• Bulletin of the Korean Space Science Society
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• 2008.10a
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• pp.26.1-26.1
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• 2008

The Korean first geostationary meteorological satellite, COMS, will be launched during second half of 2009. For the next meteorological geostationary satellite mission, KARI is now preparing the development process and tools. As one of the endeavor, a software tool is being developed for the analysis and design of geostationary transfer orbit. Generally, these kind of tools should be able to do various analysis works like apogee burn planning, dispersion analysis, ground visibility analysis, and launch window analysis etc. In this presentation, a brief introduction about a design process and analysis software tool development. And simulated calculation results are provided for the geostationary transfer orbit. These software can be used for the next geostationary satellite mission design and development.

• Bulletin of the Korean Space Science Society
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• 2004.10b
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• pp.300-303
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• 2004

KOMPSAT-2 satellite mission operations and control system has been developed by ETRI. The system functional architecture, analysis and design, implementation, and tests are presented in this paper.

• Journal of Astronomy and Space Sciences
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• v.26 no.2
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• pp.267-278
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• 2009

Automation of the key flight dynamics operations for the geostationary orbit satellite mission is analyzed and designed. The automation includes satellite orbit determination, orbit prediction, event prediction, and fuel accounting. An object-oriented analysis and design methodology is used for design of the automation system. Automation scenarios are investigated first and then the scenarios are allocated to use cases. Sequences of the use cases are diagramed. Then software components and graphical user interfaces are designed for automation. The automation will be applied to the Communication, Ocean, and Meteorology Satellite (COMS) flight dynamics system for daily routine operations.

• Journal of Space Technology and Applications
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• v.3 no.2
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• pp.101-117
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• 2023

Active debris removal, a technology that approaches and removes space debris in orbit, and the on-orbit service, a technology for extending the mission life of satellites by fuel charging or by exchanging the battery, are gaining interest with the growth of the space community. SaTReC plans to develop a satellite capable of capturing and removing Korean satellites orbiting in space after the end of their missions. In contrast to the previously launched satellites by Korea, which were mainly intended to observe Earth and the space environment, rendezvous/docking technologies, as required in the future during, for instance, space exploration missions, will be implemented and demonstrated. In this paper, an orbital transition method for next-generation small satellites that will capture and remove space debris will be introduced. It is assumed that a small satellite with a mass of approximately 200 kg will be injected into the mission orbit through Korea Space Launch Vehicle-II in 2027. Because the satellite must access the target using a minimum amount of fuel, an approaching technology using Earth's J2 perturbation force has been developed. This method is expected to enable space debris removal missions for relatively lightweight satellites and to serve as the basis for carrying out a new type of space exploration in what is termed the 'Newspace' era.

• Journal of Astronomy and Space Sciences
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• v.35 no.3
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• pp.175-183
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• 2018

Many recent satellites have mission periods longer than 10 years; thus, satellite-based local space weather monitoring is becoming more important than ever. This article describes the instruments and data applications of the Korea Space wEather Monitor (KSEM), which is a space weather payload of the GeoKompsat-2A (GK-2A) geostationary satellite. The KSEM payload consists of energetic particle detectors, magnetometers, and a satellite charging monitor. KSEM will provide accurate measurements of the energetic particle flux and three-axis magnetic field, which are the most essential elements of space weather events, and use sensors and external data such as GOES and DSCOVR to provide five essential space weather products. The longitude of GK-2A is $128.2^{\circ}E$, while those of the GOES satellite series are $75^{\circ}W$ and $135^{\circ}W$. Multi-satellite measurements of a wide distribution of geostationary equatorial orbits by KSEM/GK-2A and other satellites will enable the development, improvement, and verification of new space weather forecasting models. KSEM employs a service-oriented magnetometer designed by ESA to reduce magnetic noise from the satellite in real time with a very short boom (1 m), which demonstrates that a satellite-based magnetometer can be made simpler and more convenient without losing any performance.

