• Journal of the Korean Society of Systems Engineering
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• v.2 no.1
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• pp.54-60
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• 2006

LCC(Launch Control Center) in NARO space center performs a data monitoring and control through the interface to the external system of launch vehicle. Launch control function needs high reliability and processing speed. Hence, LCS(Launch Control System) is made up a real time system. An important role of the LCS Prototype is discovering a risk element and minimizing it through developing a launch control system. This paper deals with a real time data processing among the simulator, gateway, data distribution server, command and control server which is involving LCS Prototype.

• Proceedings of the Korea Society for Simulation Conference
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• 2005.05a
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• pp.106-111
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• 2005

LCC(Launch Control Center) in NARO Space Center perform a data monitoring and control through the interface to the external system of launch vehicle. Launch Control function needs a high reliability and processing speed. Hence, LCC's remote control system configure a real time system. An important role of the Simulation system is discovering a risk element and minimize it When developing a launch control system. Also, secure a development technique to solve the risks. Launch Vehicle simulator is composed of various component at characteristic of the Launch Vehicle. To be like this each function component the developer will be able to develop easily in order, it using the LabVIEW which is a Graphical Program and it programs, The LabVIEW GOOP(Graphical Object-orinted Programming) which supports an Object-orinted programming it uses with the Component it develops will have a strong point which reusability and a unit test, maintenance, size of program and individual developments.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1006-1010
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• 2017

This paper describes the design and test of the thermal control and fire safety system for thermal control and the fire/explosion prevention of inside the compartment during the preparation and operation of the space launch vehicle at the launch pad. The system considered here is for the test launch vehicle which is being developed as part of the development of the Korean Space launch vehicle-II. This system applies the high pressure system based on the heritage of Naro launch vehicle. The selection of thermal control and fire safety system from high pressure and low pressure system is done in consideration of the characteristics of the launch pad gas supply system and the characteristics of launch vehicle, and the system configuration is also changed accordingly. As a result, it has been confirmed that the developed system satisfies the initial design conditions through the test. Moreover the system will be applied to the development of the Korean launch vehicle in the future.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.19 no.8
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• pp.1965-1972
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• 2015

The Missile Flight Test Launch Control System is to operate in conjunction with the Fire Control System during flight test to guided weapons. Also, this is a system for the test control and situation monitoring depending on the type of guided weapons and testing purposes. Message structure, communication protocols, such as data types for interworking with the fire control system and the Missile Flight Test Launch Control System are defined in the Launch Control ICD(Interface Control Document). ICD are composed differently of each guided weapons system and each test object. Previously, in order to interwork with the Fire Control System, the interlocking software was developed, which had a variety of problems. Therefore, we developed a new parsing algorithm in order to recognize the variety of Launch Control ICD and verified that the algorithm operates normally by checking transmitting and receiving various message in conjunction with the fire control system.

• Journal of Institute of Control, Robotics and Systems
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• v.15 no.6
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• pp.567-572
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• 2009

The underwater launch system using an ATP consists of five parts: compressor tank, proportional flow control servo valve, expulsion spool valve, air turbine pump, and discharge tube. The purpose of this study is to develop an underwater launch system using an ATP and to verify the validity of the system. The proportional flow control servo valve is modeled as a 2nd order transfer function. The projectile is ejected by pressurized water through the air turbine pump, which is controlled by expulsion valve. The mathematical model is derived to estimate the dynamic characteristics of the system, and the important design parameters are derived by using simulations. The computer simulation results show the dynamic characteristics and the possibility of control for underwater launch system.

• 한국전산유체공학회:학술대회논문집
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• 2008.03b
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• pp.393-396
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• 2008

Propellant consumption control for space launch vehicle can be achieved by propellant utilization system (PUS) and tank depletion system (TDS). In the course of developing new space launch vehicles, the main target of design is on reducing of space launch vehicle weight, which results in increasing both specific impulse and payload weight. The weights of space launch vehicles are generally allocated to structure, propulsion system, and propellants loaded. The quantity of propellants filled in propellant tanks may be estimated with the propellants actually consumed by propulsion system to complete its mission and the propellants left on-board at the time of engine shut-off. To minimize the remaining quantity of propellants on-board the supplying propellants' O/F ratio should be controlled from the certain time before engine shutdown. To control an O/F ratio, a control system, which accurately measures and compares the remainder of propellants in tanks and pipes, should be needed. This paper solely dedicates its contents to explore the merits and demerits of various level sensor, which is one of the important elements for PUS and TDS, and the transmission and control of signals within space launch vehicle.

• Journal of the Korean Society of Systems Engineering
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• v.2 no.1
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• pp.37-41
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• 2006

The KSLV-I satellite launch vehicle will be launched in a space center currently under construction. The Space Center which is an advance post base of space development of Korea is located on Oenaro island in Kohung, South Cholla Province. A Ground Complex of the Space Center consists of an AC(Assembly Complex), a LC(Launch Complex), and a MCC(Mission Control Center). Assembly and test facilities are located in the AC in which stage assembly, integrated assembly, check-up, certification test, and pre-launch test are made effectively. A launch pad, fuel supply facilities, a launch control center and associated supporting facilities are located in the LC, and the MCC has control over the space center. These ground complex facilities have diverse forms of an interface with mechanical device, electric device, and etc. These should also provide optimum condition and performance during launch operation processes of the launch vehicle. This paper introduces the result of R&D for the AC of the ground complex performed during system design period.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.8
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• pp.657-665
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• 2016

Launch Control System(LCS) performs the pre-launch preparation and launch operation during launch campaign. The successful launch operation is basically influenced by hardware and software of LCS. Especially, a trivial errors in control algorithm can cause critical problem or disaster in launch operation. Therefore, the hidden or implicit errors should be distinguished and eliminated by the verification test in advance. In this paper, the design and implementation of hardware and software simulator which have already been used in LCS verification will be introduced. By presenting the detailed design and flowchart-based algorithms, we make other similar systems adopt the implementation philosophies of this paper. Especially, this paper emphasizes that all the simulation algorithms work on the self-controller in LCS without using separated computer or PLC.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.7-10
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• 2006

In order to inject satellites into a target orbit, launch vehicles should have a precise attitude and control system capable of controlling three axises of pitch, yaw and roll. For launch vehicles, there are two types of attitude control system currently in popular use; the first one is a cold gas method, and the other is a liquid propulsion system using a single and dual property propellant. The purpose of this paper is to analyze the characteristics of thrust control system using said propellant, thereby providing for a rationale for its application to the upper stages of launch vehicles, in terms of the simplicity of the system, economics of structure and operation.

• Journal of the Korean Society of Propulsion Engineers
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• v.23 no.2
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• pp.95-103
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• 2019

Control systems of compressed gas supply facility are responsible for storing and supplying compressed gases required for launch complex qualification test and launch operation. Most of the facilities that make up the launch complex require compressed gas for their operation. Therefore, such control systems should be developed and verified earlier rather than the other systems that constitute the launch complex. Each verification for hardware and software is performed separately. In particular, software verification of control algorithms loaded on the controller takes a lot of time and man power during the development period of the control system. Thus, specific test procedures and methods should be prepared in advance for efficient development. This paper introduces the configuration of a compressed gas supply facility and its control system with the verification procedure and results of major algorithms.