• 한국항공우주학회지
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• 제38권10호
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• pp.992-997
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• 2010

과학기술위성3호(STSAT-3)용 홀추력시스템(HPS)의 추력제어모듈(PCM)은 압력정밀도 5%이하와 유량정밀도 3%이하를 목표로 한다. 압력제어기는 비례유량제어밸브(PFCV)와 저압압력센서를 사용하여 목표압력을 제어하도록 하고, 유량제어기는 PFCV와 홀추력기의 에노우드(anode) 전류를 이용하여 유량을 조절한다. 제어형태로는 비례,적분(PI) 제어기를 선택하고, PI 이득은 Matlab 시뮬레이션을 통하여 정한다. 시험결과 압력정밀도 <${\pm}$5%와 유량정밀도 <${\pm}$1.87%를 얻었다. 본 논문은 홀추력 제어모듈의 설계, 구현, 그리고 성능시험 결과를 기술한다.

• 대한전기학회:학술대회논문집
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• 대한전기학회 2001년도 하계학술대회 논문집 C
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• pp.1603-1605
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• 2001

Eight 300kJ modularized capacitor-banks have been constructed. These modules have been installed and assembled to make a 2.4MJ pulse power system (PPS). This 2.4MJ PPS was developed to be used as a driver of an electrothermal-chemical (ETC) gun. Each capacitor bank has six 22kV, 50kJ capacitors connected in parallel. A triggered vacuum switch (TVS-43) was adopted as a main pulse power-closing switch in each module. The module also contains a crowbar circuit made of three high-voltage diode-stacks, a multi-tap inductor and an energy-dumping resistor. Various current shapes have been formed by a sequential firing of multiple capacitor banks. Resistive dummy load has been used and various combinations of experimental parameters, such as charging voltage, trigger time and inductance, were tested to make flexible current shapes.

• 대한전기학회:학술대회논문집
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• 대한전기학회 2000년도 하계학술대회 논문집 C
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• pp.1868-1870
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• 2000

As a drive for an ETC (Electro-thermal Chemical) launcher, a large pulse power system of a 2.4MJ energy storage was designed, constructed and tested. The overall power system consists of eight capacitive 300kJ energy storage banks. In this paper we describe the design features, setup and operation test result of the 300kJ pulsed power module. Each capacitor bank of the 300kJ module consists of six 22kV 50kJ capacitors. A triggered vacuum switch (TVS-43) was adopted as the main pulse switch. Crowbar diode circuits, variable multi-tap inductors and energy dumping systems are connected to each high power capacitor bank via bus-bars and coaxial cables. A parallel crowbar diode stack is fabricated in coaxial structure with two series 13.5kV, 60kA avalanche diodes. The main design parameters of the 300kJ module are a maximum current of 180kA and a pulse width of 0.5 - 3ms. The electrical performances of each component and current output variations into resistive loads have been investigated.

• Journal of Advanced Marine Engineering and Technology
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• 제35권7호
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• pp.946-956
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• 2011

The main objectives of this study are to analyze the leaked gas dispersion and quantify the potential overpressures due to vapor cloud explosions in order to identify the most significant contributors to risk by using Computational Fluid Dynamics (CFX & FLACS) for gas fuelled ships. A series of CFD simulations and analyses have been performed for the various gas release scenarios in a closed module, covering different release rates and ventilating methods. This study is specially focused on the LNG FGS (Fuel Gas Supply) system recently developed for the propulsion of VLCC crude oil carriers by shipyards. Most of work presented is discussed on the gas dispersion from leaks in the FGS room, and shows some blast prediction validation examples.

• 대한기계학회논문집A
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• 제29권2호
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• pp.262-269
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• 2005

Optimization of a satellite structure under severe space launching environments is performed considering various design constraints. Simulate annealing, one of combinatorial optimization techniques, is used to optimize the satellite. The optimization results by the simulated annealing are compared to those by the method of modified feasible direction and genetic algorithm. Ten bar truss structure is optimized for feasibility study of the simulated annealing. Finally, the satellite structure is optimized by the simulated annealing algorithm under space environment. Weights of the satellite upper platform and propulsion module are minimized with consideration of several static and dynamic constraints. MSC/NASTRAN is used to find the static and dynamic responses. Simulated annealing has been programmed and integrated with the finite element analysis program for optimization. It is shown that the simulated annealing algorithm can be extended to the optimization of space structures.

