open access

https://hdl.handle.net/2115/57080

Thermal Design Procedure for Micro- and Nanosatellites Pointing to Earth

英語

2014-07

American Institute of Aeronautics and Astronautics

Journal of Thermophysics and Heat Transfer

28(3)

524-533

This paper proposes a thermal design procedure for micro- and nanosatellites that can be completed in one year. Two thermal design concepts keep components within their design temperature range, reducing the temperature change by using the whole structure for heat storage and reducing the temperature change of the inner structure where the most temperature-sensitive components are mounted. One- and two-nodal analysis methods are used for the former and latter concepts, respectively, to clarify the combinations of optical properties for the structures and components to keep within the design temperature range of the components. Finally, multinodal analysis is performed for detail design based on the optical properties clarified from the one- and two-nodal analyses. This thermal design procedure was applied to the Hodoyoshi-1 satellite, which is a cube about 50cm on a side, has two inner plates and has solar cells on the body, is on a sun-synchronous orbit at an altitude of about 500km, and is pointing to Earth. The thermal design of the Hodoyoshi-1 satellite was completed in about 10 months.

学術雑誌論文

Accepted Manuscript

©2014 American Institute of Aeronautics and Astronautics

0887-8722