• 한국자동차공학회논문집
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• 제7권9호
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• pp.36-47
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• 1999

Three-way catalyst converter, cleaning up the exhaust gas contamination of SI engine, has the best efficiency when A/F ratio is near the stoichiometry . The feedback control using oxygen sensors in the exhaust manifold has limits caused by the system delays. So the accurate measurement of air flow rate to an engine is essential to control the fuel injection rate especially on transient condition like the rapid throttle opening and closing. To measure the rapid change of flow rates. the air flow meter for the engine requires quick response, flow reversal detection, and linearity . Tjhe proposed integration type air flow meter (IFM), composed of an ultrasonic flow meter with an integration circuit, has significantly improved the measurement accuracy of air mass inducted through the throttle body. The proposed control method estimated the air mass at the cylinder port using the measured air mass at the throttle . For the fuel dynamic model, the two constant fuel model is introduced . The control parameters from air and fuel dynamics are tuned to minimize the excursion of the air fuel ratio. As a result A/F ratio excursion can be reduced within 5% when throttle rapidly opens and closes at the various engine conditions.

• 한국환경과학회지
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• 제7권6호
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• pp.793-801
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• 1998

In this study, the Dilution Method is used to measure river discharge through the hydraulic model test. the dilution method is divided into Constant-Rate-Infection Method and Slug-Injection Method in the river discharge measurement techniques. When the dilution method is applied in the hydraulic model flume, it is analyzed that the estimated error of constant-rate-injection method is less than that of the slug-in-jection method, and the result shows that floodflow analysis is more efficient than lowflow analysis as compared observed discharge with calculated discharge. The result of statistical error analysis shows that the constant-rate-injection method is appropriate technique for the measurement of the river discharge. Therefore, the dilution method among the river discharge measurement techniques can be applied for the river basin which can't be measured with current meter or unsteady-flow regime in the urban-small drainage or hydraulic structure equipment area and can be obtained more exact results than any other discharge measurement techniques.

• 한국태양에너지학회 논문집
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• 제34권1호
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• pp.117-124
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• 2014

Airtightness standards using fan pressurization method are normally used for measuring small buildings, detached houses, and apartment units. And, it is easy to conduct airtightness measurement through this fan pressurization method. However, it can be difficult to achieve accurate measurement results for the large buildings as the height and volume of the buildings have been increased. In this paper, we studied the principle of airtightness method by fan pressurization. And, we reviewed the measurement process described in ISO 9972, EN 13829, ASTM E779, ATTMA TS 1, CAN/CGSB 149.15, and JIS A 2201. Then, we categorized the methods' items according by air flow rate (Q) and pressure difference(${\Delta}P$). As a result, we made a comparison analysis on the measurement methods appeared in each standards. And, we achieved 5 test conditions about air flow rate and pressure difference to state requirements for large buildings airtightness measurement.

• International Journal of Fluid Machinery and Systems
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• 제3권2호
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• pp.129-136
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• 2010

The attachment of inducer upstream of main impeller is an effective method to improve the suction performance of turbopump. However, various types of cavitation instabilities are known to occur even at the designed flow rate as well as in the partial flow rate region. The cavitation surge occurring at partial flow rates is known to be strongly associated with the inlet back flow. In the present study, in order to understand the detailed structure of internal flow of inducer, we firstly carried out the experimental and numerical studies of non-cavitating flow, focusing on the flow field near the inlet throat section and inside the blade passage of a two bladed inducer at a partial flow rate. The steady flow simulation with cavitation model was also made to investigate the difference of flow field between in the cavitating and no-cavitating conditions.

• 한국유체기계학회 논문집
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• 제17권4호
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• pp.5-10
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• 2014

It is possible for the nation's largest flowmeter calibration system in K-water to calibrate flow rate up to $2,700m^3/h$ and diameter 800mm. However, the calibration and measurement capability of K-water's system is not satisfied in comparison with other developed countries. In this study, we find the dominant factors related to the uncertainty of weight and time measurement for gravimetric flowmeter calibration system. As a results of improving the system, the combined standard uncertainty has been improved $1.099{\times}10^{-3}$ to $2.332{\times}10^{-4}$. So calibration and measurement capability got 0.08 percent of the relative expanded uncertainty for maximum flow rate using the coverage factor(k=2).

