• 전력전자학회논문지
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• 제24권1호
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• pp.40-48
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• 2019

Hybrid electric propulsion systems (H-EPSs) are an intermediate step for integrated full electric propulsion warships. H-EPSs are a dynamic combination of mechanical and electrical propulsion systems to achieve the required mission performances. The system modes could adapt to meet the requirement of the various operation conditions of a warship. This paper presents a configuration and operating modes of H-EPSs considering the operation conditions of a destroyer class warship. The system has three propulsion modes, namely, motoring mode, generating mode [power take off (PTO) mode], and mechanical mode. The PTO mode requires a careful fuel efficiency analysis because the fuel consumption rate of propulsion engines may be low compared with the generator's engines depending on the loading power. Therefore, the calculation of fuel consumption according to the operating modes is performed in this study. Although the economics of the PTO mode depends on system cases, it has an advantage in that it ensures the reliability of electric power in case of blackout or minimum generator operation.

• 한국초전도ㆍ저온공학회논문지
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• 제24권2호
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• pp.27-38
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• 2022

Urban air mobility (UAM) has recently attracted lots of attention as a solution to urban centralization and global warming. Electric vertical take-off and landing (eVTOL) is a concept that emerges as one of the promising and clean technologies for UAM. There are two difficult challenges for eVTOL aircraft to solve. One is how to improve the weight efficiency of aircraft, and the other is how to complete long-range missions for UAM's flight scenarios. To approach these challenges, we propose a consolidated concept design of battery-fuel cell hybrid tiltrotor aircraft with a liquid hydrogen (LH₂) fuel tank. The efficiency of a battery-fuel cell hybrid powertrain system on the designed eVTOL aircraft is compared to that of a battery-only powertrain system. This paper shows how much payload can increase and the flight scenario can be improved by hybridizing the battery and fuel cell and presenting a detailed concept of a cryogenic storage tank for LH₂.

• 한국항공운항학회지
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• 제30권4호
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• pp.184-190
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• 2022

In an attempt to apply hybrid rocket to the RATO (Rocket-Assisted Take Off) system, combustion characteristics of the non-circular grain were figured out in this study. Having larger combustion area, it was reconfirmed that the non-circular grain has advantages over regression rate, characteristic velocity and chamber pressure in which all gave higher values. Experiments were performed to understand the effect of the non-circular grain geometry over time where local regression rates depending on grain location were analyzed. It was found that the regression rate of five distinct locations were different. Partial conclusion driven was that these differences are due to the heat transfer caused by dissimilar distances from the flame layer. Besides, as combustion duration increased, the fuel port became circular, and the regression rate converged to a single value over the whole grain.

• 한국지능시스템학회:학술대회논문집
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• 한국퍼지및지능시스템학회 2000년도 추계학술대회 학술발표 논문집
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• pp.335-339
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• 2000

In the weaving process, tension control of the warp is important. The variation of the warp tension cause irregularities of the weft density and low quality of the woven fabrics. Due to the fact that the warp tension varies in depending on the difference between take-up velocity and let-off velocity, it is necessary to regulate the velocity of let-off in relation to that of take-up for keeping the warp tension. Futhermore, the diameter of warp beam changes in the weaving process. The changing diameter of warp beam cause changing inertia of warp beam and the velocity of the let-off. It makes the control of such a system more complex. In this paper, we propose a fuzzy controller for the warp tension control. From the computer simulation, it was observed that a developed fuzzy controller has a better performance than that of conventional PI controller.

• 한국해양공학회지
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• 제15권1호
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• pp.26-30
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• 2001

Up to now, Most studies of hydroelasticity are about frequency domain analysis. Those aren't suited for analysis of the landing take-off, and dropping of aircraft on a structure. So, the concern of this paper is the transient behavior of a VLFS subjected to dynamic load, induced by airplane landing and take-off. To predict the added mass, damping coefficient, and wave exciting force, the source-dipole distribution method was used in the frequency domain. The responses are accomplished by using the FEM scheme. A time domain analysis method is based on the Newmark β method to pursue the time step procedure, taking advantage of memory effect function for hydrodynamic effects.

• 한국건설관리학회:학술대회논문집
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• 한국건설관리학회 2008년도 정기학술발표대회 논문집
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• pp.744-747
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• 2008

