• Journal of the Korean Society of Propulsion Engineers
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• v.27 no.1
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• pp.58-67
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• 2023

Results of dry-run tests, cold-flow tests, and hot-firing tests performed to throttle a methane engine uni-element thrust chamber are covered in the paper. After installing flow control valves on the oxidizer and fuel supply lines of the methane engine combustion test facility, a number of dry-run tests were repeated so that the valves could reach set strokes quickly and stably. Then, cold-flow tests using liquid nitrogen and gaseous nitrogen were conducted to confirm the stable supply of the simulated propellants according to the valve control. Finally, using liquid oxygen and gaseous methane, hot-firing tests for fixed and continuous thrust control of 50% to 10% of the nominal thrust were successfully performed.

• Journal of the Korean Society of Manufacturing Process Engineers
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• v.19 no.3
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• pp.51-56
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• 2020

Research into natural refrigerants that use CO₂, instead of chlorofluorocarbons and hydrofluorocarbons, has increased due to the environmental problems caused by ozone depletion. CO₂ refrigerants are more environmentally friendly than conventional refrigerants because they have better latent heat of evaporation and heat transfer efficiency properties. However, they have very low critical temperatures and require high design pressures; therefore, pressure control valves, which reduce the pressure of the CO₂ refrigerant to a safe level and apply it to the refrigerant air conditioning system, are necessary to secure stability against high pressure. In the present study, we evaluated the flow characteristics and valve performance of the pressure control valve using a CO₂ refrigerant by measuring the pressure, velocity, and flow coefficient. In addition, we examined the applied forces caused by the internal pressure from the highly pressurized CO₂ refrigerant and required thrust characteristics.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.237-240
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• 2007

To control Thrust of propulsion system, we built the 50 N level PE-COx hybrid rocket, and changed the mass flow rate of COx. From the preliminary experiential results, we could see possibility of controlling thrust of the hybrid rocket by controlling mass flow rate of COx.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.257-260
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• 2008

In order to control thrust of propulsion system, we built the 50 Newton level PE-GOx hybrid rocket, and changed the mass flow rate of GOx. From the preliminary experiential results, we could see possibility of controlling thrust of hybrid rockets by controlling mass flow rate of GOx.

• Aerospace Engineering and Technology
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• v.7 no.2
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• pp.162-169
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• 2008

Dynamic characteristics of a control valve, which plays an important role in thrust control of liquid rocket engines, have been analysed by AMESim simulator modeling. A speed control method has been proposed for the control of the valve equipped with a BLDC motor and the performances of this control method have been proved in making a comparison between the predictions of simulation and experimental results. Moreover, it is shown that a control valve with a second pre-filter is enough stable to the flow disturbances. The speed control method for BLDC motor is more simpler than PI gain scheduling method for the application in complex flow system.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.15 no.6
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• pp.3821-3826
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• 2014

This paper proposes a methodology for developing the performance of a solenoid valve for vehicles based on the dynamic analysis model by an electromagnetic field. The high performance solenoid model with a low current and high thrust was induced through the shape optimal design of the yoke and plunger. To perform the dynamic analysis of the solenoid valve, the input current profile was analyzed. The speed and thrust information was analyzed by FEM with this current profile. The co-simulation method of the circuit model of control logic and electromagnetic model of the solenoid valve was also proposed to analyze the performance with several current patterns. Finally, the performance of the original model and optimal one was compared.

• 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.

• Aerospace Engineering and Technology
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• v.5 no.2
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• pp.126-133
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• 2006

This paper deals with technological and design skills for all pneumatical, hydraulical, mechanical and electrical parts related to control valve. Especially, a variety of dynamic characteristics, which are not easily extracted from field tests using control valves, are studied by system-simulation code, AMESim. The simulated results are also compared and examined with actual testing results in terms of physical dynamic characteristics. In addition, this paper contains the simulated system characteristics including dynamic characteristics in component level of valve itself. Based on the results, it is applied to control system of propellant feeding system in liquid-propellant engine of satellite launcher.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.1
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• pp.40-47
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• 2010

In this study, basic research on the thrust control by controling oxidizer mass flow rate of a $GO_2$/PE hybrid rocket is presented. For this purpose, hybrid rocket system including oxidizer flow control system and data acquisition system was developed. To control oxidizer mass flow rate, we used needle valve with stepping motor which was controled by LabVIEW program. During the fundamental experiments, this system managed to follow the pre-programmed (20 N - 10 N - 20 N - 0 N) thrust level.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.4
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• pp.18-25
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• 2011

Solid propulsion systems have simple structures compared to other propulsion systems and are suitable for long-term storage. However the systems generally have limits on control of thrust levels. In this paper we suggest control algorithms for combustion chamber pressure of variable thrust solid propulsion systems using special nozzles such as pintle valve. For the pressure control within the chamber, we use a simple pressure change model by considering only mass conservation within the combustion chamber, design a classical algorithm and also a nonlinear controller using the feedback linearization technique. Also we derive the equation of the thrust for an under-expanded one-dimensional nozzle and then design a proportional-intergral controller after linearizing the thrust model for an operating point. Finally, we demonstrate the performance of the controller through a numerical simulation.