• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.6
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• pp.56-65
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• 2008

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.555-558
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• 2010

This paper presents a design of solid rocket motor with high length to diameter applied composite propellant. Solid rocket motor with high L/D ratio can be generated erosive burning and combustion instability on longitudinal mode. Especially, Erosive burning can effectively prolong the initial pressure spike in some star grain motors. That is, the study shows design of grain, internal ballistics and structural analysis in order to perform system requirements.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.4
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• pp.46-58
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• 2010

Hydrogen peroxide(HP) and liquid methane have deserved renewed considerations as green propellants in recent years, because main design concerns in the development of the new generation propulsion system for spacecrafts are concentrated on low operation cost and environmental cleanness. Although HP has a long history of application to aerospace propulsion systems due to high density, mono-propellant characteristics and low toxicity, it had been replaced by hydrazine and liquid oxygen due to extreme performance requirement during the cold war. But HP has received a renewed interest due to its increased stability and many researches have been conducted to develop high performance LREs(Liquid Rocket Engines) using HP. Liquid methane has also received a new interest in rocket propulsion system for the future space exploration according to its possibility of ISRU(In-Situ Resource Utilization).

• Journal of the Korea Institute of Information and Communication Engineering
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• v.25 no.8
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• pp.1103-1109
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• 2021

ECS is a control device so that the warship can perform the mission stably by controlling and monitoring the entire propulsion system. As the recent provisions of the warship, it's propelling system is complicated than past, as the demand performance and mission of the warships are diverse. In accordance with the complicated propulsion system configuration, the demand for automatic control function of the ECS is increasing for convenient and stable propulsion system control for convenient and stable. As a result, verification of ECS stability and reliability is required. In this paper, we develop an interlocking signal simulator for verifying ECS control logic and communication protocol for warship with CODLOG propulsion systems. The simulator developed was implemented to simulate a signal of gas turbine, propulsion motors, diesel generator and 11 kinds of auxiliary equipment. The reliability of ECS was verified through the ECS communication program and the I/O signal static test with the simulator.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.71-74
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• 2006

This study shows the historical background, and work flow of PRA (Probabilistic Risk Assessment) method which devised by NASA during the space development. It also illustrates the possibility of adoption of the method to evaluation of reliability KSLV project.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.793-794
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• 2011

In launch process, propellants should be supplied with established temperature range for engine normal operation. In order to satisfy this temperature condition, propellant feeding systems should be considered some effects during operation. This paper studied liquid oxygen filling system operation process and cooling method of liquid oxygen during launch process.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2002.11a
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• pp.384.1-384
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• 2002

Rocket propulsion systems generate very high level noise (acoustic loads), which is due to supersonic jet of rocket propulsion system. In practice, the sound power level of rocket propulsion systems is over 180 ㏈. This high level noise excites rocket structures and payloads, so that it causes the structural failure and electronic malfunctioning of payloads. Prediction method of acoustic loads of rocket enables us to determine the safety of payloads. (omitted)

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.3-6
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• 2007

Korea Aerospce Research Institute(KARI) has been developing the first civilian rocket, Korea space launch vehicle (KSLV-I), which can put the small size satellite into designated orbit. Developing launch vehicles contains a lot of uncertainty due to large scale, complexity, and technical difficulty. The uncertainty may become risk in the areas of business and technology which causes schedule delay, cost increase, and design changes of subsystems and components. This study describes the technical risk identification methods using FTA and procedures of planning and implementation of risk assessment and reduction of launch vehicle propulsion system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.352-358
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• 2011

This paper describes on the study of mitigation technique in which a pyrosensor is automatically sensing the rate of risk of fire or explosion of solid rocket motor exposed to an unexpected fire and makes the rocket motor burn itself safely. SCO test was carried out with a rocket motor loaded with HTPB propellant, in which a thermal pyrosensor igniter was installed. The rocket motor in SCO test was located in an oven at $50^{\circ}C$ for 7 hours. The temperature was regulated to be elevated at the rate of $3.3^{\circ}C$ per hour. Results showed Type V(Burning) reaction in this SCO test.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.6
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• pp.85-91
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• 2012

This paper describes the results of study on reaction of insensitive igniter in which a pyrosensor is automatically sensing the rate of risk of fire or explosion of solid rocket motor exposed to an unexpected fire and makes the rocket motor burn itself safely. The Slow Cook Off(SCO) test following the regulation of MIL-STD-2105D was carried out with a rocket motor loaded with HTPB propellant, in which a thermal pyrosensor igniter was installed. The auto-ignition temperature measured was approximately $140^{\circ}C$ and it corresponded to Type V(Burning) reaction in SCO test, while the temperature by Kissinger equation was calculated to be $165.5^{\circ}C$.