• Transactions of the Korean Society of Pressure Vessels and Piping
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• v.7 no.3
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• pp.1-7
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• 2011

The analysis shows that the vibration is one of the main reasons of turbine failure. Especially, the problems caused by vibration occur right after retrofit of the turbine-generator and restarting the turbine. Through the case study of high vibration caused by after the turbine trip and restart, turbine vibration was identified to be influenced by startup condition. Turbine startup at high casing temperature right after unscheduled turbine trip cause radial expansion in rotor by contraction in axial direction, while casing continues to contract by steam flowing into casing. Consequently, gap between rotor and casing decrease until to metal contact to cause high vibration. Through the case study of high vibration of turbine-generator system after generator retrofit, it was identified that generator replacement could cause high vibration in turbine-generator system if the influence of generator replacement on entire system was not considered properly. To prevent startup delay caused by high vibration, it is important to keep the gaps at the design standard and start the turbine after thermal equilibrium.

• Journal of IKEEE
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• v.22 no.2
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• pp.258-265
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• 2018

This paper proposes an algorithm for reducing the starting current when the single-phase induction motor starts and analyzes its operation. Generally, the single-phase induction motors require several starters to generate the starting torque due to their structural characteristics. In this paper, a capacitor-start / capacitor-run method of the single-phase induction motor is basically adopted. This conventional method is efficient and has a large starting torque, but it generates about 5 ~ 6 times of inrush current at startup. As a result, the freezer starting device and peripheral devices are damaged and life time may be reduced. To reduce the inrush current, the current control algorithm based on the virtual dq model is presented to control the starting current. In addition, it validates the proposed algorithm through experiments to smooth transit from start-up operation to the rated operating region.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.1
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• pp.22-30
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• 2008

This paper deals with the nonlinear optimal control approach to helicopter maneuver problems using the indirect method. We apply a penalty function to the deviation from a prescribed trajectory to convert the system optimality to an unconstrained optimal control problem. The resultant two-point boundary value problem has been solved by using the multiple-shooting method. This paper focuses on the effect of the number of shooting nodes and initialization methods on the numerical solution in order to define the minimum number of shooting nodes required for numerical convergence and to provide a method increasing convergence radius of the indirect method. The results of this study can provide an approach to improve numerical stability and convergence of the indirect method when we solve the optimal control problems of an inherently unstable helicopter system.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.12
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• pp.986-993
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• 2018

Lateral thrust jet has better maneuverability performance than the control surface like the conventional fin for attitude control or orbital transition of guided weapons. However, in the supersonic region, a jet interaction flow occurs due to the lateral thrust jet during flight, and a complicated flow structure is exhibited by the interaction of the shock wave, boundary layer flow, and the vortex flow. Especially, hit-to-kill interceptors require precise control and maneuvering, so it is necessary to analyze the effect of jet interaction flow. Conventional jet interaction analyses were performed under low altitude conditions, but there are not many cases in the case of medium altitude condition, which has different flow characteristics. In this study, jet interaction flow analysis is performed on the lateral jet controlled interceptor operating at medium altitude. Based on the results, the structural characteristics of the flow field and the changes of aerodynamic coefficient are analyzed.

• Proceedings of the KIPE Conference
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• 2016.07a
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• pp.115-116
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• 2016

산업용 인버터에서 전차원 적응 자속 추정기를 적용하여 유도전동기 센서리스 제어를 하는 경우, 토크 제어 시 저속/저토크 영역에서 기동에 문제점을 보인다. 따라서 이를 해결하기 위해 본 논문에서는 동기 좌표계 상의 d축 전류의 크기를 토크에 따라 변동 시키는 방법을 제안한다. 주어진 토크 지령에 따라 발생되는 토크를 유지하기 위해, d축 전류 변동에 따라 q축 전류의 크기를 변화 시킨다. 운전 조건에 따른 d축 전류 크기의 변동 범위를 식을 통해 도출하였고, 복잡한 연산을 저 성능제어기에 적용할 수 있도록, d축 전류 크기를 간략히 설정하는 방법을 제안한다. 실제 인버터에 제안하는 방법을 적용하여 기존에 비해 훨씬 더 작은 토크만으로 기동 및 재 기동하는 것을 확인하였다.

