• Korean Journal of Remote Sensing
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• v.37 no.2
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• pp.305-319
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• 2021

The overseas calibration sites such as Mongolia used for Korea Multi-purpose Satellite (KOMPSAT-5 or K5), have a disadvantage in that maintenance and repair costs are high and immediate response is difficult when an unexpected problem occurs. Accordingly, the necessity of establishing a domestic SAR calibration site was suggested, but the progress of related research is insignificant. In this paper, we investigated what conditions should be satisfied in terms of backscattering characteristics to construct a site for SAR satellite image quality evaluation and calibration. First of all, it was selected first by applying general indicators such as accessibility and availability among places recommended as satellite image calibration candidate sitesin Korea. Next, three places, site A (Goheung-gun, Jeollanam-do), site B (Jeonju-si, Jeollabuk-do), and site C (Daedeok Research Complex, Daejeon), were selected as the final candidates because they are relatively wide and easy to install AT or CR. Site A, located in Goheung-gun, Jeollanam-do, was best considered in terms of slope measurements, minimum site area to obtain ISLR, uniformity of DN values and backscatter coefficients, interference by strong reflectors, and backscatter clutter level.

• Journal of Astronomy and Space Sciences
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• v.19 no.2
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• pp.123-132
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• 2002

The electron density and temperature in the topside ionosphere are observed by the ionosphere Measurement Sensor (IMS) onboard the KOMPSAT-1, which has the sun-synchronous orbit of the altitude of 685 km and the orbital inclination of $98^{\circ}$ with a descending node at 22:50LT. Observations have been analyzed to determine the seasonal variations of the electron density and temperature in the low-latitude region. Only the night-time (22:50LT) behavior on magnetically quiet days (Kp < 4) has been examined. Observations show a strong longitudinal and seasonal variation. Generally, in the dip equator the density increases and the temperature decreases. In equinox the latitudinal distributions of the electron density and temperature are quite symmetric about the dip equator. However, the local maximum of the density and the local minimum of the temperature shift toward the Northern hemisphere in summer solstice but the Southern hemisphere in winter solstice. Such variations are due to the influences of field-aligned plasma transport induced by F region neutral wind. Compared with the IRI95 model, the observed electron density and temperature show significant differences from those predicted by the IRI95 model.

• Journal of Astronomy and Space Sciences
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• v.20 no.4
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• pp.375-382
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• 2003

One of the mechanical system engineer's tasks of a satellite design and development is to make the control plan, keep track and estimate the characteristics of system mass properties. As the design phases are go, mass properties related activities also transit as like a data collection, system mass property estimation and measurement. Fidelity of mass properties database should be confirmed through measurement test. In this paper the control plan and estimation of system mass properties are explained by the actual data and experience of the development of satellite and the fidelity of mass properties database was confirmed through measurement test.

• Journal of Astronomy and Space Sciences
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• v.17 no.2
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• pp.309-316
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• 2000

KOMPSAT-2 will carry MSC(Multi-Spectral Camera) which provides 1m resolution panchromatic and 4m resolution multi-spectral images at the altitude of 685km sun-synchronous mission orbit. The mission operation of KOMSPAT-2 is to provide the earth observation using MSC with nadir pointing. KOMPSAT-2 will also have the capability of roll/pitch tilt maneuver using reaction wheel of satellite as required. In order to protect MSC from thermal distortion as well as direct sunlight, MSC shall be operated within the constraint of sun incidence angle. It is expected that the sunlight will not violate the constraint of sun incidence angle for normal mission operations without roll/pitch maneuver. However, during roll/pitch tilt operations, optical module of MSC may be damaged by the sunlight. This study analyzed sun incidence angle of payload using KOMPSAT-2 AOCS (Attitude and Orbit Control Subsystem) Design and Performance Analysis Soft ware for KOMPSAT-2 normal mission operations.

