• Proceedings of the Optical Society of Korea Conference
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• 2000.08a
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• pp.54-55
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• 2000

해양관측카메라 Ocean Scanning Multi-spectral Imager (OSMI)를 탑재한 다목적 실용위성(KOMPSAT) 1호기가 1999년 12월 21일 발사되었다. OSMI는 유연한 임무 수행을 위해 궤도운영중에 관측파장대역 선택과 응답 이득 조정이 가능하도록 설계되었다. 또한 OSMI는 기기 노화 등에 따른 성능 변화 감지 및 보정을 위해 태양광 보정을 궤도운영중 수행한다. 여러 이득 단계에 대해 발사후 복사 응답 특성을 기기 보정 측면에서 연구하였다. 발사전 실험실 성능 측정 결과에 근거하여 발사후 초기 운영 단계에서 측정한 태양광 보정 자료의 선형 curve fitting을 통해 발사후 복사 응답 특성을 분석하였다. 이 분석은 OSMI 기기 보정 및 영상 품질 이해에 유용할 것이다.

• Aerospace Industry
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• s.104
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• pp.40-41
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• 2009

지난 8월 25일 온 국민의 관심 속에 대한민국 최초의 우주발사체 나로호가 힘차게 하늘로 솟아올랐다. 그러나 최종적으로 과학기술위성 2호의 궤도 진입에는 실패함으로서 큰 아쉬움을 남겼다. 대한민국 우주개발의 신호탄이며 절반의 성공으로 평가되는 나로호 발사 과정을 되짚어 봤다.

• Aerospace Engineering and Technology
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• v.2 no.1
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• pp.140-152
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• 2003

Scenario is a guiding principle of launch operation and control for rocket and ground support system. Therefore, developing a scenario is the first step to prepare for rocket launch, which is a critical task for success of KSR-III flight test. The launch scenario for KSR-III flight test is a procedural sequence of command and control signals to be given to rocket and ground support systems. In this paper, the UML object modeling method is applied to development of a launch scenario. First, the subsystems of the launch system are modeled by objects, and then the interfaces between each two subsystems are modeled by association links. The finally obtained object diagram of KSR-III launch system is used to analyzing flow of data and commands and control signals, and interactions. The scenario includes the sequences of pre-launch/launch operations and emergency operations.

• 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.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.9
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• pp.41-47
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• 2005

Conceptual design process is defined for the air-launching rocket by including analysis modules like mission analysis, staging, propulsion analysis, configuration, weight analysis, aerodynamics analysis and trajectory analysis. As a result of the conceptual design, the supersonic(M=1.5) air-launching rocket with hybrid engine for first stage propulsion system is designed. For the best system alternative selection, trade study for the 1st stage engine type and launching speeds using sequential optimization and confirming feasibility of baseline air-launching rocket has been performed. As a result of trade study, all alternatives are competitive in total weight and show only small difference in total weight per unit payload weight. Therefore, it is confirmed that the baseline air-launching rocket which has advantage in system safety especially in supersonic launching is feasible.

• Journal of the Korean Magnetics Society
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• v.25 no.3
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• pp.87-91
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• 2015

This paper reports the design of solenoid in a coilgun for high velocity of projectile in a coilgun system, according to diameter of coil. Coilgun using a magnetic force means a mechanism that can control the magnetic material. When momentarily supply a large current to the solenoid instantaneous magnetic field is created around the coil, the projectile is fired by receiving a magnetic force towards the center of the coil, based on the right-hand rule of Fleming. The velocity of projectile is proportional to the magnetic force generated by the electromagnetic coil. The current affects the life of the coil and the current limit exists. Therefore, the coilgun design, which does not exceed the current limit and the magnetic forces are at the maximum, is required. In this paper, whether it is possible fire looking for the optimal number of turns according to the diameter of the coil from AWG #6 to AWG #18 for the design of the solenoid coil, and comparative analysis firing rate associated with it.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.3
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• pp.314-327
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• 2009

Weather launch criteria of launch at Oenarodo Space Center is important for the successful launch operation. In particular, most of the launch failure occurs during the period of separation from the launch pad, thus meteorological condition is critical at this phase. In earlier days, the weather launch criteria adopted wind and forecast data for the launch operation. Nevertheless, the control of position and stability require other meteorological components such as vertical wind shear, lightning, temperature and visibility, because the launch vehicle is moving mostly vertically. We analyze these meteorological components by using the observed data at KMA at neighboring Oenarodo to determine the weather launch criteria. These criteria need further refinements through long-term observation.

• Aerospace Engineering and Technology
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• v.7 no.1
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• pp.229-235
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• 2008

The ground flight termination system(GFTS) could be used for the termination of launch vehicle in flight motion when the launch vehicle deviates from the designated route due to the system malfunction or failure as well as the launch vehicle can't be tracked by the ground tracking system. This paper introduces the basic concept and design of the ground flight termination system to be used for KSLV launch mission in NARO space center. In order to design the optimal ground flight termination system for KSLV launch application, the operational concept reflected on the flight trajectory and system characteristics of KSLV launch vehicle should be considered. Moreover the RF link budget analysis, and the analysis for system availability and reliability are done. Based on the analysis above, the each subsystem of ground flight termination to transmit the termination signal in stable is designed for KSLV launch mission.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.2
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• pp.138-151
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• 2018

In this study, development information and technologies for reusable launch vehicles were surveyed. We investigated the reusable launch vehicles developed in various countries and analyzed their recovery technologies. In particular, we focus on the technologies of the Falcon 9 of SpaceX and the New Shepard of Blue Origin, which have succeeded in several flight experiments. Moreover, we explain the control algorithms for each flight condition. Finally, we discuss the reusable technologies that can be applied to the Korean Space Launch Vehicle to reduce the launch cost.

• Journal of the Korea Society for Simulation
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• v.24 no.3
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• pp.9-16
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• 2015

This research focuses on analysis of the flight trajectory characteristics of SLBM (Submarine Launched Ballistic Missile) of North Korea. Recently, North Korea tested launching of SLBM which is threatening international security. Also it is known that North Korea had possessed the technologies about SLBM since they disassembled submarines out of commission of the former Soviet Union. If the development of the SLBM of North Korea is completed, it should be affected as asymmetric threat to South Korea. Therefore, for active respondence to these threat, it is essential to analyze the SLBM systematically. In this point of view, this work made a SLBM flight model and simulated. In addition, we controled flight trajectories according to adjusting loft angle and described their characteristics. The sea-based ballistic missile defense system is required for an effective response to the flight trajectory of the SLBM from mid-course to terminal phase.