• 한국전기전자재료학회:학술대회논문집
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• 한국전기전자재료학회 2009년도 추계학술대회 논문집
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• pp.289-289
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• 2009

The series hybrid propulsion system in bimodal tram consists of CNG engine, generator, inverter, motor and battery as main components. Among them, battery is very important thing to make a hybrid bimodal tram more efficient in driving. Battery pack is composed of 168 LPB(lithium polymer battery) cells, 650Vdc-300A. LPB should be treated with a good consideration in both temperature and overvoltage. This paper had analyzed and investigated the thermal flow and distribution of LPB module(l4 LPB cells) and Pack in simulated environments by commercial thermal analysis tool.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2004년도 추계학술대회
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• pp.522-527
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• 2004

Resealed Simulated Annealing (RSA) has been devised for improving the disadvantage of Simulated Annealing (SA) which require tremendous amount of computation time. RSA and SA have been for optimization of satellite structures and for comparison of results from two algorithms. As a practical application, a satellite structure is optimized by the two algorithms. Weights of satellite upper platform and propulsion module are minimized. MSC/NASTRAN is used for the static and dynamic analysis. The optimization results of the RSA are compared with results of the classical SA. The numbers of optimization iterations could be effectively reduced by the RSA.

• 한국항공운항학회지
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• 제21권1호
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• pp.30-38
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• 2013

This paper describes the design optimization of Unmanned Aerial Vehicles(UAVs). An optimization framework has been developed and implemented for the conceptual design of UAVs. An integrated design analysis program was developed with several analysis modules such as propulsion, performance, mission, weight, and stability and control. A UAV configuration design optimization was performed by implementing the integrated analysis to enhance the endurance of UAVs. A SQP optimizer was utilized to build an optimization module for this program and sensitivity analysis was performed to determine the trends of shape variables for developing optimization objective. In conclusion, the results indicate that the resulting optimized UAVs configurations show performance improvements over the baseline design and reliable analysis results.

• 대한조선학회논문집
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• 제30권4호
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• pp.1-7
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• 1993

전문가시스템을 개발하고, 이를 현업에 적용하려는 노력이 꾸준하게 이어져 왔다. 조선분야에의 전문가시스템 개발은 외국에서 활발하게 이루어지고 있으며, 최근 국내에서도 관심이 증대되고 있다. 본 연구에서는, 초기설계시에 선박의 주기관선정을 지원할 수 있는 설계지원 전문가시스템을 상용 전문가시스템 개발도구를 사용하여 개발하였다. 개발된 시스템은, 성능 추정 모듈, 주기관 데이타베이스, 지식베이스, 그래픽 사용자 인터페이스 및 이들을 연결하는 모듈로 구성되어 있다. 지식베이스에는 약 100여개의 지식이 Rule의 형태로 구축되어 있다. 본 시스템은 설계전문가에게는 설계의 보조수단으로, 초보자에게는 교육용으로 사용가능할 것이다.

• 전력전자학회:학술대회논문집
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• 전력전자학회 2015년도 전력전자학술대회 논문집
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• pp.143-144
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• 2015

전기추진선박은 디젤엔진과 프로펠러의 회전축이 기계적으로 연결된 기존의 선박과 달리 엔진의 기계적 에너지를 전기 에너지로 변환하여 전동기 회전을 통해 추진력을 얻는 선박으로서 시추선, 군함, OSV(Offshore Support Vessel)등 높은 조종성능이 요구되는 선종에 주로 적용되고 있다. 이러한 선종은 추진력을 얻는데 가장 큰 전력을 사용하므로 날씨에 따른 전력부하량의 변동이 크다. 본 논문에서는 슈퍼커패시터로 구성된 전력버퍼모듈을 이용하여 전기추진선박의 효율적인 전력 운용 전략을 제안한다. 추진전동기의 VFD(Variable Frequency Drive)의 직류단을 전력버퍼모듈로 통합하여 각 전동기의 보조전력으로 활용함으로써 부하변동에 빠르게 대응할 수 있으며, 주 전원의 느린 응답성을 보상하여 조종성능을 향상시킬 수 있다. 제안된 전력버퍼모듈은 시뮬레이션을 통해 그 유용성을 검증하였다.