• Proceedings of KOSOMES biannual meeting
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• 2008.05a
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• pp.43-47
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• 2008

In order to investigate the hydrodynamic interaction between the tug-barge and bank or ship which is crossing to the opposite direction, we have executed the towing simulation of tug-barge transportation. Heading of barge, yaw moment and lateral force of tug boat are obtained by this simulation. We have analyzed the characteristics of results and propose the safety towing method for tug-barge operation.

• Proceedings of the KIPE Conference
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• 2019.07a
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• pp.35-37
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• 2019

본 논문은 배전선로 안정화 구현을 위한 무효전력 보상기의 새로운 무효전력 제어기법을 제안하였으며, 시뮬레이션 및 실험을 통해 무효전력제어 알고리즘의 성능을 검증하였다. 무효전력 제어는 동기좌표계 d축 전류성분 제어를 통해 수행되고, DC 링크 전압을 일정하게 유지하기 위한 전압 제어와 이에 필요한 유효전력은 q축 전류성분 제어를 통해 구현된다. 제안된 무효전력 제어기법에 포함된 DC 리플 보상방식은 추출된 DC 전압의 오프셋 성분을 제거하는 HPF(high pass filter)부와 HPF 위상 특성으로 인해 발생한 위상변화 특성을 보상하기 위한 지연함수부로 구성되며, 리플성분이 보상된 전압을 전압제어기 피드백 성분으로 적용하였다. 시뮬레이션 및 실험을 통해 DC 전압 리플 보상방식이 적용된 무효전력 제어 기법이 적용된 경우 전류 THD가 크게 향상된 결과로부터 제안된 알고리즘의 성능을 검증하였다.

• Proceedings of the KIPE Conference
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• 2020.08a
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• pp.286-287
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• 2020

본 논문은 단상 전기철도 시스템의 불평형 부하 특성으로 인한 3상 계통의 전력 불평형을 보상하기 위해 백투백 컨버터를 적용하였으며, 실험을 통해 전력 불평형 성능 개선 특성을 검증하였다. 3상 전압은 스코트 변압기를 통해 2개의 M-T상 전압으로 출력되며, 전력 불평형 개선을 위해 적용된 백투백 컨버터는 DC 링크를 공유하며 각각 M-T상에 연계된다. 백투백 컨버터는 M-T상에 연계된 부하용량 차이에 따른 불평형 조건에 관계없이 M상과 T상 계통 라인에 동일한 전력이 공급되도록 제어하는 역할을 수행하며, 제어 알고리즘은 동기좌표계에서 구현하였다. 백투백 컨버터의 프로토 타입은 3레벨 NPC 컨버터로 설계하였으며, M상 5kW, T상 1kW 부하에서 전력보상 장치가 동작하고 있음에도 완전히 해결되지 않은 불평형 현상에 대해 분석한다.

• Aerospace Engineering and Technology
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• v.2 no.2
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• pp.1-10
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• 2003

An airship is statically unstable, because it has no wing, comparatively small tail and large hull. Hence, an accurate prediction of dynamic stability is critical. In this study, dynamic stability data of the Mid-Size Airship is acquired through forced oscillation wind tests. The test was done in BAR LAMP which is Birhle Applied Research Inc's facility located in Germany. The test was composed with 16 static runs and 26 dynamic runs. As a result, dynamic characteristics of the airship depends on sideslip angle, angular rate and its direction as well as angle of attack. Generally, it is obtained that 3 directional moments have damping, but normal force, side force, and cross-derivatives are unstable. The dynamic derivatives are not sensitive to control surfaces, but have nonlinear dependency on sideslip angle.

• Journal of Advanced Marine Engineering and Technology
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• v.35 no.4
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• pp.451-459
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• 2011

Austenitic stainless steels of 300 series are widely used as the structural material due to excellent their cryogenic mechanical properties at cryogenic temperature. There are 316 steel which molybdenum is added to improve the austenitic stability, 316L which carbon contents is reduced to decrease the grain boundary precipitation during welding process, and 316LN which nitrogen is added to improve the austenitic stability and the mechanical strength. But material researches for the welding conditions and mechanical properties at the cryogenic temperature were insufficient so far. In this paper, the characteristics of mechanical properties considering the effect of welding conditions and cryogenic temperature are studied.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.10
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• pp.1-6
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• 2006

This paper predicts the stall characteristics of three-dimensional wings. An iterative decambering approach is introduced into the nonplanar lifting surface method to take into consideration the stall characteristics of wings. An iterative decambering approach uses known airfoil lift curve and moment curve to predict the stall characteristics of wings. The multi-dimensional Newton iteration is used to take into consideration the coupling between the different sections of wings. Present results are compared with experiments and other numerical results. Computed results are in good agreement with other data. This scheme can be used for any wing with the twist or control surface and for wing-wing configurations such as wing-tail configuration or canard-wing configuration.

• Proceedings of the KIPE Conference
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• 2018.07a
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• pp.132-134
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• 2018

본 논문은 태양광발전 시스템에서 P&O 방식 기반의 제어 기법인 duty 제어와 전류 제어 방식의 최대전력점 추종특성을 동일모드 조건에서 비교하였으며, 시뮬레이션 및 실험을 통해 검증하였다. Duty 제어 방식은 P-V 특성곡선을 이용하여 전력과 전압의 변화량을 통해 duty 증감을 결정함으로써 동작점을 결정한다. 이와 달리, 전류 제어 방식은 P-I 특성곡선을 이용하여 전력과 전류의 변화량을 통해 전류 지령치를 생성하고 비례-적분제어기를 통해 전류제어를 수행하여 동작점을 결정한다. 두 가지 제어 방식의 정확한 비교를 위해 등가의 ${\Delta}duty$ 및 ${\Delta}I_{ref}$의 값을 선정하여 모드 변화에 따른 ${\Delta}V$의 변화를 동일하게 맞추었다. DC - DC 부스트 컨버터를 이용하여 시뮬레이션과 실험에 두 제어 방식의 태양광발전 시스템을 구성하여 태양광 전압과 전류, 에너지 측면에서 특성을 비교하였다. 최대 전력점이 1.7kW인 특성곡선 조건 하에서, 시뮬레이션과 실험의 결과로 두 방식은 동일 MPPT 모드 시 동일한 동작점에 존재하며, 같은 값의 전력을 출력하여 동일한 성능의 효율을 보임을 검증하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.2
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• pp.85-90
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• 2013

A numerical analysis for the internal flow was carried out in order to analyze the leakage flow characteristics inside the damped bypass valve. This research has found that the valve characteristics became stable at above a specific temperature. Very small amount of leakage flow was occurred. But there was no effect in temperature. The more temperature fell, the more maximum pressure rate was increased.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.3
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• pp.30-38
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• 2010

Experiments were performed to investigate the flow characteristics of a partial admission supersonic turbine depending on the relative positions of nozzle and cascade. The flow was visualized by a Schlieren system. The static pressures at the turbine cascade inlet, passage and outlet were measured by pressure transducers. Highly complicated flow patterns including shocks, nozzle-cascade interaction and shock boundary layer interactions of the supersonic turbine were observed by the experiments. And the flow characteristics in the supersonic turbine as the relative positions were observed.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.5
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• pp.97-103
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• 2004

Nowadays, many kinds of research for airship are studying with increasing of interests of airship. But these are far from perfect. The data acquisition from the actual flight test has lots of difficulties because of the characteristics from the slow dynamic response and high sensitivity for external environment. In this paper, through the actual flight test, appropriateness of the mathematical dynamic model applied here was verified by comparing the test data with simulation data in same control conditions.