• Proceedings of the KIPE Conference
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• 2018.11a
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• pp.24-26
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• 2018

본 논문은 일사량 변화 시, 최대 출력점을 추종하는 태양광 발전시스템의 동적 응답특성을 향상시키기 위해 가변 스텝 사이즈 기반의 P&O (perturb & observe) 알고리즘을 제안하였다. 제안된 기법은 일사량과 PV (photovoltaic) 전류 관계로부터 일사량 변화에 따른 최대 전력점 전류 $I_{MPP}$변화 특성을 이용하며, 새로운 I-V 곡선에서 PV 동작점을 최대 출력점으로 빠르게 이동시키는 고속모드와 정상상태 부근에서 정상상태 효율 향상을 위한 가변 스텝 모드로 구성된다. 시뮬레이션 및 실험을 통해 $500W/m^2$와 $1000W/m^2$ 일사량 증감 조건에서 제안된 MPPT(maximum power point tracking) 기법의 추종 성능을 검증하였으며, MPPT 주기가 2초이고 일사량 $500W/m^2$과 $1000W/m^2$ 증감을 할 때 추종시간은 약 30초 정도이며, 정상상태 PV 전압변동은 약 0.1V로써 일사량 변화 조건에서 제안된 MPPT 기법의 알고리즘 성능을 검증하였다.

• Journal of the Korean Society of Propulsion Engineers
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• v.8 no.2
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• pp.32-38
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• 2004

A comprehensive understanding is given for the hot-firing test results, which were obtained throughout the verification program of mono-propellant hydrazine rocket engines (thrusters) producing 0.95 lbf (4.2 N) of nominal steady-state thrust at an inlet pressure of 350 psia (2.41 Mpa). A scrutiny for the engine performance is made in terms of thrust and temperature behavior of steady state firing mode at the given propellant injection pressures: Pinj = 400, 250, 100, and 50 psi. The thrust and specific impulse are compared with a reference performance of 1-lbf standard rocket engines and their normalization procedure is introduced. A practical engineering approach to the data measurement and reduction is addressed, too.

• Journal of the Institute of Electronics Engineers of Korea SC
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• v.44 no.1
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• pp.25-32
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• 2007

In this paper, a new method for first order plus dead time(FOPDT) model identification is proposed, which can identity multiple points on a process step response in terms of classification of time response. The process input and output to the test are decomposed into the transient part and the steady-state part. The steady-state part express one FOPDT model and the transient part express variously FOPDT model using least square estimation method. The optimum parameter tuning algorithm for PID controller of the Smith Predictor is proposed through ITAE as performance index. The Simulation results show the validity and improvement of performance for various processes.

• Journal of the Korean Society of Propulsion Engineers
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• v.7 no.3
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• pp.38-44
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• 2003

In this study, a performance model of the smart UAV propulsion system with ducts, tip jets and variable main nozzle, which has flight capability of the rotary wing mode for the take-off/landing and low speed forward flight as well as the fixed wing mode for high speed forward flight, has been newly developed With the proposed model, steady-state performance analysis was performed at various flight modes such as rotary wing mode, fixed wing mode, compound ing mode and altitude as well as at flight speed conditions. In investigation of performance analysis. it was noted that the operational capability of the propulsion system was limited due to the duct losses depending on each flight mode, and the limitation with the altitude variation case had much greater than that with the flight speed variation case.

• Proceedings of the Korean Information Science Society Conference
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• 1999.10c
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• pp.244-246
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• 1999

