• Proceedings of the KIEE Conference
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• 2015.07a
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• pp.587-589
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• 2015

본 논문에서는 IEC-61850 기반 송전선로 보호용 IED에 대한 실시간 동특성시험 방법을 학습할 수 있는 가상모의시스템을 제안한다. 가상모의시스템은 Qt Creator를 사용하여 구현하였으며, 개인의 PC를 통해서 시험환경을 구성하는 방법과 계통을 모델링하는 방법, 그리고 시험결과 확인 방법에 대하여 학습할 수 있다. 제안된 가상모의시스템을 통해 손쉽게 송전선로 보호용 IED에 대한 실시간 동특성시험 방법을 학습할 수 있음을 보였다.

• Journal of the KSME
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• v.53 no.2
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• pp.35-39
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• 2013

대형 다이나믹 시스템의 성능이 고도화되고 시스템의 크기에 비해 요구하는 정밀도가 높아지면서 이러한 대형시스템의 동특성 시험이 요구된다. 이에 이러한 시스템을 시험할 수 있는 기계장치에 대하여 소개하고자 한다.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.1
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• pp.35-44
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• 2011

Mathematical modelling for liquid rocket engine(LRE) main components were conducted to predict the dynamic characteristics when the LRE operates at the transient condition, which include engine start up, shut down, or thrust control. Propellant feeding system is composed of fuel and oxidizer feeding components except for regenerative cooling channel for the fuel circuit. Components modeling of pump, pipe, orifice, control valve, regenerative cooling channel and injector was serially made. Hydraulic tests of scale down component were made in order to validate modelling components. The mathematical models of engine components were integrated into LRE transient simulation program in concomitant with experimental validation.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.2
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• pp.83-90
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• 2002

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.54-60
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• 2010

액체로켓엔진 시스템의 시동 및 정지 또는 추력 제어와 같은 천이 작동시 동특성을 예측하기 위한 선행 연구로서 추진제 공급 시스템의 구성품에 대한 동특성 모델링을 수행하였다. 연료 공급계통과 산화제 공급 계통의 구성품들은 재생냉각채널을 제외하고 같은 것으로 가정하였다. 동특성 모델링의 대상 구성품은 펌프, 관로, 오리피스, 제어 벨브, 재생냉각채널, 인젝터 등이며 실제 엔진 시스템의 축소모형에 대한 수력시험을 통해 각 구성품의 동특성 모델링을 검증하였다.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.1
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• pp.45-54
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• 2011

A program aiming at predicting dynamic characteristics of a Liquid Rocket Engine(LRE) was developed and examined to trace entire LRE operation. In the startup period, transient characteristics of the propellant flows were predicted and validated with hydraulic tests data. An arrangement of each component for the pipelines was based on an operating circuit of open cycle LRE. The flow rate ratio for the gas generator and the main chamber was determined to mimic that of real open cycle LRE. Individual component modeling at its transient was completed and was integrated into the system prediction program. Essential parameters of the component dynamic characteristics were examined in an integrated fashion.

• Proceedings of the KIEE Conference
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• 2006.07a
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• pp.99-100
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• 2006

지금까지 국내 디지털 보호계전기의 성능 검증은 동작치 특성 시험 등 정특성시험(steady-state performance) 검증 위주로 수행되어 왔으며, 신규개발 디지털 보호계전기 및 신규 도입 디지털 보호계전기에 대해서는 정특성 시험과 함께 시뮬레이터를 이용한 동특성 시험을 병행하여 왔다. 동특성 시험은 보호계전기에 내장된 계전요소들의 유기적인 성능을 검증할 수 있는 시험으로서 복수 개의 보호계전요소를 탑재하고 있는 디지털 보호계전기를 검증하기 위해서는 필수적인 성능검증 수단이다. 그러나 이러한 장점들과 편리함에도 불구하고 디지털 보호계전기의 성능검증에 사용되는 계통 모델이 실 계통을 정확하게 반영하지 못할 경우 검증 결과의 신뢰성을 보장하기가 어렵다. 본 논문에서는 154kV 송전선로 보호용 디지털 보호계전기의 성능 검증을 위한 기반 구축 과정 및 결과에 대해서 기술한다.

• Proceedings of the KSME Conference
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• 2004.04a
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• pp.568-577
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• 2004

• Journal of Aerospace System Engineering
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• v.12 no.2
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• pp.30-36
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• 2018

In this study, a small-scaled test system for a tip jet rotor was developed to contribute to the research on unmanned compound rotorcraft. The performance and dynamic characteristics of the tip jet rotor were investigated using the test system. The diameter of the tip jet rotor was set to 2m in consideration of the size of the test site and the pneumatic supply capacity of the. The rotating speed of the rotor was controlled by the pressure of the compressed air. The thrust and forces during the rotor rotation were measured using a load measuring device. A hydraulic actuator was installed for the dynamic test and full-bridge strain gages were attached to the root of each blade to measure the flap, lag, and torsion-wise responses generated when the rotor is excited by the actuator. The performance and dynamic characteristic tests were conducted at various rotor speeds and blade pitches. In order to check the validity of the test results, the results were also compared with the CAMRAD II analysis.

• Journal of Aerospace System Engineering
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• v.11 no.6
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• pp.84-91
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• 2017

The dynamic characteristics of a ducted fan in hovering condition were investigated. The section properties of the fan blade were calculated, and a simulation model was developed according to the rotor system components. Dynamic analyses were conducted relative to the rotational speed and the collective pitch. The proposed ducted fan system showed less aero-elastic instability within the designated operating ranges. To verify the analytical approach, a rotating test stand of the ducted fan was set up. A functional test of the assembly was carried out to determine the kinematics and interference between components. The non-rotating and rotating normal frequencies were measured by excitation of the collective pitch using hydraulic actuators. The results indicated a correlation between the test equipment and the simulation model.