• 한국항공우주학회지
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• 제46권5호
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• pp.359-367
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• 2018

회전익기가 하강 비행 시 발생하는 와류 고리 상태는 회전면 근처에 도넛 모양의 순환유동을 발생시키며, 추력 상실로 인한 기체의 추락을 유발한다. 본 논문에서는 무인 비행체의 종류 중 하나인 쿼드콥터의 와류 고리 상태에서의 유동장을 물리적으로 규명하였다. 한국항공우주연구원 1m 아음속 풍동에서 쿼드콥터의 하강 비행을 모사했으며, 유동장 계측을 위해 입자 영상 유속계(PIV)를 이용했다. 정지 비행 상태의 유도 속도를 운동량이론을 이용하여 추정하고, 이를 통해 와류 고리 상태를 유발할 수 있는 하강 속도의 범위에서 시험을 수행하였다. 또한 하강률에 따른 유동장 계측뿐만 아니라 프로펠러 간의 간격을 달리 주어서도 와류 고리의 발달 및 진행방향을 확인하였다. 더불어 본 연구 결과는 쿼드콥터 주변의 유속 측정을 통해서도 와류 고리 상태를 예측할 수 있다는 것을 보여준다.

• 한국정보통신학회논문지
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• 제9권8호
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• pp.1683-1690
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• 2005

본 논문에서는 UDP에서의 동적 흐름 제어기법을 제안하며, 기존의 동적 흐름제어에서 많이 사용되는 측정 요소인 패킷 손실과 왕복시간의 특성에 대해 분석한 후 새로운 측정요소인 RSTT를 제안한다. 제안된 RSTT를 사용한 알고리즘은 전송률을 조절하는데 있어서 현재 측정된 네트워크 상태와 과거의 상태를 고려함으로써 보다 정확한 네트워크 상태측정을 할 수 있었다. 비교실험을 위하여 전송량과 네트워크의 상태를 출력하고 네트워크의 흐름패턴에 대한 상세 정보를 보여주는 네트워크 상태측정 프로그램을 구현하였다. 이를 이용한 성능실험을 통해 제안된 알고리듬이 기존 알고리듬에 비해 낮은 패킷 손실률로 네트워크 상태에 더욱 빠르게 적응함을 보여준다.

• 한국수자원학회논문집
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• 제37권5호
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• pp.375-386
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• 2004

갈수량은 수자원의 개발 및 관리에 매우 중요한 인자중의 하나이다. 신뢰성 높은 갈수량을 측정하기 위해 한국수자원공사는 2000년도에 용담댐 시험유역에 5피트 규격의 파샬플륨을 설치하였다. 파샬플륨은 유량측정을 하기 위해 독특한 모양을 가지고 있으며, 부정확한 유량관측을 유발하는 퇴사문제를 거의 해결한 시설물이다. 본 연구에서는 3차원 CFD (Computational Fluid Dynamics) 모형으로 5가지 수위에 대해서 완전월류(free flow)시 파샬플륨의 유동을 해석하였다. CFD모형에 의해 산정된 결과와 ISO에 제시된 유량공식, USBR에 제시된 유량공식 및 수위-유량관계식으로 산정한 유량을 비교하였다. 그 결과 ISO와 USBR의 공식에 의해 산정된 유량은 거의 동일했으나, 3차원 CFD모형에 의한 유량은 경험공식에 의한 유량보다 9%정도 크게 나타났고 수위-유량관계식에 의한 유량은 경험공식에 의한 유량보다 16%정도 작게 나타났다.

• International Journal of Fluid Machinery and Systems
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• 제10권3호
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• pp.307-317
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• 2017

In liquid-propellant rockets, POGO instability can occur, in which a fluctuation of propellant supply to the engine, a thrust fluctuation, and a structural vibration are coupled. For the prediction of this instability, it is required to provide dynamic characteristics of the pump represented as the transfer matrix correlating the upstream and downstream pressure and flow rate fluctuations. In the present study, the flow rate fluctuation is evaluated from the fluctuation of pressure difference at the different locations assuming that the fluctuation is caused by the inertia of the flow rate fluctuation. The experiments were performed in some flow conditions, and it was shown that the tendencies of dynamic characteristics are related to excitation frequencies, cavitation numbers and flow rate coefficients.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2001년도 춘계학술대회논문집D
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• pp.777-781
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• 2001

An Altitude Engine Test Facility(AETF) was built at the Korea Aerospace Research Institute in October 1999 and has been being operated for altitude testing of the gas turbine engines of 3,000 Ibf class or less. The AETF has been calibrated using several engines such as J69 engine of Teledyne Co. as a facility checkout engine. Based on the test results, uncertainty analyses on the air flow rate and thrust were performed according to ASME PTC 19.1-1998. As the analyses showed that the level of uncertainty was not satisfactory over the whole operating envelop, several modifications of the facility and testing method were made in order to improve the measurement uncertainty. As a result, the uncertainty of the air flow measurement was improved by 0.1 % over all the test conditions, and the net thrust measurement by upto 3%. The improved measurement uncertainties of air flow and thrust are 0.68-0.73% and 0.4-1.3%, respectively.