• Journal of Applied Reliability
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• v.4 no.2
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• pp.105-119
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• 2004

Reliability program is essential to the development of space systems like launch vehicles and satellites, as they are non-repairable after launch and the failure of a launch vehicle resulted in catastrophic consequences for the mission. Foreign advanced space organizations have developed and implemented their own reliability management programs for launch vehicles from the conceptual design stage to the detail processes for the individual components, procedures and test reports. A study on the launch failures and the reliability analysis methods for one-shot devices contained in this paper will contribute to the reliability improvement for Korean launch vehicle and components.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.581-585
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• 2009

In this study, conceptual design of the RBCC (Rocket Based Combined Cycle) engine was performed for the hypersonic propulsion system development. For the flight mission, RBCC engine takes off at sea level and accelerates up to Mach 8 at the altitude of 30km. By the flight speed characteristics, operating pattern of the engine is categorized into 3 modes : Ejector jet (~Mach 3), Ramjet (Mach 3~6), Scramjet (Mach 6~8). According to the engine mode characteristics, RBCC engine design and analysis was performed.

• Journal of electromagnetic engineering and science
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• v.2 no.1
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• pp.39-44
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• 2002

A high speed data link capability is one of the critical factors in determining the performance of the spaceborne SAR system with high resolution because of the strict requirement far the real-time data transmission of the massive SAR data in a limited time of mission. In this paper, based on the data lint model characterized by the spaceborne small SAR system, the high rate multi-channel data link module is designed including link storage, link processor, transmitter, and wide-angle antenna. The design results are presented with the performance analysis on the data link budget as well as the multi-mode data rate in association with the SAR imaging mode of operation from high resolution to the wide swath.

• 제어로봇시스템학회:학술대회논문집
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• 1988.10a
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• pp.614-619
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• 1988

In this paper, an arbitrary mission of a spacecraft from launch to orbit injection is investigated for some launch trajectories. Launch sites are selected arbitrarily from various locations in Korea. For this study, a general purpose simulation program is developed. In this program, the Earth is assumed to be a rotating ellipsold. The launch vehicle is treated as a 3-D, 6-DOF rigid body. The developed program has been evaluated by calibrating it to the 3-stage N-1 rocket developed in Japan and launched at Tanegasima. The simulated trajectory from the first-stage ignition to burnout of third-stage main engine is compared with the previously tested N-1 rocket trajectory in Japan. The result shows that the program works properly. Using the proven program, we have investigated possible launch locations in Korea, namely Marado, Sungsan and Kuryongpo. The problem of polar orbit injection is also examined.

• Aerospace Engineering and Technology
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• v.2 no.1
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• pp.44-53
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• 2003

The purpose of reliability prediction is to estimate the basic reliability and basic reliability and mission reliability of system and to make a determination of whether these reliability requirements can be achieved with the proposed design. Also, potential design weakness can be identified through the FMECA process. This technical memo summarizes the KOMPSAT-2 reliability and FMECA analysis results.

• The Bulletin of The Korean Astronomical Society
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• v.42 no.2
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• pp.63.3-64
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• 2017

KIC6118779 is an over-contact binary system having a short orbital period of about 0.36 days. The photometric data for this system are acquired by the observations of Kepler mission in the long cadence mode having a time resolution of about 30 minutes. It means that the Kepler light curves of the system may be strongly affected by phase smearing effect and the analysis of them without consideration of the phase smearing effect may result in wrong stellar properties. Additionally, this system also shows dynamical variation of light curve resulting from spot activity. For all those reasons, it is difficult to investigate KIC6118779, and the investigation should be carried out carefully. In this presentation, we introduce the phase smearing effect and carry out the light curve modeling with the 2015 version of the Wilson-Devinney binary code considering the phase smearing effect. Our results show that the system is a deep over contact binary system and has extremely low mass ratio of about 0.12. Moreover our spot modeling implies the cyclic migration of a big cool spot on the massive component.

• Proceedings of the KSR Conference
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• 2007.05a
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• pp.572-576
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• 2007

Railroad systems can be divided into the primary function for transporting passengers or freight and secondary function covering diverse environmental factors and interfaces. So, the most biggest and important reason and the goal of railroad systems is to satisfy the need for transportation based on the production and consumption of energy. Especially, the operation of safe systems is the inevitable element for achieving this objective. Performing this can be ultimately satisfied only when the relationship among operators, contractors, suppliers and assessors is established according to their missions. Therefore, we are trying to finding the way of approaching it systematically by reviewing which procedures and methodologies mission performers in various domains have to follow.

• Journal of the Korea Furniture Society
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• v.26 no.4
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• pp.334-345
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• 2015

The social design, which appeared at the end of the 19th century, is getting attention along with problems in modern society. The purpose of this paper is to analyze several cases of social furniture designs, and to present its necessity and future direction. It classifies the cases of furniture, lighting and design project regarding social design into three types. First is furniture design for social minority. Second is sustainable design, and third is social design that delivers social message. The expected effects of social design are cost-efficiency, sociality, and environment-friendliness. Also, social design requires certain direction which is first; the designer should recognize the minorities in the world. Second, the designer is obliged to accomplish social mission, and last, he or she should be aware that the design creates added values.

• Proceedings of the KSRS Conference
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• 2008.10a
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• pp.232-235
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• 2008

The mission of the EO(electro-optical) based low earth orbit satellite is provision of the high-resolution images required for GIS(Geographical Information Systems) establishment and the applications for environmental, agriculture and ocean monitoring. AEISS(Advanced Earth Imaging Sensor System) which is the main payload on the satellite consists of EOS(electro-optical subsystem) and PDTS(Payload Data Transmission Sub-system). IDHU(Image Data Handling Unit) which is one of the major unit in PDTS is capable of compression, storage, encryption and encoding. In this paper, the payload system of the EO based satellite is briefly introduced and the influence of the compression on AEISS is analyzed.

• Proceedings of the Korea Institute of Applied Superconductivity and Cryogenics Conference
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• 2000.02a
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• pp.12-16
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• 2000

The mission of SSTF is test of superconducting cables for KSTAR magnets. To make realistic environment for superconductor in SSTF, background magnets are required. Cable-in-conduit conductors (CICC) are widely used for large scale superconducting magnets such as ITER and KSTAR. Main design criteria for conductor of superconducting magnets are stability, operating margin and cable cooling requirement, caused by peak field and the gradient of fields with respect to time, in system. ZERODEE which used energy balance method, is applied for the calculation of stability. To increase conductor performance, three different strands, such as HP-I, HP-II, and HP-III, are tested. The present configuration of CICC is used for main coils of background magnet in SSTF and Central Solenoid coils of KSTAR magnets.