• The Journal of Aerospace Industry
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• s.65
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• pp.89-106
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• 2003

항공기의 자동 착륙 알고리즘을 위한 고 정밀 유도방식에 IBLS(Integrity Beacons Landing System)나 MLS(Microwave Landing System)와 같은 유도 제어 방식을 사용하여 유인 항공기나 무인 항공기의 유도 착륙에 사용하고 있다. 당 연구에서는 무인항공기의 자동 착륙을 위한 실제적인 요구사항들이 분석되었고, 자동 착륙 유도장치로 IBLS와 MLS가 선택되어 각각의 기능과 특성들이 수학적으로 모델링 되었다. 또한 고전제어와 최적제어의 2가지 방식으로 무인항공기의 자동 착륙을 통제하기 위한 autopilot이 설계되어 그 유효성과 특징들이 분석되었다. IBLS, MLS, autopilot, 그리고 이러한 자동 착륙 유도제어 시스템이 적용되는 대상체인 무인항공기와 대기환경 및 외란에 대한 수학적 모델들은 Simulink와 ANSI C를 사용하여 단위 S/W 모듈들로 작성되었고, 여기에 GUI모듈이 추가되어 하나의 통합 시뮬레이션 S/W가 완성되었다. 모의시험평가는 총 2단계로 구성되었는데, 대기 외란이 주어졌을 때 IBLS와 MLS의 유효성을 1차적으로 검증하였고, 2단계 모의수치실험에서는 MLS 유도센서 방식에 따른 고전제어기 및 최적제어기의 항공기 종 방향 운동에 대한 강인성 비교를 시도하였다.

• Journal of Energy Engineering
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• v.25 no.4
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• pp.124-132
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• 2016

In order to estimate the effect of flow distributors connected to an upper nozzle of CMT(Core Makeup Tank) on the thermal-hydraulic characteristics in the tank, a simplified 2 inch Small Break Loss of Coolant Accident(SBLOCA) was simulated by skipping the decay power and Passive Residual Heat Removal System(PRHRS) actuation. The CMT is a part of safety injection systems in the SMART (System Integrated Modular Advanced Reactor). Each test was performed with reliable boundary conditions. It means that the pressure distribution is provided with repeatable and reproducible behavior during SBLOCA simulations. The maximum flow rates were achieved at around 350 seconds after the initial opening of the isolation valve installed in CMT. After a short period of decreased flow rate, it attained a steady injection flow rate after about 1,250 seconds. This unstable injection period of the CMT coolant is due to the condensation of steam injected into the upper part of CMT. The steady injection flow rate was about 8.4% higher with B-type distributor than that with A-type distributor. The gravity injection during hot condition tests were in good agreement with that during cold condition tests except for the early stages.

• The Journal of Korean Institute for Practical Engineering Education
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• v.3 no.2
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• pp.100-105
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• 2011

By adopting HIL(Hardware-in-the-Loop), component characteristics in vehicle environment can be obtained without implementing component in the vehicle. In this paper, when specific motor is adopted as traction motor in hybrid electric vehicle HIL implementation procedures are explained. In order to implement HIL method motor testing. vehicle performance simulator and load characteristic are explained. Vehicle controller used in simulator is directly uploaded in real controller. Especially as a load dynamometer actively controlled motor system is used without connecting conventional mechanical inertia. Motor characteristics are obtained using HIL implementation when test motor is used as a traction motor for parallel hybrid electric vehicle. Proposed method can be used as experimental equipment to educate driving characteristics of hybrid electric vehicle.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.7
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• pp.660-665
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• 2011

Reconfigurable Flight Simulator for an airborne tactical mission based on virtual reality technology is developed as a software configurable cockpit with computer display as virtual instruments. It can simulate F-15K, KF-16, T/A-50 class fighter and depending on simulated cockpit, control stick and throttle are replaceable. For effective immersion, Video See-Through type HMD is applied.

• Journal of the Institute of Electronics Engineers of Korea TC
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• v.38 no.3
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• pp.1-8
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• 2001

In the DS/CDMA mobile communication systems, the parallel interference canceller is used in order to reduce the multiple access interference and the multipath fading. It is needed the accurate interference estimate in the multistage parallel cancellation. In this paper, the adaptive cancellation method and the new tentative decision device arc proposed and the performance is analyzed. The adaptive cancellation method uses the normalized least mean square(NLMS) algorithm to calculate the weight adaptively, and new tentative decision device uses the hyperbolic tangent decision with null zone. Computer simulation shows that the proposed scheme has the improved performance and the number of user is increased 48% compared with the conventional receiver.

