• 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 Korean Society for Aeronautical & Space Sciences
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• v.30 no.5
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• pp.62-70
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• 2002

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. Engine performance tests were conducted at Altitude Engine Test Facility of KARI. 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 Korean Chemical Society
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• v.14 no.1
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• pp.109-112
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• 1970

액체구조의 천이상태 이론을 알칼리토금속 염화물에 적용시켜서 상태합을 유도하였다. 이 상태합으로부터 $SrCl_2$와 $BaCl_2$의 증기압, 몰부피, 엔트로피등의 열역학적 성질을 계산하여 실험치와 비교하였으며, 천이상태 이론이 용융염에도 잘 적용된다는 결론을 얻었다.

• Proceedings of the Materials Research Society of Korea Conference
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• 2003.11a
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• pp.215-215
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• 2003

현재 이용되고 있는 위상 변위 마스크, 즉 Cr 계열의 마스크나 MoSiON 마스크는 DUV지역에서 낮은 굴절률을 갖는다. 그 겯과 마스크의 두께가 90 nm 이상이 되고, 웨이퍼에서 패턴 형성 시 에러율이 증가하게 된다. 본 연구에서는 DUV 지역에서 굴절률이 높을 것이라고 예상되는 Zr과 Hf의 oxide를 위상 변위 마스크 물질의 선정하고 각 물질의 전자 상태와 천이 상태를 분석하여 위상변위 마스크로써의 이용가능성을 연구하자 한다. 상온에서 Zr, Hf oxide의 안정한 구조는 cubic 구조와 monoclinic 구조이다. 현재 cubic 구조의 Zr, Hf oxide에 대한 전자 상태는 연구가 많이 되어 있는 반면 monoclinic 구조에서의 전자상태 연구는 미흡하다. 본 연구에서는 monoclinic 구조를 이용하여 Zr, Hf oxide의 클러스터 모델을 제작하였다. 제작된 클러스터 모델에 대하여 DV-X$\alpha$ 계산법을 적용, 기저상태의 전자상태를 계산하였다. 그리고 각 모델에서 Zr L-edge, Hf L-edge 그리고 O K-edge의 천이상태를 연구하여, 기저 상태의 전자상태와 천이상태를 연구하여 광학 성질과의 연관성을 연구하고자 하였다.

• Journal of the Institute of Electronics Engineers of Korea SD
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• v.38 no.2
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• pp.51-51
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• 2001

본 논문은 디지털 순서회로 설계시 상태할당 알고리즘 개발에 관한 연구로, 동적 소비전력을 감소시키기 위하여 상태변수의 변화를 최소로 하는 코드를 할당하여 상태코드가 변화하는 스위칭횟수를 줄이도록 하였다. 상태를 할당하는데는 Markov의 확률함수를 이용하여 hamming거리가 최소가 되도록 상태 천이도에서 각 상태를 연결하는 edge에 weight를 정의한 다음, 가중치를 이용하여 각 상태들간의 연결성을 고려하여 인접한 상태들간에는 가능한 적은 비트 천이를 가지도륵 모든 상태를 반복적으로 찾아 계산하였다. 비트 천이의 정도를 나타내기 위하여 cost 함수로 계산한 결과 순서회로의 종류에 따라 Lakshmikant의 알고리즘보다 최고 57.42%를 감소시킬 수 있었다.

• Journal of the Korean Chemical Society
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• v.12 no.1
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• pp.18-25
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• 1968

액체 분자는 고체, 천이상태 및 기체와 같은 자유도를 갖는다는 액체구조에 관한 천이상태이론을 적용하여 액체의 표면장력과 점도를 계산하여 측정 치와 좋은 일치를 얻었다. 표면장력을 계산함에 있어서 표면 각층의 밀도는 이웃 층 사이의 밀도를 주는 관계식으로부터 쉽게 얻었다. 그리고 액체가 점성 흐름을 할때 활성화된 분자는 흐르는 방향으로는 기체와 같은 자유도를 가지나, 이에 직교한 평면상에서는 천이상태 및 기체와 같은 자유도를 갖는다고 가정하였다.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.8 no.5
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• pp.1010-1019
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• 2004

In this paper, we represent Nakagami-m fading channel as finite-State Markov Channel (FSMC) and analyze the performance of wireless communication system with varying the fading channel condition. In FSMC model, the received signal's SNR is divided into finite intervals and these intervals are formed into Markov chain states. Each state is modeled by a BSC and the transition probability is dependent upon the physical characterization of the channel. The steady state probability and average symbol error rate of each state and transition probability are derived by numerical analysis and FSMC model is formed with these values. We found that various fading channels can be represented with FSMC by changing state transition index. In fast fading environment in which state transition index is large, the channel can be viewed as i.i.d. channel and on the contrary, in slow fading channel where state transition index is small, the channel can be represented by simple FSMC model in which transitions occur between just adjacent states. And we applied the proposed FSMC model to analyze the coding gain of random error correcting code on various fading channels via computer simulation.

• Transactions of the Korean Society of Mechanical Engineers
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• v.16 no.9
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• pp.1700-1710
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• 1992

The boundary element method is applied to determine thermal stress intensity factors for a cusp crack in transient state. In the steady temperature field, numerical values of thermal stress intensity factors for a Grifith crack and a symmetric lip cusp crack in a finite body are in good agreement within .+-. 5% with the previous solutions. In transient state, the numerical values of thermal stress intensity factors for the Griffith crack are also in good agreement with the pervious solutions. In both steady and transient states, those for the symmetric lip cusp crack with the crack surface insulated or fixed to the constant temperature are calculates for various effective crack lengths, configuration parameters and uniform heat flow angles. The variations of the thermal boundary conditions of the crack surface have a effect on stress intensity factors. The signs on the values of thermal stress intensity factors can be changed in time variation.

• Journal of the Korean Society of Propulsion Engineers
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• v.2 no.2
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• pp.47-55
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• 1998

Steady-state and transient performance for the medium scale civil aircraft turbofan engine was analyzed. Steady-state performance was analyzed on maximum take-off condition, maximum climb condition, and cruise condition. At 90％RPM of the low pressure compressor, the partload performance was economized. The transient performance was analyzed with cases of the step increase, the ramp increase, the ramp decrease, and the step increase and ramp decrease for the input fuel flow. For the transient performance analysis, work matching between compressor and turbine was needed. Modified Euler method was used the integration of residual torque in work matching equation. At all flight condition, the overshoot of the high pressure turbine inlet temperature was appeared in the step and ramp increase case, and the surge of high pressure compressor was appeared in the step increase case and the ramp increase case within 5.5 seconds of maximum climb condition.

• Journal of the Korea Society for Simulation
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• v.15 no.3
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• pp.49-60
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• 2006

We propose a method to use a state transition model so that the sensing object can be distinguished through classification of signal patterns sensed by a sensor array. Focusing on the design of the model that is able to distinguish the sensed object more exactly, we present an idea in which the modeling elements, 'states' and 'transitions' are defined as each same-sized angle intervals into which the angle interval $(-\frac{\pi}{2},\frac{\pi}{2})$ is divided and the angle differences between adjacent signal values on sampling signal value sequence value sequence sensed from the sensor array in the uniform time interval, respectively. In addition we show the usefulness of our model through experiments.