• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.368-373
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• 2017

Control method for DACS with variable burning area is designed and the performance of the control method is analyzed by doing simulation at various conditions. DACS, which got solid propellant on board, is designed as end-burning type typically. End-burning type DACS has the merit of controlling pressure and thrust, but it discharges the combustion gas which does not using for getting thrust. Therefore, optimal design of propellant grain and burning area changes over time as a result. Variable burning area can be assumed as a disturbance and adaptive control method is useful for pressure control of DACS effected by disturbance.

• Journal of the Korean Society of Propulsion Engineers
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• v.13 no.5
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• pp.41-47
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• 2009

Numerical computations were carried out to analyze the effect of a sub-cavity at several inlet Mach numbers on the control of cavity-induced pressure oscillations in two-dimensional supersonic flow. The present passive control method, the sub-cavity applied to the front wall of a square cavity, was studied for the inlet Mach numbers of 1.50, 1.83 and 2.50. The results show that the sub-cavity is effective in reducing the oscillations, and a resultant amount of the reduction depended on the inlet Mach number, the length of flat plate, and the depth of sub-cavity used as an oscillation suppressor.

• Explosives and Blasting
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• v.19 no.4
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• pp.5-10
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• 2001

발파시 공벽 주변에서 방사상으로 발생하는 무수한 균열들을 제어하고 일정한 방향으로 절단면을 형성하기 위해서 split tube를 이용한 발파 방법에 대한 현장 실험을 실시하였다. 현장 실험결과 절단면을 발달시키고자 하는 방향으로 제어할 수 있었다. 계산에 의한 발파압력과 제어된 균열면의 길이를 비교하였다. 현장 벤치 벽면에서 에멀젼 계열 폭약의 발파 압력이 700㎫이상일 경우 균열을 원하는 방향으루 제어할 수 있었을 뿐만 아니라, 공경의 30배까지 균열이 전파되었다.

• Proceedings of the KIPE Conference
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• 2010.07a
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• pp.91-92
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• 2010

다이어프램은 교류주파수에 의해 전후로 이동하는 진동판으로 공기의 압력을 조절하는 장치이다. 본 논문에서는 다이어프램의 공기 유량 및 유압을 제어하기 위해서 가변주파수의 전류 제어를 통해 다이어프램의 추력을 제어하고, 이를 통해 지령치가 요구하는 유량 및 유압의 제어가 이루어지도록 하였다. 다이어프램의 토출압력은 진동판의 주파수에 의해 조절이 가능하며, 진동 및 소음은 주파수에 반비례 하게 된다. 높은 주파수에서 충분한 추력을 내기위해서 본 논문에서는 가변주파수 전류제어 방식을 사용하였으며, 그 결과를 실험으로 검증하였다.

• Journal of the Korean Society of Propulsion Engineers
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• v.8 no.3
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• pp.27-36
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• 2004

This paper has been conducted to design for pressure regulation system. to simulate for performance of turbo pump unit using AMESim(Advanced Modeling Environment for Simulation of Engineering Systems). With optimized of system, pressure regulation system has been confirmed dynamic characteristics of transient and steady states range based on static modeling of open type turbo pump fed engine system. These results can be utilized to verify for performance test facility of propulsion control system for analysis on control valves, review of the fundamental principle on the control logic and certificating engine feeding system.

• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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• 2012.05a
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• pp.817-818
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• 2012

본 연구에서는 치과에서 마취 시 환자들의 고통을 최소화 하기위하여 무통마취를 위한 치과용 약물주입기를 구현하였다. 약물의 주입 시 통증을 최소화하기 위해서 온도를 $36{\pm}2^{\circ}C$ 범위로 제어하여 체온과 유사한 온도로 유지하였다. 이를 위하여 필름히터 방식을 이용한 치과범용국소약물(36mg, 2% 리도카인) 앰플 가열부를 설계하였다. 또한 약물이 주입되는 양을 능동적으로 제어하기 위하여 약물주입 환부의 환자별 흡수 속도 차이에 차등 주입을 위한 압력 측정 시스템을 구현하였다. 필름 형태의 압력 센서를 통하여 전달 압력을 측정하였으며 측정된 압력을 바탕으로 능동적으로 모터의 동작을 제어함으로써 약물주입시 환자의 고통을 최소화 할 수 있도록 구현하고자 하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.5
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• pp.325-332
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• 2022

The vertical take-off and vertical landing (VTVL) function is essential to carry out exploration missions on the moon or Mars. For this, the engine of the exploration vehicle must have appropriate thrust control accuracy and response time. The hybrid rocket engine (HRE) is known to have a high level of thrust control capability that can satisfy these conditions. This study aims to first verify whether the thrust control performance of the developed HRE is suitable for VTVL. To this end, an oxidizer supply system that does not use a pressurization device was adopted, aiming for a mission time of about 10 seconds. In this study, the thrust control characteristics appearing under various supply pressure decreasing conditions were identified through experiments. Appropriate tank and charging conditions were set from the experimental results. In addition, the results of previous studies and current study's test were compared to confirm whether the developed HRE had adequate control performance for VTVL, and finally, the thrust control performance was verified through altitude control simulation.

• Proceedings of the Korea Society for Energy Engineering kosee Conference
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• 1993.11a
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• pp.73-77
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• 1993

박막모델을 사용하여 연료전지 성능에 영향을 주는 여러 인자들에 대해 전압과 전류의 관계를 모사 하여 비교하였다. 또한 단위전지에 대해 제어루프를 구성함으로서 전극성능 모델식을 이용한 연료전지의 제어 가능성을 확인하였다. 확산계수가 증가할수록 그리고 전극두께가 얇고 전극의 세공반경이 클수록 전극성능은 증가하였다. 단위전지의 제어를 위해서 양극과 음극의 반응기체 유속을 조절할 수 있는 압력에 대해 설정치 변화와 외란의 변화에 대한 제어모사를 행한 결과 각 전극의 압력이 설정점에 빠르게 수령하여 연료전지의 효과적인 제어가 가능함을 검증하였다.

• Journal of the Korea Society for Simulation
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• v.20 no.4
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• pp.49-58
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• 2011

It is required that a developed control system should be verified using simulator in terms of functionality and reliability prior to application to a power plant that is a very critical facility in the industry. In this paper, the control model for turbine bypass system was developed for power plant simulator. In order to develop the control model for turbine bypass system, the tool that can be used to implement turbine bypass control logic was developed based on the turbine bypass control system manual. The developed tool was merged into the simulator development environment. The functionality of the developed tool was verified via the simulation based on the each function block specification. The HP turbine bypass pressure control logic was implemented using the developed tool and was integrated with process models and other control models such as boiler control model, turbine control model and boiler feed water pump turbine control model for 500 MW korean standard type fossil power plant. Finally, the validity of the developed control model was shown via simulation result under the integrated simulation environment.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.1
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• pp.1-8
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• 2019

An experimental study is performed to observe the characteristics of the thrust vectoring control (TVC) of the supersonic jet using proportional control valves. It is observed that three different TVC characteristics exist as the nozzle pressure ratio varies. Strong hysteresis phenomena are also observed during the valve control for a certain range of the nozzle pressure ratio. It is also noticed that the secondary chamber pressure is one of the influencing parameters for the TVC. Therefore, a control algorithm utilizing the secondary chamber pressure coefficient as a predictor is applied to achieve the stable TVC avoiding the hysteresis. Consequently, the stable TVC with the maximum deflection angle of about 20-degree has been realized using the proportional control valves.