• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.34 no.4
• /
• pp.102-109
• /
• 2006

In this paper, the system level EMC radiated emission test results of KoDSat(Korea Demonstration Satellite), its affects upon the Launch vehicle and H/W improving methods regarding its over exceed value of EMC specification are discussed. Regarding its over exceed value, we estimated that DAU of KoDSat generated the exceeded EMC noise source, and these test results were analyzed using the EMC2000 tool to find out how did it affect the FTS(Flight Termination Subsystem) of KSLV-1(Korea Small Launch Vehicle). To diminish the EMC noise source of UHF(430.1Mhz) band level, we redesigned the DAU power board to be applied the various schemes for EMI noise reduction such as grounding, shielding and EMI filtering, and also verified these reworks to analyze its diminishing affects in UHF band level by means of performing the DAU box level EMC test and performing the second KoDSat's system level EMC test.

• Aerospace Engineering and Technology
• /
• v.10 no.1
• /
• pp.79-88
• /
• 2011

A fill-drain valve is operated by provided control gas at the ground for liquid propellant feeding system of space launch vehicle, which fills or drains on-board propellant tanks with a cryogenic oxidizer. We have analyzed and modified the data of fill-drain valve designed by Yuzhnoye. The simulation model of fill-drain valve is designed by using the AMESim code to predict and evaluate the dynamic characteristics and pneumatic behavior of valve. In this study, we performed a dynamic characteristic simulation on design parameter. And we could predict opening/closing time and pressures, operating performances on design parameters. This study will serve as one of reference guides to enhance the developmental efficiency of fill-drain valves with the various operating requirements, which shall be used in the Koreanized Space Launch Vehicle.

• Journal of Aerospace System Engineering
• /
• v.10 no.4
• /
• pp.41-49
• /
• 2016

This research intends to make a model of space development in Korea as a sectoral innovation system. The main contents include a character analysis of the elements of three low levels of the space development innovation system, including governance (the main agent and cooperation relationship of which the center is a research institute supported by government), resources (financial resources and human resources), and the diffusion of research results. It is important to grasp the factors that bring about technological innovation of industrial sectors to produce technological innovation policy. Technology innovation policy should thus be formulated for specific, individual sectors, and not all sectors.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2017.05a
• /
• pp.1184-1187
• /
• 2017

The space launch vehicle needs the verification of each stage's propulsion system. The Propulsion System Test Complex(PSTC) is constructed for developing KSLV-II in the Naro space center. Hydraulic and pneumatic system of PSTC should supply propellants and various gases to propulsion system module according to required condition. This paper introduces liquid oxygen filling system of PSTC.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.11a
• /
• pp.109-115
• /
• 2011

Development cases of space launch vehicle upper stage engine were studied. HM-7, Vinci, LE-5, RL10 engines are representative upper stage engines of Europe, Japan, and United States. It was realized that upper stage engines were developed with more than two engine test facilities and the development period was 5 to 8 years accompanied with 10~11 engines.

• Journal of the Korean Society of Systems Engineering
• /
• v.16 no.1
• /
• pp.18-24
• /
• 2020

The KSLV-II project with high difficulties technically requires thorough technical management during long-term life cycle more than 10 years for launching into space. The TRL is a quantitative indicator developed by NASA widely used all over the world to measure technology maturity of a system development objectively and consistently. The TRL is also used to make sure technology level and to establish a future direction in the KSLV-II project. The TRL has advantage enable to identify a technology level through quantitative indicators. However, it takes a lot of efforts such as trials and errors, time and cost to apply it to the project considering the project environments, and stakeholder needs. These include not only to establish TRL management plan from ideal, conceptual and abstractive standards/guidelines such as NASA's, but also to construct TRL management environment enable to apply and manage harmoniously. In the KSLV-II project, it is required to figure out current technology level and technology development trend in the future, to access conveniently, to share related data in real time, and to update periodically for the comprehensive TRL management. From the reason above, the TRL management environment was built by using the systems engineering tool already has been used for other system management data such as requirements in the project. It also could be accomplished a practical management basis of systems engineering from the traceability among system management data including TRL. In this paper, case study results are introduced to manage the TRL for the space launch vehicle using the systems engineering tool in the KSLV-II project.