설계도면을 중심으로 산출되는 물량정보는 건설 프로젝트 생애주기 동안에 프로젝트 참여주체들에게 비용과 관련한 의사결정에 결정적인 역할을 하는 매우 중요한 정보이다. 이러한 정보를 생성하는 물량산출 업무가 수작업에 많이 의존하다보니 작업자의 실수에 의한 오류가 빈번하게 발생하고, 견적담당자의 노하우에 따라 물량의 차이가 존재하기도 한다. 또한, 설계변경에 의해서 물량산출을 위한 재작업에 들어가게 될 경우 모든 물량산출 프로세스를 다시 거쳐야 하는 문제가 있다. 이러한 제반 문제는 견적자동화를 통해 물량산출의 정확성 확보 및 설계변경 시 요구되는 물량산출의 대응력에 대한 요구를 증대시키고 있으며, 최근 3D CAD Modeler에서 생성된 3D CAD 모델을 기반으로 견적업무프로세스를 자동화하려는 연구가 다양한 관점에서 시도되고 있다. 그러나 기존 연구에서는 특정 3D CAD Modeler를 중심으로 한 견적자동화에 대한 연구로 다양한 3D CAD Modeler에서 생성된 3D CAD 모델로부터 물량정보를 취득하기 위한 공통체계 구축하고 이를 기반으로 BIM기반 견적자동화를 이루는 데 한계를 가지고 있다. 따라서 본 연구에서는 이러한 BIM기반 견적자동화 체계구축을 위한 기반 연구로 다양한 3D CAD Modeler로부터 물량산출을 자동화하기 위해 Modeler가 내부적으로 가지고 있는 Quantity Data Type을 추출하고, 이를 분석 및 검증할 수 있는 체계를 개발하였다.

• 한국운동역학회지
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• 제21권5호
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• pp.595-602
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• 2011

The long jump motion of 8 finalist of men's long jump of IAAF World Championships Daegu 2011 were analysed and the kinematic characteristics of the technique were investigated. The kinematic characteristics of long jump motion of 8 finalist were as follows. In the run-up phase, the average length of 3, 2, and 1 stride were $2.21{\pm}0.08$ m, $2.46{\pm}0.18$ m, and $2.19{\pm}0.16$ m, respectively. The change in the height of the center of gravity was $0.09{\pm}0.02$ m. The average velocity of 3, 2, and 1 stride was $10.37{\pm}0.32$ m/s, $9.63{\pm}0.32$ m/s, and $10.69{\pm}10.69$ m/s, respectively. In the take-off phase, the horizontal velocity, the vertical velocity, the reduction of horizontal velocity was $9.00{\pm}0.37$ m/s, $3.04{\pm}0.27$ m/s, and $1.69{\pm}0.34$ m/s, respectively. The minimum knee angle and the take off angle was $157{\pm}6.57^{\circ}$ and $18.5{\pm}2.24^{\circ}$, respectively. In the flight phase, the flight time and the maximum height of the center of gravity was $0.82{\pm}0.05$ s, and $1.70{\pm}0.10$ m, respectively. In the landing phase, the landing length was $0.51{\pm}0.06$ m. The body angle, the knee angle, and the hip angle was $71{\pm}20.93^{\circ}$, $136{\pm}19.19^{\circ}$, and $85{\pm}9.58^{\circ}$, respectively. The kinematic characteristics of long jump motion with good record were shown as follows. The reduction of the horizontal velocity in the take-off phase was minimized while the velocity of the run-up were maximally maintained. The vertical velocity in the take-off phase was increased with rapidly extended knee and the high center of gravity.

• 한국건축시공학회지
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• 제8권2호
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• pp.63-70
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• 2008

Reinforcing steel work plays an important role in terms of its structural performance or weight of construction cost for reinforced concrete structures. Precise estimation of re-bar quantity gives a basis for managing the reinforcing steel work effectively. However, the estimation process is still performed ineffectively based upon the expert's experience or manpower in spite of the advanced technology or improvement efforts. Therefore, the purpose of this research is to develop a prototype system for taking-off the quantity of reinforcing steel bars quickly and accurately in an order consistent with the specific members identified on the drawings. An estimate algorithm considering the connection, settlement and coating thickness of re-bars was suggested regarding to their replacement conditions which places more emphasis on constructibility. Also, this system produces the shop drawings automatically with the calculation results with work zone information.

• Journal of international Conference on Electrical Machines and Systems
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• 제1권4호
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• pp.477-482
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• 2012

This paper describes a new rotor position sensorless control method for SRM drives based on an improved simplified flux linkage method. In the traditional simplified flux linkage method, every phases take turns conduction and current chopping control method is used. Every phases take turns conduction means turning on the incoming working phase while turning off the working phase. This conduction mode causes coupling between turn-on and turn-off angles, which goes against optimal efficiency or torque ripple minimization with sensorless speed control. In the improved simplified flux linkage method, turn-off angle is calculated by flux loop, the turn-on angle can be given arbitrarily and has no relations with the turn-off angle, and the current chopping control method is used. The speed and rotor position can be estimated then. Finally, a sensorless SRM speed control system and an experiment platform with DSP are built and validity of this method is confirmed.

• 항공우주기술
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• 제12권1호
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• pp.10-21
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• 2013

오늘날 헬리콥터 기술의 발전과 더불어 함상에서 헬리콥터를 운용하는 것은 당연한 것으로 여겨지고 있다. 육상과 달리 해상에서 항공기를 운용하기 위해서는 육상보다 심한 바람과 파도와 배의 이동에 의한 착륙장의 운동과 염분에 의한 장비의 부식이 고려되어야하며 안전한 운용을 위한 운용절차가 요구된다. 본 논문에서는 수직이착륙 항공기의 함상운용 사례분석을 통하여 함상운용에 요구되는 항공기와 선박의 고려사항과 운용절차를 알아보고 이를 기반으로 틸트로터 무인기의 함상운용 기술개발 방안을 제시한다.