• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.05a
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• pp.207-210
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• 2003

The purpose of this work is to introduce the Remote Control System for KSR-III Liquid Rocket Propulsion System. We developed the high reliable Fire control System that needed for long distance control. We carried out a real time remote control and measuring for KSR-III lust Liquid Propulsion Rocket in Korea using TCP/IP Ethernet network method and Fiber-optic communication method. Also HMI operation program developed guarantee confidential control, monitoring and analysis for Fire control operation.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1205-1211
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• 2017

The Propulsion System Test Complex(PSTC) was constructed for the verification test of each stage's propulsion system of KSLV-II. Main Control System(MCS) is the system to operate the onboard equipment and the ground equipment of the PSTC simultaneously. This paper describes the critical design, the development status, and test results of Main Control System. The MCS will be used for the interface connection between ground control systems and onboard equipment. Test sequence and operation process of the Work Manager will be conducted by MCS.

• Journal of Advanced Marine Engineering and Technology
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• v.28 no.6
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• pp.894-905
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• 2004

The closed cycle diesel propulsion system is free from the problem of the intake air, exhaust gas and their control that are associated with the conventional diesel propulsion system. The system is composed of a main engine, an exhaust cooler. a $CO_2$ scrubber and a $O_2$ mixer. In this paper, a hardware using microprocessor is proposed in order to monitor and control the oxygen and ratio of specific heat for underwater diesel propulsion system. Also simulation is carried out to ascertain the performance of proposed system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.468-471
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• 2012

This paper describes a construction scheme of hot backup or triple modular redundancy control system in a ground hot-firing test facility to carry out performance assessment of propulsion system used in a space launch vehicle. It was possible for a hot backup redundancy control system with manual operated console to simulate TMR control system. A console layout of control system in control center to restrict imprudent works of operators was proposed.

• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.3
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• pp.41-48
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• 2008

One of main functions of the firing control system applied to a rocket propulsion test has been to provide electric current for ignition of a solid rocket motor. This paper describes the design and implementation of an enhanced firing control system for ground propulsion test that can also control and verify various types of squib events and flight sequences.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.14 no.9
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• pp.1965-1971
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• 2010

A ship propulsion thruster platform which is used by safety sailing takes charge of remote control of a main engine in ship. This system not only guarantees safety and reliable flight sailing but also require remote control technology of a ship. Accordingly, in this paper it deals with a telegraph lever control unit system which is a part of propulsion thruster system as localization technology. Also it makes sure of knowledge and core technology through analysis and designing and developing a telegraph lever control unit system. Moreover, it is sure of acquisition of base technology for integration of a ship propulsion thruster platform.

• Proceedings of the KSR Conference
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• 2005.11a
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• pp.671-675
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• 2005

In this paper, Development of propulsion system using IPM(Intelligent Power Module) for DC electric vehicle is proposed. Designed propulsion system is comprised of inverter stack which includes 6 IPM, BCH(Breaking Chopper) unit, FC(Filter Capacitor), Control unit. IPM can compose propulsion system simple by including gate drive circuit and protection circuit. Inverter stack is designed as a simple structure using IPM and non clamp capacitor. VVVF Inverter control is used the vector control strategy at low velocity region and slip frequency-control strategy at high velocity region. Designed propulsion system proves the performance through test and revenue service.

• Journal of Navigation and Port Research
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• v.32 no.10
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• pp.765-770
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• 2008

This paper presents the power control for the hybrid electric propulsion system. In this paper, the hybrid propulsion system consists cf the generator and battery as power supply system in ship. The hybrid control system is designed with energy saving algorithm for decreasing the power consumption of power supply system. This paper suggests the method to increase efficiency of hybrid electric propulsion system by developing battery charging system. The performance of power control system is analyzed with the experiment equipment for hybrid propulsion system, and the results showed a good property.

• Advances in aircraft and spacecraft science
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• v.10 no.1
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• pp.1-18
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• 2023

This paper investigates the integrated control of an air-breathing hypersonic vehicle considering the safety of propulsion system under acceleration. First, the vehicle/engine coupling model that contains a control-oriented vehicle model and a quasi-one-dimensional dual-mode scramjet model is established. Next, the coupling process of the integrated control system is introduced in detail. Based on the coupling model, the integrated control framework is studied and an integrated control system including acceleration command generator, vehicle attitude control loop and engine multivariable control loop is discussed. Then, the effectiveness and superiority of the integrated control system are verified through the comparison of normal case and limiting case of an air-breathing hypersonic scramjet coupling model. Finally, the main results show that under normal acceleration case and limiting acceleration case, the integrated control system can track the altitude and speed of the vehicle extremely well and adjust the angle deflection of elevator to offset the thrust moment to maintain the attitude stability of the vehicle, while assigning the two-stage fuel equivalent ratio to meet the thrust performance and safety margin of the engine. Meanwhile, the high-acceleration requirement of the air-breathing hypersonic vehicle makes the propulsion system operating closer to the extreme dangerous conditions. The above contents demonstrate that considering the propulsion system safety will make integrated control system more real and meaningful.

• Proceedings of the KSR Conference
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• 2000.05a
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• pp.576-588
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• 2000

The study was carried out about the design of the propulsion and the control systems for Korean High Speed Train. The propulsion system was studied to run the maximum operating speed of 350km/h, The capacity of the main equipment is decided for the train to run tile maximum operating speed of 350km/h with the configuration of 2 power cars, 4 motorized trailers and 14 intermediate trailers. The control system was studied to two parts the supply and the control of high and low voltages used at train, The performance study of control system would be continued to update through system analysis according to propulsion system developing.