• Journal of Energy Engineering
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• v.4 no.3
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• pp.315-323
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• 1995

차세대의 새로운 발전방식인 인산형 연료전지 발전시스템의 운용기술의 확립을 위하여 50 kW급 실증설비를 도입하고 주변기기를 설계, 설치하여 장기운전 특성시험을 실시하였다. 이 설비는 1993년 8월부터 1994년 11월 말까지 총 6,003시간의 운전기간 동안 187,190 kWh의 발전전력량을 기록하였고, 이 기간 동안의 발전운전시간 이용율은 63.01%, 평균출력은 33.5 kW였다. 설비의 운전특성에 있어서 정부하시 평균전압 및 전류는 각각 DC 130 V와 461 A였으며, 경시전압감소율은 1,000시간당 3.8 mV 정도로 나타났다. 설비의 기동·정지 특성중 기동시간은 냉간기동시 평균 4시간 50분, 난기동시 2시간 34분 정도가 소요되었고, 발전효율은 정부하시 전기효율이 37.46%, 배열이용효율은 43.8%로 전체효율 81.26%를 나타냈다. 환경 특성중 배가스중의 NOx 농도는 1 ppm 미만이었고, 소음도 63 dB 정도로 양호한 특성을 보여주었다. 운전기간 중 발생한 사고는 총23회로, 외부운전조건에 대한 민감성이 큰 것으로 나타났으며, PAFC 시스템의 상용화를 위해서는 스택수명 및 운전신뢰성을 향상시키는 것이 필요하다.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.7 no.4
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• pp.826-832
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• 2003

This paper presents a new linking methodology of direct load control(DLC) and unit commitment(UC) considering system spinning reserve characteristics. To consider system spinning reserve characteristics, we formulate new constraints. And to link DLC and UC, we employed 3-Dimensional dynamic programming which has DLC state, UC state, and stage. As a result, economical DLC and UC schedule of the power system is possible. This method is applied to the test system, and the usefulness of the method is verified.

• Proceedings of the KIPE Conference
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• 2017.07a
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• pp.335-336
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• 2017

본 논문에서는 대용량 배터리 모듈이 병렬 연결되어 있는 에너지 저장장치 시스템의 초기 기동 조건시 투입 초기의 전류를 추정할 수 있는 방법을 제시한다. 제안된 방법은 배터리 모듈을 구성하고 있는 리튬 배터리 모듈의 단자 전압 및 배터리 모듈 저항 데이터를 이용하여 병렬 연결하고자 하는 배터리의 전류를 예측하는 방법으로써 배터리 모듈의 기동 투입 가능여부 등 온 오프 시퀀스 로직에 적용할 수 있다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.6
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• pp.495-501
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• 2013

Korean Utility Helicopter (KUH) has been designed to avoid the blade passing frequency and any instability due to a coupling of dynamic characteristics between the main rotor and the airframe in ground operation. For these design objectives, the vibration analysis and the ground resonance analysis were performed to analyze the dynamic characteristics of the airframe and the main rotor. Then, the whirl-tower test was conducted to identify the dynamic characteristics of the main rotor and the ground vibration test (GVT) was conducted to identify the dynamic characteristics of the airframe. The GVT for KUH was conducted with the test conditions and test articles established in consideration of each flight and ground condition. This paper shows the method and technique for performing the GVT for KUH and presents the correlation technique and the results for the correlated analysis model.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.2
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• pp.165-170
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• 2007

During the conceptual design phase of a wing-body-canard type fighter class aircraft, as a method of maneuverability enhancement for an aircraft, effects of canard-leading edge flap scheduling have been studied. In this study, corrected supersonic panel method has been used to predict the drag polar characteristics due to canard-leading edge flap deflections in the high speed regime. Utilizing the predicted drag polar curves, the canard-leading edge flap scheduling laws have been established. These scheduling laws are the relation of canard-leading edge flap deflections and the flight conditions to maximize the lift-drag ratio. Based on the results obtained from the canard-leading edge flap scheduling, the present method has shown to be useful to enhance the maneuverability of wing-body-canard type fighter class aircraft.