• The Korean Journal of Air & Space Law and Policy
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• v.19 no.1
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• pp.9-35
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• 2004

A launching State shall be absolutely liable to pay compensation for damage caused by its space object on the surface of the earth or to aircraft in flight. The compensation which the launching State shall be liable to pay for damage under "the Convention on International Liability for Damage caused by Space Objects" shall be determined in accordance with international law and the principles of justice and equity, in order to provide such reparation in respect of the damage as will restore the person, natural or juridical, State or international organisation on whose behalf the claim is presented to the condition which would have existed if the damage had not occurred. In the event of damage being caused elsewhere than on the surface of the earth to a space object of one launching State or to persons or property on board such a space object by a space object of another launching State, and of damage thereby being caused to a third State or to its natural or juridical persons, the first two States shall be jointly and severally liable to the third State, to the extent indicated by the following: If the damage has been caused to the third State on the surface of the earth or to aircraft in flight, their liability to the third State shall be absolute; If the damage has been caused to a space object of the third State or to persons or property on board that space object elsewhere than on the surface of the earth, their liability to the third State shall be based on the fault of either of the first two States or on the fault of persons for whom either is responsible. The Insurance requirements are satisfied for a launch or return authorised by a launch permit if the holder of the permit or authorisation is insured against any liability that the holder might incur to pay compensation for any damage to third parties that the launch or return causes; and the Commonwealth is insured against any liability that Commonwealth might incur, under the Liability Convention or otherwise under international law, to pay compensation for such damage. The liability for Damage caused by Space Objects should be regulated in detail in Korea.

• Aerospace Engineering and Technology
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• v.4 no.2
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• pp.220-229
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• 2005

The Earth observation imagery from satellite provide valuable informations for the central government, local governments and diverse public organizations. The analysis of applications and data, which are sold by commercial distributors of Earth observation satellite data, shows this phenomenon clearly. The Government of Republic of Korea established and carried out a national space development plan to meet the national needs for remotely sensed imagery. After this national space development plan and on behalf of Korean government KARI has developed and launched successfully the KOMPSAT-1 and operates it up to now. KARI is now to launch by the end of year 2005 another optical remote sensing satellite with very high resolution and named as KOMPSAT-2. For the application of such very high resolution remotely sensed data the product validation should be done carefully and this product validation require lots of ancillary data such as in-situ measurements. For the purpose of diverse ancillary data acquisition joint work with other nations, related institutes and international bodies is essential. In this paper the status of Korean European Cooperations will be introduced, which are derived by KARI, ARCS and ESA for the wide use of KOMPSAT data in Europe.

• Journal of Satellite, Information and Communications
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• v.12 no.3
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• pp.1-7
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• 2017

Climate change adaptation must be prepared, because the pattern of climate change in Korea is higher than the global average. In particular, it is estimated that Korea's economic loss due to climate change will reach 2,800 trillion won, and at least 300 trillion won will be needed for adaptation to climate change(KEI, 2011). Accurate climate change forecasts and impact forecasts are essential for efficient use of enormous climate change adaptation costs. For this climate change prediction and impact analysis, it is necessary to grasp not only the global average concentration but also the inhomogeneity of the greenhouse gas concentration which appears in each region. In this study, we analyze the feasibility of developing a greenhouse gas observation satellite, which is a cause of climate change, and present a development plan for a low orbit environmental satellite by examining the current status of the operation of the greenhouse gas observation satellite. The GHG monitoring satellite is expected to expand the scope of environmental monitoring by water/soil/ecology in addition to climate change, along with weather/agriculture/soil observation satellites.

• Journal of Astronomy and Space Sciences
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• v.20 no.4
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• pp.339-350
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• 2003

Engineering qualification model payload for a communications and broadcasting satellite(CBS) was developed by ETRI from May, 2000 to April, 2003. For. the purpose of functional test and verification of the payload, a real-time hardware-in-the-loop(HITL) CBS simulator(CBSSIM) was also developed. We assumed that the spacecraft platform for the CBSSIM is a geostationary communication satellite using momentum bias three-axis stabilization control technique based on Koreasat. The payload hardware is combined with CBSSIM via Power, Command and Telemetry System(PCTS) of Electrical Ground Support Equipment(EGSE). CBSSIM is connected with PCTS by TCP/IP and the payload is combined with PCTS by MIL-STD-1553B protocol and DC harness. This simulator runs under the PC-based simulation environment with Windows 2000 operating system. The satellite commands from the operators are transferred to the payload or bus subsystem models through the real-time process block in the simulator. Design requirements of the CBSSIM are to operate in real-time and generate telemetry. CBSSIM provides various graphic monitoring interfaces and control functions and supports both pre-launch and after-launch of a communication satellite system. In this paper, the HITL simulator system including CBSSIM, communications payload and PCTS as the medium of interface between CBSSIM and communications payload will be described in aspects of the system architecture, spacecraft models, and simulator operation environment.

• Atmosphere
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• v.12 no.4
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• pp.20-42
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• 2002

Based on the "Mid to Long Term Plan for Space Development", a project to launch COMeS (Communication, Oceanography, and Meteorological Satellite) into the geostationary orbit is undergoing. Accordingly, KMA (Korea Meteorological Administration) has defined the meteorological missions and prepared the user requirements to fulfill the missions. To make a realistic user requirements, we prepared a first draft based on the ideal meteorological products derivable from a geostationary platform and sent the RFI (request for information) to the sensor manufacturers. Based on the responses to the RFI and other considerations, we revised the user requirement to be a realistic plan for the 2008 launch of the satellite. This manuscript introduces the revised user requirements briefly. The major mission defined in the revised user requirement is the augmentation of the detection and prediction ability of the severe weather phenomena, especially around the Korean Peninsula. The required payload is an enhanced Imager, which includes the major observation channels of the current geostationary sounder. To derive the required meteorological products from the Imager, at least 12 channels are required with the optimum of 16 channels. The minimum 12 channels are 6 wavelength bands used for current geostationary satellite, and additional channels in two visible bands, a near infrared band, two water vapor bands and one ozone absorption band. From these enhanced channel observation, we are going to derive and utilize the information of water vapor, stability index, wind field, and analysis of special weather phenomena such as the yellow sand event in addition to the standard derived products from the current geostationary Imager data. For a better temporal coverage, the Imager is required to acquire the full disk data within 15 minutes and to have the rapid scan mode for the limited area coverage. The required thresholds of spatial resolutions are 1 km and 2 km for visible and infrared channels, respectively, while the target resolutions are 0.5 km and 1 km.