 위한 것이다. 구현 가능한 피치평면 비행궤적을 조사하기 위해 네 가지 성능지수에 대한 비행궤적 최적화를 수행하였다. 궤적최적화 결과로부터 구속조건들을 만족시키기 위해서는 비행초기에 고앙각 기동이 필요함을 알 수 있다. 제안된 유도알고리듬은 개루프 피치자세각 명령 산출기인 피치프로그램과 증가요구속도벡터를 0으로 만들기 위한 요자세각 명령 산출기로 구성된다. 피치프로그램은 궤적최적화 결과 얻어진 피치자세각 선도를 이용하여 구성되었다.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2005년도 ICCAS
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• pp.463-467
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• 2005

In this paper, the guidance law applicable to formation flight of UAV in three-dimensional space is proposed. The concept of miss distance, which is commonly used in the missile guidance laws, and Lyapunov stability theorem are effectively combined to obtain the guidance commands of the wingmen. The propose guidance law is easily integrated into the existing flight control system because the guidance commands are given in terms of velocity, flight path angle and heading angle to form the prescribed formation. In this guidance law, communication is required between the leader and the wingmen to achieve autonomous formation. The wingmen are only required the current position and velocity information of the leader vehicle. The performance of the proposed guidance law is evaluated using the complete nonlinear 6-DOF aircraft system. This system is integrated with nonlinear aerodynamic and engine characteristics, actuator servo limitations for control surfaces, various stability and control augmentation system, and autopilots. From the nonlinear simulation results, the new guidance law for formation flight shows that the vehicles involved in formation flight are perfectly formed the prescribed formation satisfying the several constraints such as final velocity, flight path angle, and heading angle.

• 한국소성가공학회:학술대회논문집
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• 한국소성가공학회 2002년도 춘계학술대회 논문집
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• pp.77-81
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• 2002

A new method of optimal blank shape design using the initial nodal velocity (INOV) has been proposed for the drawings of arbitrary shaped cups. With the given information of tool shape and the final product shape, corresponding initial blank shape has been found from the motion of boundary nodes. Although the sensitivity method, the past work of Hynbo Shim and Kichan Son, has been proved to be excellent method to find optimal blank shapes, the method has a problem that a couple of deformation analysis is required at each design step and it also exhibits an abnormal behaviors in the rigid body rotation prevailing region. In the present method INOV, only a single deformation analysis per each design stage is required. Drawings of practical products as well as oil-pan have been chosen as the examples. At every case the optimal blank shapes have been obtained only after a few times of modification without predetermined deformation path. The deformed shape with predicted optimal blank almost coincides with the target shape at every case. Through the investigation the INOV is found to be very effective in the arbitrary shaped drawing process design.

• 소성∙가공
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• 제11권6호
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• pp.487-494
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• 2002

A new method of optimal blank shape design using the initial nodal velocity (INOV) has been proposed for the drawings of arbitrary shaped cups. With the given information of tool shape and the final product shape, corresponding initial blank shape has been found from the motion of boundary nodes. Although the sensitivity method, the past work of the present authors, has been proved to be excellent method to find optimal blank shapes, the method has a problem that a couple of deformation analysis is required at each design step and it also exhibits an abnormal behaviors in the rigid body rotation prevailing region. In the present method INOV, only a single deformation analysis per each design stage is required. Drawings of practical products as well as oil-pan, have been chosen as the examples. At every case the optimal blank shapes have been obtained only after a few times of modification without predetermined deformation path. The deformed shape with predicted optimal blank almost coincides with the target shape at every case. Through the investigation the INOV is found to be very effective in the arbitrary shaped drawing process design.