• Proceedings of the KSRS Conference
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• 2003.11a
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• pp.1197-1199
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• 2003

ROCSAT-2 mission is to daily image over Taiwan and the surrounding area for disaster monitoring, land use, and ocean surveillance during the 5-year mission lifetime. The satellite will be launched in December 2003 into its mission orbit, which is selected as a 14 rev/day repetitive Sun-synchronous orbit descending over (120 deg E, 24 deg N) and 9:45 a.m. over the equator with the minimum eccentricity. National Space Program Office (NSPO) is developing a ROCSAT-2 Image Processing System (IPS), which aims to provide real-time high quality image data for ROCSAT-2 mission. A simulated ROCSAT-2 image, based on Level 1B QuickBird Data, is generated for IPS verification. The test image is comprised of one panchromatic data and four multispectral data. The qualification process consists of four procedures: (a) QuickBird image processing, (b) generation of simulated ROCSAT-2 image in Generic Raw Level Data (GERALD) format, (c) ROCSAT-2 image processing, and (d) geometric error analysis. QuickBird standard photogrammetric parameters of a camera that models the imaging and optical system is used to calculate the latitude and longitude of each line and sample. The backward (inverse model) approach is applied to find the relationship between geodetic coordinate system (latitude, longitude) and image coordinate system (line, sample). The bilinear resampling method is used to generate the test image. Ground control points are used to evaluate the error for data processing. The data processing contains various coordinate system transformations using attitude quaternion and orbit elements. Through the qualification test process, it is verified that the IPS is capable of handling high-resolution image data with the accuracy of Level 2 processing within 500 m.

• Bulletin of the Korean Space Science Society
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• 2003.10a
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• pp.47-47
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• 2003

Analytical formulae are presented to approximate the evolution of the semi major axis, the maneuver time, and the final mass fraction for low thrust orbital transfers with circular initial orbit, circular target orbit, and constant thrust directed either always along or always opposite the velocity vector. For comparison, the associated results for high-thrust transfers, i.e. the two-impulse Hohmann transfer, are summarized. All results are implemented in a computer code designed to analyze planar planetary and interplanetary space missions. This implementation yields fast and reasonably accurate approximations to trajectory performance boundaries. Consequently, the approach can provide trajectory analysis for each spacecraft configuration during the conceptual space mission design phase. As an example, a mission from Low-Earth Orbit (LEO) to Jupiter's moon Europa is analyzed.

• Bulletin of the Korean Space Science Society
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• 1993.04a
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• pp.15-15
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• 1993

During the past two decades, ultraviolet(UV) observations of elliptical galaxies and spiral bulges from the OAO-2 and HE satellites have established that the upturn in the specturm below 2000A is a common feature of these early-type system Because of its important implications for the formation of galaxies, astuonemical literature is replete with nurmerous discussions about the origin of the UV flux yet the situation remains controversal. New light on the problem is shed by the recent observations Some the Astro-1 space shuttle mission which suggest that the metal-poor horizontal-branch(HB) stars merit more detailed consideration for the origin of the UV flux It is shown here that such stars in these systems can indeedexplain the UV flux It is suggested that ttle obserred correlation between the UVupturn and total mass is due to the Possibility that the more massive galaxies tend to form earlier than the less massive galaxies as a result of mere efficient star formation in denser environments. It remains a task of mere detailed population synthesis nudels, now in progress, to put these results on a firmer quantitative basis.

• Proceedings of the KSRS Conference
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• 2004.10a
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• pp.386-388
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• 2004

The International Space Station (ISS) offers research opportunities to researchers through crew's space mission in the field of remote sensing. ISS provides the facilities to place and operate experiment equipments in a variety of fields, especially, microgravity experiments and Earth observations. This paper is intended to give readers a brief introduction to the ISS utilization and the capabilities for remote sensing researches. We investigate what kind of crew missions and payloads should be developed for remote sensing researches on the ISS.

• Advances in aircraft and spacecraft science
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• v.3 no.2
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• pp.225-242
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• 2016

Euclid is an astronomy and astrophysics space mission of the European Space Agency. The mission aims to understand why the expansion of the Universe is accelerating and what is the nature of the source responsible for this acceleration which physicists refer to as dark energy. This paper provides both an overview of the spacecraft mechanical architecture and a synthesis of the process applied to establish adequate mechanical loads for design and testing. Basic methodologies and procedures, logics and criteria which have been used with the target to meet a compliant, "optimised" design are illustrated. The strategy implemented to limit the risk for overdesign and over-testing without jeopardizing the design margins is also addressed.