• Proceedings of the KIEE Conference
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• 2015.07a
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• pp.1573-1574
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• 2015

본 연구에서는 선형동기전동기(Linear Synchronous Motor)의 회전형 시험기 설계를 위해서 그 기본 모델이 되는 선형동기 전동기의 기초 설계 과정을 통해 주요 파라미터를 선정하고 FEM 모델을 도출하였다. 또한 유한요소법을 이용하여 전자계 해석을 수행하여 선형동기전동기의 특성을 분석하였고, 설계된 선형동기전동기를 바탕으로 회전형으로 모델링하여 시험기의 형태로 설계하였으며, 유한요소해석을 통해 요구 사양을 만족함을 확인하였다.

• Proceedings of the Korean Institute of Electrical and Electronic Material Engineers Conference
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• 2005.05b
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• pp.89-93
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• 2005

인버터 구동 회전기기의 운전수명을 보장하기 위해서는 기존의 시험 방법에 포함되지 않은 PWM 가변속 구동에 따른 고조파 손실과 과도전압 충격의 문제점을 고려한 새로운 장기 신뢰성 평가 기법이 절실히 필요한 상황이기 때문에 본 연구에서 시험모델을 설정하고자 한다. 결과로는 종래는 비파괴시험에 의한 off-line 진단법이 주로 시행되었지만, 최근에는 상태량을 계측하는 신종 센서의 개발이 진행되어 모니터링법에 의한 on-line 진단법이 점차로 증가하고 있다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.977-980
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• 2011

In this paper, explain to development of low pressure axial compressor performance test rig in KARI. Performance test rig consist of a entrance section, rotor, stator, shaft, rig housing, bearing housing and exit section. Test rig design structural optimization to rotor dynamics analysis of the simplified rotor-shaft assembly and flow analysis of entrance/exit section.

• Proceedings of the KIPE Conference
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• 1999.07a
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• pp.531-534
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• 1999

벡터제어기법은 유도전동기의 무부하 시험 및 구속시험 등을 통하여 구한 고정자 및 회전자 상수를 이용한 전동기의 수학적 모델을 기초로 하여 이루어진다. 따라서 유도전동기의 수학적 모델을 구성하는 고정자 및 회전자 상수의 정확성은 곧 벡터제어의 성능과도 직결된다. 하지만, 온도 상승 등의 영향으로 회전자 저항값은 정상치보다 최대 80∼100%까지 상승 할 수 있으며, 이는 벡터제어의 특성을 저하시키는 요인이 된다. 따라서, 본 연구에서는 회전자 저항을 이용하는 자속 PI제어부를 회전자 저항을 사용하지 않는 자속 퍼지제어부로 대체하고 측정한 3상 전류를 이용하여 회전자 저항값의 변화를 실시간으로 추정·보상하는 퍼지추론기를 구성하므로써 회전자 저항의 변화에도 최적의 효율 및 성능을 가지는 보완된 벡터 제어 기법을 개발하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.10
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• pp.975-983
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• 2009

This paper presents the work being carried out in order to deduce hover performance of a small-scale single rotor blade as a preliminary study of a small coaxial rotor helicopter development. As an initial research, a test stand capable of measuring thrust and torque of a small-scale rotor blade in hover state was constructed and fabricated. The test stand consists of three parts; a rotating device, a load measuring sensor and a data acquisition system. Thrust and torque were measured with varying collective pitch angle at fixed RPM. Through this research, hover performance tests were conducted for a small-scale single rotor blade operating in low Reynolds number ($Re\;{\approx}3{\times}10^5$), as well as for verifying the test stand itself for acquiring hover performance.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.10
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• pp.894-900
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• 2012

The purpose of this research is to investigate the dynamic roll-damping characteristics of a spin-stabilized projectile in wind-tunnel testing. In the present work, the high-speed wind-tunnel tests for the roll-damping measurements were conducted on a finned spin-stabilized projectile model in the Agency for Defense Development's Trisonic Wind Tunnel at spin rates about 8,000 rpm. The test Mach numbers ranged from 0.6 to 0.9, and the angles of attack ranged from 0 to +15 deg. The evaluation of the bearing friction parameter was also conducted to eliminate the tare damping moment from the aerodynamic damping moment.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.10a
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• pp.173-178
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• 2003

The study was performed to understand combustion characteristics of the slinger combustor. Liquid fuel is discharged radially outwards through injection holes drilled in the high speed rotating shaft. We observed atomizing characteristics with variation of fuel nozzle rotating speed by using PDPA system. The mean drop diameter highly depends on fuel nozzle rotating speed. In KARI combustion test facility, Ignition and combustion tests were performed by using real scale combustor. In the test results, ignition and combustion efficiency were increased according to increasing fuel nozzle rotating speed. The measured radial temperature distribution at the combustor exit shows stable and fairly good distribution.

• Journal of the Korean Society of Propulsion Engineers
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• v.8 no.1
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• pp.38-43
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• 2004

The study was performed to understand combustion characteristics of the slinger combustor. Liquid fuel is discharged radially outwards through injection holes drilled in the high speed rotating shaft. The spray test was peformed to verify atomizing characteristics with variation of fuel nozzle rotational speed by using PDPA system. SMD was measured at different RPM and values are 70$\mu\textrm{m}$ at 5,000RPM rpm, 60$\mu\textrm{m}$ at 10,000RPM and 40$\mu\textrm{m}$ at 20,000RPM. In the results, we found out that SMD is grown smaller with increasing rotational speed. In KARI combustion test facility, Ignition and combustion tests were performed by using combustor test rig. In the test results, ignition and combustion efficiency were improved according to increasing rotational speed. The measured radial temperature distribution at the combustor exit shows stable and fairly good distribution.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.34 no.4
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• pp.391-397
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• 2010

Performance tests of a liquid-oxygen pump were carried out using liquid nitrogen (LN2) as a working fluid in a cryogenic turbopump test facility in Korea Aerospace Research Institute (KARI). The tests were performed at 30-55% of the design rotational speed, and the results were compared with those from a water test. The experimental results confirmed the similarity of the hydraulic performance, which allows the prediction of the pump performance at a design rotational speed of 20,000 rpm. The overall cavitation performance of the pump in the cryogenic environment was better than that in the water environment for all ranges of flow rates and rotational speeds. Critical cavitation number at the design flow rate was determined as 0.012 from the cryogenic test, and as 0.024 from the water test. The improved cavitation performance is due to the thermodynamic effect in cryogenic fluids.

• 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.