본 논문에서는, multiple-buffered crossbar 스위치를 이용한 다층 연결 망의 성능 분석 모형을 제안하고, 스위치에 장착된 buffer의 개수 증가에 따른 성능 향상 추이를 분석하였다. Buffered 스위치 기법은 다층 연결 망 (Multistage Interconnection Network, MIN)의 내부의 데이터 충돌 문제를 효과적으로 해결할 수 있는 방법으로 알려져 있다. 제안된 성능 분석 모형은 먼저 네트웍 내부 임의 스위치 입력 단에 유입되는 데이터 패킷이 buffered 스위치 내부에서 전송되는 패턴을 확률적으로 분석하여 수립하였다. 분석 모형의 수학적 복잡도 절감을 위하여 확률식 유도 과정에 정상상태 확률 rosa(steady state probability)을 도입하였다. 제안한 모형은 스위치의 크기 및 스위치에 장착된 buffer의 수와 무관하게 확대 적용이 가능하다. 제안한 수학적 성능 분석 연구의 실효성 검증을 위하여 병행된 시뮬레이션 처리 결과는 상호 미세한 오차 범위 내에서 모형의 예측 데이터와 일치하는 결과를 보여 분석 모형의 타당성을 입증하였다. 2$\times$2 스위치로 구성된 8$\times$8 MIN을 대상으로 분석을 시행한 결과 스위치에 2~4개의 buffer를 장착했을 경우 unbuffer 스위치 경우와 비교하여 네트웍 정상상태 Throughout의 증가율이 높고 네트웍 Delay 또한 낮아져 효율적인 것으로 나타났다. 따라서 2~2 crossbar 스위치로 구성된 MIN의 경우 스위치에 장착된 buffer의 개수가 네 개 정도일 경우가 가격 대 성능비 면에서 가장 유리한 것으로 연구되었다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.10a
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• pp.61-64
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• 2003

A comprehensive understanding is given for the hot-firing test results, which were obtained throughout the verification program of mono-propellant hydrazine thrusters producing 0.95 lbf (4.2 Newtons) of nominal steady-state thrust at an inlet pressure of 350 psia (2.41 ㎫). The scrutiny is made in terms of thrust and temperature behavior of steady state firing mode at the given propellant injection pressures of 400, 250, 100, and 50 psi. Engineering philosophy of data measurement and reduction is shortly mentioned, too.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.05a
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• pp.189-192
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• 2003

This paper summarizes a satellite program-specific performance requirements and test results for the verification of standard mono-propellant hydrazine thruster (MRE-1) producing 0.95 lbf (4.2 Newtons) nominal steady-state thrust at an inlet pressure of 350 psia (2.41 Mpa). Performance characteristics are shown in terms of thrust behavior at steady state and pulse mode firing. Hot firing test philosophy is briefly introduced, too.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.22 no.5
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• pp.296-302
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• 2021

This paper proposes an approach to the classification of respiratory states of humans based on visual information. An ultra-wide-band radar sensor acquired respiration signals, and the respiratory states were classified based on two-dimensional (2D) images instead of one-dimensional (1D) vectors. The 1D vector-based classification of respiratory states has limitations in cases of various types of normal respiration. The deep neural network model was employed for the classification, and the model learned the 2D images of respiration signals. Conventional classification methods use the value of the quantified respiration values or a variation of them based on regression or deep learning techniques. This paper used 2D images of the respiration signals, and the accuracy of the classification showed a 10% improvement compared to the method based on a 1D vector representation of the respiration signals. In the classification experiment, the respiration states were categorized into three classes, normal-1, normal-2, and abnormal respiration.

• The Journal of the Institute of Internet, Broadcasting and Communication
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• v.14 no.4
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• pp.71-76
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• 2014

In this paper, we propose a SMMA(Sliced-Multi Modulus Algorithm) adaptive blind equalization algorithm with Flag for high order QAM system. SMMA has improved characteristics by applying the multi contour to MMA. However, SMMA still has a limit that the mismatch problem causes the residual error in the steady state is large. In order to significantly reduce the residual error in the steady state, we propose SMMA, which is controlled by the binary Flag of '1 'or '0' obtained from SMMA and a decision-directed algorithm, and analyze the performance of the proposed algorithm. By computer simulation, it is confirmed that the proposed algorithm has improved performance highly in terms of a residual ISI and a residual error in the steady state compared with MMA and SMMA.

• Journal of the Korean Society of Propulsion Engineers
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• v.6 no.2
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• pp.53-63
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• 2002

The steady-state and transient performance simulation program for a turboprop engine(PT6A-62) was developed. Specially this program included some algorithms, such as flat-rated behaviors in performance and limit control algorithms to prevent the compressor surge and the compressor-turbine inlet limit temperature overshoot. In order to minimize analysis errors, on interpolation method in component characteristics using matching errors and specific heat and specific heat ratio, which are functions of temperatures were used. The developed steady state performance analysis program can handle various conditions such as altitude, bleed extraction, inlet temperature and pressure and part throttle, and the transient performance analysis program incorporated a general mode for transient simulation and a control mode for prevention of the compressor surge and the turbine inlet limit temperature overshoot.