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Erschienen in:
2018 | OriginalPaper | Buchkapitel
12. Thermal Design
verfasst von : George Sebestyen, Steve Fujikawa, Nicholas Galassi, Alex Chuchra
Erschienen in: Low Earth Orbit Satellite Design
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Abstract
The altitude, inclination, epoch and angle of the orbit plane to the Sun (the Beta angle) determine the thermal environment of a spacecraft. In the direction of the Sun, the heat incident on a spacecraft can be huge, while on the side opposite the Sun, the spacecraft faces cold space. The objective of the thermal design is to bring these temperatures into a range where the spacecraft components can safely operate, and to ensure that internally generated heat from the spacecraft components is conducted or radiated out to maintain all spacecraft temperatures within the operating temperature ranges of its components. Typical component temperature operating ranges are given in Fig. 12.1. The goal is to design for component temperatures in the 10°–20 °C range.