• Proceedings of the KSRS Conference
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• 2007.10a
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• pp.187-190
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• 2007

The Geostationary Ocean Color Imager (GOCI) is under development to provide a monitoring of ocean-color around the Korean Peninsula from geostationary platforms. It is planned to be loaded on Communication, Ocean, and Meteorological Satellite (COMS) of Korea. The GOCI has been designed to provide multi-spectral data to detect, monitor, quantify, and predict short term changes of coastal ocean environment for marine science research and application purpose. The target area of GOCI observation covers sea area around the Korean Peninsula. Based on the nonlinear radiometric model, the GOCI calibration method has been derived. The nonlinear radiometric model for GOCI will be validated through ground test. The GOCI radiometric calibration is based on on-board calibration devices; solar diffuser, DAMD (Diffuser Aging Monitoring Device). In this paper, the GOCI radiometric error propagation is analyzed. The radiometric model error due to the dark current nonlinearity is analyzed as a systematic error. Also the offset correction error due to gain/offset instability is considered. The radiometric accuracy depends mainly on the ground characterization accuracies of solar diffuser and DAMD.

• Proceedings of the KSRS Conference
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• 2002.10a
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• pp.89-94
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• 2002

Recently, DARI implemented the receiving and processing system for MODIS sensor data from NASA EOS satellites (TERRA and AQUA). This paper shows the development strategy considered, system requirement derived, system design, characteristic and test results of processing system. System operation concept and sample image are also provided. Implemented system was proven to be fully operational through lots of pass operations activities from RF signal reception to level-1 processing.

• Journal of Aerospace System Engineering
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• v.10 no.1
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• pp.59-65
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• 2016

Korea Aerospace Research Institute (KARI) is developing an electric-driven HALE UAV in order to secure system and operational technologies since 2010. Based on the 5 years of flight tests and design experiences of the previously developed electric-driven UAVs, KARI has designed EAV-3, a solar-powered HALE UAV. EAV-3 weighs 53 kg, the structure weight is 21 kg, and features a flexible wing of 19.5 m in span with the aspect ratio of 17.4. Designing the main wing and empennage of the EAV-3 the amount of the bending due to the flexible wing, 404 mm at 1-G flight condition based on T-800 composite material, and side wind effects due to low cruise speed, V_cr = 6 m/sec, are carefully considered. Also, unlike the general aircraft there is no center of gravity shift during the flight. Thus, the static margin cuts down to 28.4% and center of gravity moves back to 31% of the Mean Aerodynamic Chord (MAC) comparing to the previously developed scale-down HALE UAVs, EAV-2 and EAV-2H, to minimize a trim drag and enhance a performance of the EAV-3. The first flight of the EAV-3 has successfully conducted on the July 29, 2015 and the test flight above the altitude 14 km has efficiently achieved on the August 5, 2015 at the Goheung aviation center.

• Journal of Institute of Control, Robotics and Systems
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• v.18 no.11
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• pp.1034-1039
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• 2012

In this paper, a structure of precise positioning based on satellite navigation system is proposed. The proposed system is consisted with three parts, range domain filter, navigation filter and position domain filter. The range domain filter generates carrier phase-smoothed-Doppler and Doppler-smoothed-code measurements. And the navigation filter calculates position and velocity using double-differenced code/carrier phase/Doppler measurements. Finally, position domain filter smooth position error, and it means enhancement of positioning performance. The proposed positioning method is evaluated by trajectory analysis using precise map date. As a result, the position error occurred by multipath or cycle slip was reduced and the calculated trajectory was in true lane.

• Journal of Institute of Control, Robotics and Systems
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• v.19 no.10
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• pp.947-954
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• 2013

This article focuses on a hemispherical resonator gyro driven by the Coriolis effect. The operational principle of resonator gyros and mathematical models are introduced. These models are useful to explain the behavior of a resonator and to design controllers. Several control tests of a resonator have been done. A resonator has been excited by electromagnets controlled by a computer. Its amplitude has been adjusted by a PI control. The transient response is matched with a simulation result based on a mathematical model. A vibrating pattern may drift due to non-uniform factors of a resonator. The drift of the vibrating pattern is controlled and aligned to a reference direction by a PI control. These results are very useful to understand the behavior of resonator gyros and to design advanced control algorithm for better performance.

• International Journal of Advanced Culture Technology
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• v.5 no.3
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• pp.1-10
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• 2017

In this paper, we examine the points of similarity and difference between Korea, Japan, and the USA in terms of the spin-off effects of space technology on cultural life. In Japan and the USA, spin-off effects of space development research by government funded research centers are diffusive while in Korea they are interruptive. Spin-offs of research results impact cultural life via technology transfer and commercialization in businesses. This is because the Korean aerospace industry has progressed largely based on an overall system, but the promotion of internal parts and sub-systems, which can trigger technological development and spin-off effects in manufacturing, has been neglected. In the case of the KARI, the government funded research center, we argue that it is necessary for KARI to devote more resources to transfer (or promote spin-offs of) space technology to small and medium-sized businesses and other industries.

• 한국연소학회:학술대회논문집
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• 2012.11a
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• pp.297-299
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• 2012

Korea Aerospace Research Institute has been doing researches on the hypersonic propulsion system and hypersonic wind-tunnel since 2000 and started scramjet engine researches from 2005. Total 5 kinds of scramjet engine were designed and tested and two of them were hydrocarbon-fueled scramjet engine. For verifying the own characteristics of each components like the intake and combustor, several component tests were done at the KSPC of JAXA and KARI. In this paper, current scramjet engine research activities of KARI will be described.

• Proceedings of the KSRS Conference
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• 2007.10a
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• pp.41-44
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• 2007

Korea Aerospace Research Institute (KARI) has jointly developed a bipropellant propulsion system for Communication, Ocean and Meteorological Satellite (COMS) with EADS Astrium in UK. The technology relevant to a bipropellant propulsion system is quite new one in Korea, which is transferred for the first time, with development of COMS propulsion system. It hasn't ever attempted before, and hasn't got any general idea itself as well, in Korea. The COMS Chemical Propulsion System (CPS) is designed to perform both the orbital injection function, to take the spacecraft from transfer orbit to Geostationary Earth Orbit (GEO), and all on-station propulsive functions throughout the lifetime of the satellite. All station keeping manoeuvres are performed using the CPS. The design, manufacture and testing of COMS CPS are addressed in this paper. Feasibility of COMS CPS applicable to the other advanced mission is investigated as well.

• 한국연소학회:학술대회논문집
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• 2012.11a
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• pp.295-296
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• 2012

In Korea, study of monopropellant thruster have been started from 1990s by KARI (Korea Aerospace Research Institute). 5N hydrazine thruster that is a first Koreanized hydrazine thruster, have been used as flight model for several satellite. In parallel, in order to retain core technology for monopropellant thruster, catalyst and test facility development have been carried out and successfully completed. On the basis of these technology, KARI is performing development of 1N/200N hydrazine thruster and basic research of green propellant thruster.

• Aerospace Engineering and Technology
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• v.8 no.2
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• pp.41-53
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• 2009

This study describes to design the interface between VDL (VHF Digital Link) Mode 2 system and AOA (ACARS Over AVLC) network. KARI-Wrapper using aircraft and ground station design requirements should be designed to the system configuration of the in-out interface of the components and analyzed with the ARINC 618, 620, 622 documentations. According to the system interface test, we are verified the satisfactions of uplink and downlink VDL Mode 2 requirements.