• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.620-621
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• 2010

Thermal models are made to verify the process that operate in space orbit. In this study, thermal analysis model correlation was performed to satisfy the criteria of correlation. Ground thermal vacuum test results are used for the correlation thermal model in the process of thermal model verification.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.8
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• pp.834-841
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• 2010

The STSAT-3 (science and technology satellite) is the first satellite whose entire structure was made of composite materials in Korea and it will be launched later in 2011. As like other small satellites, it is also equipped with several advanced instruments whose major objectives focused on the scientific tests in space. The HPS (hall thruster propulsion system) using xenon gas as a propellant has been developed and its overall ground tests were conducted. This research emphasizes on the technologies and procedure applied to the development of the entire HPS and its function and environment tests.

• 한국전산유체공학회:학술대회논문집
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• 2004.10a
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• pp.137-139
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• 2004

The monopropellant hydrazine thrusters are widely used for the satellite on-board propulsion system fulfilling various missions in space. They have outstanding features caused by the nearly unlimited restart capability and the very high credibility. The sole monopropellant thruster used at precent in nation is MRE-1 that is a standard component of NASA. It can produce 4.45 N of nominal thrust. Due to the glowing complexity with a satellite mission, the needs for thrusters of the diverse performance are being increased. The numerical simulation could give useful information to develop a new type thruster instead of the experiments performed previously. Therefore it is critical to make a reliable computer code to prepare design change of a thruster. In this paper, the performance analysis and validation of the satellite monopropellant hydrazine thruster currently used is accomplished as the preliminary study to serve valuable data for future design change.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.04a
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• pp.6-6
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• 2000

On-orbit thermal behavior of KOMPSAT (Korea Multi-purpose Satellite) propulsion system employing hydrazine (N$_2$H$_4$) liquid monopropellant is addressed. Thermal control performance to prevent propellant freezing in spacecraft-operational orbit was verified by flight telemetry data obtained during LEOP (Launch and Early Operation Phase). Results are depicted in terms of temperature history during several orbits selected and are compared with acceptable temperature ranges of system components. Cyclic behavior of temperature is reduced into duty cycles of the avionics heaters and subsequently converted into the electrical power required to keep away from propellant freezing. Temperature of each component which was achieved under on-ground thermal-balanced condition of spacecraft, is presented for comparison with the flight data, additionally.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2002.04a
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• pp.43-43
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• 2002

인공위성은 일반적으로 추력기(thruster)에서 플룸(plume)을 거의 진공에 가까운 외부환경으로 사출하여 자세를 제어한다. 이 때, 사출되는 플룸에 의해 위성체의 고도에 영향을 줄 수 있는 교란추력/교란토크, 열하중(thermol loading), 정밀계측장비에 영향을 주는 오염(contamination) 등, 여러 부정적인 효과들이 야기될 수 있으며, 이들 효과들은 결론적으로 위성체의 수명을 단축하기 때문에 이들에 대한 정확한 예측은 위성체 설계단계에서 매우 중요하다.

• Journal of Astronomy and Space Sciences
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• v.19 no.3
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• pp.207-214
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• 2002

One of the way to derive design parameters of the fuel feeding system in satellite propulsion system is to analyze unsteady flow of liquid propellant (hydrazine). During steady thruster firing the flow rate is constant: if a thruster valve is abruptly shut down among a set of thrusters, pressure spikes much higher than the initial tank pressure occur. This renders the fuel flow unsteady, and the fluid pressure and flow rate to oscillate. If the pressure spikes are high enough, there are possibilities that propellant explosively decomposes, thruster valves we damaged, and adiabatic detonation of the hydrazine propellant is potentially incurred. Reflected shockwaves could also affect the calibration and operation of the pressure transducers. These necessitate the analysis of unsteady flow in the propulsion system design, and pressure behavior inside the propellant line obtained through some governing parameter variation is presented in this work.

• Journal of the Korean Society of Propulsion Engineers
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• v.11 no.6
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• pp.42-49
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• 2007

In this study, we analyzed flow characteristics of micro-nozzles for basic research to develop micro propulsion system. Cold gas propulsion system was used, and micro-nozzles having nozzle throat diameters of 1.0, 0.5, 0.25 mm were fabricated with EDM method. Thrust was measured through the use of plate-spring and strain gage based thrust measurement system, and flow characteristics of micro-nozzles were analyzed under ambient condition and vacuum condition. We used argon and nitrogen gases as propellant, and compared experimental results with CFD analysis. From the result, we verified the flow losses of viscosity and back-pressure caused by minimization of nozzle.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.5
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• pp.89-95
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• 2011

Korea Space Launch Vehicle II (KSLV-II) planned to launch in 2021 is 3 stage rocket which can inject 1.5 ton satellite in low earth orbit. KSLV-II will adapt the newly developed liquid rocket engines for its propulsion system of each stage. For the evaluation of development level for rocket engine, integrated system test performed in appropriate facility is needed. In this study, test article and major parameters for certifying the propulsion system of KSLV-II were reviewed and optimum test cycle and test duration for satisfying system reliability requirement were illustrated.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.598-602
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• 2017

Korea Aerospace Research Institute has been developing 3-stage launcher KSLV-II, which can inject 1.5-ton satellite into sun synchronous orbit (SSO). For development process, Test Launch Vehicle(TLV) adopting the $2^{nd}$ and $3^{rd}$ stage of KSLV-II will be scheduled to launch in 2018. The propulsion system of TLV is composed of $2^{nd}$ stage engine system (ground type) and propellant supply system including LOX, Kerosene tanks. Until now, system integration of engineering model of TLV and delivery of qualification model have been done. In this paper, the product assurance activities for propulsion system KSLV-II will be illustrated.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.8
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• pp.695-701
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• 2016

Spacecraft propulsion system is a kind of rocket engine that has been developed from the end of 1950s for attitude control and orbit maintenance of satellite. Since the spacecraft propulsion system has to be used for a relatively long time, therefore, stability of propellant and life of thruster could be very important factor for propulsion system design. Recently, green propellant propulsion and all electrical propulsion system have became very important issue, and we also need a development according to well organized plan. In this paper, we will introduce the development status, key technologies and development prospect of spacecraft propulsion system.