• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.8-13
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• 2011

본 연구에서는 대형 로켓엔진시스템의 시동 시 안정적인 유량공급을 위한 제어기 설계가 이루어졌다. 펌프, 오리피스, 제어밸브, 파이프, 인젝터 및 재생 냉각채널과 같은 엔진시스템 구성품들에 대한 동특성 모델링을 수행하였고 유량공급 제어가 가능한 밸브의 구동신호를 조절 가능한 PID 제어기를 설계하였다. 시동 시 안정적인 유량공급을 위하여 실험을 통해 얻은 밸브의 적정 개도율을 적용시켰으며, 이를 기준으로 하여 제어밸브의 작동신호를 조절하여 유량비를 제어하였다. 시뮬레이션 한 결과 제어기를 통해 시동 시 정상추력까지 유량공급을 제어 하는 방법이 적절함을 확인하였다.

• Proceedings of the Korean Nuclear Society Conference
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• 1996.05a
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• pp.526-531
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• 1996

영광5,6호기 유출관계통은 영광3,4호기의 유출관계통과는 달리 세개의 유출수 압력강하 오리피스 및 유출관 오리피스 개폐밸브론 이용하여 유출유량 및 압력을 제어한다. 새로이 설계 변경된 유출관계통의 성능 및 운전을 평가하기 위해서 Modular Modeling System(MME) 코드를 이용하여 분석을 수행하였다. 분석결과 배압제어기 제어변수의 계수선정이 계통의 과도현상에 매우 큰 영향을 미치고 있기 때문에 배압제어기 제어변수 선정이 계통의 과도현상 완화에 매우 중요한 인자임을 알 수 있었다. 그리고 배압제어기의 계수만 적절하게 선정되어 있다면, 유출관오리피스 개폐밸브의 Stroke 속도변화에 따른 계통의 과도현상에 미치는 영향은 거의 없음을 알 수 있었다. 또한 유출관오리피스 개폐밸브 특성이 선형인 경우가 Equal Percentage 특성을 갖는 경우 보다 과도현상 방지측면에서 우수하며, 배압제어기 제어변수의 계수만 적절하게 잘 선정된다면 유출관오리피스 개폐밸브의 운전에는 관계없이 계통의 과도상태를 적절하게 제어할 수 있다는 것을 알 수 있었다.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 2003.10a
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• pp.214-214
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• 2003

• 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.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.995-999
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• 2017

The factors affecting the flow coefficient of a control valve were identified and analyzed. The flow coefficient of a control valve are affected by not only Reynolds Number but also the figure and the roughness of the inlet/outlet pipes. Therefore, the flow coefficient is not a constant value. For the purpose of use in the system such as LRE, requiring the exact flow-coefficient of a control valve, the flow-coefficient should be measured under similar Reynolds Number using the inlet and outlet pipes which have the same figure and roughness with a real system.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.10
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• pp.1026-1030
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• 2010

This paper summarizes the activities performed for the development of a BLDC(Brushless Direct Current) motor driven cryogenic thrust control valve with application to KSLV-II rocket engine. The developed thrust control valve can modulate the flow rate of liquid oxygen under cryogenic temperature of 90K and high pressure of 113.2 bar with the help of electro-mechanical actuator driven by a BLDC motor. This valve can be applied to an engine combustion test after minor change because all development certification test have been performed successfully.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.139-141
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• 2017

By modulating the flow rate of $N_2O$ into a HR motor assembly, a control valve of a hybrid rocket engine plays a role to increase or decrease the thrust. In this study, the control valve has been designed to meet the requirements which are response speed(${\leq}$ about 1 second) and torque(${\geq}$ about $36N{\cdot}m$). Then, when analog signal 0~10V is applied, the situation where the valve is opened and closed has to be realized. To do this, the data values have to be entered into the actuator. Finally, the performance evaluation of the control valve has been performed to validate this product.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.8
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• pp.704-710
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• 2017

The supply of the liquid oxygen into a rocket combustor is simply controlled by the 'on' and 'off' positions of a main oxidizer shut-off valve. However, the partially opened position of a three-position valve can control and optimize the engine start transients by regulating the liquid oxygen flow rate during the start-up of the engine. In this paper, the design and performances of a three-position pneumatic poppet valve, which is intended to be employed in liquid rocket engines, have been presented.

• Journal of Aerospace System Engineering
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• v.13 no.4
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• pp.50-59
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• 2019

The design of the main control valve, which is the main component of the flap control system, was based on actual manufacturing experience on the basis of trial and error method. In this paper, a model-based part design method is proosed. The flap control system consists of a main control valve, fail-safe valve, solenoid valve, LVDT and force motor. The main control valve consists mainly of a spool and slot. The important design parameters of the main control valve are the slot width, overlap and clearance. AMESim is linked to the model and it analyzes the flow path of the main control valve. Applying the proposed design procedure, it was confirmed that the required performance was satisfied within the allowable machining error range.

• Proceedings of the KIEE Conference
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• 2004.07d
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• pp.2263-2265
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• 2004

발전소 증기터빈 밸브제어의 핵심을 이루고 있는 서보밸브 제어특성을 파악하고, 조속기 개조에 필요한 제어루프 구성방법 및 각종 제어상수를 시험을 통해 미리 파악하여 교체 적응 시에 발생될 문제점을 해결하고자 시험한 내용을 서술하고자 한다.