• Current Industrial and Technological Trends in Aerospace
• /
• v.7 no.2
• /
• pp.68-75
• /
• 2009

Up to date, demands for satellite including communication are increasing. Advanced countries on space technology such as America, Russia, Europe, Japan, China and so on already had secured launch vehicle technology which can insert a large class satellite to proper orbit. The introduction of technologies on the large class launch vehicle including propulsion system is difficult due to the utilization possibility for defensive reason. The acquisition of indigenous technical expertise on the design and manufacture of valves is believed to contribute to the successful local development of valves for propulsion systems and to significant improvement of local technical level of valve design and development. This paper introduces current status of valves developed by other countries as well as valves developed in domestic. The Developed technology of valves may underlie the construction of engine control systems required for the reliable operation of the KSLV-II engine system and propulsion system.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.36 no.12
• /
• pp.1180-1185
• /
• 2008

In-house code which simulates the performance of pre-burner in staged-combustion liquid-fueled rocket engine was developed and demonstrated. Chemical reaction of pre-burner was modeled based on analytic algorithm of CEA (Chemical Equilibrium with Applications) and gas dynamics model was incorporated with it. Comparison results between in-house code and CEA have shown small relative errors except at very high or very low O/F ratio. Also the performance curve obtained by in-house code revealed that the calculated values follow the overall trend of real engine (RD-8) performance quite well and at steady-state operation, the deviation became very small.

• The Korean Journal of Air & Space Law and Policy
• /
• v.26 no.1
• /
• pp.177-213
• /
• 2011

The purpose of this paper is to research on the liability and cases for space damage with reference to the space activity under the international space treaty and national space law of major countries. The United Nations has adopted two treaties relating to the liability for space damage as follows: the Outer Space Treaty of 1967 and the Liability Convention of 1972. Korea has enacted the Outer Space Damage Compensation Act of 2008 relating to the liability for space damages. The Outer Space Treaty of 1967 regulates the international responsibility for national activities in outer space, and the national tort liability for damage by space launching object. The Liability Convention of 1972 regulates the absolute liability by a launching state, the faulty liability by a launching state, the joint and several liability by a launching state, the person claiming for compensation, the claim method for compensation, the claim period of compensation, the claim for compensation and local remedy, the compensation amount for damage by a launching state, and the establishment of the Claims Commission. The Outer Space Damage Compensation Act of 2008 in Korea regulates the definition of space damage, the relation of the Outer Space Damage Compensation Act and the international treaty, the non-faulty liability for damage by a launching person, the concentration of liability and recourse by a launching person, the exclusion of application of the Product Liability Act, the limit amount of the liability for damage by a launching person, the cover of the liability insurance by a launching person, the measures and assistance by the government in case of occurring the space damage, and the exercise period of the claim right of compensation for damage. There are several cases with reference to the liability for damage caused by space accidents as follows: the Collision between Iridium 33 and Cosmos 2251, the Disintegration of Cosmos 954 over Canadian Territory, the Failure of Satellite Launching by Martin Marietta, and the Malfunctioning of Westar VI Satellite. In the disputes and lawsuits due to such space accidents, the problems relating to the liability for space damage have been settled by the application of absolute(strict) liability principle or faulty liability principle. The Liability Convention of 1972 should be improved as follows: the clear definition in respect of the claimer of compensation for damage, the measure in respect of the enforcement of decision by the Claims Commission. The Outer Space Damage Compensation Act of 2008 in Korea should be improved as follows: the inclusion of indirect damage into the definition of space damage, the change of the currency unit of the limit amount of liability for damage, the establishment of joint and several liability and recourse right for damage by space joint launching person, and the establishment of the Space Damage Compensation Review Commission. Korea has built the space center at Oinarodo, Goheung Province in June 2009. Korea has launched the first small launch vehicle KSLV-1 at the Naro Space Center in August 2009 and June 2010. In Korea, it will be the possibility to be occurred the problems relating to the international responsibility and the liability for space damage in the course of space activity. Accordingly the Korean government and launching organization should make the legal and systematic policy to cope with such problems.

• Journal of Satellite, Information and Communications
• /
• v.7 no.2
• /
• pp.67-71
• /
• 2012

This paper represents the impact analysis results of antenna reflector for the UHF-band antenna of Space Launch Vehicle. Three types of UHF-band antenna reflector model have been proposed and simulated to compare their characteristics such as resonance frequency, reflection loss and radiation pattern etc. Simulation results showed that resonance frequency and return loss of each reflector models were rarely affected even if reflector sizes are changed. The antenna gain and 3dB bandwidth were slightly changed to the worse directions as the reflector sizes are smaller.