• Proceedings of the KIEE Conference
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• 2002.11b
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• pp.329-334
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• 2002

우리나라 전력계통의 특성상 남부의 전원단과 수도권의 부하중심단과의 거리가 존재하여 안정적인 계통전압제어에 어려움이 존재한다. 이러한 계통전압제어의 어려움을 극복하기 위해 154kV 계통에 SC Bank를 설치 운용중에 있다. 운전 환경상 차단기의 투입과 차단이 잦은 154kV SC Bank에 리액터가 소손되는 등의 문제점이 발생하고 있어 154kV SC Bank의 써지응답특성을 규명하고 차단기의 투입차단시 발생하는 써지전류의 저감에 대한 연구의 필요성이 대두되고 있다. 본 연구에서는 154kV SC Bank를 대상으로하여 현장조사와 현장실증을 통해 써지전류를 측정하고, 모의를 통해 써지응답특성을 규명하였다. 그 결과, 차단기의 접점의 상태와 피뢰기의 동작여부에 의해 써지전류가 크게 영향을 받는다는 점을 확인하였다. 154kV SV Bank를 대상으로 한 현장시험과 서지응답특성의 분석결과를 기본으로 하여 피뢰기의 영향과 차단기의 투입차단 영향을 최소화하는 방안으로 피뢰기의 분리운전으로 전류재단현상을 막아 급준써지전류의 발생을 억제하고 저항투압방식의 차단기로 써지전류를 30%이하로 억제할 수 있음을 실증과 모의로 확인하였다.

• The Journal of the Korea institute of electronic communication sciences
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• v.14 no.2
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• pp.339-344
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• 2019

In this paper, a digital home electric overload alarm system based on DSP for smart home automation which can minimize electrical fire damage caused by an home electrical overload was made experimentally. To verify the validity of the home electrical overload alarm technology, an electric overload alarm performance evaluation system which can artificially generate the electrical overloads was designed, developed, and constructed, and the effectiveness of the overload alarm developed by the overload test was verified. In particular, an overload test EMTP model based on EMTP-RV was developed, and simulation and measurement results obtained from the overload test were compared, and the reliability of overload performance verification results was confirmed.

• Journal of the Korea Society for Simulation
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• v.21 no.1
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• pp.81-88
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• 2012

In the M&S filed, The Battle Lab is available for acquisition, design, development tool, validation test, and training in the weapon system of development process. Recently, the Battle Lab in the military of Korea is still in an early stage, in spite of importance of battle lab construction. In the environment of network centric warfare, a practical use of the M&S which is connecting live, virtual and constructive model can be applied to all field of System Engineering process. It is necessary thar the Battle Lab is not restricted by time and space, and is possible for the technical implementation. In this paper, to guarantee the interoperability of live and virtual simulation, virtual simulators connect live simulators by using the tactical data link. To guarantee the interoperability of virtual and constructive simulation, both virtual simulators and constructive simulators use the RTI which is the standard tool of M&S. We propose the System that constructed the Air Defence Battle Lab. In case of the approach of target tracks, The Air Defence Battle Lab is the system for the engagement based on a command of an upper system in the engagement weapon system. Constructive simulators which are target track, missile, radar, and launcher simulator connect virtual simulators which are MCRC, battalion, and fire control center simulators using the RPR-FOM 1.0 that is a kind of RTI FOM. The interoperability of virtual simulators and live simulators can be guaranteed by the connection of the tactical data links which are Link-11B and ATDL-1.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.11
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• pp.35-41
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• 2006

This paper proposes an algorithm for switching LQ(Linear Quadratic) controllers designed at each flight envelope without a bump phenomenon. This algorithm is derived to apply to LQ controller more easily than existing implementation algorithm and is proposed to consider trim points of nonlinear models, which is adequate to real applications. This paper exemplifies the control performance improvement via simulations applied to LQ control of a supersonic test aircraft as a benchmark problem to test the proposed algorithm performance.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.20 no.8
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• pp.181-189
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• 2019

An aircraft power distribution device distributes and controls the power generated by the generator and provides overcurrent protection. There are many defect phenomena that make AC power distribution impossible during flight, which poses a problem in because some electronic equipment cannot be operated. We describe a process of deriving the root cause of defects by using vibration testing equipment to simulate the vibration conditions during aircraft flight, which result in defects. The results show that the cause of the defect is internal wiring damage caused by the vibration of the contactor of the AC power distribution device. Therefore, the shape of the contactor was improved to solve this problem. We also improved the test procedure by performing defect detection tests using vibration testing equipment to detect a faulty contactor. As a result of the improvements, a component certification test and flight test proved that the defect phenomena of the AC electrical master box were improved.