• Proceedings of the Korean Society of Surveying, Geodesy, Photogrammetry, and Cartography Conference
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• 2007.04a
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• pp.145-148
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• 2007

The Korea Multi-Purpose Satellite-2 (KOMPSAT-2) was launched in July 2006 and The main mission of the KOMPSAT-2 is a high resolution imaging for the cartography of Korea peninsula by utilizing Multi Spectral Camera (MSC) images. The camera resolutions are 1 m in panchromatic scene and 4 m in multi-spectral imaging. KOMPSAT-2 measure the position, velocity and attitude data of satellite using by star sensor, gyro sensor, and GPS sensor. This paper provides an initial geometric accuracy assessment of the KOMPSAT-2 high resolution image, both geometric Cal/Val overview.

• Proceedings of the KSRS Conference
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• 2007.03a
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• pp.308-310
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• 2007

복사 보정에 해당하는 NUC(Non-Uniformity Correction)은 MSC 각각의 픽셀들이 가지는 상이한 특성을 균일한 이미지를 얻기 위해 보정하는 작업으로서 KOMPSAT-2 검보정 작업 중 Video Processor 의 Electrical Gain/Offset 의 보정 과 더 불어 매 우 중요한 비중을 차지하는 과정이다. 본 논문에서는 KOMPSAT-2 의 Panchromatic 밴드의 raw image 를 이 용한 NUC 보정 작업 의 과정과 그 결과에 대해서 소개하고자 한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.9
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• pp.836-842
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• 2007

This paper describes the development of an automated operational orbit processing system (KGS automated Operational Orbit Processing System, KOOPS), which can determine, evaluate, update, and generate the orbit data automatically. Developed system can be applied to the multi satellite mission operations as a generic satellite orbit processing system in that the KOOPS has a capability to process various kinds of tracking data and assign pre and post processes according to the satellite system respectively. Results of applying the KOOPS to the KOMPSAT-1 and KOMPSAT-2 mission operations show that man power is greatly reduced and the efficiency and stability of the mission operations are significantly increased. The experiences to develop the KOOPS and operate multi satellite missions using this system can be applied to enhance the multi and generic flight dynamics system further.

• Proceedings of the Korean Society of Surveying, Geodesy, Photogrammetry, and Cartography Conference
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• 2003.10a
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• pp.439-444
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• 2003

The burial culture has prevailed in our county because of the effect of Confucianism. First of all, tombs've had an negative effect on the vista of national land and caused an ineffective use of national land recently. for this reason, the systematic management of the toms is necessary The purpose of this project is to identify tombs' geographical coordinates from orthoimage and to analysis algorithms for extracting tombs on the satellite image. We've used IKONOS image for those purpose, because it's very similar to KOMPSAT-2 image's characteristics which will be launched near future. and, It will make the best use of tombs management of each local government.

• Proceedings of the IEEK Conference
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• 2003.11a
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• pp.421-424
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• 2003

The KOMPSAT-II has a MSC(Multi-Spectral Camera) payload for earth observatory. The image data acquired during the pass over the Korean Peninsula can be sent to the ground station directly. But the image data out of the contact range should be stored temporally for later transmission. The KOMPSAT-II has a device for this purpose called the DCSU(Data Compression and Storage Unit) and the DCSU also performs compression functions for saving storage space and transmission time to send image data to the ground station. In this paper, we'd like to introduce the DCSU memory structures and operation.

• 제어로봇시스템학회:학술대회논문집
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• 2000.10a
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• pp.101-101
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• 2000

MSC(Multispectral Camera), which will be a unique payload on KOMPSAT-II, is designed to collect panchromatic and multi-spectral imagery with a ground sample distance of 1m and a swath width of 15km at 685km altitude in sun-synchronous orbit. The instrument is designed to have an orbit operation duty cycle of 20% over the mission life time of 3 years. MSC electronics consists of three main subsystems; PMU(Payload Management Unit), CEU(Camera Electronics Unit) and PDTS(Payload Data Transmission Subsystem). PMU performs all the interface between spacecraft and MSC, and manages all the other subsystems by sending commands to them and receiving telemetry from them with software protocol through RS-422 interface. CEU controls FPA(Focal Plane Assembly) which contains TDI(Timc Delay Integration) CCD(Charge Coupled Device) and its clock drivers. PMU provides a Master Clock to synchronize panchromatic and multispectral camera. PDTS performs compression, storage and encryption of image data and transmits them to the ground station through x-band.