• 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 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.

• The Journal of Korean Institute of Communications and Information Sciences
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• v.37A no.12
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• pp.1085-1092
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• 2012

Mobile communication systems define user state transition mechanisms in order to manage radio resources and battery power efficiently. In the state transition mechanism, a state with a higher energy consumption inherently offers a shorter access delay, so there is a tradeoff between the energy and delay performances. In this paper, we analyze the user state transition mechanism of UMTS by considering the bursty traffic attributes of mobile applications. We perform a numerical evaluation for both the energy consumption and the activation delay by Markov modeling of the state transition mechanism, and investigate their tradeoff relationship as functions of operational parameters. The resulting energy-delay tradeoff curves clearly show an achievable performance bound of the user state transition mechanism and also offer an optimal operation strategy to minimize the energy consumption while guaranteeing the delay requirement.

• 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.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1998.04a
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• pp.6-6
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• 1998

중형항공기용 터보팬 엔진의 정상상태 및 천이상태 성능을 해석하고 제어기 설계를 위한 선형모델을 구하였다. 정상상태 성능해석은 설계점으로 선정한 지상정지조건과 최대상승조건(Mach=0.78, 고도=36000ft) 및 순항조건(Mach=0.78, 고도=39000ft)을 고려하였으며, 저압압축기의 공회전 상태에서 최대 회전속도까지의 부분부하성능해석을 수행하였다. 부분부하 성능해석 결과 90% RPM 조건에서 가장 연료소모율이 적어 경제적임을 알 수 있다. 동적 성능모사는 각각의 대기조건에서 연료가 Step 증가, Ramp 증가 및 감소, Step 증가 후 Ramp 감소하는 경우에 대해 수행하였다. 모사결과 고려된 모든 조건에서 연료의 Step 증가시 고압압축기의 터빈입구온도가 제한온도를 초과하여, 보다 빠른 가속과 최적의 성능을 위해서는 적절한 제어가 필요함을 알 수 있었다. 또한 최대상승조건에서 연료를 Step 증가시킬 경우 고압압축기에서 실속이 발생하여 이에 대한 대책도 필요함을 알 수 있었다.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.6
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• pp.63-69
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• 2011

The Smart UAV must have the control characteristics of propulsion system necessary for both rotary aircraft and fixed wing aircraft though it equips turbo-shaft engine. To develop an electronic engine controller in the future, it is necessary to accumulate the experience of engine operation and data of tilt rotor aircraft. For this purpose, the computer programs which predict engine performance in the steady state and transient state can be utilized for the supplementation of flight test data. In this work, we developed a dynamic analysis program using engine performance data gathered during the flight tests. In addition the accuracy of the program was verified through comparison with flight test data and the results of steady-state performance analysis program.

• Proceedings of the Korea Information Processing Society Conference
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• 2021.11a
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• pp.910-913
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• 2021

Successor representation (SR) 은 두뇌 내 해마의 공간 세포가 인지맵을 구성하여 환경을 학습하고, 이를 활용하여 변화하는 환경에서 유연하게 최적 전략을 수립하는 기전을 모사한 강화학습 방법이다. 특히, 학습한 환경 정보를 활용, 환경 구조 안에서 목표가 변화할 때 강인하게 대응하여 일반 model-free 강화학습에 비해 빠르게 보상 변화에 적응하고 최적 전략을 찾는 것으로 알려져 있다. 본 논문에서는 SR 기반 강화학습 알고리즘이 보상의 변화와 더불어 환경 구조, 특히 환경의 상태 천이 확률이 변화하여 보상의 변화를 유발하는 상황에서 어떠한 성능을 보이는 지 확인하였다. 벤치마크 알고리즘으로 SR 의 특성을 목적 기반 강화학습으로 통합한 SR-Dyna 를 사용하였고, 환경 상태 천이 불확실성과 보상 변화가 동시에 나타나는 2-stage 마르코프 의사결정 과제를 실험 환경으로 사용하였다. 시뮬레이션 결과, SR-Dyna 는 환경 내 상태 천이 확률 변화에 따른 보상 변화에는 적절히 대응하지 못하는 결과를 보였다. 본 결과를 통해 두뇌의 강화학습과 알고리즘 강화학습의 차이를 이해하여, 환경 변화에 강인한 강화학습 알고리즘 설계를 기대할 수 있다.

• The Journal of Korean Institute of Communications and Information Sciences
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• v.37 no.5B
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• pp.317-326
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• 2012

Recently, many researchers have studied to solve the energy consumption of network equipments since the interest of Green IT has been increased. In this paper, we apply Low Power Idle (LPI) to OBS network to reduce energy consumption of network devices. Many previous researches have focused on maximizing the sleep time of network equipments to increase the energy saving efficiency of LPI. But transition overhead caused by LPI might not only depreciate the performance of energy saving but also increase packet delay. In this paper, Transition Decision (TD) algorithm is proposed to improve energy saving efficiency by reducing the number of unnecessary transition and guarantee the required QoS such as packet delay. To evaluate the performance of proposed algorithm, we model OBS edge router with LPI by OPNET and analyze the performance of the proposed algorithm in views of energy saving, transition count and average packet delay.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.5
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• pp.100-109
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• 2003

A performacne simulation model of the PT6A-62 turboprop engine using the $SIMULINK^R$ was proposed to predict transient and steady state behaviors. The $SIMULINK^R$ has several advantages such as user-friendliness due to the GUI(Graphic User Interfaces) and ease in the modification of the computer program. The $SIMULINK^R$ model consists of subsystems to represent engine gas path components such as flight initial subsystem, compressor subsystem, burner subsystem, compressor turbine subsystem, power turbine, exhaust nozzle subsystem and integrator subsystem. In addition to subsystems, there are search subsystems to find an appropriate operating point by scaling from the 2-D components look-up table, Gasprop Subsystem to calculate the gas property precisely. In case of steady state validation, performance results analyzed by the proposed $SIMULINK^R$ model were agreed well with the analysis results by the commercial GASTURB program. Moreover in validation of the transient model, it was found that performance simulation results by the proposed model were reasonable agreement with analysis results by the well-proved computer program using FORTRAN.