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http://dx.doi.org/10.5139/JKSAS.2011.39.4.474

Thermal Design and Analysis for Space Imaging Sensor on LEO  

Shin, So-Min (국방과학연구소 영상정보체계개발단)
Oh, Hyun-Ung (국방과학연구소 영상정보체계개발단)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.39, no.5, 2011 , pp. 474-480 More about this Journal
Abstract
Space Imaging Sensor operated on LEO is affected from the Earth IR and Albedo as well as the Sun Radiation. The Imaging Sensor exposed to extreme environment needs thermal control subsystem to be maintained in operating/non-operating allowable temperature. Generally, units are periodically dissipated on spacecraft panel, which is designed as radiator. Because thermal design of the imaging sensor inside a spacecraft is isolated, heat pipes connected to radiators on the panel efficiently transfer dissipation of the units. First of all, preliminary thermal design of radiating area and heater power is performed through steady energy balance equation. Based on preliminary thermal design, on-orbit thermal analysis is calculated by SINDA, so calculation for thermal design could be easy and rapid. Radiators are designed to rib-type in order to maintain radiating performance and reduce mass. After on-orbit thermal analysis, thermal requirements for Space Imaging Sensor are verified.
Keywords
Thermal Design; Thermal Analysis; Radiator; Heater; Rib-type;
Citations & Related Records
Times Cited By KSCI : 1  (Citation Analysis)
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