• Proceedings of the CALSEC Conference
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• 2002.01a
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• pp.461-466
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• 2002

테스트 목적 -제공받은 3D 게임엔진 품질을 기능성, 신뢰성, 성능 등에 의거 객관적이고 -정확한 방법 및 기준을 적용하여 시험평가 실시 -테스트 방법 및 기술을 게임종합지원센터에 접수 테스트 범위 -게임엔진의 주요 기능별 가능 시험 -게임엔진의 신뢰성 시험 -게임엔진의 성능 시험 -게임엔진의 문서화 시험 -게임엔진의 사용 편이성 시험(중략)

• Aerospace Engineering and Technology
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• v.2 no.2
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• pp.186-198
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• 2003

Small sized engine test stand has been built up and modified to measure the engine performance for 15g class small UAV propulsion systems. An engine performance standard test stand was developed in order to validate the prediction performance and to shoot trobles. The performance data were measured and analyzed for the newly developed gasoline engine.

• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.6
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• pp.42-49
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• 2014

Test device using virtual engine simulator can help reduce the number of engine tests through tests similar to the actual engine tests and repeat the test under the same condition, and thus reduce the engine maintenance and operating costs. Also, as it is possible to easily implement extreme conditions in which it is hard to conduct actual tests, it can prevent engine damages that may happen during the actual engine test under such conditions. In this study, an upgraded small jet engine performance test device was developed that can conduct both real and virtual engine test by applying real-time engine model to the existing micro jet engine performance test device that was previously developed by authors. This newly developed multi-purpose small jet engine performance test device is expected to be used for various educational and research purposes.

• Journal of Aerospace System Engineering
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• v.14 no.5
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• pp.91-99
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• 2020

A liquid rocket engine goes through many tests to prove its performance before liftoff. It means the tests for setting ignition and start-up conditions or a test on design condition, which verifies the design performance. However, the development process requires verification of performance under off-design conditions through tests involving different operating conditions, which affects the duration of engine development. The off-design performance test is performed by altering the conditions of the propellant supplied to the engine in conjunction with the engine performance test that varies the opening of the control valves in the engine. This paper is based on the results of the engine tests performed at the KSLV-II engine test facilities in the Naro Space Center and describes the operations of the test facility for off-design condition test that changes the inlet conditions of the turbo-pump due to changes in the pressure and temperature of the propellant supplied to the test engines.

• Aerospace Engineering and Technology
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• v.2 no.1
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• pp.1-10
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• 2003

Methodology of predicting steady performance of gas turbine engine from transient test data was explored to develop an economic performance test technique. Discrepancy of transient performance from steady performance was categorized as dynamic, thermal and aerodynamic transient effects. Each effect was mathematically modeled and quantified to provide correction factors for calculating steady performance. The influence of engine inlet/outlet condition change on engine performance was corrected firstly, and then steady performance was predicted from the correction factors. The result was compared with steady performance test data. This correction method showed an acceptable level of precision, 3.68% difference of fuel flow.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.16 no.5
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• pp.3030-3034
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• 2015

It is important to consider powertrain cooling performance, when engine is applied to new vehicle. If the performance is poor, engine will be damaged by overheating. But, the development timing of engine is faster than timing of vehicle, it is difficult to test the cooling performance of new engine and vehicle. In this study the powertain cooling performance was estimated with some test and calculation data. First, the heat rejection test was conducted. From this test, the heat rejection data at required rpm and load was acquired. Second, coolant flow test was conducted. From this test coolant flow rate to radiator was measured. Then engine torque and rpm was calculated from vehicle load and speed. Vehicle load and speed was calculated from test mode. Then by comparing these data, the powertrain cooling performance was estimated.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.165-169
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• 2007

Qualification test range for Lox/Kerosene gas generator cyle liquid rocket engine was determined by considering engine dispersion and flight inlet conditions. With various pump characteristics, the operation range of components and system was investigated through dispersion analysis. The variation of engine performance shows opposite trends in calibration and dispersion.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1999.10a
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• pp.5-5
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• 1999

3단형 과학로켓(KSR-III)의 기본형 및 응용형에 공통으로 사용되는 주엔진은 액체산소를 산화제로, 케로신을 연료로 사용하는 액체추진기관이다. 엔진 기본설계를 통하여 로켓 임무 요구사항에 부합되도록 엔진 각 부분의 기본제원을 설정하였고, 엔진의 형상을 결정하였다. 설계된 엔진의 성능검증 작업은 분사시험용 엔진, 축소형 엔진, 엔지니어링 모델 및 비행시험모델의 설계/제작/시험을 통하여 순차적으로 수행할 계획이다. 본 연구는 3단형 과학로켓 엔진의 기본설계 및 성능검증 계획에 관한 것이다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.11a
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• pp.9-9
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• 2000

우주추진기관의 모든 부품은 생산 시 규정된 절차를 거쳐서 작동의 이상유무를 확인하는 시험을 거친다. 우주추진기관은 특별한 경우를 제외하고는 실 비행 상태에서 시험하기가 어렵거나 불편하기 때문에 지상에서 시험을 수행하여 성능 및 안정성 등을 확인하게 된다. 지상연소시험을 수행하기 위해서는 비행용 엔진을 대상으로 엔진 메니폴드에 비행 시와 같은 조건의 추진제가 공급될 수 있게 해줘야 한다. 기존에 시험장이 이미 구축되어 있는 경우 엔진의 운용조건에 맞추어 엔진에 맞게 엔진과 시험설비 연결부분이 수정되게 된다.(중략)

• Journal of the Korean Society of Propulsion Engineers
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• v.7 no.3
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• pp.53-60
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• 2003

A test stand was developed to measure static performance of a reciprocating engine on the ground, related to the small aircraft being developed by KARI. The test stand consists of an apparatus to install and operate a pusher-type propulsion system and a data acquisition system to process many performance parameters including engine torque and propeller thrust as well as monitoring of the engine operations. First, the performance data from the basic operation tests were compared with the original engine data so the capacity of the test stand was verified. Engine performance tests were carried out with various test conditions through three stages, and it was measured and analyzed that the manifold pressure, the torque, and the back pressure of the engine, and the static thrust of the propeller.