• 한국수자원학회논문집
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• 제41권6호
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• pp.575-585
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• 2008

수자원의 계획 평가 관리 및 수공구조물의 설계를 위해서는 정확하고 신뢰성 높은 유량 자료가 필수적이다. 본 연구에서는 Chiu의 유속분포와 최대유속 추정을 이용하여 하천유량을 계산하는 새로운 방법을 제시하였다. 기존 면적유속법과 비교 검토한 바, 본 연구에서 개발한 방법은 기존 유속면적법과 매우 유사한 하천유량을 보였다. Price-AA를 이용하여 유속을 측정할 경우 측선의 수심에 따라 정해진 지점에서 유속을 측정하여야 하는데, 본 연구에서 제시한 방법을 이용하면 임의의 측선과 측점에서 유속을 측정하여도 정확한 유량계산이 가능하다. 그러나 흐름 단면이 매우 복잡하거나 좌우의 비대칭성이 심한 경우에는 엔트로피 개념의 Chiu의 유속분포가 실제 자연하천의 흐름분포에서 멀어지고 유량산정에 Chiu의 유속분포의 정확도가 떨어지기 때문에 본 연구에서 제시한 방법을 적용하기 어렵다.

• 항공우주기술
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• 제8권1호
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• pp.108-116
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• 2009

본 논문에서는 한국형발사체를 사용한 달 탐사 위성의 궤적 설계를 수행하였다. 발사체는 달탐사위성과 킥모터 스테이지를 지구 저궤도에 투입하고, 이후 킥모터 스테이지의 연소에 의해 직접전이궤도 또는 고타원궤도에 투입된다. 설계된 궤적에 대해 TLI 및 LOI 기동을 실제와 가깝게 finite burn으로 모델링하여 요구속도 및 필요한 추진제량을 계산하여, 한국형 발사체를 사용할 경우 발사 임무에 대한 가능성을 제시하였다.

• Wind and Structures
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• 제5권2_3_4호
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• pp.257-266
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• 2002

In the recent years flow around bridges are investigated using computer modeling. Selvam (1998), Selvam and Bosch (1999), Frandsen and McRobie (1999) used finite element procedures. Larsen and Walther (1997) used discrete vorticity procedure. The aeroelastic instability is a major criterion to be checked for long span bridges. If the wind speed experienced by a bridge is greater than the critical wind speed for flutter, then the bridge fails due to aeroelastic instability. Larsen and Walther (1997) computed the critical velocity for flutter using discrete vortex method similar to wind tunnel procedures. In this work, the critical velocity for flutter will be calculated directly (free oscillation procedure) similar to the approaches reported by Selvam et al. (1998). It is expected that the computational time required to compute the critical velocity using this approach may be much shorter than the traditional approach. The computed critical flutter velocity of 69 m/s is in reasonable comparison with wind tunnel measurement. The no flutter and flutter conditions are illustrated using the bridge response in time.

• 한국유체기계학회 논문집
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• 제12권5호
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• pp.33-38
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• 2009

In this study, the effect of flow disturbance such as contraction, expansion pipe and velocity deviation from low velocity of $0.1\;^m/s$ to $2.5\;^m/s$ on the error characteristics of the flowmeter was studied. Flow experiments using flowmeter calibration facility of K-water were undertaken for the cases of ultrasonic flowmeter based on transit-time method and electromagnetic flowmeter. Experimental results are presented that measurement error of expansion pipe are larger than contraction pipe. It is shown that the minimum straight length were required to remain of ${\pm}0.5%$ error for electromagnetic flowmeter and ${\pm}2.0%$ error for ultrasonic flowmeter.

• 한국해양공학회지
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• 제16권6호
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• pp.55-59
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• 2002

Delamination means that cracking occurs on the interface layer between composite laminates. In this paper, to predict the delamination growth in composite laminates subjected to low-velocity impact, the unit load method was introduced, and an eighteen-node 3-D finite element analysis, based on assumed strain mixed formulation, was conducted. Strain energy release rate, necessary to determine the delamination growth, was calculated by using the virtual crack closure technique. The unit load method saves the computation time more than the re-meshing method. The virtual crack closure technique enables the strain energy release rate to be easily calculated, because information of the singular stress field near the crack tip is not required. Hence, the delamination growth in composite laminates that are subjected to low-velocity impact can be efficiently predicted using the above-mentioned methods.