• Aerospace Engineering and Technology
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• v.3 no.2
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• pp.104-115
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• 2004

In this study, contains Design and Simulation data for Tone filter applied to the KSLV-1 FTS Receiver. Received Signal contains unwanted Noise and Jitter which should be eliminated by any kind of filters. In the design of KSLV-1 FTS Receiver, two different type of filters are used. One is Low-Pass Filter for rejecting high order harmonics and another is Tone Filter for sorting pure original signal in the mixed demodulate Signals. For the purpose of this development, various kinds of filter are studied and simulated for finding adequate type of filter.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.16-19
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• 2005

The basic research on KM(Kick Motor) for space launch vehicle was carried out. KM whick will be used as 2nd stage solid rocket motor. in Korean Satellite Launch Vehicle(I) has been developing. KM is a solid rocket motor using composite propellant based on HTPB and is composed of composite motor case and submerged nozzle. To develop KM rocket motor satisfing a given set of requirement, firstly the full-scale KM was designed, then sub-scale motor reduced about $50\%$ were manufactured and tested.

• Aerospace Engineering and Technology
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• v.3 no.2
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• pp.98-103
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• 2004

This paper describes a system design of Launch Ground Complex for the Korea Space Launch Vehicle-I which will play so important roles of successful execution for Korea National Space Development Program. Launch Ground Complex has to supply safe work space, construction and equipments for assembling, check-out and launching of the space launch vehicle, and it consists of Mechanical, Electrical, Fluid Ground Support Equipment and Infrastructure. Mechanical Ground Support Equipment consists of Launch Pad, Mobile Assembly Tower, Umbilical Tower, Lightning Tower, Theodolite Building and Auxiliary.

• Aerospace Engineering and Technology
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• v.8 no.2
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• pp.105-112
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• 2009

Telemetry data is very important for the Launch Mission and Flight Safety Control during the Space Launch. In Naro Space Center, several telemetry stations such as a small station in the NARO space center, two stations in Jeju and a downrange station on a ship are deployed for the stable acquisition/receiving of the telemetry signals. In this paper, the Link Margin and Reliability for the telemetry are analyzed to evaluate the probability of the signal receiving of each station. Even though the proper analysis is to using the on-board EIRP(Effective Isotropic Radiation Power) values in the direction of the ground station considering the predicted flight trajectory and the locations of the stations, the global EIRP of 95% spatial coverage has been used for the analysis, due to the limitation of the available data.

• Bulletin of the Korean Space Science Society
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• 2004.10b
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• pp.96-96
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• 2004

• Aerospace Engineering and Technology
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• v.4 no.1
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• pp.196-202
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• 2005

In cryogenic feeding system of turbo pump fed liquid-propulsion rocket, rise of cryogenic propellant temperature can bring into geysering in pipe or cavitation in turbo pump. In this paper, performance analysis of recirculation line which is one of the method to inhibit these phenomenon is carried out based on the configuration of KSLV-I 1st stage LOX feeding system, and parametric study to find design parameter. Diameter and re-entrance height, initial LOX temperature, ullage pressure, and natural convection heat transfer coefficient are varied to see the effects on performance. Additional He is injected into recirculation line to promote LOX recirculation. 1-dimensional analysis using network-solver, SINDA/FLUINT is carried out.

• Aerospace Engineering and Technology
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• v.4 no.2
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• pp.209-215
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• 2005

A qualification of propellant for a AKM(Apogee Kick Motor) has been conducted by firing standard motors. The Standard motor used in developing process of KSLV-I's AKM is ST-6 whose diameter is about six inches. HTPB composite propellant are used in these motors. Several standard motors are fired and compared with simulation results. A mean value of characteristic velocity is 1518 m/s. The characteristic value for prediction is 1516 m/s, and the thrust loss is about 5.9%. Differences between the measurements and prediction are less than 3%.

• The Korean Journal of Air & Space Law and Policy
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• v.17
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• pp.163-174
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• 2003

The space center will be constructed by 2005 for launch of KSLV-I at Woinara-Do, Haban Village, Yenae-Ri, Bongrae-Myon, Kohung-Goon, Junlanam Province on the southern coast of the Korean peninsular. This will make Korea be the 13th advanced country in space development having launching site in the world. This paper presents licensing and safety requirements to protect the public from the risks associated with activities at a launch site.

• Aerospace Engineering and Technology
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• v.6 no.1
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• pp.190-200
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• 2007

A pyrogen type igniter was designed to satisfy the requirements of KSLV-I Kick Motor system. To insure the reliability of the igniter before the production of the flight model, we have been performed the structure, environmental, combustion tests. The hydraulic test was carried out to confirm the strength of the components of the igniter. The shock and vibration tests were considered to check whether the igniter operates normally under the severe environmental condition. The combustion tests were also performed to understand the ignition characteristics with the variation of initial condition. Finally, we confirmed that the igniter could provide the acceptable energy to ignite the propellant of kick motor at the ground test.

• Aerospace Engineering and Technology
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• v.6 no.1
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• pp.165-172
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• 2007

A space launch vehicle is a very complex system composed of many kinds of components. It is necessary for even a small piece of components in it to be free of defects, malfunctions and to operate normally for the sake of the mission success. For these reasous, a variety of tests are carried out. Burn-in test is to detect latent material and workmanship defects which occurs early in the components use. Developed countries for the space technology have considered the burn-in test for flight vehicles in the standard test documents and performed it. Referred to the documents, application methods of burn-in test will be considered for the components of domestic space launch vehicles such as KSLV-I in this document.